OptiStruct 13.0 Reference Guide

HyperWorks 13.0 OptiStruct Reference Guide

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OptiStruct 13.0 Reference Guide

Reference ........................................................................................................................................... Guide 1 Input Data ............................................................................................................................................... 2 The Bulk Data Input File ................................................................................................................................... 3 Guidelines for I/O Options and Subcase Information Entries ................................................................................................................................... 7 Guidelines for Bulk Data Entries ................................................................................................................................... 9 Solution Sequences Data Selectors (Table) ................................................................................................................................... 14 Summary of Defaults for I/O Options ................................................................................................................................... 15 I/O Options Section ................................................................................................................................... 22 Subcase Information Section ................................................................................................................................... 233 Bulk................................................................................................................................... Data Section 318 Element Quality Check ................................................................................................................................... 2160 Material Property Check ................................................................................................................................... 2189 Output Data ............................................................................................................................................... 2197 List of Files Created by OptiStruct (Alphabetical) ................................................................................................................................... 2200 Results Output by OptiStruct ................................................................................................................................... 2346 Legacy Data ............................................................................................................................................... 2378 Previous (OS3.5) Input Format ................................................................................................................................... 2379 Setting Up Decks in OptiStruct 5.0 with OptiStruct 3.5 Objectives and Constraints ................................................................................................................................... 2384 Previously Supported Input ................................................................................................................................... 2388

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Reference Guide Input Data Output Data Legacy Data

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Input Data I/O Options Section Subcase Information Section Bulk Data Section Element Quality Check Material Property Check

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The Bulk Data Input File The input file in OptiStruct is composed of three distinct sections: The I/O Options Section The Subcase Information Section The Bulk Data Section The I/O Options Section controls the overall running of the analysis or optimization. It controls the type, format, and frequency of the output, the type of run (check, analysis, super element generation, optimization or optimization restart), and the location and names of input, output, and scratch files. The Subcase Information Section contains information for specific subcases. It identifies which loads and boundary conditions are to be used in a subcase. It can control output type and frequency, and may contain objective and constraint information for optimization problems. For more information on solution sequences, see the table included on the Solution Sequences page of the online help. The Bulk Data Section contains all finite element data for the finite element model, such as grids, elements, properties, materials, loads and boundary conditions, and coordinates systems. For optimization, it contains the design variables, responses, and constraint definitions. The bulk data section begins with the BEGIN BULK statement.

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These sections can be arranged in either a one-file setup or a multi-file setup (there is also an obsolete two-file setup that is no longer recommended).

One-File Setup In a one-file setup, all three data sections are included in one file. The bulk data section must be the last section. It is recommended that the extension .fem be used for this file.

Multi-File Setup A multi-file setup is facilitated through the use of INCLUDE statements. This option enables you to include information from other files without cutting and pasting. INCLUDE statements may be placed in any section of the one or two-file setup, but must include information appropriate to the section. The following example shows how an additional subcase can be added to the Subcase Information section. input.fem file

sub2.inc

$ Subcase 1 SPC = 1 Load = 2 $ INCLUDE sub2.inc $ BEGIN BULK $

Subcase 2 SPC = 1 Load = 3

The solver reads all files and positions the lines of the included file at the location of the INCLUDE statement in the input.fem file. An echo of the input.fem file as read by OptiStruct would be: $ Subcase 1 SPC = 1 Load = 2 $ Subcase 2 SPC = 1 Load = 3 $ BEGIN BULK $

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Two-File Setup This setup is obsolete; the one-file or multiple-file setups are recommended. The two-file setup separates the control data (I/O Options section and Subcase Information section) from the model data (Bulk Data section). If the input file does not contain a BEGIN BULK statement, the solver attempts to read the model data from another file: If the INFILE card is present in the I/O Options section, the argument given on this card is the name of the file that contains the model data. If the INFILE card is not present in the I/O Options section, and the input file does not have the extension .fem, the name of the file containing the model data will be constructed from the input file by replacing the extension with .fem. The two-file setup allows you to perform runs using multiple control data files and a single model file and vice versa. It is recommended that the .parm extension be used for control data files and the .fem extension be used for model data files. Notes: The format of the input sections in OptiStruct are similar to those of the Nastran format. File names specified on INCLUDE and other cards (RESTART, EIGVNAME, LOADLIB, OUTFILE, TMPDIR, ASSIGN) can be arbitrary file names with optional paths appropriate to the operating system (Windows or UNIX). They may be enclosed in quotes (double or single quotes can be used), and either forward slash (/) or back slash (\) characters can be used to separate parts of the pathname. The solver uses the following rules to locate a file name on the INCLUDE cards: When the argument contains the absolute path of the file (if it starts with "/" on UNIX or a drive letter, such as "D:", on Windows, for example), the file at the given location is used. When only the file name is given (without the path), the file has to be located in the same directory as the file containing the INCLUDE statement. When the argument contains a relative path (../filename or sub/filename, for example), it is located in the directory relative to the file containing the INCLUDE statement and is NOT relative to the directory in which the solver was executed, or to the directory where the main file is located.

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Compressed input files An input file and referenced included files can be optionally compressed using gzip compression. A compressed file has to have the extension .gz appended to the file name. Valid example file names are: input.fem.gz, input.gz, and input.dat.gz. Compressed files can be mixed with plain ASCII files. The INCLUDE card does not have to be modified when a file is compressed. For example, if the card INCLUDE infile.dat were present, the reader would search for infile.dat and continue on to search for the compressed file, infile.dat.gz, if not found. Other input files (such as RESTART, ASSIGN) cannot be compressed.

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Guidelines for I/O Options and Subcase Information Entries The following guidelines apply to all entries in the I/O Options and Subcase Information sections: All input cards are limited to 80 characters per line; all characters after the 80th are skipped. SYSSETTING,CARDLENGTH may be used to change the number of characters allowed in each line. Cards which require a file name (OUTFILE, RESTART, INCLUDE, LOADLIB, TMPDIR, EIGVNAME, ASSIGN) can contain up to 200 characters in a single line. Alternatively, the file name may be continued in several lines if it is enclosed in quotes (" or ‘). When combining continuation lines, all trailing and leading blanks in each line are omitted. Other blanks, including all blanks between the quote and file name, are considered as part of the file name. File names can contain an absolute or relative path. Forward slash (/) or back slash (\) characters can be used to separate parts of a path name. Absolute paths are discouraged since they prevent moving files from one location to another, and may cause unexpected failures, as in PBS or a similar batch environment. Windows style file names, starting with the drive letter (for example: D:/users/mbg/ workarea), can be used on UNIX/Linux only when environment variable(s) DOS_DRIVE_# are defined. Content of the respective environment variable replaces the first two letters (‘D:’) in the file name, and the expanded file name must fit within 200 characters. Alternatively, the DOS_DRIVE_# option can be specified in the config file. UNC format (//server/path/filename) is not accepted. Each line of data contains up to ten fields in free format. Entries in the free format are separated by any number of characters from the following set: (blank) , (comma) ( ) = File names and titles (TITLE, SUBTITLE, LABEL) are exceptions to this rule. P2G / K2GG / M2GG / B2GG entries allow more than ten fields per line (up to CARDLENGTH limit). GROUNDCHECK / WEIGHTCHECK / EIGVRETRIEVE / XYPLOT allow more than ten fields per line and are the only entries which allow continuation. Dollar signs, $, in any column denote comments. All characters after the dollar sign until the end of the line are ignored. A dollar sign can be a part of a file name or title, but the full title or file name must be enclosed in quotes (" or ‘) in such cases. Lines which begin with two slashes, //, or a pound symbol, #, are read as comment lines. Blank lines are also assumed to be comment lines.

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Continuation lines are marked with a trailing comma character in the preceding line. Numeric entries must start with a digit, ‘+’, or ‘-’. Integer entries may not contain decimal points or exponent parts, and must fit in the range of values allowed for INTEGER*4 (usually –2**31

ALL, blank:

Output is at all times.

SID:

If a set ID is given, output is only at times in that set.

Default = ALL

Comments 1.

When an OTIME command is not present the output for all times will be computed.

2.

This command is particularly useful for requesting a subset of the output (for example, stresses at only peak times, and so on).

\

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OUTFILE I/O Options Entry OUTFILE - Filename Definition Description The OUTFILE command is used in the I/O Options section to define the prefix for the results files output. Format OUTFILE = option

Argument

Options

Description

option



file prefix: The path to and file prefix used for the results files output.

Default = passed in from the command line. Comments 1.

Prefixes specified on the OUTFILE card can be arbitrary file prefixes with optional paths appropriate to the operating system (Windows or UNIX). They may be enclosed in quotes (double or single quotes can be used), and either forward slash (/) or back slash (\) characters can be used to separate parts of the path name. The following rules are used for the OUTFILE card: When the argument contains an absolute path of the file (if it starts with "/" on UNIX or a drive letter, such as "D:", on Windows, for example), output files are created at the given location. When only the file prefix is given (without the path), output files will be created in the current directory, meaning the directory from which the solver has been executed, and not in the directory where the input file is located. When the argument contains a relative path (../filename or sub/filename, for example), output is created in a directory relative to where the solver is executed and NOT relative to the directory where the input file is located.

2.

The total length of information on this card is limited to 200 characters (including the card name and spaces between arguments). This data can be on a single line or span multiple continuation lines. See Guidelines for I/O Options and Subcase Information Entries for an example showing how to enter long file names on multiple lines.

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OUTPUT I/O Options Entry OUTPUT – Output Control Description The OUTPUT command can be used in the I/O Options section to control the format of results output and the creation of certain results files. Format OUTPUT, keyword, frequency, option1, option2

Argument

Options

Description

keyword

See below

See below

frequency

FIRST, LAST, FL, ALL, NONE, N or blank

FIRST:

Output first iteration only.

LAST:

Output last iteration only.

FL:

Output first and last iterations.

ALL:

Output all iterations.

NONE:

No output

N:

Output first and last iterations and every Nth iteration. If N=5, output occurs at iterations 0, 5, 10, 15, 20, and so on, and the final iteration.

blank:

The default listed below for the given keyword.

option

See below

See below

Standard Result Outputs Note that if there is no result OUTPUT defined, then default result output is both HM and H3D. If any result OUTPUT commands exist, then there is no default OUTPUT type.

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Keyword Description

HM

Output results in HyperMesh binary format.

Default frequency FL

Affect ed files *.res

Options

Details



Determines whether or not to output results for interior points of external superelements. See comment 16.

Default = DMIGSET

NODMIG: recovery is deactivated DMIGALL: recovery is activated for all grids/ elements DMIGSET: recovery is activated for grids/elements in the SET defined on the corresponding output request (default)

H3D, HV

Output results in Hyper3D format.

FL

*.h3d

Default = BYSUB

Determines the way the output files are arranged in an optimization run. See comment 15.

(Applicable to optimization runs only). Default = DMIGSET

Determines whether or not to output results for interior points of external superelements. See comment 16. NODMIG: recovery is deactivated DMIGALL: recovery is activated for all grids/ elements DMIGSET: recovery is activated for grids/elements in the SET defined on the corresponding output request

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Keyword Description

Default frequency

Affect ed files

Options

Details

(default)

OP2, OUT2, OUTPUT2

Output analysis results in Nastran output2 format.

FL

*.op2



Turns on / off the output of the model data to the file.

Default = MODEL

See comments 11 and 12.

Default = DMIGSET

Determines whether or not to output results for interior points of external superelements. See comment 16. NODMIG: recovery is deactivated DMIGALL: recovery is activated for all grids/ elements DMIGSET: recovery is activated for grids/elements in the SET defined on the corresponding output request (default)

NASTRAN , PUNCH

Output analysis results in Nastran punch format.

FL

*.pch

Default = DMIGSET

Determines whether or not to output results for interior points of external superelements. See comment 16. NODMIG: recovery is deactivated DMIGALL: recovery is activated for all grids/ elements

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Keyword Description

Default frequency

Affect ed files

Options

Details

DMIGSET: recovery is activated for grids/elements in the SET defined on the corresponding output request (default) OPTI, ASCII, OS

Output results in OptiStruct ASCII format.

FL

*.cstr , *.dens , *.disp , *.forc e, *.gpf, *.load , *.mpcf , *.spcf , *.strs

-

-

PATRAN, APATRAN

Output analysis results in Patran ASCII format.

FL

*.#.#. #.dis, *.#.#. dis, *.#.#. els, *.#.di s, *.#.el s,

-

-

(APATRAN uses an alternate file naming convention , with the iteration number after the file extension).

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*.#.#. dis.#, *.#.di s.#, *.#.el s.#, *.dis. #, *.els. #

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Keyword Description

NONE

Default frequency

Affect ed files

-

-

Default frequenc y

Affected files

Results are not output in any of the formats listed above.

Options

Details

-

-

Optimization Outputs

Keyword

Description

DESIGN

Controls the frequency of output for design results such as DENSITY, SHAPE, and THICKNESS

ALL

SHRES

Controls the frequency of output of the shape files.

GRID

Requests the output of the state file (.grid file) for topography or shape optimization.

Options

Details

All files that design results are written to.

-

-

L

*.sh, *.grid

-

-

L

*.grid

BASIC: Grid definitions are Default = BASIC output to the .grid file, referencing the basic coordinate system. LOCAL: Grid definitions are output to the .grid file, referencing local coordinate systems as

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Keyword

Description

Default frequenc y

Affected files

Options

Details

defined by the CP field on the GRID definitions. FSTOSZ

Automatic generation of a sizing model after freesizing of a composite structure.

L

*_sizing.fe m

1.

Bundles

See comment 18.

Integer > 0 Default = 4 2.

Method Default = ADVFREE

3.

SZTOSH

Automatic generation of a shuffling model after ply-based sizing optimization.

L

*_shuffling .fem

FSTHICK

Controls output of freesizing results to .fsthick file.

-

*.fsthick

Requests the output of updated design variable values.

L

DESVAR

Ignore -



-

See comment 13.

Default = NO

*.desvar, *.out

Default = FILE

FILE: Updated property design variable values are output to the .desvar file. OUT: Updated design variable values are output to the .out file.

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Keyword

Description

Default frequenc y

Affected files

Options

Details

BOTH: Updated design variable values are output to both the .out file and the .desvar file. NONE: Updated design variable values are not output. PROPERTY

Requests the output of the updated property definitions.

L

*.prop, *.out



ANY: All properties are output.

Default = DESIGN

DESIGN: Only designable properties are output.

Note: In the Description and Details columns of the PROPERTY keyword: “Property” stands for “Properties, Materials and Elements”.

FILE: Updated property definitions and non-design properties are output to the .prop file. OUT: Updated property definitions and non-design properties are output to the .out file. BOTH: Updated property definitions and non-design properties are output to both the .out file and the .prop file.

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Keyword

Description

Default frequenc y

Affected files

Options

Details NONE: Updated property definitions are not output.

Specialized Result Outputs

Keyword

Description

ADAMSMNF

Output of flexible body to a modal neutral file for MSC.ADAMS.

Default Affected files frequenc y -

*.mnf

Options



Details

-

Default = YES

See comment 17. HGFREQ

Frequency Analysis output presentation for HyperGraph.

FL

*_freq.mvw, *_s#_a.frf, *_s#_d.frf, *_s#_v.frf

-

-

-

*_tran.mvw, *_s#_a.trn, *_s#_d.trn, *_s#_v.trn

-

-

See comment 3. HGTRANS

Transient Analysis output presentation for HyperGraph. See comments 2 and 3.

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Keyword

Description

HGMBD

Multi-body Dynamics output presentation for HyperGraph.

Default Affected files frequenc y -

*_mbd.mvw, *_s#_a.mbd, *_s#_d.mbd, *_s#_v.mbd

Options

-

Details

-

See comments 2 and 3. HGSENS

Sensitivity output presentation for HyperGraph.

FL

*_sens.#.mvw, *.#.sens



See comment 4 for details on options.

Default = NOSTRESS MSSENS

Sensitivity output in Microsoft Excel SYLK format.

FL

*.#.slk



See comment 4 for details on options.

Default = NOSTRESS ASCSENS

H3DSENS

H3DTOPOL

138

Topology and free-sizing sensitivity (response with respect to design element density) output in ASCII format.

FL

Sensitivity output in H3D format.

FL

Sensitivity output in H3D format for contouring of topology and

FL

*.#.asens



See comment 4 for details on options.

Default = NOSTRESS

*_dsa.#.h3d

Default = NOUSER

*_topol.#.h3d



See comment 19 for details on options.

See comment 4 for details on options.

Default =

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Keyword

Description

Default Affected files frequenc y

free-sizing sensitivity. H3DGAUGE

HGHIST

Sensitivity output in H3D format for contouring of shell thickness sensitivity. Design history output presentation for HyperGraph.

HGEFFMASS Effective mass is output as a HyperGraph bar chart. HGMODFAC

DVGRID

Modal participation factor output presentation for HyperGraph3D. Output of shape variable definitions to .dvgrid file.

Options

Details

NOSTRESS

FL

*_gauge.#.h3d



See comment 4 for details on options.

Default = NOSTRESS -

-

FL

*_hist.mvw, *.hist *.hgdata

*.mass, *_mass.mvw

*_modal.mvw, *_modal.#.mvw

Integer < 32 Default = 31

-



See comment 5 for details on options.

-

See comment 14.

Default = REGULAR -

*.dvgrid

-

-

*.out

-

The center of gravity is specified in the basic coordinate system. The Mass Properties are with respect to the

See comment 6. MASSPROP

Controls the output of Center of Gravity and Mass Moments of Inertia tables based on properties to .out file.

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Keyword

Description

Default Affected files frequenc y

Options

Details

center of gravity of the item. MASSCOMP

Controls the output of Mass based on HyperMesh Components to .out file.

REGCOMPL

Controls the output of regional compliance table to .out file.

FL

*.out

*.out

-

-

Default = YES

File Output Controls

Keyword

Description

CMF

Controls output of .cmf files.

OSS

Default frequenc y

Affected files

Options

-

*.HM.badel.c mf, *.HM.comp.cm f, *.HM.ent.cmf , *.HM.conn.cm f

Default = YES

Controls output of .oss file.

-

*.oss

Default = YES

HTML

Controls output of .html file.

-

*.html

Default = YES

STAT

Controls output

-

*.stat



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Details

See comment 9.

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Keyword

Description

Default frequenc y

Affected files

of .stat file.

Options

Details

Default = YES

Comments 1.

Frequency does not apply for any of the keywords where a dash (-) is given as the default frequency in the keywords table above.

2.

HGTRANS and HGMBD are currently available for analysis only.

3.

HGFREQ, HGTRANS, and HGMBD will only use output requests where a Set ID is specified. For example, if DISPLACEMENT = ALL or DISPLACEMENT(HG) = ALL is given, displacement information will not be present in the presentation, whereas if DISPLACEMENT = 1 or DISPLACEMENT(HG) = 1 is given, displacement information will be present in the presentation for the constituent nodes of Set 1.

4.

For HGSENS, ASCSENS, or MSSENS options: If NOSTRESS or blank: results are printed, but stress, strain, and force responses are ignored. If ALL or STRESS: results are printed, including stress, strain, and force responses.

5.

For HGHIST options: The integer value given is equal to the sum of the desired options: 1: Design Variable. 2: Objective function and maximum % constraint violation. 4: All non-stress responses. 8: All DRESP2 responses. 16: All DRESP3 responses. If blank: all of the above are output. For example: If you want Design Variables and all DRESP2 responses, you would use 9.

6.

The DVGRID option creates shape variable definitions for displacement or eigenvector results of linear static, normal modes, or liner buckling analyses. These shape variable definitions can then be used in subsequent optimizations. This process facilitates the use of "natural" shape functions.

7.

For the keywords HM, H3D, HV, ASCII, OPTI, OS, NASTRAN, PUNCH, OP2, OUT2, OUTPUT2, PATRAN and APATRAN, the information provided by the OUTPUT I/O option entry takes precedence over information provided on the older FORMAT and RESULTS I/O option entries.

8.

OUTPUT entries are read sequentially; therefore, where multiple OUTPUT entries exist with the same keyword, the last instance is used.

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9.

If OUTPUT,STAT,NO is defined, the *.stat file is deleted at the end of the run (as long as the run was successful), but the file always exists during the run.

10. OUTPUT,DESIGN takes precedence over the information provided on the older DENSRES I/O option entry. OUTPUT,DESIGN will write design results, at the frequency defined, to all active output formats (HM, H3D, or OPTI), regardless of the frequency chosen for that output format. By default, HM is the only active output format. 11. When CMSMETH is used, or when a full multi-body dynamics run is performed, the CMS stress modes can be written to OP2 format. This only happens when OUTPUT,OP2 (or FORMAT,OP2) is defined. One file for each is generated. Stresses are written for shells and solids, while forces are written for bars/beams and welds. Each mode is written as a static load case with ID equal to the mode index. This output is compatible with FEMFAT by MAGNA. 12. The MODEL/NOMODEL option for OUTPUT, OP2 may be overridden by the PARAM, OGEOM bulk data entry. 13. The FSTHICK keyword generates a file with the .fsthick extension. The file contains bulk data entries for elements (CQUAD4, CQUAD8, CTRIA3, and CTRIA6) contained in freesize design spaces. The element definitions have the optimized thickness defined as nodal thicknesses (Ti) for each element. 14. The HGMODFAC keyword generates a HyperGraph3D presentation providing 3D plots of modal participation factors. The plots display the mode number on the x-axis, the frequency (for frequency response analyses) or time (for transient analyses) on the yaxis and the modal participation factor on the z-axis. The NORM option normalizes the participation factors with respect to 1. In HyperGraph3D, it is possible to define cross-sections to generate 2D plots of either: a) Modal participation factor vs. frequency or time for a given number. b) Modal participation factor vs. mode number at a given frequency or time. For frequency response analyses, plots are generated for the real part, the imaginary part and the magnitude of the participation factors. Magnitude plot is visible by default, while real and imaginary plots are hidden by default. 15. The H3D output from optimization runs consists of a number of files. The BYSUB/BYITER option allows switching between two modes of H3D output. There is a no default option (BYSUB/BYITER) for analysis runs. BYSUB (This is the default option for optimization runs) outputs one _des.h3d file for the animation of the optimization history. The frequency of the optimization results in this file is defined by OUTPUT, DESIGN (Default = ALL). In addition, an _si.h3d file for each subcase i is written that contains the history of the analysis results for each subcase. Frequency determines the analysis result output frequency. Optimization results can be written to the subcase files using DENSITY, SHAPE, or THICKNESS output requests. (Using OUTPUT, H3D, or BYSUB for analysis runs (without optimization) will output the same files as above (except for the _des.h3d file), however no design results or analysis history will be available within the files).

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BYITER outputs one .#.h3d file per iteration that contains the optimization and analysis results for all subcases per iteration. Frequency determines at which iteration these files are created. It overwrites the default of OUTPUT, DESIGN unless an actual OUTPUT, DESIGN statement is present. In the case of a shape optimization, the GRID coordinates of the model in the respective iteration are updated to the new shape. (Using OUTPUT, H3D, or BYITER for analysis runs (without optimization) will output only one .h3d file since there are no multiple iterations). 16. Results for interior points of external superelements will be output by default to HM, H3D, PUNCH, and OP2 files. 17. If GPSTRESS output is requested in addition to OUTPUT, ADAMSMNF, then nodal stress results for solid elements will be written to the .mnf file. 18. For FSTOSZ options: Bundles: This specifies the number of ply bundles to be generated per fiber orientation. Method: Ply bundle thicknesses are determined based on the method defined. ADVFREE: Advanced algorithm with free thicknesses. ADVMAN: Advanced algorithm with manufacturable thicknesses. SIMFREE: Simple algorithm with free thicknesses. SIMMAN: Simple algorithm with manufacturable thicknesses. The advanced algorithm is available for 2, 4 and 8 ply bundles. It takes into account the thickness distribution when generating the ply bundles, which results in a more accurate representation of the original free-sized thickness profile. Ply bundle thickness can also be multiples of the manufacturable ply thickness. Ignore: Elements may be ignored in a given ply orientation when their thickness is less than 5% of the maximum thickness. This option is inactive by default. 19. H3DSENS, USER indicates that the user-defined responses should be included in the DSA output. NOUSER indicates that user-defined responses should not be included. In both cases, responses defined through the DSA output request are included in the DSA output.

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PFGRID I/O Options Entry PFGRID – Output Request for Acoustic Grid Participation Description The PFGRID command can be used in the I/O Options section to request output of acoustic grid participation factors for all frequency response subcases. The output will be in the .h3d file. Format PFGRID (GRIDS=setg, GRIDF=setfl, FREQUENCY=setf, NULL=ipower, RPCUTOFF=rval, RPDBACUT=rpdba, CONTOUR=YES/NO,PEAKOUT) = setdof/PEAKOUT Examples PFGRID(FREQUENCY=391)=12 PFGRID(PEAKOUT)=23 PFGRID(PEAKOUT)=PEAKOUT

Argumen Options t

Description

setg

ALL:

Output acoustic grid participation for all structural grid points at the fluid-structure interface.

NONE:

Do not output acoustic grid participation for any structural grid points.

SID:

Output acoustic grid participation factors for a set of grids. SID refers to the ID of a SET of type GRID.

ALL:

Output acoustic grid participation for all fluid grid points at the fluid-structure interface.

NONE:

Do not output acoustic grid participation for any fluid grid points.

SID:

Output acoustic grid participation factors for a set of grids. SID refers to the ID of a SET of type GRID.

Default = NONE

setfl

Default = NONE

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Argumen Options t

Description

setf

ALL:

Participation factors are processed for all excitation frequencies.

SID:

Participation factors are only processed for a set of excitation frequencies. SID refers to the ID of a SET of type FREQ.

Default = ALL

ipower



When the magnitude of a grid participation is below 10 to the minus ipower, the grid participation will not be output. In other words, if the grid participation is less than 10-ipower, the result output for this grid will be skipped.

Default = 30

rval

Default = 0.0

rpdba

Default = 0.0

CONTOUR

(YES/NO) Default = YES

PEAKOUT

The grid participation will be calculated at the excited frequencies when the magnitude of the pressure is above rval. The excitation frequency will be a subset of setf.

RPDBACUT is the decibel pressure cutoff value for fluid responses, and is similar to RPCUTOFF. It will take precedence over RPCUTOFF for fluid responses. A weighting is applied to RPDBACUT values at the excitation frequency. The grid participation will be calculated when the magnitude of the response is about the cutoff value. See comment 4 for decibel calculations and reference pressure settings.

If CONTOUR is specified as YES, the area projected value for the fluid grid participation is output. Otherwise, the output of fluid grid participation would be the actual complex value.

If PEAKOUT is present as an option inside the parenthesis of the PFGRID data, then the filtered frequencies from the PEAKOUT data will be considered for output of grid participation.

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Argumen Options t

Description

setdof/ PEAKOUT

Degrees of freedom for which the grid participation factors are to be processed. SID refers to the ID of a SET of type GRID. If “PEAKOUT” is specified instead of SID, the output will be considered at the filtered frequencies corresponding to the degree of freedom in the PEAKOUT card in the bulk section.



Comments 1.

Output is to the H3D file only.

2.

Acoustic grid participation factors are available in a coupled frequency response analysis (both in direct and modal frequency response).

3.

The FREQUENCY keyword can be used to select a subset of excitation frequencies available.

4.

The dB value is calculated using 20 * log10(P/P0), where P0 is the reference pressure. The reference pressure is dependent on the units specified on the UNITS input data. If the units are SI, the value is set as 2.0E-5 Pa. If they are CGS, it is set as 2.0E-4 barye. If they are MPa, it is set as 2.0E-11 MPa. If they are BG or EE, then it is set as 4.17E-7 lbf/ft 2. If no UNITS data is present, the default value is 2.0E-11 MPa.

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PFMODE I/O Options Entry PFMODE – Output Request for Modal Participation Description The PFMODE command can be used in the I/O Options section to request output of modal participation factors for all modal frequency response subcases. Format PFMODE (type, FLUIDMP=fmp, STRUCTMP=smp, PANELMP=setp, FREQUENCY=setf, FILTER=fratio, NULL=ipower, RPCUTOFF=rval, RPDBACUT=rpdba, MTYPE=otype, CMSSET=seset, RTYPE=rtype, outfile, PEAKOUT) = setdof/PEAKOUT Examples PFMODE(FLUID,STRUCTMP=30,FREQUENCY=391,PANELMP=ALL)=393 PFMODE(STRUCTURE,H3D)=23 PFMODE(FLUID,H3D,PEAKOUT)=11 PFMODE(STRUCTURE,H3D,PEAKOUT)=PEAKOUT PFMODE(FLUID,PUNCH)=31

Argument Options

Description

type

STRUCTURE:

Requests output of structural modal participation factors.

FLUID:

Requests output of acoustic modal participation factors.

ALL:

Participation factors will be computed for all calculated fluid modes.

Default = STRUCTURE

fmp



Default = NONE N:

NONE:

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Number of fluid modes for which modal participation factors will be computed, based on the largest magnitude of modal contribution. Participation factors are not calculated for fluid modes.

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Argument Options

Description

smp

ALL:



Default = NONE N:

setp





Participation factors are not calculated for structural modes.

ALL:

Output structural modal participation for each panel specified in the PANEL data.

NONE:

Do not output panel modal participation.

ALL:

Participation factors are processed for all excitation frequencies.

SID:

Participation factors are only processed for a set of excitation frequencies. SID refers to the ID of a SET of type FREQ.

Default = ALL

fratio



Specifies the value of a filter to be applied to the output. Values of modal participation below fratio times the displacement or pressure are not output.

Default = 0.001

ipower



When the magnitude of a modal participation is below 10 to the minus ipower, the modal participation will not be output. In other words, if the modal participation is less than 10-ipower, the result output for this mode will be skipped.

Default = 30

rval

Default = 0.0

148

Number of structural modes for which modal participation factors will be computed based on the largest magnitude of modal contribution.

NONE:

Default = NONE

setf

Participation factors will be computed for all calculated structural modes.

The modal participation will be calculated at the excited frequencies when the magnitude of the response is above rval. The excitation frequency will be a subset of setf.

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Argument Options

Description

rpdba

over RPCUTOFF for fluid responses. A weighting is applied to Default = 0.0 RPDBACUT values at the excitation frequency. The modal participation will be calculated when the magnitude of the response is about the cutoff value. See comment 9 for decibel calculations and reference pressure settings.

otype

the whole model. Component modal participation will not be output by default. However, when using ALL or CMS, the Default = component modal participation will be output. For the CMS SYSTEM option, there will not be system modal participation. Component modal participation can also be calculated for internal grids in the superelement.

seset

Default = ALL

Component modal participation of all the H3D superelements will be output by default. However, you can specify a specific set of superelement names for output.

rtype



The Structural modal participation will be output for Displacement, Velocity or Acceleration respectively based on Default = DISP the specified option (DISP, VELO, ACCE).

outfile

Modal participation can be exported either into the H3D file or PUNCH file. Because of the large volume of data, it is Default = H3D recommended to export the modal participation data into a H3D file.

PEAKOUT

If PEAKOUT is present inside the bracket of the PFMODE option, the filtered frequencies from the PEAKOUT card will be considered for the output of modal participation.

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Argument Options

Description

setdof/ PEAKOUT

Degrees-of-freedom for which the participation factors are to be processed. SID refers to the ID of a SET of type GRIDC for structure participation and GRID for fluid participation. If “PEAKOUT” is specified instead of SID, the output will be considered at the filtered frequencies corresponding to the degree of freedom on the PEAKOUT card in the bulk section.



Comments 1.

The output of both the PFMODE and PFPANEL must be either to an H3D file or to a PUNCH file. Both PFPANEL and PFMODE must have the same output option.

2.

The modal participation output is sorted in descending order by magnitude of the modal participation in the PUNCH file output.

3.

PFMODE(FLUID,..) and PFMODE(STRUCTURE,…) can coexist in the input data, but only one PFMODE(FLUID) and one PFMODE(STRUCTURE) are allowed in a single SUBCASE.

4.

Keywords FLUIDMP and PANELMP are only valid if FLUID is specified.

5.

If STRUCTURE is specified, setdof must reference a set of structural degrees-of-freedom. If FLUID is specified, setdof must reference a set of acoustic degrees-of-freedom.

6.

The FREQUENCY keyword can be used to select a subset of excitation frequencies available.

7.

The filter is applied to the magnitude of the modal participation factors. Only modal participation factors that pass the filter are output.

8.

If the magnitude of the total response at a selected response degree-of-freedom is less than 10-ipower, then no modal participation factors are processed. If ipower is not in the range of 1 to 31, the default of 30 is used.

9.

The dB value is calculated using 20 * log10 (P/P0), where P0 is the reference pressure. The reference pressure is dependent on the units specified on the UNITS input data. If the units are SI, the value is set as 2.0E-5 Pa. If they are CGS, it is set as 2.0E-4 barye. If they are MPa, it is set as 2.0E-11 MPa. If they are BG or EE, then it is set as 4.17E-7 lbf/ft 2. If no UNITS data is present, the default value is 2.0E-11 MPa.

10. Legacy format for the export of modal participation to H3D or PUNCH files: PFMODE (type, OUTPUT=outfile)=setdof/PEAKOUT is also supported. 11. If you wish to output modal participation factors for interior points of a superelement (in a CMS model), the SEINTPNT entry can be used in the subcase information section to convert the interior points of interest to exterior points. After conversion, these points can now be referenced by the option for the sedof/PEAKOUT argument.

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PFPANEL I/O Options Entry PFPANEL – Output Request for Acoustic Panel Participation Description The PFPANEL command can be used in the I/O Options section to request output of acoustic panel participation factors for all frequency response subcases. Format PFPANEL (PANEL=setp, FREQUENCY=setf, outfile,peakout) = setdof/PEAKOUT Examples PFPANEL(PANEL=ALL,FREQUENCY=45)=12 PFPANEL(H3D, PEAKOUT)=56 PFPANEL(H3D, PEAKOUT)=PEAKOUT PFPANEL(PUNCH)=32

Argumen Options t

Description

setp

ALL:

Output acoustic panel participation for all panels.

NONE:

Do not output acoustic panel participation.

ALL:

Participation factors are processed for all excitation frequencies.

SID:

Participation factors are only processed for a set of excitation frequencies. SID refers to the ID of a SET of type FREQ.

Default = NONE

setf

Default = ALL

outfile

Default = H3D

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Panel participation can be exported either into a H3D file or a PUNCH file. Because of the large volume of data, it is recommended to export the panel participation data into a H3D file.

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Argumen Options t

Description

PEAKOUT

If PEAKOUT is present as an option inside the parentheses of the PFPANEL data, then the filtered frequencies from the PEAKOUT data will be considered for output of panel participation.

setdof/ PEAKOUT



Degrees-of-freedom for which the panel participation factors are to be processed. SID refers to the ID of a SET of type GRID. If “PEAKOUT” is specified instead of SID, the output will be considered at the filtered frequencies corresponding to the degree-of-freedom in the PEAKOUT card in the bulk section.

Comments 1.

Output is to the H3D or PUNCH files only. The output of both PFMODE and PFPANEL must be either to an H3D file or to a PUNCH file. Both PFPANEL and PFMODE must have the same output option.

2.

Acoustic panel participation factors are available in a coupled frequency response analysis (both in direct and modal frequency response).

3.

The FREQUENCY keyword can be used to select a subset of excitation frequencies available. The closest loading frequency will be chosen in this case.

4.

Legacy format for the export of acoustic panel participation to H3D or PUNCH files: PFPANEL (OUTPUT=outfile)=setdof/PEAKOUT is also supported.

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PFPATH I/O Options Entry PFPATH – Output Request Description The PFPATH command can be used in the I/O Options section for transfer path analysis for a response at the connection points. Format PFPATH = SID Comments SID references a PFPATH card in the Bulk Data section.

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POWERFLOW I/O Options Entry POWERFLOW – Output Request Description The POWERFLOW command can be used in the I/O Options section to request output of the power flow field. Format POWERFLOW (format,peakoutput) = option

Argument Options

Description

format

H3D:

Results are output in Hyper3D format (.h3d file).

PEAKOUT:

If PEAKOUT is present, only the filtered frequencies from the PEAKOUT card will be considered for this output.

Default = H3D

peakoutpu t Default = blank

option

blank: Default = ALL

Power flow field is output for all elements.

NO, NONE:

Power flow field is not output.

SID:

If a set ID is given, power flow field is output only for the contents of that set.

Comments 1.

Power flow field output is only available to the .h3d file.

2.

The power flow field indicates the magnitude and direction of vibrational energy which travels in dynamically loaded structures. It helps with identifying the energy transmission paths as well as the vibration sources and energy sinks. Structural intensity, defined as the power flow per unit area, is also available.

3.

The references used in the calculation of the power flow field are listed in the References section of the User’s Guide.

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PRESSURE I/O Options and Subcase Information Entry PRESSURE - Output Request Description The PRESSURE command is analogous to the DISPLACEMENT command. Refer to the documentation for the DISPLACEMENT command.

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PRETBOLT I/O Options and Subcase Information Entry PRETBOLT - Output Request Description The PRETBOLT command can be used in the I/O Options or Subcase Information sections to request output of pretension force/adjustment values in the pretension bolts for all pretensioning and pretensioned subcases. Format PRETBOLT (format) = option

Argument

Options

Description

format



OPTI:

Results are output in OptiStruct results format (.pret file).

blank:

Results are output in all active formats for which the result is available.

YES:

Pretension force/adjustment values are output for all bolts.

NO:

Pretension force/adjustment values are not output.

Default = blank

option

Default = YES

Example PRETBOLT (OPTI) = YES PRETBOLT = NO PRETBOLT (OPTI) PRETBOLT Comments 1.

When a PRETBOLT command is not present, pretension force/adjustment values are not output.

2.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

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PROPERTY I/O Options Entry PROPERTY - Output Control Description The PROPERTY command can be used in the I/O Options section to request the output of the property definitions used in the final iteration of an optimization. Format PROPERTY = option

Argument

Options

Description

option



FILE or blank: Updated property definitions are output to the .prop file.

Default = FILE

OUT:

Updated property definitions are output to the .out file.

BOTH:

Updated property definitions are output to both the .out file and the .prop file.

NONE:

Updated property definitions are not output.

Comments 1.

When a PROPERTY command is not present the updated property definitions will not be output.

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RADSND I/O Options and Subcase Information Entry RADSND - References RADSND Bulk Data to specify sound generation panels and microphone field points Description The RADSND command can be used in the I/O Options or Subcase Information sections to request radiated sound output for all subcases or individual subcases respectively. Format RADSND = option

Argument

Options

Description

option



SID:

ID of RADSND bulk data entry.

No default Comments 1.

158

Multiple instances of this card are allowed. If the instances are conflicting, the last instance will be considered.

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RCROSS I/O Options Entry RCROSS – Output Request Description The RCROSS command can be used in the I/O Options section to request computation and output of cross-power spectral density functions for random response analysis. Format RCROSS(format_list,form,type, randid=RANDPS_ID) = option

Argume nt

Options

Description

format



PUNCH:

Results are output in Nastran punch results format (.pch file).

blank:

Results are output in all active formats for which the result is available.

COMPLEX:

Provides a combined magnitude/phase form of complex output to the .res file if HM output format is chosen. The REAL form of complex output is used for other formats if they are not specifically defined. (Phase output is in degrees).

REAL or IMAG:

Provides rectangular format (real and imaginary) of complex output.

PHASE:

Provides polar format (phase and magnitude) of complex output.

BOTH:

Provides both rectangular and polar formats of complex output.

PSDF:

Requests the cross-power spectral density function be calculated and output for random analysis postprocessing.

Default = blank

form

Default = COMPLEX

type

Default = PSDF

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Argume nt

Options

Description

option

RCROSS_ID:

Set identification of an RCROSS bulk data entry.

randid



Set identification number of a RANDPS bulk data entry (see comments 3 and 4).

Comments 1.

The RCROSS I/O option must be used in conjunction with the RANDOM subcase information entry.

2.

Response quantities, such as DISPLACEMENT, STRESS and STRAIN, must be requested by corresponding I/O Options in order to compute cross-power spectral density between the two response quantities specified by the RCROSS bulk data entry.

3.

Multiple RCROSS bulk data entries must be defined when each RCROSS subcase information entry references different randid. For example: rcross(PUNCH, rcross(PUNCH, rcross(PUNCH, rcross(PUNCH,

4.

160

PHASE, PHASE, PHASE, PHASE,

PSDF, PSDF, PSDF, PSDF,

randid=210020)=451 randid=210050)=452 randid=210070)=453 randid=210090)=454

randid= must be specified within the RCROSS I/O options entry when multiple RANDOM subcase information entries are present.

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REQUEST I/O Options and Subcase Information Entry REQUEST – Multi-Body Request Selection Description The REQUEST command can be used in the I/O Options or Subcase Information sections to select a multi-body request definition to be used in a multi-body problem. Format REQUEST = option

Argument

Option

Description

option



SID:

Set identification of MBREQ, MBREQE, or MBREQM bulk data entries.

No default Comments 1.

Only one REQUEST entry can be present for each subcase.

2.

This subcase information entry is only valid when it appears in a multi-body subcase.

3.

If the SID referenced by the REQUEST subcase information entry matches with the SID defined for an MBREQ bulk data entry, the information on this entry alone is selected. However, if no MBREQ bulk data entry has the referenced SID defined, any of the multibody motion entries: MBREQE or MBREQM which have this SID will be selected.

4.

If present above the first subcase, it is applied to each multi-body dynamics subcase without a REQUEST entry.

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RESPRINT I/O Options Entry RESPRINT - Output Control Description The RESPRINT command can be used in the I/O Options section to force all unretained responses of a certain type to be printed to the output file, provided they are referenced either as an objective or a constraint. This also applies to manufacturing constraints for composites. Format RESPRINT = option

Argument Options

Description

option

MASS:

Mass and massfrac responses are output.

VOLUME:

Volume and volfrac responses are output.

DISP:

Acceleration, Displacement and Velocity responses are output.

BUCK:

Buckling responses are output.

STRESS:

Stress responses, including CSTRESS and CFAILURE responses, are output.

FREQ:

Frequency responses are output.

EQUA, WCOMP, WFREQ, or COMB:

All equation and combination responses are output.

EXTERNAL:

External responses (defined by DRESP3) are output.

COMP:

Compliance responses are output.

No default

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Argument Options

Description STRAIN:

Strain responses, including CSTRAIN responses, are output.

FORCE:

Force responses are output.

COG:

Center of gravity responses are output.

INERTIA:

Inertia responses are output.

MANUF:

Manufacturing constraints for composites are output.

ALL:

All design responses are output. However, manufacturing constraints for composites are not listed.

Comments 1.

When a RESPRINT command is not present, only retained responses will be output.

2.

The arguments may be placed on a single card in a comma-separated list. For example: RESPRINT = STRESS, DISP will force all stress and displacement responses referenced as either an objective or constraint to be output.

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RESTART I/O Options Entry RESTART - Run Control Command Description The RESTART command can be used in the I/O Options section to indicate that the current optimization is to be restarted from the final iteration of a previous optimization. Format RESTART = option

Argument

Options

Description

option



File prefix:

Default = prefix of .fem file

The prefix of the .sh file to be used as the starting iteration for the restart.

Comments 1.

To restart an optimization, you will need information about the final iteration of a previous optimization run. This information is contained in the .sh file.

2.

The purpose of the restart functionality is for restarting with unconverged optimization runs or optimization runs that were terminated before completion (due to a power outage, and so on). Only limited changes are allowed to be made to the model data. Refer to the User's Guide section Restarting OptiStruct.

3.

This I/O Option is not valid for analysis mode.

4.

Output files from a restart run are appended with the extension _rst#, where # is a 3 digit number indicating the starting iteration for the restart run. For example, filename_rst030.out is the .out file created when restarting filename.fem from iteration 30.

5.

The total length of information on this card is limited to 200 characters (including the card name and spaces between arguments). This data can be on a single line or span multiple continuation lines. See Guidelines for I/O Options and Subcase Information Entries for an example showing how to enter long file names on multiple lines.

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RESULTS I/O Options Entry RESULTS - Output Control Description The RESULTS command can be used in the I/O Options or Subcase Information sections to determine the frequency of output of analysis results for all subcases or for individual subcases respectively. Format RESULTS = frequency

Argument

Options

Description

frequency



FIRST:

Output analysis results for the first iteration only.

Default = FL

LAST:

Output analysis results for the final iteration only.

FL, blank:

Output analysis results for both the first and last iterations.

ALL:

Output analysis results for all iterations.

NONE:

Do not output analysis results.

N:

Output analysis results for the first and last iterations and for every Nth iteration. If N = 5, output occurs for iterations 0, 5, 10, 15, 20, and so on, and the final iteration. All equation and combination responses are output.

Comments 1.

When a RESULTS command is not present, analysis results are output for formats that are activated by the FORMAT command for both the first and last iterations.

2.

The information on this card pertains to all analysis output formats that are not specifically described by an OUTPUT command.

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3.

166

It is recommended to use the OUTPUT command as it allows different frequencies of output to be defined for different formats.

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SACCELERATION I/O Options and Subcase Information Entry SACCELERATION - Output Request Description The SACCELERATION command can be used in the I/O Options or Subcase Information sections to request the form and type of modal participation accelerations output for all subcases or individual subcases respectively. Format SACCELERATION (sorting,format_list,form,peakoutput) = option

Argument

Options

Description

sorting



This argument only applies to the PUNCH format (.pch file) or the OUTPUT2 format (.op2 file) output for normal modes, frequency response, and transient subcases. It will be ignored without warning if used elsewhere.

Default = blank

format

SORT1:

Results for each frequency/ timestep are grouped together.

SORT2:

Results for each grid/element are grouped together (See comment 7).

blank:

SORT1 is used for all results except for transient analysis, where SORT2 is used.



H3D:

Results are output in Hyper3D format (.h3d file).

Default = blank

PUNCH:

Results are output in Nastran punch results format (.pch file).

OP2:

Results are output in Nastran output2 format (.op2 file) (see comment 9).

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Argument

form

Options

Description PLOT:

Results are output in Nastran output2 format (.op2 file) when PARAM, POST is defined in the bulk data section.

blank:

Results are output in all active formats for which the result is available.

REAL or IMAG:

Provides rectangular format (real and imaginary) of complex output.

PHASE:

Provides polar format (magnitude and phase) of complex output. Phase output is in degrees.

PEAKOUT:

If PEAKOUT is present, only the filtered frequencies from the PEAKOUT card will be considered for this output.



YES, ALL, blank:

Results are output.

Default = ALL

NO, NONE:

Results are not output.

Default = REAL

peakoutput

Default = blank

option

Comments 1.

When the SACCELERATION command is not present, modal participation accelerations are not output.

2.

The SACCELERATION command is only valid for modal frequency response and modal transient solution sequences.

3.

The OFREQUENCY and OTIME I/O Options may be used to control the amount of output.

4.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

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5.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

6.

For optimization, the frequency of output to a given format is controlled by the I/O option OUTPUT. In previous versions of OptiStruct, a combination of the I/O options FORMAT and RESULTS were used; this method is still supported, but not recommended as it does not allow different frequencies for different formats.

7.

In general, HyperView does not recognize the SORT2 format for results from the .op2 file. When results are output only in SORT2 format ( (SORT2, OUTPUT2, … .)), the results are written by OptiStruct into the .op2 file in SORT2 format, but when the .op2 file is imported into HyperView, the results in SORT2 format are not recognized. Therefore, the SORT1 option is recommended for results output in OUTPUT2 format and SORT2 option is recommended for results output in PUNCH format.

8.

The abbreviations SACCE and SACCEL are interchangeable with SACCELERATION.

9.

format=OUTPUT2 can also be used to request results to be output in the Nastran output2 format (.op2 file).

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SCREEN I/O Options Entry SCREEN - Output Control Description The SCREEN command can be used in the I/O Options section to control the output of model, analysis, and optimization information to the UNIX or DOS shell. Format SCREEN = option

Argument

Options

Description

option



OUT, blank:

The .out file is echoed to the screen.

Default = NONE

LOG:

A log of the optimization process is echoed to the screen.

NONE:

No information is echoed to the screen.

Comments 1.

When a SCREEN command is not present, no information is echoed to the screen.

2.

If the option LOG is chosen, the value of the objective function and the maximum constraint violation at every iteration, as well as indication of satisfied convergence ratios, are echoed to the screen.

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SDISPLACEMENT I/O Options and Subcase Information Entry SDISPLACEMENT - Output Request Description The SDISPLACEMENT command can be used in the I/O Options or Subcase Information sections to request the form and type of modal participation displacements output for all subcases or individual subcases respectively. Format SDISPLACEMENT (sorting,format_list,form,peakoutput) = option

Argument

Options

Description

sorting



This argument only applies to the PUNCH format (.pch file) or the OUTPUT2 format (.op2 file) output for normal modes, frequency response, and transient subcases. It will be ignored without warning if used elsewhere.

Default = blank

format

SORT1:

Results for each frequency/timestep are grouped together.

SORT2:

Results for each grid/element are grouped together (See comment 7).

blank:

SORT1 is used for all results except for transient analysis, where SORT2 is used.



Results are output in Hyper3D format (.h3d file).

Default = blank

PUNCH:

Results are output in Nastran punch results format (.pch file).

OP2:

Results are output in Nastran output2 format (.op2 file) (see comment 9).

PLOT:

Results are output in Nastran output2 format (.op2 file) when PARAM, POST is defined in the bulk data section.

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Argument

Options

Description blank:

form

Results are output in all active formats for which the result is available.

REAL, IMAG:

Provides rectangular format (real and imaginary) of complex output.

PHASE:

Provides polar format (magnitude and phase) of complex output. Phase output is in degrees.

PEAKOUT:

If PEAKOUT is present, only the filtered frequencies from the PEAKOUT card will be considered for this output.



YES, ALL, blank:

Results are output.

Default = ALL

NO, NONE:

Results are not output.

Default = REAL

peakoutput Default = blank

option

Comments 1.

When the SDISPLACEMENT command is not present, modal participation displacements are not output.

2.

The SDISPLACEMENT command is only valid for modal frequency response and modal transient solution sequences.

3.

The OFREQUENCY and OTIME I/O options may be used to control the amount of output.

4.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

5.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

6.

For optimization, the frequency of output to a given format is controlled by the I/O option OUTPUT. In previous version of OptiStruct, a combination of the I/O options FORMAT and RESULTS were used; this method is still supported, but not recommended as it does not allow different frequencies for different formats.

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7.

In general, HyperView does not recognize the SORT2 format for results from the .op2 file. When results are output only in SORT2 format ( (SORT2, OUTPUT2, … .)), the results are written by OptiStruct into the .op2 file in SORT2 format, but when the .op2 file is imported into HyperView, the results in SORT2 format are not recognized. Therefore, the SORT1 option is recommended for results output in OUTPUT2 format and SORT2 option is recommended for results output in PUNCH format.

8.

The abbreviation SDISP is interchangeable with SDISPLACEMENT.

9.

format=OUTPUT2 can also be used to request results to be output in the Nastran output2 format (.op2 file).

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SENSITIVITY I/O Options Entry SENSITIVITY - Output Request Description The SENSITIVITY command can be used in the I/O Options section to request the output of the responses and sensitivities for size and shape design variables to a Microsoft Excel spreadsheet. Format SENSITIVITY = option

Argument

Options

Description

option



NO, NONE:

The results and sensitivities are not output.

Default = NONE

YES, NOSTRESS, blank:

The results and sensitivities are output excepting stress, strain, and force responses.

ALL or STRESS:

The results and sensitivities are output including stress, strain, and force responses.

Comments 1.

This command is ignored when OUTPUT, MSSENS command is present.

2.

When SENSITIVITY is not present, sensitivity information is not output.

3.

The frequency of this output is controlled by the SENSOUT option.

4.

For more details on the output format, go to the #.slk file page in the output section of the Reference Guide.

5.

Additional sensitivity output requests for topology, free-sizing and gauge design variables can be made through OUTPUT,H3DTOPOL and OUTPUT,H3DGAUGE (in H3D format), and OUTPUT,ASCSENS (ASCII format).

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SENSOUT I/O Options Entry SENSOUT - Output Control Description The SENSOUT command can be used in the I/O Options section to control the frequency of output of responses and sensitivities for size and shape design variables to a Microsoft Excel spreadsheet. Format SENSOUT = frequency

Argument

Options

Description

frequency



FIRST:

The results and sensitivities are output for the first iteration only.

Default = FL

LAST:

The results and sensitivities are output for the final iteration only.

FL, blank:

The results and sensitivities are output for both the first and last iterations.

ALL:

The results and sensitivities are output for all iterations.

N:

The results and sensitivities are output for the first and last iterations and for every Nth iteration. If N = 5, output occurs for iterations 0, 5, 10, 15, 20, and so on, and the final iteration. All equation and combination responses are output.

Comments 1.

This command is ignored when OUTPUT, MSSENS command is present.

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SHAPE I/O Options and Subcase Information Entry SHAPE - Output Request Description The SHAPE command can be used in the I/O Options section to request altered shape output for a shape optimization. Format SHAPE (format_list,type) = option

Argument Options

Description

format

HM:

Results are output in HyperMesh results format (.res file).

H3D:

Results are output in Hyper3D format (.h3d file).

blank:

Results are output in all active formats for which the result is available.

ALL:

Results are output in all simulations.

DES, blank:

Results are only output in the design history simulations.

YES, ALL, blank:

Results are output.

NO, NONE:

Results are not output.

Default = blank

type

Default = DES

option

Default = YES

Comments 1.

When the SHAPE command is not present, shape results are output.

2.

Shape results are only available for shape, topography, and free-shape optimizations.

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3.

Outputting the shape results in all simulations allows analysis results to be plotted on the altered shape.

4.

The frequency of this output is controlled by the DESIGN keyword on an OUTPUT definition or, if no OUTPUT definition exists with the DESIGN keyword, by the DENSRES I/O option.

5.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

6.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

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SINTENS I/O Options and Subcase Information Entry SINTENS - Output Request Description The SINTENS command can be used in the I/O Options section to request Sound Intensity output for all frequency response subcases. The SINTENS command can be used in the I/O Options or Subcase Information sections to request Sound Intensity output for all subcases or individual subcases respectively. Format SINTENS(type) = option

Argument Options

Description

type

PANEL, blank:

Sound Intensity is output for both panels and microphone locations.

NOPANEL:

Sound Intensity is output only for microphone locations.

ALL, blank:

Sound Intensity is output for all panel grids and all grids defined as microphone locations on the RADSND bulk data. In addition, the total Sound Intensity for each Panel and all the microphone locations is output.

Default = PANEL

option

Default = ALL

Note: Sound Intensity is output only for microphone locations if type=NOPANEL is specified. Comments 1.

When the SINTENS command is present, Sound Intensity is output for all RADSND panel grids and all microphone grids for all frequency response subcases. (If type=NOPANEL is specified, sound intensity results are output only for microphone locations).

2.

Sound Intensity results (via SINTENS) are output to the .h3d file.

3.

SINTENS can only be requested for frequency response subcases.

4.

Sound intensity is always output for microphone locations regardless of the specified type (PANEL/NOPANEL).

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SPCFORCE I/O Options and Subcase Information Entry SPCFORCE - Output Request Description The SPCFORCE command can be used in the I/O Options or Subcase Information sections to request single-point force of constraint vector output for all subcases or individual subcases respectively. Format SPCFORCE (sorting,format_list,form,type,peakoutput) = option

Argument

Options

Description

sorting



This argument only applies to the PUNCH format (.pch file) or the OUTPUT2 format (.op2 file) output for normal modes, frequency response, and transient subcases. It will be ignored without warning if used elsewhere.

Default = blank

format



SORT1:

Results for each frequency/timestep are grouped together.

SORT2:

Results for each grid/element are grouped together (See comment 10).

blank:

For frequency response analysis, if no grid SET is specified, SORT1 is used, otherwise, SORT2 is used.

HM:

Results are output in HyperMesh results format (.res file).

H3D:

Results are output in Hyper3D format (.h3d file).

OPTI:

Results are output in OptiStruct results format (.spcf file).

PUNCH:

Results are output in Nastran punch results

Default = blank

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Argument

Options

Description format (.pch file).

form



OP2:

Results are output in Nastran output2 format (.op2 file) (see comment 11).

PLOT:

Results are output in Nastran output2 format (.op2 file) when PARAM, POST is defined in the bulk data section.

blank:

Results are output in all active formats for which the result is available.

COMPLEX (HM only), blank:

Provides a combined magnitude/phase form of complex output to the .res file for the HM output format.

Default (HM only) REAL, = COMPLEX IMAG: Default (all other formats) = REAL PHASE:

type



Provides rectangular format (real and imaginary) of complex output. Provides polar format (magnitude and phase) of complex output. Phase output is in degrees.

BOTH (HM only):

Provides both polar and rectangular formats of complex output.

ALL:

Single-point force of constraint is output for all selected nodes.

SPARSE:

Single-point force of constraint is output only for selected nodes with a component with a magnitude of 1.0E-10 or greater.

PEAKOUT:

If PEAKOUT is present, only the filtered frequencies from the PEAKOUT card will be considered for this output.

Default = SPARSE

peakoutput Default = blank

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Argument

Options

Description

option



YES, ALL, blank:

Single-point force of constraint is output for all nodes.

NO, NONE:

Single-point force of constraint is not output.

SID:

If a set ID is given, single-point force of constraint is output only for nodes listed in that set.

Default = ALL

Comments 1.

When an SPCFORCE command is not present, single-point force of constraint vector is not output.

2.

Single-point force of constraint values are highly dependent on mesh density and type of elements used.

3.

For modal frequency analysis, residual forces are zero only in modal space. Therefore, the single-point force of constraint vector may not be accurate unless all modes are used in the modal solution. When all possible modes in the model space are used, the modal frequency analysis solution should match the direct frequency analysis solution.

4.

When single-point force of constraint is calculated, the reaction force summary, the load summary, and the strain energy residuals for the affected subcases are written to the .out file.

5.

The form argument is only applicable for frequency response analysis. It is ignored in other instances.

6.

The forms BOTH and COMPLEX do not apply to the .frf output files.

7.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

8.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

9.

For optimization, the frequency of output to a given format is controlled by the I/O option OUTPUT. In previous versions of OptiStruct, a combination of the I/O options FORMAT and RESULTS were used; this method is still supported, but not recommended as it does not allow different frequencies for different formats.

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10. In general, HyperView does not recognize the SORT2 format for results from the .op2 file. When results are output only in SORT2 format ( (SORT2, OUTPUT2, … .)), the results are written by OptiStruct into the .op2 file in SORT2 format, but when the .op2 file is imported into HyperView, the results in SORT2 format are not recognized. Therefore, the SORT1 option is recommended for results output in OUTPUT2 format and SORT2 option is recommended for results output in PUNCH format. 11. format=OUTPUT2 can also be used to request results to be output in the Nastran output2 format (.op2 file).

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SPL I/O Options and Subcase Information Entry SPL - Output Request Description The SPL command can be used in the I/O Options or Subcase Information sections to request Sound Pressure output for all subcases or individual subcases respectively. SPL can only be requested for frequency response subcases. Format SPL = option

Argument Options

Description

option

ALL, blank:

Default = ALL

Sound Pressure is output for all grids defined as microphone locations on the RADSND bulk data.

Comments 1.

When the SPL command is present, Sound Pressure is output for all microphone grids for all frequency response subcases.

2.

Sound Pressure results (via SPL) are output to the .h3d file.

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SPOWER I/O Options and Subcase Information Entry SPOWER - Output Request Description The SPOWER command can be used in the I/O Options or Subcase Information sections to request Sound Power output for all subcases or individual subcases respectively. SPOWER can only be requested for frequency response subcases. Format SPOWER(type) = option

Argument Options

Description

type

PANEL, blank:

Sound Power is output for both panels and microphone locations.

NOPANEL:

Sound Power is output only for microphone locations.

ALL, blank:

Sound Power is output for all panel grids and all grids defined as microphone locations on the RADSND bulk data. In addition, the total Sound Power for each Panel and all the microphone locations is output.

Default = PANEL

option

Default = ALL

Note: Sound Power is output only for microphone locations if type=NOPANEL is specified. Comments 1.

When the SPOWER command is present, Sound Power is output for all RADSND panel grids and all microphone grids for all frequency response subcases. (If type=NOPANEL is specified, sound power results are output only for microphone locations).

2.

Sound power is always output for microphone locations regardless of the specified type (PANEL/NOPANEL).

3.

Sound Power results (via SPOWER) are output to the .h3d file.

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STRAIN I/O Options and Subcase Information Entry STRAIN - Output Request Description The STRAIN command can be used in the I/O Options or Subcase Information sections to request strain output for all subcases or individual subcases respectively. Format STRAIN (sorting,format_list,form,type,location,extras_list,random,peakoutput,modal) = option

Argument

Options

Descriptions

sorting



This argument only applies to the PUNCH format (.pch file) or the OUTPUT2 format (.op2 file) output for normal modes, frequency response, and transient subcases. It will be ignored without warning if used elsewhere.

Default = blank

format



SORT1:

Results for each frequency/timestep are grouped together.

SORT2:

Results for each grid/element are grouped together (See comment 12).

blank:

For frequency response analysis, if no element SET is specified, SORT1 is used, otherwise, SORT2 is used; for transient analysis, SORT2 is used.

HM:

Results are output in HyperMesh results format (.res file). Refer to Strain Results Written in HyperMesh .res Format.

H3D:

Results are output in Hyper3D format (.h3d file). Refer to Strain Results Written in HyperView .h3d Format.

Default = blank

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Argument

Options

Descriptions OPTI:

Results are output in OptiStruct results format (.strn file).

PUNCH:

Results are output in Nastran punch results format (.pch file). Refer to Strain Results Written in Nastran .op2 and .pch Formats.

OP2:

Results are output in Nastran output2 format (.op2 file) (see comment 15, and also refer to Strain Results Written in Nastran .op2 and .pch Formats).

PLOT:

Results are output in Nastran output2 format (.op2 file) when PARAM, POST is defined in the bulk data section. Refer to Strain Results Written in Nastran .op2 and .pch Formats. If PARAM, POST is not defined in the bulk data section, this format allows the form for complex results to be defined for XYPUNCH output without having other output.

blank:

form

Results are output in all active formats for which the result is available.



Provides a combined magnitude/phase form of complex output to the .res file for the HM output format.

Default (HM only) = COMPLEX

Provides rectangular format (real and imaginary) of complex output.

REAL or IMAG:

Default (all other PHASE: formats) = REAL

Provides polar format (phase and magnitude) of complex output.

BOTH (HM only): Provides both rectangular and polar formats of complex output.

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Argument

Options

Descriptions

type



VON:

Only von Mises strain results are output.

PRINC, MAXS, SHEAR:

von Mises and maximum principal strain results are output.

ALL:

All strain results are output.

TENSOR:

All strain results are output. Tensor format is used for H3D output.

DIRECT:

All strain results are output. Direct format is used for H3D output.



Element strains for shell and solid elements are output at the element center only.

Default = ALL

location

Default = CENTER

extras



CUBIC:

Element strains for shell and solid elements are output at the element center and grid points using the strain gage approach with cubic bending correction.

SGAGE:

Element strains for shell and solid elements are output at the element center and grid points using the strain gage approach.

CORNER or BILIN:

Element strains for shell elements are output at the element center and at the grid points using bilinear extrapolation. (see comment 11)

MECH:

Output Mechanical strain (in addition to total strain). This output is only available for H3D format.

No default

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Argument

random

Options

Descriptions



THER:

Output Thermal strain (in addition to total strain). This output is only available for H3D format.

PLASTIC:

Output Plastic strain (in addition to total strain). This output is only available for H3D format.

PSDF:

Requests PSD and RMS results from random response analysis to be output for solid and shell elements only (See comment 13).

No default

Only valid for the H3D format. The "RMS over Frequencies" output is at the end of the Random results in the .h3d file. RMS:

Requests only the “RMS over Frequencies” result from random response analysis to be output for solid and shell elements only (see comment 13). Valid only for the H3D format.

peakoutput

PEAKOUT:

If PEAKOUT is present, only the filtered frequencies from the PEAKOUT card will be considered for this output.

MODAL:

If MODAL is present, strain results of the structural modes and residual vectors are output to the PUNCH, OUTPUT2 and H3D files for modal frequency response and transient analyses.

Default = blank

modal

Default = blank

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Argument

Options

Descriptions

option



YES, ALL, blank:

Results are output for all elements.

NO, NONE:

Results are not output.

SID:

If a set ID is given, results are output only for elements listed in that set.

PSID:

If a property set ID is given, results for the elements referencing properties listed in the property set are output.

Default = ALL

Comments 1.

When the STRAIN command is not present, no strain data is output.

2.

HyperView can internally derive strain results from the strain tensor when the options TENSOR or ALL are used. If the option DIRECT is used, it will display the strain results that were directly computed.

3.

The von Mises and Principal stresses are not available for frequency response analysis.

4.

For elements that reference PCOMP and PCOMPG properties, the STRAIN I/O option controls only strain results for the homogenized composite. The CSTRAIN I/O option must be used to obtain ply strain results.

5.

The form argument is only applicable for frequency response analysis. It is ignored in other instances.

6.

The forms BOTH and COMPLEX do not apply to the .frf output files.

7.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

8.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

9.

For optimization, the frequency of output to a given format is controlled by the I/O option OUTPUT. In previous versions of OptiStruct, a combination of the I/O options FORMAT and RESULTS were used; this method is still supported, but not recommended as it does not allow different frequencies for different formats.

10. The mechanical and thermal contributions to strain may be requested in addition to the total strain. 11. Corner strain of solid element is not available.

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12. In general, HyperView does not recognize the SORT2 format for results from the .op2 file. When results are output only in SORT2 format ( (SORT2, OUTPUT2, … .)), the results are written by OptiStruct into the .op2 file in SORT2 format, but when the .op2 file is imported into HyperView, the results in SORT2 format are not recognized. Therefore, the SORT1 option is recommended for results output in OUTPUT2 format and SORT2 option is recommended for results output in PUNCH format. 13. PSDF and RMS von Mises strain results based on the Segalman Method are also written to the .h3d file for Random Response Analysis (only available in the H3D format). 14. The four-letter abbreviation STRA is interchangeable with STRAIN. 15. format=OUTPUT2 can also be used to request results to be output in the Nastran output2 format (.op2 file).

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STRESS/ELSTRESS I/O Options and Subcase Information Entry STRESS - Output Request Description The STRESS command can be used in the I/O Options or Subcase Information sections to request stress output for all subcases or individual subcases respectively. Format STRESS (sorting,format_list,form,type,location,random,peakoutput,modal) = option

Argument

Options

Description

sorting



This argument only applies to the PUNCH format (.pch file) or the OUTPUT2 format (.op2 file) output for normal modes, frequency response, and transient subcases. It will be ignored without warning if used elsewhere.

Default = blank

format



Results Written in HyperMesh .res Format.

Default = blank H3D:

Results are output in Hyper3D format (.h3d file). Refer to Stress Results Written in HyperView .h3d Format.

OPTI:

Results are output in OptiStruct results format (multiple files).

PUNCH:

Results are output in Nastran punch results format (.pch file). Refer to Stress Results Written in Nastran .op2 and .pch formats.

OP2:

Results are output in Nastran output2 format (.op2 file) (see comment 15, and also refer to Stress Results Written in Nastran .op2 and .pch Formats).

PATRAN:

Results are output in Patran format (multiple files).

APATRAN:

Results are output in Patran format (multiple files).

PLOT:

Results are output in Nastran output2 format (.op2 file) when PARAM, POST is defined in the bulk data section. Refer to Stress Results Written in Nastran .op2 and .pch Formats. If PARAM, POST is not defined in the bulk data section, this format allows

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Argument

Options

Description the form for complex results to be defined for XYPUNCH output, without having other output.

form



blank:

Results are output in all active formats for which the result is available.

COMPLEX (HM only), blank:

Provides a combined magnitude/phase form of complex output to the .res file for the HM output format.

REAL or IMAG:

Provides rectangular format (real and imaginary) of complex output.

PHASE:

Provides polar format (phase and magnitude) of complex output.

BOTH (HM only):

Provides both rectangular and polar formats of complex output.

VON:

Only von Mises stress results are output (HM, OPTI, and H3D only).

PRINC, MAXS, SHEAR:

von Mises and maximum principal stress results are output (HM and H3D only).

ALL:

All stress results are output.

TENSOR:

All stress results are output. Tensor format is used for H3D output.

Default (HM only) = COMPLEX Default (all other formats) = REAL

type

Default = ALL, TENSOR

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Argument

location

Options

Description



DIRECT:

All stress results are output. Direct format is used for H3D output.

CENTER:

Element stresses for shell and solid elements are output at the element center only.

CUBIC:

Element stresses for shell elements are output at the element center and grid points using the strain gage approach with cubic bending correction.

SGAGE:

Element stresses for shell elements are output at the element center and grid points using the strain gage approach.

CORNER or BILIN:

Element stresses for shell and solid elements are output at the element center and grid points using bilinear extrapolation.

PSDF:

Requests PSD and RMS results from random response analysis to be output for solid and shell elements only (See comment 13).

Default = CENTER

random

No default

Only valid for OUTPUT2 and H3D formats. The "RMS over Frequencies" output is at the end of the Random results in the .h3d file and labeled "Simulation 1" in the .op2 file.

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Argument

Options

Description Requests only the “RMS over Frequencies” result from random response analysis to be output for solid and shell elements only (See comment 13).

RMS:

Valid only for OUTPUT2 and H3D formats. It is labeled “Simulation 1” in the .op2 file.

peakoutput

PEAKOUT:

If PEAKOUT is present, only the filtered frequencies from the PEAKOUT card will be considered for this output.

MODAL:

If MODAL is present, stresses of the structural modes and residual vectors are output to the PUNCH and OUTPUT2 files for modal frequency response and transient analysis.

Default = blank

modal

Default = blank

option



YES, ALL, blank: Stress results are output for all elements.

Default = ALL

NO, NONE:

Stress results are not output.

SID:

If a set ID is given, stress results are output only for elements listed in that set.

PSID:

If a property set ID is given, stress results for the elements referencing properties listed in the

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Argument

Options

Description property set are output.

Comments 1.

When a STRESS command is not present, stress results are output for all elements for all linear static analysis, nonlinear quasi-static gap analysis, and inertia relief analysis subcases.

2.

HyperView can internally derive STRESS results from the stress tensor when the options TENSOR or ALL are used. If the option DIRECT is used, it will display the stress result that were directly computed.

3.

For elements that reference PCOMP or PCOMPG properties, the STRESS I/O option controls only stress results for the homogenized composite. The CSTRESS I/O option must be used to obtain ply stress and failure index results.

4.

The Von Mises and Principal stresses are not available for frequency response analyses.

5.

The form argument is only applicable for frequency response analysis. It is ignored in other instances.

6.

The forms BOTH and COMPLEX do not apply to the .frf output files.

7.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

8.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

9.

For optimization, the frequency of output to a given format is controlled by the I/O option OUTPUT. In previous versions of OptiStruct, a combination of the I/O options FORMAT and RESULTS were used; this method is still supported, but not recommended as it does not allow different frequencies for different formats.

10. For normal modes analysis output, if there is USET U6 data, the stresses for each residual displacement vector associated with the USET U6 DOF are also output to the H3D, PUNCH, and OUTPUT2 files. 11. For modal frequency response and transient analysis, the stress vectors associated with the residual vectors are written to the .op2 and .pch files after the modal stress vectors if the keyword MODAL is used. 12. In general, HyperView does not recognize the SORT2 format for results from the .op2 file. When results are output only in SORT2 format ( (SORT2, OUTPUT2, … .)), the results are written by OptiStruct into the .op2 file in SORT2 format, but when the .op2 file is imported into HyperView, the results in SORT2 format are not recognized. Therefore, the SORT1 option is recommended for results output in OUTPUT2 format and SORT2 option is recommended for results output in PUNCH format.

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13. PSDF and RMS von Mises stress results based on the Segalman Method are also written to the .h3d file for Random Response Analysis (only available in the H3D format). 14. The four-letter abbreviation STRE is interchangeable with STRESS. 15. format=OUTPUT2 can also be used to request results to be output in the Nastran output2 format (.op2 file).

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SUBTITLE I/O Options Entry SUBTITLE - File Header Description The SUBTITLE command can be used in the I/O Options or Subcase Information sections to define the subtitle for all subcases or for individual subcases respectively. Format SUBTITLE = name

Argument

Description

name

The subtitle for the subcase. No default

Comments 1.

198

The subtitle is written to the output files.

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SVELOCITY I/O Options and Subcase Information Entry SVELOCITY - Output Request Description The SVELOCITY command can be used in the I/O Options or Subcase Information sections to request the form and type of modal participation velocities output for all subcases or individual subcases respectively. Format SVELOCITY (sorting,format_list,form,peakoutput) = option

Argument

Options

Description

sorting



This argument only applies to the PUNCH format (.pch file) or the OUTPUT2 format (.op2 file) output for normal modes, frequency response, and transient subcases. It will be ignored without warning if used elsewhere.

Default = blank

format

SORT1:

Results for each frequency/ timestep are grouped together.

SORT2:

Results for each grid/element are grouped together (see comment 7).

blank:

SORT1 is used for all results except for transient analysis, where SORT2 is used.



H3D:

Results are output in Hyper3D format (.h3d file).

Default = blank

PUNCH:

Results are output in Nastran punch results format (.pch file).

OP2:

Results are output in Nastran output2 format (.op2 file) (see comment 9).

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Argument

form

Options

Description PLOT:

Results are output in Nastran output2 format (.op2 file) when PARAM, POST is defined in the bulk data section.

blank:

Results are output in all active formats for which the result is available.

REAL, IMAG:

Provides rectangular format (real and imaginary) of complex output.

PHASE:

Provides polar format (magnitude and phase) of complex output. Phase output is in degrees.

PEAKOUT:

If PEAKOUT is present, only the filtered frequencies from the PEAKOUT card will be considered for this output.



YES, ALL, blank:

Results are output.

Default = YES

NO, NONE:

Results are not output.

Default = REAL

peakoutput

Default = blank

option

Comments 1.

When the SVELOCITY command is not present, modal participation velocities are not output.

2.

The SVELOCITY command is only valid for modal frequency response and modal transient solution sequences.

3.

The OFREQUENCY and OTIME I/O Options may be used to control the amount of output.

4.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

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5.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

6.

For optimization, the frequency of output to a given format is controlled by the I/O option OUTPUT. In previous versions of OptiStruct, a combination of the I/O options FORMAT and RESULTS were used; this method is still supported, but not recommended as it does not allow different frequencies for different formats.

7.

In general, HyperView does not recognize the SORT2 format for results from the .op2 file. When results are output only in SORT2 format ( (SORT2, OUTPUT2, … .)), the results are written by OptiStruct into the .op2 file in SORT2 format, but when the .op2 file is imported into HyperView, the results in SORT2 format are not recognized. Therefore, the SORT1 option is recommended for results output in OUTPUT2 format and SORT2 option is recommended for results output in PUNCH format.

8.

The abbreviation SVELO is interchangeable with SVELOCITY.

9.

format=OUTPUT2 can also be used to request results to be output in the Nastran output2 format (.op2 file).

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SYSSETTING I/O Options Entry SYSSETTING – Run Control Description The SYSSETTING command can be used in the I/O Options section to alter system settings. Any setting defined here may be over-ridden by command line arguments (see Run Options for OptiStruct). Most of these options can also be specified in one of the config files (see OptiStruct Configuration File). Format SYSSETTING(setting=option_list,setting=option_list,…) Examples SYSSETTING(RAMDISK=100) SYSSETTING(SCRFMODE=buffered,stripe) SYSSETTING(SPSYNTAX=mixed,RAMDISK=100,SCRFMODE=buffered,stripe,OS_RAM=1234)

Setting

Options

Description

BARPROP



STRICT: The CBAR and CBEAM beam element connections cannot reference the PBEAM beam property entries, respectively.

Default = STRICT

MIXED: The CBAR and CBEAM beam element connections can reference the PBEAM and PBAR beam property entries, respectively. BUFFSIZE

BUFFSIZE = 16832

The maximum size in 8 byte words of the records of data written to the .op2 file. Use -1 to turn off buffering.

CARDLENGTH



Defines the number of characters read on a single line in the I/O Options and Subcase Information sections. This can vary between 80 and 132 characters.

Default = 80

In the Bulk Data section, CARDLENGTH applies to free and long free format lines only (fixed and long format lines are always limited to 72 characters).

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Setting

Options

Description

DUPTOL

Integer

Controls accuracy used during elimination of potential duplicate cards. Two cards with identical ID's are replaced by the first one, if all integer values on both cards match exactly, and all float values match with accuracy controlled by this setting, otherwise identical IDs are flagged as ERROR. Currently only GRID, CORDxx, and base MAT/PROP entry duplicates are allowed (MATX, MATT, and PROPX entries do not allow duplicates).

Default = 0

0: no tolerance, the values defined must be an exact match. 1: for standard fixed 8-character without exponent, the value must match up to 6 decimal places. 2: for standard fixed 8-character without exponent, the value must match up to 5 decimal places. 3: for standard fixed 8-character without exponent, the value must match up to 4 decimal places. 4: for standard fixed 8-character without exponent, the value must match up to 3 decimal places. 5: for standard fixed 8-character without exponent, the value must match up to just 2 decimal places. If values are too large or too small to represent without exponent, then both values must match exactly when converted to 8-character form. Also, for negative values, the accuracy is one digit lower. H3DVTAG

Default = NO

Appends the version of the H3D format used, onto the .h3d file output by OptiStruct. So the results file would then be {filename}.h3d11 or {filename}.h3d12. Note: It is not possible to select the H3D format used for output; this is built into the executable.

MAXLEN



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Setting

Options

Description memory to be used in MB. There is no default. MAXLEN is not supported when the MUMPS solver is used (including –ddm parallel runs).

MINLEN



NPROC (legacy command: CPU) Default = 1 OS_RAM

Default = 1Gbyte

PLOTELID

Used to define the initial memory allocation in MB. The default is 10% of OS_RAM. This is the same as the legacy command, OS_RAM_INIT. Same as –nproc and -cpu options (see Run Options for OptiStruct). Sets number of processors in a multiprocessor (SMP) run. Memory limit in Mb. The solver will attempt to run at least the minimum core solution regardless of the memory limit. See Memory Limititations in the User’s Guide for details.



Controls the numbering scheme of the PLOTEL ID.

Default = UNIQUE

UNIQUE requires all PLOTEL elements have unique element IDs. ALLOWFIX allows OptiStruct to automatically fix ID collisions for PLOTEL. If PLOTEL elements have the same IDs as some other elements, OptiStruct renumbers the IDs of all PLOTEL by adding a large offset value.

RAM_SAFETY

Same as -rsf option. (see Run Options for OptiStruct).

Default = 1.0

Specifies an area in RAM allocated to store information which otherwise would be stored in Default = See comment scratch files on the hard drive. 5 See comment 5 below for more details.

RAMDISK



SAVEFILE

SAVEFILE = OUT

SAVEFILE controls the behavior of the solver when an output file with the same name already exists when the program starts. SAVEFILE = ALL will prevent overwriting output

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Setting

Options

Description files by renaming an existing file by adding numeric suffix, for example, jobname.h3d will be renamed to jobname_nnn.h3d where nnn represents the smallest number for file which does not exists yet. This option tries to preserve files with all known extensions, and it may use a large amount of disk space if the same run is repeated multiple times. SAVEFILE = OUT (default) will preserve only .out and .stat files. SAVEFILE = NONE will allow the solver to overwrite any existing file. SAVEFILE = ext, where ext is arbitrary file extension (case insensitive, up to 9 characters). See comments 8 and 9.

SCRFMODE

Allows for the selection of different modes of storing scratch files for a linear solver process (especially for out-of-core and minimum-core Primary options: BASIC, modes). BUFFERED, UNBUFFER, BASIC: FORTRAN mode, direct access file. STRIPE

Secondary option: MIXFCIO

BUFFERED: FORTRAN buffered. UNBUFFER: C i/o mode (default).

Default = 1. For Linux: UNBUFFER 2. For Windows (without AMSES): BUFFERED, MIXFCIO 3. For Windows (using AMSES): BASIC SKIP10FIELD

Default = CHECK

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STRIPE: Stripe main solver files on multiple disks (except ones marked as slow). MIXFCIO (only valid when combined with BUFFERED): Use C (native) I/O routines instead of FORTRAN read/write for main solver files. See comment 7 below for more details. To detect disallowed use of potential expansion of free format, error will be generated when 10 or more data fields is found on a bulk data card in free format. Use SKIP10FIELD=WARN to allow reading such card (extra fields will be disregarded instead of causing error).

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Setting

Options

Description

SPSYNTAX



Controls how strict the checks are in the reader for mixing GRIDs and SPOINTs.

Default = CHECK

STRICT: When both grid/component pairs (G#/C#) and grid lists for a given component (as on the alternate formats ASET1 and USET1 bulk data entries) are defined, this option will require that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). CHECK: When grid/component pairs (G#/C#) are defined, this option will require that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). But when grid lists for a given component (as on alternate formats ASET1 and USET1 bulk data entries) are defined, this option will allow the grid reference to be scalar points (SPOINT) or structural grid points (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. MIXED: When grid/component pairs (G#/C#) and grid lists for a given component (as on alternate formats ASET1 and USET1 bulk data entries) are defined, this option will allow the grid reference to be scalar points (SPOINT) or structural grid points (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. See comment 6 below for more details.

SYNTAX



Controls how strict the syntax checker in the reader is.

Default = ALLOWINT ALLOWINT is the default setting for OptiStruct, and converts integer values to real values whenever real values are expected. In those instances, where the form of the input (Integer or Real) indicates the nature of the input (for example, when reading vector entries (X,Y,Z) with alternate form (GID, , )), a negative integer value in the first field, or a non-blank value in the second or third field indicates the (X,Y,Z) format and all fields are

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Setting

Options

Description read as real values. STRICT follows more closely with other Nastran codes, where integer values may only be entered in integer value fields and real values must be entered in real value fields. An error termination will occur if an integer value is placed in a real value field when this setting is chosen. Note: This setting never changes results – it can only cause the rejection of files that do not follow the restrictions.

TABSTOPS

UNDEFTEMP

TABSTOPS = 8



TABSTOPS allows you to change interpretation of TAB character in the input. By default TAB stops are spaced by 8 columns, which is standard on all Unix/Linux terminals. Possible values are 4 (used often on Windows) and 1 (replace each TAB with exactly one space). STRICT

OptiStruct will error out if there are some grid points without a specified temperature (that is, a minimum of one, but not all, grid points in the model has a specified temperature). The error message includes information about GRID ID, Element ID, and Load Set number.

ZERO

OptiStruct will use a value of zero for grids without a specified temperature (that is, a minimum of one, but not all, grid points in the model has a specified temperature). This allows users to revert to the behavior of versions prior to OptiStruct 13.0.

Default = STRICT

UPDATE

UPDATE option (quiet, verbose, strict, off, unique, permissive)

Controls the behavior of ASSIGN,UPDATE,. quiet

Less output (default).

Defaults = quiet and strict

verbose

More output including old and new values.

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Setting

Options

Description strict

Do not allow non-supported cards in update deck (default).

off

Disable update.

unique

Each ID only once.

permissive

Allow all cards and repeat IDs.

Choose only one option from: quiet, verbose. Choose only one option from: strict, off, unique, permissive. USERAM



Memory limit in Mb. The solver will use more than the minimum memory required up to this limit, but only if it improves the speed of the solution. See Memory Limitations in the User’s Guide for details.

Comments 1.

The number of fields in this card is not limited to 10, but it is limited by the current line length (default 80).

2.

Continuation lines are not allowed, multiple SYSSETTING cards are allowed.

3.

The settings CPU and NPROC are interchangeable, and can also be specified on the command line.

4.

Each option except SCRFMODE must have exactly one argument. SCRFMODE arguments should be comma separated.

5.

For RAMDISK setting: a) Use of a virtual disk instead of physical files may speed up solutions by reducing wait time to access physical disk drives. Note that the use of RAMDISK will reduce the amount of memory available for the solver and for file buffering performed by the operating system (by Linux or Windows), and because of that it may not always reduce the wall clock time for the solution. The most impact can be observed on machines with very large physical memory (20GB or more) or when used to speed-up main solver scratch file access using the SCRFMODE setting. b) RAMDISK is automatically protected for overflow, so it is fine to specify 200MB for RAMDISK when the total amount of scratch files will be larger than that. c) RAMDISK is automatically specified for very small jobs, (less than 10,000 GRIDS). This can be disabled by specifying RAMDISK=0. Automatic RAMDISK is not allocated for fixed RAM jobs (the -fixlen command line option is used, see Run Options for OptiStruct).

6.

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a) When the component from a grid/component pair or for a list of grids (as on alternate formats ASET1 and USET1 bulk data entries) is greater than 1, the grid reference must always be a structural grid (GRID). b) This control may also be set in the OptiStruct Configuration File. 7.

For SCRFMODE setting: a) This command controls the way scratch files from the linear equation solver are written to the disk. These files are usually written and read several times, often in random pattern, and this can have a significant impact on the total (wall clock) time for the solution of large jobs. The default mode is optimal in most configurations, but choosing between BASIC, BUFFERED or UNBUFFER may improve speed for some hardware and/or some types of solution sequences, especially jobs including Lanczos eigenvalue solver. b) In out-of-core and minimum-core solver modes, the solver creates one large scratch file for each subcase and this file may be optionally located across multiple TMPDIRs. In order to use this capability, SCRFMODE=STRIPE must be defined, otherwise the same method as for other files (BASIC, BUFFERED or UNBUFFER) is used, and this large file must therefore fit on a single TMPDIR. c) STRIPE mode can be used when all TMPDIRs (not marked as SLOW) are fully independent (that is, they should not be partitions on the same physical drive). This mode results in the access to all disks similar to RAID0 - consecutive blocks of data are split between separate TMPDIRs, and accessed in parallel, which can speed up disk access considerably. Warning: Using STRIPE with TMPDIRs allocated on the same physical drive (even on different partitions) will usually slow down the solution by increasing wait times. Check with your system administrator for information on the actual hardware structure of your computer. d) STRIPE requires multiple TMPDIR cards and has effect only for out-of-core or minimumcore solutions. e) Most modern operating systems (Linux in particular) use excess available RAM for the buffering of disk i/o. The SCRFMODE command will have effect only for jobs which exceed the capabilities of this buffer. f) When AMSES is used on Windows, BASIC mode is enforced during AMSES calculations. g) The –scrfmode option can be specified on the command line (see Run Options for OptiStruct) – this overrides any information specified in the input file.

8.

The SAVEFILE option tries to preserve only files in the start directory, that is, this option has no effect when the input file is specified with a path, or the OUTFILE option defines a different location for all output files. Unless SAVEFILE,NONE is specified, standard .out and .stat files are always renumbered, even if they are created in different folder. All files are renumbered at program start – .out file is preserved first, and then the same NNN is used for all files found in the current folder. Only files with default names are preserved (that is those starting with the same root as outfile). Note that this option may sometimes cause the solver to fail if it renames the file which is intended for the input.

9.

Multiple SAVEFILE cards overwrite each other (the last one is in effect). Multiple SAVEFILE,ext cards can be used (up to 5 extensions can be defined), but using of any of the standard options (NONE/ALL/OUT) empties the list of previously defined extensions.

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TCURVE I/O Options Entry TCURVE – Output Request Description The TCURVE command can be used in the I/O Options section to define the plot title for XYPLOT output from a random response analysis. Format TCURVE = title

Argument

Description

title

Character string. Default = A default title is provided.

Comments 1.

TCURVE may not be continued onto the next line.

2.

A TCURVE definition applies to all plots defined after TCURVE until another definition of TCURVE occurs. Example: XTITLE = X-A YTITLE = Y-A XYPLOT (first plot definition) YTITLE = Y-B TCURVE = C-A XYPLOT (second plot definition) would assign X-A, Y-A and the default plot title to the first plot, then X-A, Y-B and C-A to the second plot.

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THERMAL I/O Options and Subcase Information Entry THERMAL – Output Request Description The THERMAL command can be used in the I/O Options or Subcase Information sections to request temperature output for all heat transfer analysis subcases or individual heat transfer analysis subcases respectively. Format THERMAL (format_list) = option

Argument

Options

Description

format



PUNCH:

Results are output in Nastran punch results format (.pch file).

Default = blank

OP2:

Results are output in Nastran output2 format (.op2 file) (see comment 7).

PLOT:

Results are output in Nastran output2 format (.op2 file) when PARAM, POST is defined in the bulk data section.

H3D:

Results are output in Hyper3D format (.h3d file).

blank:

Results are output in all active formats for which the result is available.



YES, ALL, blank:

Thermal results are output at all grid points for which temperature results are available.

Default = ALL

NO, NONE:

Thermal results are not output

SID:

If a set ID is specified, Thermal results are output only for grid points referenced by that set.

option

Comments 1.

When the THERMAL command is not present, thermal results are not output.

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2.

Thermal output is only available for the heat transfer analysis solution sequence.

3.

The PUNCH output produces TEMP bulk data entries, and the SID on the entries will be the subcase number (=1 if no SUBCASES are specified).

4.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on the results available and their respective formats.

5.

Temperature output via the THERMAL output request is available for both linear steady state heat transfer and linear transient heat transfer analyses.

6.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

7.

format=OUTPUT2 can also be used to request results to be output in the Nastran output2 format (.op2 file).

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THICKNESS I/O Options and Subcase Information Entry THICKNESS - Output Request Description The THICKNESS command can be used in the I/O Options section to request thickness output for elements referencing a PSHELL or PCOMP property in: Size/Free-size optimization Analysis runs Topology optimization Format THICKNESS (format_list, comp) = option

Argument

Options

Description

format



HM:

Results are output in HyperMesh results format (.res file).

H3D:

Results are output in Hyper3D format (.h3d file).

blank:

Results are output in all active formats for which the result is available. (See comments 1 and 2)



ALL:

Thickness results are output for all plies.

Default = DESIGN

DESIGN, blank:

Thickness results are output for designable plies only.

NOPLY:

No ply thickness results are output.

Default = blank

comp

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Argument

Options

Description

option



YES, ALL, blank:

Thickness results are output

NO, NONE:

Thickness results are not output.

Default = YES

Comments 1.

When the THICKNESS command is not present, thickness results are output. THICKNESS results for analysis runs, however, are not output by default and will be output only if the THICKNESS data entry is present in the solver deck.

2.

Thickness results are available for analysis runs, size/free-size optimization, and topology optimization only.

3.

When thickness results are output to the .h3d file, percentage thickness change is also output.

4.

Outputting the density results in all simulations allows analysis results to be plotted on the density iso-surface in HyperView.

5.

The frequency of this output is controlled by the DESIGN keyword on an OUTPUT definition or, if no OUTPUT definition exists with the DESIGN keyword, by the DENSRES I/O option.

6.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

7.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

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THIN I/O Options and Subcase Information Entry THIN - Output Request for Geometric Nonlinear Analysis Subcase Description The THIN command can be used in the I/O Options or Subcase Information sections to request thinning and thickness output for all geometric nonlinear analysis subcases or individual geometric nonlinear analysis subcases respectively. Format THIN (format, type) = option

Argument Options

Description

format

H3D:

Results are output in Hyper3D format (.h3d file).

blank:

Results are output in all active formats for which the result is available.

ALL:

Thinning and thickness results are output.

THIN:

Percentage element thinning only is output.

THICK:

Element thickness only is output.



YES, ALL, blank:

Thinning/thickness are output for all elements.

Default = ALL

NO, NONE:

Thinning/thickness are not output.

SID:

If a set ID is given, thinning/ thickness are output only for elements listed in that set.

Default = blank

type

Default = ALL

option

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Argument Options

Description PSID:

If a property set ID is given, thinning/thickness results for the elements referencing properties listed in the property set are output.

Comments 1.

THIN is only applicable for geometric nonlinear analysis subcases which are defined by an ANALYSIS = NLGEOM subcase entry.

2.

Only formats that have been activated by an OUTPUT or FORMAT statement are valid for use on this card.

3.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

4.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

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TITLE I/O Options Entry TITLE - File Header Description The TITLE command can be used in the I/O Options section to define the title for the OptiStruct job. Format TITLE = name

Argument

Description

name

The title for the job. No default

Comments 1.

The title is printed into the output and results files.

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TMPDIR I/O Options Entry TMPDIR - Directory Selection Description The TMPDIR command is used in the I/O Options section to choose the directory in which the scratch files are to be written. Format TMPDIR = path

Argument

Options

Description

options

-FILESIZE=n

Maximum allowable file size in GB.

SLOW=1

Non-zero value denotes a network drive.

path

The path to the directory where scratch files are to be written. Default = ./

Examples Windows Operating System Local Drive TMPDIR = -FILESIZE=13 D:\Dir1\Dir2\...\DirN\Scratch TMPDIR = -FILESIZE=13 D:\Dir1\Dir2\...\DirN\Scratch Files Network Drive 1.

Map the network drive (drive on a remote machine) to a drive (Y:\) on your computer.

2.

Use the path to your preferred scratch directory on the mapped network drive as the “path” argument for TMPDIR. TMPDIR = -FILESIZE=13 SLOW=1 Y:\Scratch TMPDIR = -FILESIZE=13 SLOW=1 Y:\Scratch Files

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Linux Operating System Local Drive TMPDIR = -FILESIZE=13 /Dir1/Dir2/.../DirN/Scratch TMPDIR = -FILESIZE=13 D:/Dir1/Dir2/.../DirN/Scratch Files Comments 1.

The total length of information on this card is limited to 200 characters (including the card name and spaces between arguments). This data can be on a single line or span multiple continuation lines. See Guidelines for I/O Options and Subcase Information Entries for an example showing how to enter long file names on multiple lines.

2.

Multiple TMPDIR cards are allowed (up to five entries). Scratch files will be allocated in all directories depending on the options defined (see comments 3 through 8).

3.

Before opening any scratch file during the solution process, the solver checks the available free space on all TMPDIRs and allocates that file on the directory which has most free space. This algorithm tends to spread disk usage between different directories, but does not guarantee full usage of each TMPDIR area.

4.

The main scratch file used during a linear solver process (that is solution of linear system or eigen problem) can be split between multiple TMPDIRs (see SCRFMODE).

5.

When TMPDIR is marked as SLOW, it is used only after other TMPDIRs are filled up. Selecting directories for TMPDIR on disk drives shared across the network (that is on different computers or on centralized file servers) is not recommended, and should be avoided if possible. Some scratch files (especially for out-of-core and minimum-core mode) are heavily used, and accessing them across the network will dramatically increase wall clock time for the solution. The main purpose of the TMPDIR command is to avoid this delay when work areas (home directories) are allocated on a central server, as is customary at many large organizations. All scratch files are stored in the specified directories. The scratch files are automatically removed at the end of the analysis unless there is a system error or core dump (in which case, the scratch file may need to be cleaned up manually).

6.

See the SCRFMODE setting on the SYSSETTING I/O option for an additional way to use multiple TMPDIR cards for large jobs.

7.

The –tmpdir option can be specified on the command line (see Run Options for OptiStruct); this overrides any information specified in the input file.

8.

The filesize option is needed in rare cases when there is a file size limit imposed by operating system. This limit is large enough for all practical problems in most cases. The following cases are known to have a file size limit of 2GB: FAT32 file system (Windows, sometimes Linux) ext2 file system (older Linux distributions) NFS version 2 It is recommended to upgrade hardware and/or operating system in these cases.

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TTERM I/O Options and Subcase Information Entry TTERM - Termination Time for Geometric Nonlinear Analysis Subcase Description The TTERM command can be used in a geometric nonlinear subcase to define the termination time. Format TTERM = value

Argument

Description

value

Termination time for a geometric nonlinear subcase. Default = 1.0 (Real)

Comments 1.

TTERM is only allowed in geometric nonlinear subcases which are defined by an ANALYSIS = NLGEOM, IMPDYN, or EXPDYN subcase entry.

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UNITS I/O Options Entry UNITS - Unit System for the Model Description The UNITS command can be used in the I/O Options section to define a system of units for the model. Format UNITS = system

Argument

Options

Description

system



SI:

International system of units. Length: meter = m Mass: kilogram = kg

No default

Time: second = s Temperature: Kelvin = K Pressure - Pa CGS:

Centimeter-gram-second system of units. Length: centimeter = cm Mass: gram = g Time: second = s Temperature: Kelvin = K Pressure = barye = 0.1 Pa

MPA:

Mega Length: millimeter = mm Mass: tonne = tonne Time: second = s Temperature: Kelvin = K Pressure - MPa

BG:

British Gravitational system of units. Length: feet = ft Mass: slug = slug Time: second = s Temperature: Rankine = R

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Argument

Options

Description Pressure = Ibf/ft 2

Comments 1.

Only one instance of this card is supported. If multiple instances are defined, the last occurrence will be used.

2.

This UNITS data entry is the same as the DTI,UNITS entry.

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VELOCITY I/O Options and Subcase Information Entry VELOCITY - Output Request Description The VELOCITY command can be used in the I/O Options or Subcase Information sections to request velocity vector output for all subcases or individual subcases respectively. Format VELOCITY(sorting,format,form,rotations,random,peakoutput) = option

Argument

Options

Description

sorting



This argument only applies to the PUNCH format (.pch file) or the OUTPUT2 format (.op2 file) output for normal modes, frequency response, and transient subcases. It will be ignored without warning if used elsewhere.

Default = blank

format



SORT1:

Results for each frequency/ timestep are grouped together.

SORT2:

Results for each grid/element are grouped together (See comment 8).

blank:

For frequency response analysis, if no grid SET is specified, SORT1 is used, otherwise, SORT2 is used; for transient analysis, SORT2 is used.

HM:

Results are output in HyperMesh results format (.res file).

H3D:

Results are output in Hyper3D format (.h3d file).

OPTI:

Results are output in OptiStruct results format (.disp file).

Default = blank

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Argument

Options

Description PUNCH:

Results are output in Nastran punch results format (.pch file).

OP2:

Results are output in Nastran output2 format (.op2 file) (see comment 11).

HG:

Results are output in HyperGraph presentation format (_freq.mvw file and _tran.mvw file) – see OUTPUT keywords HGFREQ and HGTRANS.

PLOT:

Results are output in Nastran output2 format (.op2 file) when PARAM, POST is defined in the bulk data section. If PARAM, POST is not defined in the bulk data section, this format allows the form for complex results to be defined for XYPUNCH output without having other output.

form

Default (HM only) = COMPLEX

blank:

Results are output in all active formats for which the result is available.

COMPLEX (HM only), blank:

Provides a combined magnitude/ phase form of complex output to the .res file for the HM output format.

REAL or IMAG:

Provides rectangular format (real and imaginary) of complex output (See comment 9).

PHASE:

Provides polar format (magnitude and phase) of complex output. Phase output is in degrees (See comment 9).

Default (all other formats) = REAL

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Argument

rotations

Options

Description



BOTH (HM only):

Provides both polar and rectangular formats of complex output.

ROTA:

Requests output of rotational velocity results (in addition to rotational velocity results).

NOROTA:

Rotational velocity results are not output.

PSDF:

Requests PSD and RMS results from random response analysis to be output.

Default = NOROTA

random

No default

Only valid for the H3D format. The "RMS over Frequencies" output is at the end of the Random results. RMS:

Requests only the “RMS over Frequencies” result from random response analysis to be output. Valid only for the H3D format.

peakoutput

PEAKOUT:

If PEAKOUT is present, only the filtered frequencies from the PEAKOUT card will be considered for this output.



YES, ALL, blank:

Velocity is output for all nodes.

Default = YES

NO, NONE:

Velocity is not output.

Default = blank

option

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Argument

Options

Description SID:

If a set ID is given, velocity is output only for nodes listed in that set.

Comments 1.

When the VELOCITY command is not present, velocity vector is not output.

2.

Velocity output is available for frequency response and transient analysis solution sequences.

3.

The form argument is only applicable for frequency response analysis. It is ignored for other analysis types.

4.

The forms BOTH and COMPLEX do not apply to the .frf output files.

5.

Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

6.

Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates.

7.

For optimization, the frequency of output to a given format is controlled by the I/O option OUTPUT. In previous versions of OptiStruct, a combination of the I/O options FORMAT and RESULTS were used; this method is still supported, but not recommended as it does not allow different frequencies for different formats.

8.

In general, HyperView does not recognize the SORT2 format for results from the .op2 file. When results are output only in SORT2 format ( (SORT2, OUTPUT2, … .)), the results are written by OptiStruct into the .op2 file in SORT2 format, but when the .op2 file is imported into HyperView, the results in SORT2 format are not recognized. Therefore, the SORT1 option is recommended for results output in OUTPUT2 format and SORT2 option is recommended for results output in PUNCH format.

9.

Results in binary format (.h3d or .op2) are always output in PHASE/MAG form, regardless of the options specified in the FORM field. The corresponding post-processors (HyperView/HyperGraph) can easily convert the PHASE/MAG format to the required formats. Results in ASCII formats are output in the specified/requested FORM.

10. The four-letter abbreviation VELO is interchangeable with VELOCITY. 11. format=OUTPUT2 can also be used to request results to be output in the Nastran output2 format (.op2 file).

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XTITLE I/O Options Entry XTITLE – Output Request Description The XTITLE command can be used in the I/O Options section to define the x-axis label for XYPUNCH or XYPLOT output from a random response analysis. Format XTITLE = title

Argument

Description

title

Character string. Default = blank

Comments 1.

XTITLE may not be continued onto the next line.

2.

An XTITLE definition applies to all plots defined after XTITLE until another definition of XTITLE occurs. Example: XTITLE = X-A YTITLE = Y-A XYPLOT (first plot definition) YTITLE = Y-B TCURVE = C-A XYPLOT (second plot definition) would assign X-A, Y-A and the default plot title to the first plot, then X-A, Y-B, and C-A to the second plot.

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XYPEAK / XYPLOT / XYPUNCH I/O Options Entry XYPEAK - Output Request XYPLOT - Output Request XYPUNCH - Output Request Description The XYPEAK, XYPLOT, and XYPUNCH commands can be used in the I/O Options section to request output from a random response analysis. The XYPUNCH command can also be used with the RESPONSE plot-type to request .pch file output from a frequency response analysis. Format operation, curve-type, plot-type / entity ID(item code) list

Argument

Options

Description

operation



XYPEAK:

Generates a .peak file containing a summary of the requested output for random response analysis.

XYPLOT:

Generates a HyperGraph session file and related data files for the requested output for random response analysis.

No default

XYPUNCH: Generates a .pch file for the requested output for random response analysis. With the plot-type RESPONSE, this command can also be used to generate .pch file output for frequency response analysis.

curve-type

ACCE: No default

Requests output for velocity.

FORCE:

Requests output for acceleration. Requests output for force. For plot-type RESPONSE: CBUSH and CELAS elements only.

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Argument

Options

Description For plot-type PSDF: CBUSH, CVISC, CDAMP, and CELAS elements only. STRESS:

Requests output for element stress. For plot-types PSDF and AUTO.

STRAIN:

Requests output for element strain. For plot-types PSDF and AUTO.

plot-type

No default AUTO:

Requests power spectral density function for random response analysis. (see comment 5)

Requests autocorrelation for random response analysis.

RESPONSE: Requests time or frequency in SORT2 format or grid identification numbers in SORT1 format. RESPONSE is only supported for the XYPUNCH operation for frequency response analysis.

entity ID (item List of grid or GRID: code) list element, component pairs. The list must come after a slash "/". Each entry in the list is comma separated. No default

Each entry consists of a GRID or SPOINT ID followed by a component of motion (T1, T2, T3, R1, R2, or R3) in parentheses. In the components of motion, T signifies translation and R signifies rotation while the numbers indicate the translational direction or rotational axis. For frequency response analyses, the components of motion are T1RM, T2RM, T3RM, T1IP, T2IP, T3IP, R1RM, R2RM, R3RM, R1IP, R2IP, and R3IP, where RM signifies Real or Magnitude and IP signifies Imaginary or Phase. The type of the response depends on a preceding output request. For SPOINTs, the component must be T1, T1RM, or T1IP.

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Argument

Options

Description ELEMENT:

For elements, the item code (number code only) represents a component of the element stress/ strain, which is described in DRESP1 – Frequency Response Stress/Strain Item Codes and DRESP1 – _Frequency Response Force Item Codes

Examples XYPLOT, XYPEAK, VELO, PSDF / 3(T2), 6(T2) XYPEAK, DISP, AUTO / 223(T3) XYPEAK, XYPLOT, XYPUNCH, ACCE, PSDF / 8(T1), 9(T1), 8(T2), 9(T2) Comments 1.

Unlike other output requests, XYPEAK, XYPLOT, and XYPUNCH may be combined on a single line (as shown in the example above).

2.

If the XYPEAK, XYPLOT, or XYPUNCH commands are not supplied, then no random response results will be output.

3.

If the XYPEAK, XYPLOT, or XYPUNCH commands are supplied, but with an incomplete definition, an error termination will occur.

4.

For complex results, the format of XYPUNCH output (Real/Imaginary or Phase/Magnitude) is determined by the relevant result output request (ACCELERATION, DISPLACEMENT, STRESS, STRAIN, FORCE or VELOCITY). Real/Imaginary is the default if not otherwise indicated.

5.

Multiple RANDOM subcase information entries with non-unique ID’s are allowed in a single model. Therefore, if the plot-type field is set to PSDF, then the RANDOM ID will be added to the XYPUNCH headers in the corresponding result sections of the .pch file when multiple RANDOM entries are present in the same deck. If only one RANDOM entry is present, the RANDOM ID is not printed.

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YTITLE I/O Options Entry YTITLE – Output Request Description The YTITLE command can be used in the I/O Options section to define the y-axis label for XYPUNCH or XYPLOT output from a random response analysis. Format YTITLE = title

Argument

Description

title

Character string. Default = blank

Comments 1.

YTITLE may not be continued onto the next line.

2.

A YTITLE definition applies to all plots defined after YTITLE until another definition of YTITLE occurs. Example: XTITLE YTITLE XYPLOT YTITLE TCURVE XYPLOT

= X-A = Y-A (first plot definition) = Y-B = C-A (second plot definition)

would assign X-A, Y-A and the default plot title to the first plot, then X-A, Y-B, and C-A to the second plot.

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Subcase Information Section

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A2GG Subcase Information Entry A2GG - Direct Input Fluid-Structure Coupling Matrix Selection Description The A2GG command can be used in the Subcase Information section to select a direct input fluid-structure coupling matrix. Format A2GG = name

Argument

Description

name

Name of a fluid-structure coupling matrix that is input in the bulk data section using the DMIG card.

Comments 1.

DMIG matrices will not be used unless selected in the Subcase Information section.

2.

The matrix selected applies to all subcases.

3.

The selected fluid-structure coupling matrix is always added to the computed coupling matrix.

4.

The referenced DMIG entry must be a square matrix (field 4 must be 1), where GJ corresponds to fluid points, CJ = 0, Gi corresponds to structural points, Ci corresponds to DOF, and Ai corresponds to the area values.

5.

Multiple instances of A2GG are not allowed, and will result in an error termination.

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ANALYSIS Subcase Information Entry ANALYSIS - Run Control and Solution Sequence Identifier Description The ANALYSIS command can be used in the I/O Options section to request that only a finite element analysis be performed (optimization input is ignored). It may also be used in the I/O Options or Subcase Information sections to identify the solution sequence for all subcases or for individual subcases, respectively. Format ANALYSIS = option

Argument

Options

Description

option



The first two options ONLY and OPTSKIP refer to the run control functionality of the ANALYSIS command:

Default = ONLY

The remaining options refer to the solution sequence identification functionality of the ANALYSIS command:

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ONLY:

Performs finite element analysis run only. Optimization inputs are checked but ignored.

OPTSKIP:

Performs finite element analysis run only. Optimization inputs are ignored.

STATICS:

Linear static or nonlinear quasi-static gap analysis.

NLSTAT:

Nonlinear quasi-static analysis.

HEAT:

Linear steady-state heat transfer analysis or linear transient heat transfer analysis.

NLHEAT:

Nonlinear steady-state heat transfer analysis.

MODES:

Normal modes analysis.

MCEIG:

Modal complex eigenvalue analysis.

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Argument

Options

Description BUCK:

Linear buckling analysis.

DFREQ:

Direct frequency response analysis.

MFREQ:

Modal frequency response analysis.

DTRAN:

Direct transient response analysis.

MTRAN:

Modal transient response analysis.

DFOUR:

Direct transient response analysis through Fourier transformation.

MFOUR:

Model transient response analysis through Fourier transformation.

MBD:

Multi-body dynamics analysis.

NLGEOM:

Geometric nonlinear implicit (quasi-)static analysis.

IMPDYN:

Geometric nonlinear implicit dynamic analysis.

EXPDYN:

Geometric nonlinear explicit dynamic analysis.

FATIGUE:

Fatigue analysis.

Comments 1.

ANALYSIS=ONLY or ANALYSIS=OPTSKIP are only applicable in the I/O Options section.

2.

ANALYSIS=ONLY or ANALYSIS=OPTSKIP may be used in combination with one of the other ANALYSIS options.

3.

When ANALYSIS=ONLY or ANALYSIS=OPTSKIP are used, all elements (including design elements) are treated as non-design elements.

4.

When ANALYSIS=ONLY or ANALYSIS=OPTSKIP are used, all properties and grids referenced by size and shape variables will be set at the values on the associated property and GRID data.

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B2GG Subcase Information Entry B2GG – Direct Input Viscous Damping Matrix Selection Description The B2GG command can be used in the Subcase Information section to select a direct input viscous damping matrix. Format B2GG = name

Argument

Description

name

Name of a damping matrix that is input in the bulk data section using the DMIG card.

Comments 1.

DMIG matrices will not be used unless selected.

2.

This matrix is handled like the damper elements CDAMPi and CVISC.

3.

Terms are added to the viscous damping matrix before any constraints are applied.

4.

The matrix must be symmetric, that is field 4 on the referenced DMIG entry must contain the integer 6.

5.

When multiple instances of this card occur, the referenced DMIG entries are combined. This behavior differs from that of Nastran, which only recognizes the last instance of this card in the same situation.

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CMETHOD Subcase Information Entry CMETHOD – Data Selection Description The CMETHOD command can be used in the Subcase Information section to select the method for complex eigenvalue extraction. Format CMETHOD = option

Argument

Options

Description

option

< SID >

SID:

Set identification of an EIGC bulk data entry.

No default Comments 1.

Only one CMETHOD entry can be defined in a subcase.

2.

A CMETHOD entry is required for complex eigenvalue analysis.

3.

If present above the first subcase, it is applied to all complex eigenvalue subcases.

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CMSMETH Subcase Information Entry CMSMETH – Run Control Description The CMSMETH command can be used in the Subcase Information section to request that only a component mode synthesis solution be performed and to select a component mode synthesis method definition to be used. Format CMSMETH = option

Argument

Option

Description

option



CMSID: Identification of a CMSMETH bulk data entry.

No default Comments 1.

All subcases must have the same MPC reference; in which case it runs the component mode synthesis (flexible-body preparation) solution sequence using the CMSMETH reference and the common MPC reference.

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CNTNLSUB Subcase Information Entry CNTNLSUB – Continue nonlinear solution sequence from a preceding nonlinear subcase Description The CNTNLSUB command can be used in the Subcase Information section to continue a nonlinear solution from a preceding nonlinear subcase, and thus create complex loading sequences. Format CNTNLSUB = option

Argumen Option t

Description

option

Yes:

Default = Yes

240

This nonlinear subcase continues the nonlinear solution from the nonlinear subcase immediately preceding. "Preceding" refers to the sequence of subcases in the deck, not the subcase numbering. If CNTNLSUB,YES is used within a subcase, then the preceding subcase must be nonlinear subcase of the same type. If CNTNLSUB,YES is used above the first subcase, then all the consecutive nonlinear subcases of the same type will continue each other (however, other types of subcases interspersed between nonlinear ones will “break” the continuation sequence).

No:

This nonlinear subcase executes a new solution sequence starting from the initial, stress-free state of the model. See comment 1.

SID: Subcase ID

This nonlinear subcase continues nonlinear solution from SUBCASE SID. SUBCASE SID must precede the current subcase in the deck and must be a nonlinear subcase of the same type. See comment 1.

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Comments 1.

This command applies only to nonlinear subcases. Nonlinear subcases may only be continued from other nonlinear subcases of the same analysis type. that is, geometric linear subcases (ANALYSIS=NLSTAT) may only be continued from other geometric linear subcases, and geometric nonlinear subcases (ANALYSIS=NLGEOM, IMPDYN or EXPDYN) may only be continued from other geometric nonlinear subcases.

2.

Only one CNTNLSUB entry can be defined for each subcase.

3.

If CNTNLSUB = option is present above the first subcase, it is applied to all nonlinear subcases. (CNTNLSUB = SID is only allowed within a subcase).

4.

CNTNLSUB is mostly relevant in path-dependent problems, such as plasticity or gap/ contact analysis with friction/stick. In these problems, subcase continuation can be used to create complex loading paths that will typically produce very different results than simple proportional loading of a single subcase. CNTNLSUB also affects the convergence history and, to some extent, the results in problems that typically are not pathdependent, such as gap/contact analysis without friction.

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DEFORM Subcase Information Entry DEFORM – Data Selection Description The DEFORM command can be used in the Subcase Information section to select an element deformation set. Format DEFORM = option

Argument

Options

Description

option

< SID >

SID:

Set identification of a DEFORM bulk data entry.

Comments 1.

Only one DEFORM entry can be defined for each subcase.

2.

If present above the first subcase, it is applied to all linear static, linear buckling, and nonlinear quasi-static (Gap/Contact) subcases.

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DESOBJ Subcase Information Entry DESOBJ – Objective Selection Description The DESOBJ command is used in the Subcase Information section to select a single response definition as the objective function of an optimization, or to select system response definitions when the objective function is the least squares sum of these definitions. The DESOBJ command also indicates if this response is to be minimized or maximized. Format DESOBJ (type) = integer, PROB

Argument

Options

Description

type



MIN:

The objective is to minimize the response.

Default = MIN

MAX:

The objective is to maximize the response.

MINP:

The objective is to minimize the percentile value of the response (see comment 8).

MAXP:

The objective is to maximize the percentile value of the response (see comment 8).

ID:

Identification number of a DRESP1, DRESP2, DRESP3, or DSYSID bulk data entry.

integer

< ID > No default

PROB

Probability

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Probability related to the reliability requirement (see comment 8).

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Comments 1.

Only one DESOBJ card can be present.

2.

For global DRESP1 responses (responses which are not subcase dependent) or DRESP2 or DRESP3 responses containing either DRESP1L/DRESP2L data or global DRESP1 responses, the DESOBJ data must be above the first SUBCASE statement.

3.

If the DESOBJ data references responses that are subcase specific, then the DESOBJ statement must be within the appropriate subcase definition and the subcase must be of the appropriate type.

4.

If the DSYSID entry is referenced by a DESOBJ subcase entry, a least squares objective function is used in the optimization. The objective function is the sum of the squared, weighted, normalized differences between the target responses and those calculated by the finite element analysis.

5.

DSYSID entries must have unique identification numbers with respect to DRESP1, DRESP2, and DRESP3 entries.

6.

DRESP1, DRESP2, and DRESP3 entries referenced by the DSYSID entry can define only a single response per subcase when the DESOBJ formulation is used.

7.

Time dependent responses should not be referenced by the DESOBJ entry. The minmax formulation should be used for optimization problems that have time-dependent responses as the objective functions. The minmax formulation can be selected using the MINMAX or MAXMIN subcase information entry.

8.

The MAXP, MINP, and PROB options can be input during a Reliability-based Design Optimization run. MINP and MAXP are not supported if random design variables or random parameters are not defined in the model.

9.

This entry is represented as an optimization objective in HyperMesh.

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DESSUB Subcase Information Entry DESSUB – Constraint Selection Description The DESSUB command can be used in the Subcase Information section, within a subcase definition, to select a constraint set that is subcase dependent. Format DESSUB = integer

Argument

Options

Description

integer

< SID >

SID:

Set identification of a DCONSTR or DCONADD bulk data entry.

No default Comments 1.

The constrained response referenced by the DESSUB constraint selection must be subcase dependent.

2.

This entry is represented as an optimizationconstraint in HyperMesh.

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DESVAR Subcase Information Entry DESVAR – Data Selection Description The DESVAR command can be used in the Subcase Information section to select a set of design variables for use in an optimization run. Format DESVAR = option

Argument

Options

Description

option



ALL:

All design variables in the input data, as defined by DESVAR bulk data entries, are used in the optimization.

SID:

The ID of a SET I/O Option definition. Only those design variables, as defined by DESVAR bulk data entries with IDs appearing in the referenced SET entry are considered in the optimization.

Default = ALL

Comments 1.

Only one DESVAR command may appear in the Subcase Information section and should appear before the first SUBCASE statement.

2.

The DESVAR command is optional. If it is absent, all DESVAR bulk data entries will be used.

3.

DESVAR bulk data entries that are not selected by this command are frozen at their initial values (that is same as setting XINIT=XLB=XUB) and all referenced properties will still be governed by the DESVAR settings.

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DLOAD Subcase Information Entry DLOAD - Data Selection Description The DLOAD command can be used in the Subcase Information section to select a dynamic load to be applied in a transient or frequency response problem. Format DLOAD = option

Argument

Options

Description

option

< SID >

SID:

No default

Set identification of a DLOAD, TLOAD1, TLOAD2, RLOAD1, RLOAD2, ACSRCE, or CAALOAD bulk data entry.

Comments 1.

RLOAD1 and RLOAD2 are for frequency response loadings.

2.

TLOAD1 and TLOAD2 are for transient response loadings.

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EIGVRETRIEVE Subcase Information Entry EIGVRETRIEVE - External Data Selection Description The EIGVRETRIEVE command can be used in the Subcase Information section to retrieve eigenvalue and eigenvector results of a normal modes analysis from an external data file (.eigv). Format EIGVRETRIEVE = integer1, integer2, integer3, ...

Argument

Options

Description

integer#



Retrieves eigenvalues and eigenvectors from external data files for use in a modal frequency response analysis.

No default

The external eigenvalue data file names are of the form: _#.eigv where is defined by the EIGVNAME I/O Options entry and # is one of the integer arguments defined here. Comments 1.

Only one occurrence of EIGVRETRIEVE is permitted per subcase.

2.

When multiple integer arguments are provided, eigenvalues are retrieved from multiple external data files and combined.

3.

If EIGVRETRIEVE is not present, eigenvalue and eigenvector results are not retrieved from external data files and a normal modes analysis is performed for the modal frequency response or modal transient response analysis subcase.

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EIGVSAVE Subcase Information Entry EIGVSAVE - Output Request Description The EIGVSAVE command can be used in the Subcase Information section to output eigenvalue and eigenvector results of a normal modes analysis to an external data file (.eigv). Format EIGVSAVE = integer

Argument

Options

Description

integer



Outputs eigenvalues and eigenvectors obtained from a normal modes analysis to an external data file.

No default

The external eigenvalue data file name is of the form: _#.eigv where, is defined by the EIGVNAME I/O Options entry and # is the integer argument defined here. Comments 1.

Only one occurrence of EIGVSAVE per subcase is permitted.

2.

If EIGVSAVE is not present, eigenvalue and eigenvector results do not get exported to an external data file.

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ESLTIME Subcase Information Entry ESLTIME – Data Selection Description The ESLTIME command can be used in the Subcase Information section to select particular time steps for geometric nonlinear response ESLM optimization or Multi-body Dynamics ESLM optimization. Format ESLTIME = option

Argument

Option

Description

option

< SID >

SID:

No default

Set identification number of an ESLTADD or ESLTIME bulk data entries (see Comments 1 and 2).

Comments 1.

Only one ESLTIME entry can be present for each subcase. It can only be used in subcases that contain an ANALYSIS = NLGEOM, IMPDYN, EXPDYN or MBD entry.

2.

If the SID referenced by the ESLTIME subcase information entry matches with the SID defined for an ESLTADD bulk data entry, then the information on this entry alone is selected. However, if an ESLTADD bulk data entry does not exists with the referenced SID, then any ESLTIME bulk data entries that have this SID will be selected.

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EXCLUDE Subcase Information Entry EXCLUDE - Exclusion Set Selection Description The EXCLUDE command can be used in the Subcase Information section to select a set of elements to be excluded from a linear buckling analysis. Format EXCLUDE = option

Argument

Options

Description

option



ESID - set identification number of an element set.

No default Comments 1.

The element set is defined using the SET bulk data entry.

2.

This subcase information entry is only valid when it appears in a buckling subcase.

3.

The excluded elements are only removed from the geometric stiffness matrix, resulting in a buckling analysis with elastic boundary conditions. This means that the excluded elements may still be showing movement in the buckling mode.

4.

Extreme caution is advised when using the EXCLUDE command. In general, excluding any region from buckling analysis can, and usually will, result in a higher, overestimated critical load calculation, which then may produce false overconfidence in a structure’s load bearing capacity. The excluded region will have no effect on the calculated critical load only if the excluded modes are geometrically separated from, or orthogonal to, the actual critical buckling mode.

5.

A descriptive engineering explanation is as follows: buckling analysis by design seeks the weakest, least stable configuration of the structure. Excluding any region from this search can cause you to miss the actual critical buckling mode that involves the respective region and has the least load bearing capacity.

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FATDEF Subcase Information Entry FATDEF – Data Selection Description The FATDEF command can be used in the Subcase Information section to select a FATDEF bulk data entry that will define the elements, and their associated fatigue properties, to be considered for fatigue analysis. Format FATDEF = option

Argument

Option

Description

Option

< SID >

SID:

Set identification of a FATDEF bulk data entry.

No default Comments 1.

FATDEF bulk data entries will not be used unless selected in the Subcase Information section.

2.

If present above the first subcase, it is applied to all fatigue analysis subcases.

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FATPARM Subcase Information Entry FATPARM – Data Selection Description The FATPARM command can be used in the Subcase Information section to select a FATPARM bulk data entry that will define the parameters to be used for a fatigue analysis. Format FATPARM = option

Argument

Option

Description

Option

< SID >

SID:

Set identification of a FATPARM bulk data entry.

No default Comments 1.

FATPARM bulk data entries will not be used unless selected in the Subcase Information section.

2.

If present above the first subcase, it is applied to all fatigue analysis subcases.

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FATSEQ Subcase Information Entry FATSEQ – Data Selection Description The FATSEQ command can be used in the Subcase Information section to indicate that a subcase is a fatigue analysis subcase and to select a FATSEQ bulk data entry that will define the loading sequence for the fatigue analysis. Format FATSEQ = option

Argument

Option

Description

Option

< SID >

SID:

Set identification of a FATSEQ bulk data entry.

No default Comments 1.

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This command may not appear above the first subcase.

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FREQUENCY Subcase Information Entry FREQUENCY - Data Selection Description The FREQUENCY command can be used in the Subcase Information section to select the set of forcing frequencies to be solved in a frequency response problem. Format FREQUENCY = option

Argument

Option

Description

option

< SID >

SID:

Set identification of FREQ, FREQ1, FREQ2, FREQ3, FREQ4, and FREQ5 bulk data entries.

No default Comments 1.

A frequency set selection is required for transient response by the Fourier transform method when TSTEP (FOURIER) is used. The Fourier transform will be performed at the frequencies specified.

2.

All FREQi data with the same set identification number will be used.

3.

If present above the first subcase, it is applied to each frequency response or transient subcase without a FREQUENCY command.

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GLOBSUB Subcase Information Entry GLOBSUB - Global Model and Transfer Zone Selection Description The GLOBSUB entry can be used in the Subcase Information section to select a subcase that references the global structure for local-global analysis. A set of grid points in the local structure that defines the transfer zone can also be specified. Format GLOBSUB, SUBID, SID

Argument

Value

Description

SUBID

0> Specifies the identification number of the subcase that contains the global structure definition (via SUBMODEL).

SID

0> Specifies the set of grid points in the local structure that defines the transfer zone. The displacements from the global structure are interpolated and applied to this set of grid points.

Comments 1.

The transfer zone should contain only 3-dimensional elements in both the local and global structures. Second order elements (for example, CHEXA20) are allowed. There is no further restriction on element types elsewhere in the structure.

2.

The transfer zone may represent single or multiple cuts (sections) through the structure. Multiple cuts should be separated from each other, that is, they should not exist closer than the element size of the global model.

3.

The GLOBSUB entry should always reference the subcase ID of a global subcase that is defined above its corresponding local subcase.

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GROUNDCHECK Subcase Information Entry GROUNDCHECK – Rigid Body Motion Grounding Check Description The GROUNDCHECK command can be used in the Subcase Information section to perform a grounding check analysis on the stiffness matrix to expose unintentional constraints by moving the model rigidly. Format GROUNDCHECK(print,GRID=gid,THRESH=thresh) = option

Argument

Option

Description

print

< PRINT, NOPRINT > Default = PRINT

PRINT:

Write output to the .out file.

NOPRINT:

Do not write output to the .out file.

grid

< GID > Default = geometric center of the structure.

Grid Point ID: Reference grid point for the calculation of the rigid body motion.

thresh

Default = largest term in the stiffness matrix, divided by 1.0E10.

Maximum strain energy which passes the check.

option

< YES, NO > Default = YES

YES: Grounding check is performed. NO:

Grounding check is not performed.

Comments 1.

GROUNDCHECK must be specified before the first SUBCASE.

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2.

Grounding check is performed on all degrees-of-freedom of the model and all degrees-offreedom that are not constrained by SPC. MPC equations are not used in the check.

3.

Any MPC that will be violated due to rigid body modes is reported. An equivalent energy magnitude is also calculated between MPC violation and the strain energy. The equivalent energy from MPC violation is added to the strain energy when performing the grounding check.

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IC Subcase Information Entry IC – Transient and Explicit Analysis Initial Condition Set Selection Description The IC command may be used in the Subcase Information section to select initial conditions for transient and explicit analysis. Format IC = option Example IC = 10

Argument

Option

Description

option

< SID >

SID:

Set identification number of TEMP, TEMPD, TIC, TICA bulk data entries.

No default Comments 1.

TIC and TICA entries will not be used (therefore, no initial conditions) unless selected in the Subcase Information section.

2.

Initial conditions cannot be used with modal transient analysis.

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INVEL Subcase Information Entry INVEL – Multi-Body Initial Velocity Selection Description The INVEL command can be used in the Subcase Information section to select a multi-body initial velocity set to be applied in a multi-body problem. Format INVEL = option

Argument

Option

Description

option

< SID >

SID:

Set identification if INVELB or INVELJ bulk data entries.

No default Comments 1.

Only one INVEL entry can be present for each subcase.

2.

This subcase information entry is only valid when it appears in a multi-body subcase.

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K2GG Subcase Information Entry K2GG - Direct Input Stiffness Matrix Selection Description The K2GG command can be used in the Subcase Information section to select a direct input stiffness matrix. Format K2GG = name

Argument

Description

name

Name of a stiffness matrix that is input in the bulk data section using the DMIG card or name list, with or without factors.

Example K2GG=KAAX K2GG=1.25*KAAX,1.5*KBBX Comments 1.

DMIG matrices will not be used unless selected in the Subcase Information section.

2.

The matrix selected applies to all subcases.

3.

The matrix must be symmetric, that is field 4 on the referenced DMIG entry must contain the integer 6.

4.

When multiple instances of this card occur, the referenced DMIG entries are combined. This behavior differs from that of Nastran, which only recognizes the last instance of this card in the same situation.

5.

The entries in the name list are separated by comma or blank. With factors, each entry consists of a factor followed by a star and a name. The factors are real numbers.

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K2PP Subcase Information Entry K2PP - Direct Input Stiffness Matrix Selection Description The K2PP command can be used in the Subcase Information section to select a direct input stiffness matrix, which is not included in normal modes. Format K2PP = name

Argument

Description

name

Name of a stiffness matrix that is input in the bulk data section using the DMIG card.

Comments 1.

DMIG matrices will not be used unless selected in the Subcase Information section.

2.

The matrix selected applies to all subcases.

3.

K2PP matrices are used only in dynamic response problems. They are not used in normal modes.

4.

When multiple instances of this card occur, the referenced DMIG entries are combined. This behavior differs from that of Nastran, which only recognizes the last instance of this card in the same situation.

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K42GG Subcase Information Entry K42GG - Direct Input Structural Element Damping Matrix Selection Description The K42GG command can be used in the Subcase Information section to select a direct input structural element damping matrix. Format K42GG = name

Argument

Description

name

Name of a damping matrix that is input in the bulk data section using the DMIG card.

Comments 1.

DMIG matrices will not be used unless selected.

2.

This matrix is handled like the contributions from the structural element damping coefficients GE on MATi, PBUSH, and PELAS.

3.

Terms are added to the damping matrix before any constraints are applied.

4.

The matrix must be symmetric, that is field 4 on the referenced DMIG entry must contain the integer 6.

5.

When multiple instances of this card occur, the referenced DMIG entries are combined. This behavior differs from that of Nastran, which only recognizes the last instance of this card in the same situation.

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LABEL Subcase Information Entry LABEL - Subcase Label Description The LABEL command can be used in the Subcase Information section to provide a subcase with a label. Format LABEL = name

Argument

Description

name

Any string of ASCII characters can be used to label a subcase.

Comments 1.

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This label is inserted into output files for post-processing purposes.

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LOAD Subcase Information Entry LOAD – Data Selection Description The LOAD command can be used in the Subcase Information section to select a static load set to be applied in linear static solutions. Format LOAD = option

Argument

Options

Description

option

< SID >

SID:

No default

Set identification of a LOAD bulk data entry or, if no LOAD bulk data entry exists with this SID, the set identification of FORCE, FORCE1, MOMENT, MOMENT1, PLOAD, PLOAD1, PLOAD2, PLOAD4, GRAV, RFORCE, and SPCD, bulk data entries.

Comments 1.

Only one LOAD entry can be present for each subcase.

2.

A METHOD entry cannot be present in the same subcase definition as a LOAD entry.

3.

If the SID referenced by the LOAD subcase information entry matches with the SID defined for a LOAD bulk data entry, the information on this entry alone is selected. However, if no LOAD bulk data entry has the referenced SID defined, any of the static load entries: FORCE, FORCE1, MOMENT, MOMENT1, PLOAD, PLOAD1, PLOAD2, PLOAD4, GRAV, RFORCE, and SPCD, which have this SID will be selected.

4.

In versions of OptiStruct prior to 8.0, thermal loads were selected in the Subcase Information section using the LOAD data selector. In version 8.0, the TEMPERATURE data selector was added to perform this function. It is possible to revert to the old behavior mode by setting the LOADTEMP option to SHAREID in the OptiStruct Configuration File.

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M2GG Subcase Information Entry M2GG - Direct Input Mass Matrix Selection Description The M2GG command can be used in the Subcase Information section to select a direct input mass matrix. Format M2GG = name

Argument

Description

name

Name of a mass matrix that is input in the bulk data section using the DMIG card.

Comments 1.

DMIG matrices will not be used unless selected in the Subcase Information section.

2.

The matrix selected applies to all subcases.

3.

The matrix must be symmetric, that is field 4 on the referenced DMIG entry must contain the integer 6.

4.

By default, mass contribution of the external mass matrix (M2GG) is considered for the generation of gravity and centrifugal loads.

5.

When multiple instances of this card occur, the referenced DMIG entries are combined. This behavior differs from that of Nastran, which only recognizes the last instance of this card in the same situation.

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MBSIM Subcase Information Entry MBSIM – Multi-Body Simulation Selection Description The MBSIM command can be used in the Subcase Information section to select a multi-body simulation definition to be applied in a multi-body problem. Format MBSIM = option

Argument

Option

Description

option

< SID >

SID:

Set identification of MBSEQ, MBSIM, or MBLIN bulk data entries.

No default Comments 1.

Only one MBSIM entry can be present for each subcase.

2.

This subcase information entry is only valid when it appears in a multi-body subcase.

3.

MBSIM can be used to select only one bulk data entry. MBSEQ, MBSIM, and MBLIN must have unique IDs.

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METHOD Subcase Information Entry METHOD - Data Selection Description The METHOD command can be used in the Subcase Information section to select a method for real eigenvalue extraction. Format METHOD (type) = option

Argument

Options

Description

type



The referenced EIGRL or EIGRA bulk data entry is applied to the structural (STRUCTURE) or fluid (FLUID) portion of the model.

Default = Structure option

< SID > No default

SID: Set identification of an EIGRL or EIGRA bulk data entry.

Comments 1.

Only one METHOD entry of each type can be defined for each subcase. If only one type of METHOD entry is defined (either METHOD(STRUCTURE) or METHOD(FLUID)), this definition will be used for both the structure and the fluid portion of the model.

2.

A METHOD entry cannot be present in the same subcase definition as a LOAD entry.

3.

A METHOD entry is required for normal modes, linear buckling, modal frequency response, and modal transient response solution sequences.

4.

If present above the first subcase, it is used in all subsequent subcases which can accept a METHOD entry. However, this does not apply to subcases which already contain their own METHOD entry.

5.

AMSES can be used for the fluid (FLUID) part of the model. METHOD(FLUID) can reference an EIGRA bulk data entry.

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MFLUID Subcase Information Entry MFLUID - Virtual Fluid Mass Selection Description The MFLUID command can be used in the Subcase Information section to select the parameters and damp elements and activate the calculation of virtual fluid mass. Format MFLUID = option

Argument

Options

Description

option

< SID >

SID:

Set identification number of one or more MFLUID bulk data entries.

No default Comments 1.

Only one MFLUID entry can be present.

2.

MFLUID may be requested for a normal modes, complex eigenvalue, frequency response, or transient response analysis.

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MINMAX or MAXMIN Subcase Information Entry MINMAX / MAXMIN - Objective Selection Description The MINMAX or MAXMIN commands can be used in the Subcase Information section to select normalized response or system identification definitions as the objective function for a "Minmax" or "Maxmin" optimization. Format MINMAX = integer MAXMIN = integer

Argument

Options

Description

integer

< DOID >

DOID:

Design objective identification number of a DOBJREF or DSYSID bulk data entry.

No default Comments 1.

Multiple MINMAX entries are allowed and multiple MAXMIN entries are allowed, but a MAXMIN entry cannot appear in the same input file as a MINMAX entry.

2.

The multiple MINMAX or MAXMIN entries define the same optimization problem.

3.

Refer to the Optimization Problem page of the User's Guide for more information on "Minmax" optimization.

4.

If the DSYSID entry is referenced by a MINMAX or a MAXMIN subcase entry, the beta method is applied in the optimization as follows:

5.

This entry is represented as an optimization objective in HyperMesh.

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MLOAD Subcase Information Entry MLOAD – Multi-Body Load Selection Description The MLOAD command can be used in the Subcase Information section to select a multi-body load set to be applied in a multi-body problem. Format MLOAD = option

Argument

Option

Description

option

< SID >

SID:

No default

Set identification of GRAV, MBFRC, MBFRCC, MBFRCE, MBMNT, MBMNTC, MBMNTE, MBSFRC, MBSFRCC, MBSFRCE, MBSMNT, MBSMNTC, MBSMNTE, and MLOAD bulk data entries.

Comments 1.

Only one MLOAD entry can be present for each subcase.

2.

This subcase information entry is only valid when it appears in a multi-body subcase.

3.

If the SID referenced by the MLOAD subcase information entry matches with the SID defined for an MLOAD bulk data entry, the information on this entry alone is selected. However, if no MLOAD bulk data entry has the referenced SID defined, any of the multibody load entries: GRAV, MBFRC, MBFCC, MBFRCE, MBMNT, MBMNTC, MBMNTE, MBSFRC, MBSFRCC, MBSFRCE, MBSMNT, MBSMNTC, or MBSMNTE which have this SID will be selected.

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MODESELECT I/O Options and Subcase Information Entry MODESELECT – Mode Selection Description The MODESELECT command can be used in the I/O Options or the Subcase Information section to select a subset of computed modes in modal dynamic analysis subcases. Format MODESELECT (type) = n Mode selection based on arbitrary mode numbers. Alternate Format 1 MODESELECT (type, LMODES = lm) Mode selection based on lowest modes. Alternate Format 2 MODESELECT (type, LMODENM = lom, HMODENM = him) Mode selection based on a range of mode numbers. Alternate Format 3 MODESELECT (type, LFREQ = lof, HFREQ = hif, UNCONSET = m) Mode selection based on a range of frequencies.

Argument

Options

Description

type

STRUCTURE

If STRUCTURE is specified, the MODESELECT command references modes associated with structural analysis only.

(Default)

n

FLUID

If FLUID is specified, the MODESELECT command references modes associated with fluid analysis only.

n > 0

Set identification number n of a set of mode numbers. The modes corresponding to the mode numbers specified in set n will be included in the analysis. If no such set exists, then mode n will be included in the analysis.

(Integer)

n < 0 (Integer)

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Set identification number |n| of a set of mode numbers. The modes corresponding to the mode numbers specified in set | n| will be excluded from the analysis. If no such set exists,

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Argument

Options

Description then mode |n| will be excluded from the analysis.

LMODES

Specifies the number of lowest modes to be selected.

lm (Integer > 0)

LMODENM

lom (Integer > 0)

HMODENM

him (Integer > lom > 0)

LFREQ

Specifies the upper bound of the mode number range for selecting modes (See comment 3).

Specifies the lower bound of the frequency range for selecting modes (See comment 4).

lof (Real > 0.0)

HFREQ

Specifies the lower bound of the mode number range for selecting modes (See comment 3).

hif (Real > lof > 0.0)

Specifies the upper bound of the frequency range for selecting modes (See comment 4).

UNCONSET

UNCONSET

This flag indicates that the following fields specify a single mode or a set of modes for unconditional inclusion or exclusion.

m

m > 0

Set identification number m of a set of mode numbers. The modes corresponding to the mode numbers specified in set m will be unconditionally included in the analysis. If no such set exists, then mode m will be unconditionally included in the analysis.

(Integer)

m < 0 (Integer)

Set identification number |m| of a set of mode numbers. The modes corresponding to the mode numbers specified in set | m| will be unconditionally excluded from the analysis. If no such set exists, then mode |m| will be unconditionally excluded from the analysis.

Comments 1.

The MODESELECT I/O Options entry is only supported in modal frequency response, modal transient and complex eignenvalue analyses. It is not supported in Response Spectrum Analysis.

2.

Multiple MODESELECT entries are allowed in a model. MODESELECT entries can be specified above the first subcase or within each subcase.

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3.

If LMODENM is specified without HMODENM, a default value of 10000000 (ten million) is assumed for HMODENM. If HMODENM is specified without LMODENM, a default value of 1 is assumed for LMODENM.

Defaults

4.

LMODENM

HMODENM

specified

1.0E+7

1

specified

If LFREQ is specified without HFREQ, a default value of 1.0E+30 is assumed for HFREQ. If HFREQ is specified without LFREQ, a default value of 0.0 is assumed for LFREQ.

Defaults

LFREQ

HFREQ

specified

1.0E+30

0.0

specified

5.

When the MODESELECT Case Control command is used in conjunction with the parameter LFREQ, the MODESELECT Case Control takes precedence.

6.

If the use of MODESELECT results in all or none of the computed modes for use, you are informed with a message.

7.

The faster method for modal frequency response analysis (activated by PARAM,FASTFR,YES) cannot be used in conjunction with MODESELECT.

8.

Modes that are eliminated by MODESELECT will display:

274

a)

an “S” next to the mode number, if the mode is eliminated by MODESELECT in one subcase and PARAM, LFREQ or PARAM, HFREQ in another subcase, or

b)

an “M” next to the mode number, if eliminated by MODESELECT in at least one subcase.

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MODEWEIGHT Subcase Information Entry MODEWEIGHT - Optimization Parameter Description The MODEWEIGHT command can be used in the Subcase Information section to define a multiplier for computed eigenvalues that are to be used in the calculation of the "weighted reciprocal eigenvalue" and "combined compliance index" optimization responses. Format MODEWEIGHT (mode) = weight

Argument

Description

mode

Mode number. No default (0 < Integer < highest calculated mode)

weight

The multiplier to be used for the corresponding mode in the calculation of "weighted reciprocal eigenvalue" or "combined compliance index." Default = 1.0 (Real)

Comments 1.

OptiStruct will terminate with an error if no mode number is provided.

2.

Modes for which there is no MODEWEIGHT definition are not included in the calculation of the "weighted reciprocal eigenvalue" and "combined compliance index" optimization responses.

3.

Refer to the Responses page of the User's Guide for more information on "weighted reciprocal eigenvalue" and "combined compliance index" optimization response calculations.

4.

MODEWEIGHT is only used in conjunction with DRESP1, RTYPE = WFREQ, COMB.

5.

If there is no MODEWEIGHT defined, but a DRESP1 with RTYPE = WCOMP exists, the following default is applied: MODEWEIGHT (1) = 1.0 in most cases for topology optimization. MODEWEIGHT (7) = 1.0 if no SPC is defined for the subcase, EIGRL does not define a V1 > 0.0, and it is solving for more than 6 modes or all modes below an upper bound.

6.

This entry is represented as an optimization response in HyperMesh.

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MODTRAK Subcase Information Entry MODTRAK – Controls Mode Tracking Description The MODTRAK command can be used in the Subcase Information section to control mode tracking. Format MODTRAK = option

Argument

Options

Description

option



ON or blank:

Mode tracking is active.

OFF:

Mode tracking is not active.

Default = OFF Comments 1.

MODTRAK entry is only valid for normal modes subcases.

2.

If a MODTRAK entry is present in the input, then PARAM, MODETRAK is ignored.

3.

Positive integers are accepted as option, and are interpreted as ON.

4.

Negative integers or 0 are not accepted as option and will result in an error termination.

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MOTION Subcase Information Entry MOTION – Multi-Body Motion Selection Description The MOTION command can be used in the Subcase Information section to select a multi-body motion set to be applied in a multi-body problem. Format MOTION = option

Argument

Option

Description

option

< SID >

SID:

No default

Set identification of MOTION, MOTNG, MOTNGC, MOTNGE, MOTNJ, MOTNJC, and MOTNJE bulk data entries.

Comments 1.

Only one MOTION entry can be present for each subcase.

2.

This subcase information entry is only valid when it appears in a multi-body subcase.

3.

If the SID referenced by the MOTION subcase information entry matches with the SID defined for a MOTION bulk data entry, the information on this entry alone is selected. However, if no MOTION bulk data entry has the referenced SID defined, any of the multibody motion entries: MOTNG, MOTNGC, MOTNGE, MOTNJ, MOTHJC, or MOTIONJE which have this SID will be selected.

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MPC Subcase Information Entry MPC - Data Selection Description The MPC command can be used in the Subcase Information section to select a multi-point constraint set. Format MPC = option

Argument

Options

Description

option

< SID >

SID:

No default

Set identification of a MPCADD bulk data entry or, if no MPCADD bulk data entry exists with this SID, the set identification of an MPC bulk data entry.

Comments 1.

Only one MPC entry can be present for each subcase.

2.

If the SID referenced by the MPC subcase information entry matches with the SID defined for a MPCADD bulk data entry, then the information on this entry alone is selected. However, if no MPCADD bulk data entry has the referenced SID defined, then any MPC bulk data entries that have this SID defined will be selected.

3.

If present above the first subcase, it is the default for each subcase without an MPC command, with the exception of linear buckling analysis subcases. Linear buckling analysis subcases inherit the MPC information from the referenced static subcase.

4.

MPC may be set to 0 to override the default in subcases where no MPC is required.

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NLOAD Subcase Information Entry NLOAD - Data Selection Description The NLOAD command can be used in the Subcase Information section to select a time dependent load to be applied in geometric nonlinear analysis problem. Format NLOAD = option

Argument

Options

Description

option

< SID >

SID:

Set identification of an NLOAD or NLOAD1 bulk data entry.

No default Comments 1.

NLOAD can only be used in subcases that contain an ANALYSIS = NLGEOM entry.

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NLPARM Subcase Information Entry NLPARM - Data Selection Description The NLPARM command can be used in the Subcase Information section to activate nonlinear solution methods for this subcase and to select the parameters used for nonlinear quasi-static analysis and geometric nonlinear implicit analysis. Format NLPARM = option

Argument

Option

Description

option

< SID >

SID: Set identification of an NLPARM bulk data entry.

No default Comments 1.

NLPARM bulk data entries will not be used unless selected in the Subcase Information section.

2.

If present above the first subcase, it is applied to all linear static subcases. Nonlinear quasi-static analysis subcases, by their definition, will already have an NLPARM reference which is used.

3.

The NLPARM command is supported in quasi-static analysis, geometric nonlinear analysis, and optimization subcases.

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NONLINEAR Subcase Information Entry NONLINEAR - Data Selection Description The NONLINEAR command can be used in the Subcase Information section to select a nonlinear dynamic load set for direct transient analyses. Format NONLINEAR = option

Argument

Option

Description

option

< SID >

SID:

Set identification of NOLIN1, NOLIN2, NOLIN3, NOLIN4 or NLRGAP bulk data entries.

No default Comments 1.

NONLINEAR is only allowed in direct transient analysis subcases.

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NORM Subcase Information Entry NORM - Optimization Parameter Description The NORM command can be used in the Subcase Information section to define a normalization factor used in the computation of the "combined compliance index" optimization response. Format NORM = option

Argument

Description

option

Normalization factor. Default = OptiStruct determines a weighting factor based on the lowest eigenvalue and highest compliance of the initial iteration step. (Real)

Comments 1.

282

Refer to the Responses page of the User's Guide for more information on the "combined compliance index" optimization response calculation.

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NSM Subcase Information Entry NSM – Data Selection Description The NSM command can be used in the Subcase Information section to select a non-structural mass set for mass generation. The selector command must appear before the first SUBCASE statement. Format NSM = option

Argument

Option

Description

option

< SID >

SID:

No default

Set identification number of a NSMADD bulk data entry or, if no NSMADD bulk data entry exists with this SID, the set identification of NSM, NSM1, NSML and NSML1 bulk data entries.

Comments 1.

Only one NSM subcase information entry can be present in the model.

2.

This subcase information entry must appear before the first SUBCASE statement.

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P2G Subcase Information Entry P2G – Direct Input Load Matrix Selection Description The P2G command is used before the first subcase to select a direct input load matrix. Format P2G = name Examples P2G = PAX P2G = PAX + 2*PAY

Argument

Description

name

Name of a load matrix that is input in the bulk data section using the DMIG card.

Comments 1.

Terms are added to the load matrix before any constraints are applied.

2.

The DMIG matrix must be rectangular (columnar), that is field 4 on the referenced DMIG entry must contain the integer 9.

3.

A scale factor may be applied to this input using the CP2 parameter (See PARAM bulk data entry).

4.

By default, gravity and centrifugal loads are not generated based on the external mass matrix (M2GG). In this case, gravity and centrifugal loads should be included in generating the reduced loads in the DMIG.

5.

When multiple instances of this card occur, the referenced DMIG entries are combined. This behavior differs from that of Nastran, which only recognizes the last instance of this card in the same situation.

6.

The P2G statement must be above the first SUBCASE.

7.

If the DMIG data referenced by the P2G statement has multiple load columns, then they are applied in order in the linear and nonlinear static structural analysis subcases. If there are more static subcases than columns, then only the subcases up to the number of columns will get loads. If there are more columns than static subcases, then the number of columns used with be the number of static subcases. For example, if the DMIG has two columns and there are three static subcases, only the first two subcases will get

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loads. If the DMIG has two columns and there is just one static subcase, then only the first column is used. 8.

For more control, to add a single DMIG load to one of multiple static subcases, use P2GSUB.

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P2GSUB Subcase Information Entry P2GSUB – Direct Input Load Matrix Selection Description The P2GSUB command is used in a specific subcase to select a direct input load matrix. Format P2GSUB = factor*name (column index) Examples P2GSUB = PAX P2GSUB = PAY(2) P2GSUB = 2.5*PAZ(3)

Argument

Description

factor

Optional scale factor Default = 1.0

name

Name of a load matrix that is input in the bulk data section using the DMIG card.

column index Optional column index value 0> Default = 1 Comments 1.

Terms are added to the load matrix before any constraints are applied.

2.

The DMIG matrix must be rectangular (columnar), that is field 4 on the referenced DMIG entry must contain the integer 9.

3.

A scale factor may be applied to this input using the CP2 parameter (see PARAM bulk data entry).

4.

By default, gravity and centrifugal loads are not generated based on the external mass matrix (M2GG). In this case, gravity and centrifugal loads should be included in generating the reduced loads in the DMIG.

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5.

Only one name may be specified on each P2GSUB entry. Multiple P2GSUB entries may be used inside a single subcase section to combine multiple DMIG entries (or to combine multiple columns from the same DMIG).

6.

The P2GSUB statement cannot be specified above the first SUBCASE.

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PEAKOUT Subcase Information Entry PEAKOUT – Data Selection Description The PEAKOUT command can be used in the Subcase Information section to select the criteria for automatic identification of loading frequencies at which result peaks occur. Other result output may then be requested at these “peak” loading frequencies. This data selector is for frequency response solution sequences only. Format PEAKOUT = option

Argument

Option

Description

option

< SID >

SID:

Set identification of a PEAKOUT bulk data entry.

No default Comments 1.

Only one PEAKOUT entry can be defined for each subcase.

2.

If present above the first subcase, it is applied to all subcases which can accept it but do not contain a PEAKOUT card.

3.

Other result output may be obtained at the peak loading frequencies by using the PEAK keyword in the option field. Currently, support is only available for PFMODE, PFPANEL, and PFGRID.

4.

OFREQ is ignored when PEAKOUT is used.

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PRETENSION Subcase Information Entry PRETENSION – Data Selection Description The PRETENSION command can be used in the Subcase Information section to select and activate a pretensioning bolt load. Format PRETENSION = option

Argument

Option

Description

option

< PSID >

Pretensioning load set identification of a PTADD bulk data entry or, if no PTADD bulk data entry exists with this PSID, the set identification of PTFORCE, PTFORC1, PTADJST and PTADJS1 bulk data entry.

Comments 1.

Only one PRETENSION entry can be defined for each subcase.

2.

Combinations of PRETENSION and STATSUB(PRETENS) can be used to create more complex pretensioning sequences.

3.

The rules for sequencing pretensioning subcases on the same pretension section are as follows: a) Pretensioning force (PTFORCE) can only be activated in the new or “fresh” pretensioning subcase for a given section. In other words, a subcase with PRETENSION pointing to PTFORCE cannot also include STATSUB(PRETENS) referencing a subcase that had already pretensioned this section. b) Pretensioning adjustment (PTADJST) may be activated in any of the pretensioning subcases for a given section. The effect of adjustment is cumulative relative to the pretensioning status reached in the respective previous subcase, as referenced by STATSUB(PRETENS).

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RANDOM Subcase Information Entry RANDOM – Random Analysis Set Selection Description Selects the RANDPS and RANDT1 bulk data entries to be used in random analysis. Format RANDOM = n Example RANDOM = 177

Argument

Option

Description

n

(Integer > 0)

Set identification of RANDPS and RANDT1 bulk data entries to be used in random analysis.

Comments 1.

This command must select RANDPS bulk data entries in order to perform random analysis.

2.

Multiple RANDOM data can exist in the Subcase Information section.

3.

This data can be placed anywhere in the Subcase Information section. It is not SUBCASE specific.

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REPGLB Subcase Information Entry REPGLB – Selection of Response to be Reported without being Constrained. Description The REPGLB command can be used in the Subcase Information section, before the first subcase statement, to select a report set that is not subcase dependent. Format REPGLB = integer

Argument

Options

Description

integer

< DRID >

DRID:

No default

Set identification of a DREPORT or DREPADD bulk data entry.

Comments 1.

The response referenced by the REPGLB selection must not be subcase dependent.

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REPSUB Subcase Information Entry REPSUB – Selection of Response to be Reported without being Constrained Description The REPSUB command can be used in the Subcase Information section, within a subcase definition, to select a report set that is subcase dependent. Format REPSUB = integer

Argument

Options

Description

integer

< DRID >

DRID:

No default

Set identification of a DREPORT or DREPADD bulk data entry.

Comments 1.

292

The response referenced by the REPSUB selection must be subcase dependent.

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RESVEC Subcase Information Entry RESVEC – Controls Residual Vector Calculation Description The RESVEC command can be used in the Subcase Information section to control the calculation of residual vectors. Format RESVEC(type, damping) = option

Argument

Options

Description

type



UNITLOD:

Generates residual vectors based on unit loads at the dynamic loading's degrees of freedom. A unit load residual vector is created for every loaded DOF from all SUBCASEs. For normal modes and modal complex eigenvalue analysis, a residual vector is created for each USET and USET1 U6 DOF.

APPLOD:

Generates residual vectors based on the dynamic loading of the modal frequency response analysis at zero Hz.and transient analysis at time = zero. For frequency response analysis, one or two residual vectors are generated for each SUBCASE based on whether the real and imaginary loads are different at zero Hz. A single residual vector is created for each transient SUBCASE. The values at each loaded DOF correspond to the load on that DOF at zero Hz. or time = zero. APPLOD is not valid for normal modes analysis and UNITLOD will always be used.

DAMPLOD:

Generates a viscous damping residual vector for each viscous element based on the eigenvector of the viscous element.

Default = UNITLOD

damping

Default = DAMPLOD

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Argument

option

Options

Description NODAMP:

Turns off the generation of the viscous damping residual vectors.



YES:

Residual vectors are calculated.

See comments for default.

NO:

Residual vectors are not calculated.

Comments 1.

RESVEC can be requested for normal modes, modal complex eigenvalue analysis, modal frequency response, and modal transient response analysis subcases.

2.

If the RESVEC does not exist in a subcase (and is not defined above the first subcase), then the default is YES for modal frequency response and transient response analysis subcases, and the default is NO for all other applicable subcases. If a RESVEC card exists without the YES/NO option, the default is YES.

3.

If EXCITEID=SPCD is defined on RLOAD1/RLOAD2 or TLOAD1/TLOAD2, unit residual vectors for each enforced motion DOF are always computed, even if RESVEC=NO.

4.

For normal modes analysis, the unit load method (type=UNITLOD) is applied to the degrees-of-freedom defined by USET and USET1 U6 entities. If the Lanczos eigensolver is used then RESVEC=YES must be present. If the AMSES or AMLS eigensolver is used, then the USET and USET1 U6 residual vectors will always be calculated (even if RESVEC=NO is specified).

5.

Even though DAMPLOD and NODAMP may be defined inside each subcase, the setting from the last RESVEC data will be used for all of the modal complex eigenvalue analysis, modal frequency response, and modal transient subcases in the model.

6.

Residual vectors from USET and USET1 U6 data are only available for modal complex eigenvalue analysis when AMSES or AMLS is used to calculate the normal modes. They are not created if Lanczos is used.

7.

For modal frequency response and modal transient analysis, the USET and USET1 U6 residual vectors will always be calculated if the AMSES or AMLS eigensolver is used, and they will never be calculated if the Lanczos eigensolver is used. The RESVEC command has no effect on the USET and USET1 U6 residual vector creation for modal frequency response and modal transient analysis.

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RGYRO Subcase Information Entry RGYRO – This data entry can be used in the subcase information section to activate gyroscopic effects in Rotor dynamics Description Identifies a RGYRO bulk data entry that contains information required to implement Rotor dynamics in Modal Complex Eigenvalue Analysis and/or Modal Frequency Response Analysis. Format RGYRO = option Example RGYRO = 3 RGYRO = NO

Argument

Option

Description

option



SID:

Identification number of a RGYRO bulk data entry. (Integer)

NO:

Gyroscopic effects are not included in any solution sequences.

Comments 1. Multiple RGYRO subcase information entries are allowed in different subcases, however, only one RGYRO subcase entry can exist within each subcase.

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RSPEC Subcase Information Entry RSPEC – Data Selection Description The RSPEC command can be used in the Subcase Information section to reference combination rules, excitation degrees of freedom, and input spectra for use in response spectrum analysis. Format RSPEC = option

Argument

Options

Description

option

< SID >

SID:

Set identification of an RSPEC bulk data entry.

No default Comments 1.

Only valid in a response spectrum analysis subcase.

2.

Refer to the Response Spectrum Analysis section of the User’s Guide for more details.

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RWALL Subcase Information Entry RWALL – Data Selection Description The RWALL command can be used in the Subcase Information section to select rigid walls for geometric nonlinear analysis. Format RWALL = option

Argument

Option

Description

option

< SID >

SID:

No default

Set identification of an RWALADD bulk data entry or, if no RWALADD bulk data entry exists with this SID, the set identification of RWALL bulk data entries.

Comments 1.

Only one RWALL entry can be present for each subcase. It can only be used in subcases that contain an ANALYSIS = NLGEOM entry.

2.

If the SID referenced by the RWALL subcase information entry matches with the SID defined for an RWALADD bulk data entry, then the information on this entry alone is selected. However, if no RWALADD bulk data entry has the referenced SID defined, then any XHSIT bulk data entries that have this SID defined will be selected.

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SDAMPING Subcase Information Entry SDAMPING - Data Selection Description The SDAMPING command can be used in the Subcase Information section to apply modal damping as a function of natural frequency in modal solutions. Format SDAMPING (type) = option

Argument

Option

Description

type

< STRUCTURE, FLUID > Default = STRUCTURE

The referenced bulk data entry is applied to the structural (STRUCTURE) or fluid (FLUID) portion of the model.

option

< SID >

SID: Set identification of a TABDMP1 bulk data entry.

No default Comments 1.

SDAMPING can only be used in modal transient, modal frequency response and modal complex eigenvalue analyses; and must reference a TABDMP1 bulk data entry.

2.

Only one SDAMPING entry of each type can be defined for each subcase.

3.

If only one type of SDAMPING entry is defined (either SDAMPING(STRUCTURE) or SDAMPING(FLUID)), this definition will be used for both the structure and the fluid portion of the model.

4.

If present above the first subcase, it is applied to each modal frequency or modal transient subcase without an SDAMPING entry.

5.

To achieve identical displacements in Modal frequency response or Modal transient analyses when the SDAMPING bulk data entry is used instead of PARAM, G, the steps described here can be followed: The TYPE field in the TABDMP1 bulk data entry should be set to CRIT. This TABDMP1 bulk data entry is referenced by the SDAMPING subcase information entry. Set the damping value (field gi) in the TABDMP1 bulk data entry equal to half of the value of PARAM, G (that is set the constant value to C/C0). Set PARAM, KDAMP,-1.

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SEINTPNT Subcase Information Entry SEINTPNT - Selection of Super Element Internal Point Description The SEINTPNT command can be used in the Subcase Information section to select a set of interior DOF of super elements to be converted to exterior DOF. Format SEINTPNT = option Example SEINTPNT = 100 BEGIN BULK SET,100,GRIDC, +,10643,T1,10643,T2,10643,T3 GRID 10643 1 234 55 322

Argument

Option

Description

option



SID refers to the ID of a bulk card SET of type GRIDC.

No default Comments 1.

SEINTPNT can be used when CMS super elements in .h3d files are present in residual runs. After the conversion, these DOF are part of the analysis DOF and can be used as connection points, load DOF, response DOF during optimization.

2.

SEINTPNT is not supported for fluid grids.

3.

GRID point information for interior grids (that are to be converted to exterior grids) should be included in the GRID bulk data entry, which in turn should be included in the solver deck if SEINTPNT is used.

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SOLVTYP Subcase Information Entry SOLVTYP - Solver Selection Description The SOLVTYP command can be used in the Subcase Information section to select the solver for linear and nonlinear static subcases, nonlinear geometric implicit static subcase (ANALYSIS=NLGEOM), and nonlinear geometric implicit dynamic subcase (ANALYSIS=IMPDYN).

Format SOLVTYP = option

Argument

Option

Description

option

< SID >

SID: Set identification of an SOLVTYP bulk data entry. Selects a SOLVTYP bulk data entry that is used to define various settings for the solver, such as different pre-conditioners and convergence criteria for the solver.

Comments 1.

Only one SOLVTYP entry can be defined for each linear and nonlinear static subcases or nonlinear geometric implicit subcase.

2.

If present above the first subcase, it is applied to all compatible linear and nonlinear static subcases and nonlinear geometric implicit subcases. For more details on subcase type and solver compatibility, refer to the SOLVTYP bulk data entry.

3.

If SOLVTYP is present in a subcase, a solver, specified by the referenced SOLVTYP in the bulk data, is used in the solution of linear and nonlinear static subcases and nonlinear geometric implicit subcases. The option selects the SOLVTYP bulk data entry that can be used to define alternate settings such as different pre-conditioners and convergence criteria for the solver.

4.

In optimization, if the responses DRESP1, RTYPE = DISP, LAMA, STESS, STRAIN, CSTRESS, CSTRAIN, CFAILURE, or FORCE are present the solver is automatically reverted to the direct solver.

5.

The iterative solver is a preconditioned conjugate gradient solver. A Factored Approximate Inverse Preconditioner is the default method. This solver is also SMP parallelized.

6.

The performance of the iterative solver depends on the conditioning of the stiffness matrix. For compact solid models, the iterative solver may perform considerably better than the direct solver in terms of memory usage and elapsed times for a single linear

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static subcase. In the case of multiple linear static subcases, the iterative solver may perform worse than the direct solver. The break-even point is at about 4-6 subcases. The performance depends on model, hardware, operating system, and potentially the system load.

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SPC Subcase Information Entry SPC - Data Selection Description The SPC command can be used in the Subcase Information section to select a single-point constraint set. Format SPC = option

Argument

Option

Description

option

< SID >

SID:

No default

Set identification of an SPCADD bulk data entry or, if no SPCADD bulk data entry exists with this SID, the set identification of SPC or SPC1 bulk data entries.

Comments 1.

Only one SPC entry can be present for each subcase.

2.

If the SID referenced by the SPC subcase information entry matches with the SID defined for an SPCADD bulk data entry, then the information on this entry alone is selected. However, if no SPCADD bulk data entry has the referenced SID defined, then any SPC or SPC1 bulk data entries that have this SID defined will be selected.

3.

If present above the first subcase, it is the default for each subcase without an SPC command, with the exception of linear buckling analysis subcases. Linear buckling analysis subcases inherit the SPC information from the referenced static subcase.

4.

SPC may be set to 0 to override the default in subcases where no SPC is required.

5.

SPC must be present for linear static solutions. The SID may be set to 0 to run linear static solutions with no constraints.

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STATSUB Subcase Information Entry STATSUB - Subcase Selection Description The STATSUB command can be used in the Subcase Information section to select a static solution subcase. Format STATSUB(type) = option

Argument

Option

Description

type

PRELOAD: Default = BUCKLING PRETENS:

Referenced static subcase is used in forming the geometric stiffness needed for the linear buckling solution. Referenced static subcase defines a preload. Referenced static subcase introduces pretensioning loads on bolts. (See comment 4).

STRUCTURE: Referenced static subcase will determine the CONTACT / GAP status for a heat transfer analysis (See comment 6). option

< SID >

SID:

Subcase identification number of a static solution subcase. (See comment 5).

No default Comments 1.

A METHOD entry to define the eigenvalue extraction method is required in addition to a STATSUB entry for a linear buckling solution subcase.

2.

A linear buckling solution cannot be performed on a linear static subcase that uses inertia relief.

3.

STATSUB(PRELOAD) is supported for linear static, normal modes, and direct frequency response solution sequences.

4.

STATSUB(PRETENS) is supported for linear and nonlinear static subcases. Other subcase types can use STATSUB(PRELOAD), which refers to a pretension subcase, in order to incorporate the effect of pretensioning on natural frequencies, dynamic solutions, and so

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on. 5.

STATSUB(PRETENS) can only reference a subcase that precedes the current subcase in the input deck.

6.

STATSUB(STRUCTURE) is supported for both steady-state and transient heat transfer solution sequences.

7.

STATSUB(PRELOAD) can be used with the AMSES eigensolver.

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SUBCASE Subcase Information Entry SUBCASE - Subcase Selection Description The SUBCASE command can be used in the Subcase Information section to indicate the start of a new subcase definition. Format SUBCASE = integer

Argument

Description

integer

Subcase identification number (SID) No default (Integer > 0)

Comments 1.

Each subcase must be declared with a separate SUBCASE header and a unique SID.

2.

The SUBCASE header is not needed if there is just one subcase.

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SUBCOM Subcase Information Entry SUBCOM - Combination Subcase Delimiter Description Delimits and identifies a combination subcase. Format SUBCOM = n Example SUBCOM = 125

Argument

Description

n

Subcase identification number (Integer > 2)

Comments 1.

A SUBSEQ command must follow this command.

2.

SUBCOM may only be used with STATIC subcases.

3.

Output requests above the subcase level will be used.

4.

If the referenced subcases contain thermal loads or element deformations, you must define the temperature field in the SUBCOM with a TEMP(LOAD) command or the element deformations with a DEFORM command.

5.

If the reference subcases contain STATSUB(PRELOAD), then all of the referenced subcases must contain the same STATSUB(PRELOAD); the same STATSUB(PRELOAD) should also be used in the SUBCOM.

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SUBMODEL Subcase Information Entry SUBMODEL - Subcase-specific Model Selection Description The SUBMODEL entry can be used in the Subcase Information section to select a submodel as a set of elements. Subcase entries specific to the selected element set can be used to solve the submodel without affecting the rest of the structure. Format SUBMODEL, SID, SID_r

Argument

Value

Description

SID

0>

Specifies the SID of a SET of elements that defines the submodel.

SID_R

0>, NONE, blank

0>

Specifies the SID of a set of rigid elements to be included with the submodel.

NONE:

The subcase containing this SUBMODEL entry will skip all rigid elements in the input deck.

blank:

If SID_r is blank, the subcase containing this SUBMODEL entry will include all rigid elements defined in the input deck.

Comments 1.

A SUBMODEL entry can only be defined within a subcase and cannot be specified above the first subcase.

2.

The SUBMODEL entry does not automatically apply the specific attributes (loads, constraints and so on) to the defined submodel. It is your responsibility to specify corresponding attributes that apply exclusively to the subcase-specific model defined via SUBMODEL.

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SUBSEQ Subcase Information Entry SUBSEQ - Subcase Sequence Coefficients Description Gives the coefficients for forming a linear combination of the previous static subcases. Format SUBSEQ=R1 [, R2, R3, ..., Rn] Example SUBSEQ=1.0, -1.0, 0.0, 2.0

Argument

Description

Ri

Coefficients of the previously occurring static subcases. (Real)

Comments 1.

Can only appear after a SUBCOM command.

2.

R1 to Rn refer to the immediately preceding statis subcases. Rn is applied to the most recently appearing static subcase, R(n-1) is applied to the second most recently appearing static subcase, and so on. The embedded comments ($) describe the following example: DISPL = ALL SUBCASE 1 SUBCASE 2 SUBCOM 3 SUBSEQ = 1.0, -1.0 $ SUBCASE 1 - SUBCASE 2 SUBCASE 11 SUBCASE 12 SUBCOM 13 SUBSEQ = 0.0, 0.0, 1.0, -1.0 $ SUBCASE 11 - SUBCASE 12 or SUBSEQ = 1.0, -1.0 $ EQUIVALENT TO PRECEDING COMMAND.

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SUPORT1 Subcase Information Entry SUPORT1 - Data Selection Description The SUPORT1 command can be used in the Subcase Information section to select the fictitious support set to be applied to the model. Format SUPORT1 = option

Argument

Options

Description

option

< SID >

SID: Set identification of a SUPORT1 bulk data entry.

No default Comments 1.

SUPORT1 entries will not be used unless selected in the Subcase Information section by the SUPORT1 command.

2.

SUPORT1 entries will be applied in all subcases.

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TEMPERATURE Subcase Information Entry TEMPERATURE – Temperature Set Selection Description Selects the temperature set to be used in either material property calculations or thermal loading. Format TEMPERATURE (type) = option Examples TEMPERATURE(LOAD)=15 TEMP(MATERIAL)=7 TEMPERATURE=7

Argument

Option

Description

type



INITIAL:

The selected temperature set will be used to determine initial temperature distribution.

Default = BOTH

MATERIAL:

The selected temperature set will be used to determine temperature-dependent material properties indicated on the MATTi bulk data entries. In addition, the SUBCASE ID of a thermal analysis SUBCASE can be specified. The calculated temperature field is then used to determine temperature-dependent material properties indicated on the MATTi bulk data entries.

option

< SID >

LOAD:

The selected temperature set will be used to determine an equivalent static load.

BOTH:

Both MATERIAL and LOAD will use the same temperature set.

SID:

Set identification number of TEMP or TEMPD bulk data entries.

No default

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Comments 1.

Only one of TEMPERATURE(MATERIAL) or TEMPERATURE (INITIAL) is allowed in any problem and should be specified above the subcase level (although it will be accepted inside the subcase).

2.

TEMPERATURE(BOTH) and TEMPERATURE(LOAD) can be used before the subcase level or inside the subcase. If used before the subcase level, it will apply to all subcases that do not have their own TEMP(BOTH) or TEMP(LOAD) command.

3.

If multiple temperature-dependent material requests are made (for example, by using TEMP(MATERIAL) and TEMP(BOTH)), then the last request will be used to define material properties.

4.

The total load applied will be the sum of external (LOAD command), thermal (TEMP(LOAD) command) and constrained displacement (SPC command) loads.

5.

Static and thermal loads should have unique set identification numbers.

6.

In linear static analysis, temperature strains are calculated with:

where, A(T0 ) is the thermal expansion coefficient defined on the MATi bulk data entries, T is the load temperature defined with TEMPERATURE(LOAD), and T0 is the initial temperature which is defined in one of the following ways: If TEMPERATURE(INITIAL) and TREF (specified on the MATi or PCOMPi cards) are specified, then the TEMPERATURE(INITIAL) set will be used as the initial temperature to calculate both the thermal loads and the material properties. If TEMPERATURE(MATERIAL) and TREF are specified, then TREF will be used as the initial temperature in calculating the thermal load and the TEMPERATURE (MATERIAL) set will be used for the calculation of the material properties. If neither TEMPERATURE(MATERIAL) nor TEMPERATURE(INITIAL) are specified, TREF will be used to calculate both the thermal load and the material properties. If none of TEMPERATURE(INITIAL),TEMPERATURE(MATERIAL), and TEMPERATURE(BOTH) is present, TREF will be used to calculate the load. The material properties will be obtained from the MATi entry. The MATTi is not used in this case. 7.

In versions of OptiStruct prior to 8.0, thermal loads were selected in the Subcase Information section using the LOAD data selector. In version 8.0, the TEMPERATURE data selector was added to perform this function. It is possible to revert to the old behavior mode by setting the LOADTEMP option to SHAREID in the OptiStruct Configuration File.

8.

TEMPERATURE(LOAD) or TEMPERATURE(MATERIAL) can point to a heat transfer subcase or TSTRU ID. The temperature field from a steady state heat transfer analysis or at the final time step of a transient heat transfer analysis will be used.

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TSTEP Subcase Information Entry TSTEP – Transient Time Step Set Selection Description The TSTEP command can be used in the Subcase Information section to select integration for transient analysis. Format TSTEP (type) = option Example TSTEP = 731 TSTEP (FOURIER) = 755

Argument

Option

Description

type



TIME:

The transient response is computed by time step integration in the time domain.

FOURIER:

The transient response is computed in the frequency domain using the Fourier transform method.

SID:

Set identification number of a TSTEP bulk data entry.

Default = TIME

option

< SID > No default

Comments 1.

A TSTEP entry must be selected to execute a transient analysis.

2.

A TSTEP entry can also be used to execute a transient thermal analysis (only for type=TIME or Default).

3.

For the application of time-dependent loads in modal frequency response analysis, a TSTEP bulk data entry must be selected by the TSTEP (FOURIER) command. The timedependent loads will be recomputed in the frequency domain by a Fourier transform.

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TSTEPNL Subcase Information Entry TSTEPNL – Nonlinear Implicit Dynamics Time Step Set Selection Description The TSTEPNL command can be used in the Subcase Information section to select integration and other parameters for nonlinear implicit dynamics analysis. Format TSTEPNL = option Example TSTEPNL = 731

Argument

Option

Description

option

< SID >

SID:

Set identification number of a TSTEPNL bulk data entry.

No default Comments 1.

A TSTEPNL entry must be selected to execute a nonlinear implicit dynamic analysis.

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TSTRU Subcase Information Entry TSTRU - Temperature Set ID for Structural Analysis Description The TSTRU command can be used in the Subcase Information section to assign a temperature set identification number to the resulting nodal temperatures of a steady-state heat transfer analysis or the last time step of a transient heat transfer analysis. Format TSTRU = option

Argument

Option

Description

option

< SID >

SID:

Default = Subcase ID

This is a temperature set identification number. It may be referenced from a static analysis subcase, in which case the resulting nodal temperatures of a steady-state heat transfer analysis or the last time step of a transient heat transfer analysis are considered as applied loads for the static analysis.

Comments 1.

TSTRU is only valid in a heat transfer subcase.

2.

If TSTRU does not explicitly appear in a heat transfer subcase, then the Subcase ID is used as the default.

3.

A temperature set from a heat transfer analysis will override any temperature set defined by the bulk data entries TEMP or TEMPD.

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WEIGHT Subcase Information Entry WEIGHT - Optimization Parameter Description The WEIGHT command can be used in the Subcase Information section to define a weighting factor (multiplier) for the compliances of individual linear static solution subcases, which are used in the calculation of the "weighted compliance" and "combined compliance index" optimization responses. Format WEIGHT = value

Argument

Description

value

The multiplier to be used for the compliance of this subcase in the calculation of "weighted compliance" or "combined compliance index." Default = 1.0 (Real)

Comments 1.

Refer to the Responses page of the User's Guide for more information on "weighted compliance" and "combined compliance index" optimization response calculations.

2.

WEIGHT is only used in conjunction with DRESP1, RTYPE = WCOMP, COMB.

3.

If a WEIGHT is not defined in any subcase, but a DRESP1 with RTYPE = WCOMP or COMB exists, all static subcases are assigned a WEIGHT of 1.0 by default.

4.

This entry is represented as an optimization response in HyperMesh.

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XHIST Subcase Information Entry XHIST – Data Selection Description The XHIST command can be used in the Subcase Information section to select time history output for geometric nonlinear analysis. Format XHIST = option

Argument

Option

Description

option

< SID >

SID:

No default

Set identification of an XHISTADD bulk data entry or, if no XHISTADD bulk data entry exists with this SID, the set identification of XHIST bulk data entries.

Comments 1.

Only one XHIST entry can be present for each subcase. It can only be used in subcases that contain an ANALYSIS = NLGEOM entry.

2.

If the SID referenced by the XHIST subcase information entry matches with the SID defined for an XHISTADD bulk data entry, then the information on this entry alone is selected. However, if no XHISTADD bulk data entry has the referenced SID defined, then any XHSIT bulk data entries that have this SID defined will be selected.

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XSTEP Subcase Information Entry XSTEP – Explicit Analysis Parameter Selection Description The XSTEP command can be used in the Subcase Information section to activate the explicit solution method for this subcase and to select the parameters used for explicit analysis. Format XSTEP = option

Argument

Option

Description

option

< SID >

SID:

Set identification of an XSTEP bulk data entry.

No default Comments 1.

XSTEP bulk data entries will not be used unless selected in the Subcase Information section.

2.

The XSTEP command is supported in explicit analysis and optimization subcases.

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Bulk Data Section

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ACCLR Bulk Data Entry ACCLR – Accelerometer for Geometric Nonlinear Analysis Description Defines accelerometer for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

AC C LR

AID

GID

FC UT

(5)

(6)

(7)

(8)

(9)

(10)

(9)

(10)

Example

(1)

(2)

(3)

(4)

AC C LR

100

34

100.0

(5)

(6)

Field

Contents

AID

Unique accelerometer identification number.

(7)

(8)

(Integer > 0) GID

Grid point identification number. (Integer > 0)

FCUT

Cutoff frequency. (Real > 0)

Comments 1.

The accelerometer option computes a filtered acceleration in the output system.

2.

These filtered accelerations provided by an accelerometer are used in either a SENSOR or in post-processing acceleration time history without aliasing problems.

3.

A 4-pole Butterworth filter is used.

4.

The recommended value for FCUT is 1650 Hz (1.65 ms-1) to obtain a class 1000 SAE filtering.

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5.

In addition to these filtered accelerations, the accelerometer also allows the output of the integrals of X, Y, and Z of the raw accelerations projected to the output coordinate system to time history. These quantities are not used by SENSOR.

6.

Note that if the coordinates are moving, the integrals of X, Y, and Z raw accelerations projected to the output coordinate system are not the same as the velocities projected to the output coordinate system, as described in XHIST. Computation of these integrals in a post-processor allows retrieving the accelerations projected to the output coordinate system without aliasing problems. Integration and differentiation are acting like another filter on top of the 4-pole Butterworth.

7.

This card is unsupported in HyperMesh.

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ACMODL Bulk Data Entry ACMODL – Fluid-Structure Interface Parameters Description Defines model parameters for the Fluid-Structure interface. Format (1)

(2)

(3)

(4)

(5)

(6)

AC MODL

INTER

INFOR

FSET

SSET

NORMAL

INTOL

(7)

(8)

(9)

SKNEPS

DSKNEPS

(10)

SRC HUNIT MAXSGRID

Field

Contents

INTER

Fluid-structure interface type. Default = DIFF (IDENT or DIFF)

INFOR

Defines whether grids or elements identified by FSET and SSET are to be used to define the fluid-structure interface. Default = GRID (GRID or ELEMENT)

FSET

ID of a SET of fluid elements or grids to be considered for the interface. Default = blank (Integer)

SSET

ID of a SET of structural elements or grids to be considered for the interface Default = blank (Integer)

NORMAL

Fluid normal tolerance. Default = 1.0 when INTER = DIFF; Default = 0.001 when INTER = IDENT (Real)

SKNEPS

Fluid skin growth tolerance (See comments 4 and 5). Default = 0.5 (Real)

DSKNEPS

Secondary fluid skin growth tolerance (See comments 4 and 5).

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Field

Contents Default = 1.5 * SKNEPS (Real)

INTOL

Tolerance of inward normal. Default = 0.5 (Real)

SRCHUNIT

Search units. ABS for absolute model units or REL for relative model units based on element size. Default = REL (ABS or REL)

MAXSGRID

The maximum number of structural grids that can be interfaced with one fluid element face. Default = 200 (Integer > 0)

Comments 1.

ACMODL card is optional in the deck. If provided, only one ACMODL card is allowed.

2.

For INTER=IDENT, the interface would be calculated based on a grid to grid match between fluid and structural parts. For INTER=IDENT, INFOR must be GRID or blank. Each grid specified on the FSET/SSET must be able to find a matching interface grid. If either FSET or SSET is not provided, a searching algorithm would find the grids on the skin of the surface.

3.

For INTER=DIFF, if FSET/SSET is provided, the skin of the surface would be based on the set. If either FSET or SSET is not provided, a searching algorithm would find the skin of the surface. The searching algorithm for this case is based on the normal distance from the fluid face. When INTER=DIFF, a grid to grid match is no longer a requirement.

4.

The search box is described by several parameters:

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The height of the searching box is based on the NORMAL parameter. If L is the smallest edge of the fluid element face, the height of the search box would be NORMAL x L. SKNEPS represents the enlargement of the plane of the fluid surface used to define the search box. The diagonal distance, D, from the center of the fluid surface to each surface grid is pushed out by (1.0+SKNEPS) x D. DSKNEPS represents a secondary enlargement of the plane of the fluid surface used to define the search box if SKNEPS fails to find ANY structural elements. The diagonal distance from the center of the fluid surface to each surface grid is pushed out by (1.0 +DSKNEPS) x D. INTOL represents a normal direction into the fluid for the case when the fluid protrudes past the structural interface. It is defined as INTOL x L, where L is the smallest edge of the fluid element surface. 5.

The value required in the secondary fluid skin growth tolerance (DSKNEPS) field must always be greater than the value of the fluid growth tolerance (SKNEPS). If the required value of DSKNEPS is less than SKNEPS, then an ERROR message will be output and the run will be terminated. If the DSKNEPS field is left blank, a default value equal to 1.5 * SKNEPS is assigned to it.

6.

This card is represented as a control card in HyperMesh.

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ACSRCE Bulk Data Entry ACSRCE – Acoustic Source Description Defines acoustic source as a function of power vs. frequency. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

AC SRC E

SID

EXC ITEID

DELAY

DPHASE

TP

RHO

B

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

AC SRC E

111

29

-0.2

87

14

1.0

15

Field

Contents

SID

Identification number of a dynamic load set.

(9)

(10)

No default (Integer > 0) EXCITEID

Identification number of an SLOAD entry set that defines A. No default (Integer > 0)

DELAY

Defines time delay . If it is a non-zero integer, it represents the identification number of a DELAY bulk data entry that defines . If it is real, then it directly defines the value of that will be used for all degrees-of-freedom that are excited by this dynamic load entry. Default = 0 (Integer > 0, or Real)

DPHASE

324

Defines phase . If it is a non-zero integer, it represents the identification number of a DPHASE bulk data entry that defines . If it is real, then it

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Field

Contents directly defines the value of that will be used for all degrees-of-freedom that are excited by this dynamic load entry. Default = 0 (Integer > 0, or Real)

TP

Set identification number of the TABLED1, TABLED2, TABLED3, or TABLED4 entry that gives P(f). Default = 0 (Integer > 0)

RHO

Fluid Density No default (Real > 0.0)

B

Bulk modulus of fluid. No default (Real > 0.0)

Comments

1.

where, 2.

Dynamic load sets must be selected in the I/O Options or Subcase Information sections with the command DLOAD = SID.

3.

SID must be unique with respect to other dynamic load sets, that is ACSRCE, DLOAD, RLOAD1, RLOAD2, TLOAD1, and TLOAD2 entries.

4.

The referenced EXCITEID, DELAY and DPHASE entries must specify fluid points only.

5.

If either DELAY or DPHASE are blank or zero, the corresponding

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will be zero.

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ASET Bulk Data Entry ASET – Boundary Degrees-of-Freedom of a Superelement Assembly Description Defines the boundary degrees-of-freedom of a superelement assembly for matrix reduction. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

ASET

G1

C1

G2

C2

G3

C3

G4

C4

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

ASET

564

4

765

4561

8

5

Field

Contents

Gi

Grid or scalar point identification numbers.

(8)

(9)

(10)

No default (Integer > 0) Ci

Component numbers. (Integer zero or blank for scalar points, or up to 6 unique digits (0 < integer < 6) may be placed in the field with no embedded blanks for grid points. The components refer to the coordinate system referenced by the grid points.)

Comments 1.

Refer to the User's Guide section on The Direct Matrix Approach for more information on the use of this card.

2.

A fatal error will be issued if the input contains ASET or ASET1, but PARAM, EXTOUT is not given.

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3.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

4.

This card is represented as a constraint load in HyperMesh.

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ASET1 Bulk Data Entry ASET1 – Boundary Degrees-of-Freedom of a Superelement Assembly, Alternate Form Description Defines the boundary degrees-of-freedom of a superelement assembly for matrix reduction. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

ASET1

C

G1

G2

G3

G4

G5

G6

G7

G8

G9

G10

-etc.-

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

ASET1

123

34

88

4

12

19

7

70

1234

65

(10)

Alternate Format and Example (1)

(2)

(3)

(4)

(5)

ASET1

C

G1

"THRU"

G2

ASET1

123456

88

THRU

207

328

(6)

(7)

(8)

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(9)

(10)

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Field

Contents

C

Component number. (Integer zero or blank for scalar points, or up to 6 unique digits (0 < integer < 6) may be placed in the field with no embedded blanks for grid points. The components refer to the coordinate system referenced by the grid points.)

Gi

Grid or scalar point identification numbers. (Integer > 0, for THRU option, G1 < G2)

Comments 1.

If the alternate format is used, all points in the sequence G1 through G2 are not required to exist, but there must be at least one boundary degree-of-freedom for the model, or a fatal error will result. Any grids implied in the THRU that do not exist will collectively produce a warning message, but will otherwise be ignored.

2.

Refer to the User's Guide section on The Direct Matrix Approach for more information on the use of this card.

3.

A fatal error will be issued if the input contains ASET or ASET1, but PARAM, EXTOUT is not given.

4.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or MIXED, it is allowed that when grid lists are provided for a given component, that the grid references be either scalar points (SPOINT) or structural grid points (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When SPSYNTAX is set to STRICT it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid references are to scalar points (SPOINT), and that the component be > 1 when the grid references are to structural grid points (GRID). When the component is greater than 1, the grid references must always be a structural grid (GRID).

5.

This card is represented as a constraint load in HyperMesh.

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BEAD The BEAD bulk data entry will no longer be supported for the definition of topography optimization. All definitions must be provided using the DTPG bulk data entry. HyperMesh will continue to read BEAD entries, but will convert them into DTPG entries. Information regarding the BEAD entry can be found in the Previously Supported Input section of the Reference Guide.

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BEGIN Bulk Data Entry BEGIN – Indicates the beginning of data input for a specific entity. Description The BEGIN bulk data entry indicates the beginning of data that is used to describe a specific entity (or entities) for inclusion in a model. The BEGIN entry is used in conjunction with the END entry to define the data required for a specific entity. Format (1)

(2)

(3)

(4)

BEGIN

TYPE

NAME

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

BEGIN

FEMODEL

Bumper

(1)

(2)

(3)

(4)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(5)

(6)

(7)

(8)

(9)

(10)

BEGIN HYPRBEAM Square

Field

Contents

TYPE

Specifies the entity type that will be defined by the BEGIN data entry (see Comment 2). (HYPRBEAM or FEMODEL)

NAME

This field specifies the name of the entity that is defined by the BEGIN entry (see Comment 2). (Character String)

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Comments 1.

The BEGIN and END bulk data entries are used in conjunction to define an entity within the full model.

2.

TYPE = HYPRBEAM: Data required for the definition of an arbitrary beam section will be specified between the BEGIN and END data entries. TYPE = FEMODEL: In a model containing multiple parts, the parts are included within the full model specifying part data between the BEGIN and END bulk data entries (the INCLUDE entry can also be used for part data referencing). The name of the included part should be specified in the NAME field.

3.

The INCLUDE entry, similar to almost any other bulk data entry, is allowed between BEGIN and END entries. However, BEGIN and END should exist in the same file.

4.

Models are often defined in separate files, and the block (BEGIN – END) contains only INCLUDE entries. It is possible to duplicate a single part by including the same file(s) in different BEGIN-END blocks.

5.

There can be multiple sections of arbitrary beam data; one for each beam section.

6.

An example set of data for the definition of an arbitrary beam section is as follows: BEGIN,HYPRBEAM,SQUARE $ GRIDS,1,0.0,0.0 GRIDS,2,1.0,0.0 GRIDS,3,1.0,1.0 GRIDS,4,0.0,1.0 $ CSEC2,10,100,1,2 CSEC2,20,100,2,3 CSEC2,30,100,3,4 CSEC2,40,100,4,1 $ PSEC,100,1000,0.1 $ END,HYPRBEAM

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BLKHDF Bulk Data Entry BLKHDF – Blank Holder Force for One-Step Stamping Simulation Description Defines the blank holder force in a one-step stamping simulation. Format (1)

(2)

(3)

(4)

(5)

BLKHDF

BHID

MU

FORC E

TOGGLE

(6)

(7)

(8)

(9)

(10)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

BLKHDF

6

0.3

3.0

0.0

Field

Contents

BHID

Blank holder identification number.

(6)

(7)

(8)

No default (Integer > 0) MU

Coefficient of friction. No default (Real > 0.0)

FORCE

Blank holder force. No default (Real)

TOGGLE

Flag assigned based on option (Pressure or Tonnage). 0.0 – Uniform pressure is applied on blank holder. 1.0 – Net force is applied on blank holder.

Comments 1.

This entry is only valid with an @HyperForm statement in the first line of the input file.

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BMFACE Bulk Data Entry BMFACE – Barrier Mesh Face Description Defines quad or tria faces that are in turn used to define a barrier to limit the total deformation for free-shape design regions. Format (1)

(2)

(3)

(4)

(5)

(6)

BMFAC E

BMID

G1

G2

G3

G4

(7)

(8)

(9)

(10)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

BMFAC E

10

8203

8204

8100

(6)

(7)

(8)

Field

Contents

BMID

Barrier mesh identification number. Referenced from a DSHAPE bulk data entry. No default (Integer > 0)

G#

Grid point identification number of connection points. G1, G2, and G3 are required to define tria faces, G4 is required to define quad faces. No default (Integer > 0, all unique)

Comments 1.

334

Grid points used in the definition of BMFACE entries cannot be used to define structural elements.

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BNDFIX Bulk Data Entry BNDFIX – Boundary Degrees-of-Freedom of a Superelement Assembly Description Defines the degrees-of-freedom to be fixed during DMIG generation using CMSMETH card. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

BNDFIX

GID1

IC 1

GID2

IC 2

GID3

IC 3

(8)

(9)

(10)

Example

(1)

(2)

(3)

BNDFIX

1220

12345

(4)

(5)

(6)

Field

Contents

GIDi

Grid of scalar point identification numbers.

(7)

(8)

(9)

(10)

No default (Integer > 0) ICi

Component numbers. No default (Integer > 0)

Comments 1.

BNDFIX and BSET are equivalent.

2.

ASET, BNDFIX and BNDFREE; all three are not allowed in the same deck.

3.

If BNDFREE and ASET are present, the DOFs associated with ASET would be in BNDFIX; except the DOF assigned to BNDFREE.

4.

If BNDFIX and ASET are present, the DOFs associated with ASET would be in BNDFREE; except the DOF assigned to BNDFIX.

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BNDFIX1 Bulk Data Entry BNDFIX1 – Fixed Boundary Degrees-of-Freedom of a Superelement Assembly Description Defines the fixed (B-set) degrees-of-freedom to be fixed during DMIG generation using CMSMETH card. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

BNDFIX1

C

GID1

GID2

GID3

GID4

"thru"

GID6

GID7

GID8

GID9

etc.

Example

(1)

(2)

(3)

(4)

(5)

(6)

BNDFIX1

12345

1220

1221

THRU

1229

Field

Contents

C

Component numbers.

(7)

(8)

(9)

(10)

No default (Integer > 0 or blank). Zero or blank for SPOINT and any unique combination of integers 1 through 6 for grid points with no embedded blanks. GIDi

Grid of scalar point identification numbers. No default (Integer > 0)

THRU

336

Keyword to allow a range of GID. THRU can be in any field.

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Comments 1.

BNDFIX1 and BSET1 are equivalent.

2.

The combination of the three ASET/ASET1, BNDFIX/BNDFIX1 and BNDFREE/BNDFRE1 are not allowed together in the same input data.

3.

If BNDFREE/BNDFRE1 and ASET/ASET1 are present, the DOFs associated with ASET will be in the B-set; except the DOF assigned to BNDFREE which will be in the C-set.

4.

If BNDFIX/BNDFIX1 and ASET/ASET1 are present, the DOFs associated with ASET would be in C-set; except the DOF assigned to BNDFIX which will be in the B-set.

5.

Multiple “thru” sequences can be used on a single card, and can span across continuation lines.

6.

If the "thru" comment is used, G1 and G2 must exist, but the grid points between G1 and G2 are not required to exist.

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BNDFRE1 Bulk Data Entry BNDFRE1 – Free Boundary Degrees-of-Freedom of a Superelement Assembly Description Defines the free (C-set) degrees-of-freedom to be fixed during DMIG generation using CMSMETH card. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

BNDFRE1

C

GID1

GID2

GID3

GID4

"thru"

GID6

GID7

GID8

GID9

etc.

(7)

(8)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

BNDFRE 1

12345

1220

1221

thru

1229

Field

Contents

C

Component numbers.

(9)

(10)

No default (Integer > 0 or blank). Zero or blank for SPOINT and any unique combination of integers 1 through 6 for grid points with no embedded blanks. GIDi

Grid of scalar point identification numbers. No default (Integer > 0)

THRU

338

Keyword to allow a range of GID. THRU can be in any field.

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Altair Engineering

Comments 1.

BNDFRE1 and CSET1 are equivalent.

2.

The combination of the three ASET/ASET1, BNDFIX/BNDFIX1, and BNDFREE/BNDFRE1 are not allowed together in the same input data.

3.

If BNDFREE/BNDFRE1 and ASET/ASET1 are present, the DOFs associated with ASET will be in the B-set; except the DOF assigned to BNDFREE which will be in the C-set.

4.

If BNDFIX/BNDFIX1 and ASET/ASET1 are present, the DOFs associated with ASET would be in C-set; except the DOF assigned to BNDFIX which will be in the B-set. Any number of continuations may appear.

5.

Multiple “thru” sequences can be used on a single card, and can span across continuation lines.

6.

If the "thru" comment is used, G1 and G2 must exist, but the grid points between G1 and G2 are not required to exist.

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BNDFREE Bulk Data Entry BNDFREE – Boundary Degrees-of-Freedom of a Superelement Assembly Description Defines the degrees-of-freedom to be fixed during DMIG generation using CMSMETH card. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

BNDFREE

GID1

IC 1

GID2

IC 2

GID3

IC 3

(8)

(9)

(10)

Example

(1)

(2)

(3)

BNDFREE

1220

12345

(4)

(5)

(6)

Field

Contents

GIDi

Grid of scalar point identification numbers.

(7)

(8)

(9)

(10)

No default (Integer > 0) ICi

Component numbers. No default (Integer > 0)

Comments 1.

BNDFREE and CSET are equivalent.

2.

ASET, BNDFIX and BNDFREE are not allowed in the same deck.

3.

If BNDFREE and ASET are present, the DOFs associated with ASET would be in BNDFIX; except the DOF assigned to BNDFREE.

4.

If BNDFIX and ASET are present, the DOFs associated with ASET would be in BNDFREE; except the DOF assigned to BNDFIX.

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BSET Bulk Data Entry BSET – Boundary Degrees-of-Freedom of a Superelement Assembly Description BSET entry is equivalent to BNDFIX. Refer to the documentation for the BNDFIX Bulk Data Entry.

Altair Engineering

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BSET1 Bulk Data Entry BSET1– Fixed Boundary Degrees-of-Freedom of a Superelement Assembly Description BSET1 entry is equivalent to BNDFIX1. Refer to the documentation for the BNDFIX1 Bulk Data Entry.

342

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CAABSF Bulk Data Entry CAABSF – Frequency-dependant Fluid Acoustic Absorber Element Description Defines the frequency-dependant fluid acoustic absorber element in coupled fluid-structural analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

C AABSF

EID

PID

G1

G2

G3

G4

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

C AABSF

71

4

1

10

5

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PAABSF property entry. No default (Integer > 0)

Gi

Grid point identification numbers of fluid connection points. Default = blank (Integer > 0 or blank)

Input File - mdcaabsf.parm

Altair Engineering

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$$ $$ Optistruct Input Deck Generated by HyperMesh Version : 10.0build60 $$ Generated using HyperMesh-Optistruct Template Version : 10.0-SA1-120 $$ $$ Template: optistruct $$ $$ $ DISPLACEMENT(PHASE) = 1 OUTPUT,HGFREQ,ALL OUTPUT,OPTI,ALL OUTPUT,H3D,ALL OUTPUT,PUNCH,ALL $$------------------------------------------------------------------------------$ $$ Case Control Cards $ $$------------------------------------------------------------------------------$ $ $HMNAME LOADSTEP 1"Piston_Load" 6 $ SUBCASE 1 LABEL Piston_Load SPC = 12 METHOD(STRUCTURE) = 4 METHOD(FLUID) = 5 FREQUENCY = 3 DLOAD = 9 XYPUNCH DISP 1/ 11(T1) XYPUNCH DISP 1/ 43(T1) XYPUNCH DISP 1/ 55(T1) XYPUNCH DISP 1/ 67(T1) XYPUNCH DISP 1/ 79(T1) XYPUNCH DISP 1/ 91(T1) XYPUNCH DISP 1/ 103(T1) XYPUNCH DISP 1/ 115(T1) XYPUNCH DISP 1/ 127(T1) XYPUNCH DISP 1/ 139(T1) XYPUNCH DISP 1/ 151(T1) XYPUNCH DISP 1/ 163(T1) XYPUNCH DISP 1/ 175(T1) XYPUNCH DISP 1/ 187(T1) XYPUNCH DISP 1/ 199(T1) XYPUNCH DISP 1/ 531(T1) XYPUNCH DISP 1/ 543(T1) XYPUNCH DISP 1/ 555(T1) XYPUNCH DISP 1/ 567(T1) XYPUNCH DISP 1/ 579(T1) XYPUNCH DISP 1/ 591(T1) XYPUNCH DISP 1/ 603(T1) XYPUNCH DISP 1/ 615(T1) XYPUNCH DISP 1/ 627(T1) XYPUNCH DISP 1/ 639(T1) XYPUNCH DISP 1/ 651(T1) XYPUNCH DISP 1/ 663(T1) XYPUNCH DISP 1/ 675(T1) XYPUNCH DISP 1/ 687(T1) $ $HMSET 1 1 "pressure" SET 1 = 43,55,67,79,91,103,115, 127,139,151,163,175,187,199, 531,543,555,567,579,591,603, 615,627,639,651,663,675,687, 6798 $ $$-------------------------------------------------------------$$ HYPERMESH TAGS $$-------------------------------------------------------------$$BEGIN TAGS $$END TAGS

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$ BEGIN BULK ACMODL $$ $$ Stacking Information for Ply-Based Composite Definition $$ PARAM,AUTOSPC,YES PARAM,POST,-1 $$ $$ DESVARG Data $$ $$ $$ GRID Data $$ GRID 9 GRID 10 GRID 11 GRID 12 GRID 13 GRID 14 GRID 15 GRID 16 GRID 17 GRID 18 GRID 19 GRID 20 GRID 21 GRID 22 GRID 23 GRID 24 GRID 25 GRID 26 GRID 27 GRID 28 GRID 29 GRID 30 GRID 31 GRID 32 GRID 33 GRID 34 GRID 35 GRID 36 GRID 37 GRID 38 GRID 39 GRID 40 GRID 41 GRID 42 GRID 43 GRID 44 GRID 45 GRID 46 GRID 47 GRID 48 GRID 49 GRID 50 GRID 51 GRID 52 GRID 53 GRID 54 GRID 55 GRID 56 GRID 57 GRID 58 GRID 59 GRID 60 GRID 61 GRID 62

Altair Engineering

0.492 0.0 -1.72-15 0.246 0.0 -8.59-16 0.0 0.0 0.0 -0.246 0.0 8.589-16 -0.492 0.0 1.718-15 -0.492 0.246 1.718-15 -0.492 0.492 1.718-15 -0.246 0.492 8.589-16 0.0 0.492 0.0 0.246 0.492 -8.59-16 0.492 0.492 -1.72-15 0.492 0.246 -1.72-15 0.0 0.246 0.0 -0.246 0.246 8.589-16 0.246 0.246 -8.59-16 0.492 -0.246 -1.72-15 0.492 -0.492 -1.72-15 0.246 -0.492 -8.59-16 0.0 -0.492 0.0 -0.246 -0.492 8.589-16 -0.492 -0.492 1.718-15 -0.492 -0.246 1.718-15 0.0 -0.246 0.0 0.246 -0.246 -8.59-16 -0.246 -0.246 8.589-16 0.246 5.049-29-.300073 -5.99-130.0 -.300073 -5.62-130.246 -.300073 0.246 0.246 -.300073 0.246 2.524-29-.600146 -1.2-12 0.0 -.600146 -1.12-120.246 -.600146 0.246 0.246 -.600146 0.246 2.919-29-0.90022 -1.79-120.0 -.900219 -1.68-120.246 -.900219 0.246 0.246 -0.90022 0.246 3.787-29-1.20029 -2.39-120.0 -1.20029 -2.24-120.246 -1.20029 0.246 0.246 -1.20029 0.246 4.733-29-1.50037 -3.0-12 0.0 -1.50037 -2.81-120.246 -1.50037 0.246 0.246 -1.50037 0.246 5.364-29-1.80044 -3.6-12 0.0 -1.80044 -3.37-120.246 -1.80044 0.246 0.246 -1.80044 0.246 6.311-29-2.10051 -4.2-12 0.0 -2.10051 -3.93-120.246 -2.10051 0.246 0.246 -2.10051 0.246 7.258-29-2.40059

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

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GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

346

63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131

-4.79-120.0 -2.40059 -4.49-120.246 -2.40059 0.246 0.246 -2.40059 0.246 8.204-29-2.70066 -5.39-120.0 -2.70066 -5.06-120.246 -2.70066 0.246 0.246 -2.70066 0.246 8.835-29-3.00073 -5.99-120.0 -3.00073 -5.62-120.246 -3.00073 0.246 0.246 -3.00073 0.246 9.782-29-3.30081 -6.59-120.0 -3.30081 -6.18-120.246 -3.30081 0.246 0.246 -3.30081 0.246 1.073-28-3.60088 -7.19-120.0 -3.60088 -6.74-120.246 -3.60088 0.246 0.246 -3.60088 0.246 1.136-28-3.90095 -7.78-120.0 -3.90095 -7.3-12 0.246 -3.90095 0.246 0.246 -3.90095 0.246 1.231-28-4.20102 -8.38-120.0 -4.20102 -7.86-120.246 -4.20102 0.246 0.246 -4.20102 0.246 1.294-28-4.5011 -8.99-120.0 -4.5011 -8.43-120.246 -4.5011 0.246 0.246 -4.5011 0.246 1.388-28-4.80117 -9.59-120.0 -4.80117 -8.99-120.246 -4.80117 0.246 0.246 -4.80117 0.246 1.452-28-5.10124 -1.02-110.0 -5.10124 -9.55-120.246 -5.10124 0.246 0.246 -5.10124 0.246 1.515-28-5.40132 -1.08-110.0 -5.40132 -1.01-110.246 -5.40132 0.246 0.246 -5.40132 0.246 1.609-28-5.70139 -1.14-110.0 -5.70139 -1.07-110.246 -5.70139 0.246 0.246 -5.70139 0.246 1.672-28-6.00146 -1.2-11 0.0 -6.00146 -1.12-110.246 -6.00146 0.246 0.246 -6.00146 0.246 1.735-28-6.30154 -1.26-110.0 -6.30154 -1.18-110.246 -6.30154 0.246 0.246 -6.30154 0.246 1.83-28 -6.60161 -1.32-110.0 -6.60161 -1.23-110.246 -6.60161 0.246 0.246 -6.60161 0.246 1.893-28-6.90168 -1.38-110.0 -6.90168 -1.29-110.246 -6.90168 0.246 0.246 -6.90168 0.246 1.956-28-7.20176 -1.44-110.0 -7.20176 -1.35-110.246 -7.20176 0.246 0.246 -7.20176 0.246 2.019-28-7.50183 -1.5-11 0.0 -7.50183

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161 162 163 164 165 166 167 168 169 170 171 172 173 174 175 176 177 178 179 180 181 182 183 184 185 186 187 188 189 190 191 192 193 194 195 196 197 198 199 200

Altair Engineering

-1.4-11 0.246 -7.50183 0.246 0.246 -7.50183 0.246 2.083-28-7.8019 -1.55-110.0 -7.8019 -1.46-110.246 -7.8019 0.246 0.246 -7.8019 0.246 2.146-28-8.10198 -1.61-110.0 -8.10198 -1.51-110.246 -8.10198 0.246 0.246 -8.10198 0.246 2.209-28-8.40205 -1.67-110.0 -8.40205 -1.57-110.246 -8.40205 0.246 0.246 -8.40205 0.246 2.272-28-8.70212 -1.73-110.0 -8.70212 -1.63-110.246 -8.70212 0.246 0.246 -8.70212 0.246 2.335-28-9.0022 -1.79-110.0 -9.0022 -1.68-110.246 -9.0022 0.246 0.246 -9.0022 0.246 2.398-28-9.30227 -1.85-110.0 -9.30227 -1.74-110.246 -9.30227 0.246 0.246 -9.30227 0.246 2.461-28-9.60234 -1.91-110.0 -9.60234 -1.79-110.246 -9.60234 0.246 0.246 -9.60234 0.246 2.524-28-9.90241 -1.97-110.0 -9.90241 -1.85-110.246 -9.90241 0.246 0.246 -9.90241 0.246 2.556-28-10.2025 -2.03-110.0 -10.2025 -1.91-110.246 -10.2025 0.246 0.246 -10.2025 0.246 2.619-28-10.5026 -2.09-110.0 -10.5026 -1.96-110.246 -10.5026 0.246 0.246 -10.5026 0.246 2.682-28-10.8026 -2.15-110.0 -10.8026 -2.02-110.246 -10.8026 0.246 0.246 -10.8026 0.246 2.745-28-11.1027 -2.21-110.0 -11.1027 -2.07-110.246 -11.1027 0.246 0.246 -11.1027 0.246 2.777-28-11.4028 -2.27-110.0 -11.4028 -2.13-110.246 -11.4028 0.246 0.246 -11.4028 0.246 2.84-28 -11.7029 -2.33-110.0 -11.7029 -2.19-110.246 -11.7029 0.246 0.246 -11.7029 0.246 2.871-28-12.0029 -2.39-110.0 -12.0029 -2.24-110.246 -12.0029 0.246 0.246 -12.0029 0.246 2.935-28-12.303 -2.45-110.0 -12.303 -2.3-11 0.246 -12.303 0.246 0.246 -12.303 0.246 2.966-28-12.6031 -2.51-110.0 -12.6031 -2.35-110.246 -12.6031

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

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GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

348

201 522 523 524 525 526 527 528 529 530 531 532 533 534 535 536 537 538 539 540 541 542 543 544 545 546 547 548 549 550 551 552 553 554 555 556 557 558 559 560 561 562 563 564 565 566 567 568 569 570 571 572 573 574 575 576 577 578 579 580 581 582 583 584 585 586 587 588 589

0.246 0.246 -12.6031 0.246 2.935-28-12.903 -7.36-110.0 -12.903 -6.9-11 0.246 -12.903 0.246 0.246 -12.903 0.246 2.903-28-13.2031 -7.42-110.0 -13.2031 -6.95-110.246 -13.2031 0.246 0.246 -13.2031 0.246 2.84-28 -13.5032 -7.48-110.0 -13.5032 -7.01-110.246 -13.5032 0.246 0.246 -13.5032 0.246 2.777-28-13.8032 -7.54-110.0 -13.8032 -7.06-110.246 -13.8032 0.246 0.246 -13.8032 0.246 2.745-28-14.1033 -7.6-11 0.0 -14.1033 -7.12-110.246 -14.1033 0.246 0.246 -14.1033 0.246 2.682-28-14.4034 -7.67-110.0 -14.4034 -7.19-110.246 -14.4034 0.246 0.246 -14.4034 0.246 2.619-28-14.7034 -7.73-110.0 -14.7034 -7.24-110.246 -14.7034 0.246 0.246 -14.7034 0.246 2.587-28-15.0035 -7.78-110.0 -15.0035 -7.3-11 0.246 -15.0035 0.246 0.246 -15.0035 0.246 2.524-28-15.3036 -7.84-110.0 -15.3036 -7.35-110.246 -15.3036 0.246 0.246 -15.3036 0.246 2.461-28-15.6037 -7.9-11 0.0 -15.6037 -7.41-110.246 -15.6037 0.246 0.246 -15.6037 0.246 2.398-28-15.9037 -7.96-110.0 -15.9037 -7.47-110.246 -15.9037 0.246 0.246 -15.9037 0.246 2.335-28-16.2038 -8.02-110.0 -16.2038 -7.52-110.246 -16.2038 0.246 0.246 -16.2038 0.246 2.272-28-16.5039 -8.08-110.0 -16.5039 -7.58-110.246 -16.5039 0.246 0.246 -16.5039 0.246 2.209-28-16.804 -8.14-110.0 -16.804 -7.63-110.246 -16.804 0.246 0.246 -16.804 0.246 2.146-28-17.104 -8.2-11 0.0 -17.104 -7.69-110.246 -17.104 0.246 0.246 -17.104 0.246 2.083-28-17.4041 -8.26-110.0 -17.4041 -7.75-110.246 -17.4041 0.246 0.246 -17.4041 0.246 2.019-28-17.7042 -8.32-110.0 -17.7042 -7.8-11 0.246 -17.7042 0.246 0.246 -17.7042

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

590 591 592 593 594 595 596 597 598 599 600 601 602 603 604 605 606 607 608 609 610 611 612 613 614 615 616 617 618 619 620 621 622 623 624 625 626 627 628 629 630 631 632 633 634 635 636 637 638 639 640 641 642 643 644 645 646 647 648 649 650 651 652 653 654 655 656 657 658

Altair Engineering

0.246 1.956-28-18.0042 -8.38-110.0 -18.0042 -7.86-110.246 -18.0042 0.246 0.246 -18.0042 0.246 1.893-28-18.3043 -8.44-110.0 -18.3043 -7.91-110.246 -18.3043 0.246 0.246 -18.3043 0.246 1.83-28 -18.6044 -8.5-11 0.0 -18.6044 -7.97-110.246 -18.6044 0.246 0.246 -18.6044 0.246 1.735-28-18.9045 -8.56-110.0 -18.9045 -8.03-110.246 -18.9045 0.246 0.246 -18.9045 0.246 1.672-28-19.2045 -8.62-110.0 -19.2045 -8.08-110.246 -19.2045 0.246 0.246 -19.2045 0.246 1.609-28-19.5046 -8.68-110.0 -19.5046 -8.14-110.246 -19.5046 0.246 0.246 -19.5046 0.246 1.515-28-19.8047 -8.74-110.0 -19.8047 -8.19-110.246 -19.8047 0.246 0.246 -19.8047 0.246 1.452-28-20.1048 -8.8-11 0.0 -20.1048 -8.25-110.246 -20.1048 0.246 0.246 -20.1048 0.246 1.388-28-20.4048 -8.86-110.0 -20.4048 -8.31-110.246 -20.4048 0.246 0.246 -20.4048 0.246 1.294-28-20.7049 -8.92-110.0 -20.7049 -8.36-110.246 -20.7049 0.246 0.246 -20.7049 0.246 1.231-28-21.005 -8.98-110.0 -21.005 -8.42-110.246 -21.005 0.246 0.246 -21.005 0.246 1.136-28-21.3051 -9.04-110.0 -21.3051 -8.47-110.246 -21.3051 0.246 0.246 -21.3051 0.246 1.073-28-21.6051 -9.1-11 0.0 -21.6051 -8.53-110.246 -21.6051 0.246 0.246 -21.6051 0.246 9.782-29-21.9052 -9.16-110.0 -21.9052 -8.59-110.246 -21.9052 0.246 0.246 -21.9052 0.246 8.835-29-22.2053 -9.22-110.0 -22.2053 -8.64-110.246 -22.2053 0.246 0.246 -22.2053 0.246 8.204-29-22.5053 -9.28-110.0 -22.5053 -8.7-11 0.246 -22.5053 0.246 0.246 -22.5053 0.246 7.258-29-22.8054 -9.34-110.0 -22.8054 -8.75-110.246 -22.8054 0.246 0.246 -22.8054 0.246 6.311-29-23.1055

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

349

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

350

659 660 661 662 663 664 665 666 667 668 669 670 671 672 673 674 675 676 677 678 679 680 681 682 683 684 685 686 687 688 689 690 691 692 693 694 695 696 697 698 699 700 701 702 703 704 705 706 707 708 709 710 711 712 713 714 715 716 717 718 719 720 721 722 723 724 725 726 727

-9.4-11 0.0 -23.1055 -8.81-110.246 -23.1055 0.246 0.246 -23.1055 0.246 5.364-29-23.4056 -9.46-110.0 -23.4056 -8.87-110.246 -23.4056 0.246 0.246 -23.4056 0.246 4.733-29-23.7056 -9.52-110.0 -23.7056 -8.92-110.246 -23.7056 0.246 0.246 -23.7056 0.246 3.787-29-24.0057 -9.58-110.0 -24.0057 -8.98-110.246 -24.0057 0.246 0.246 -24.0057 0.246 2.84-29 -24.3058 -9.64-110.0 -24.3058 -9.04-110.246 -24.3058 0.246 0.246 -24.3058 0.246 1.893-29-24.6059 -9.7-11 0.0 -24.6059 -9.09-110.246 -24.6059 0.246 0.246 -24.6059 0.246 9.466-30-24.9059 -9.76-110.0 -24.9059 -9.15-110.246 -24.9059 0.246 0.246 -24.9059 0.246 4.151-12-25.206 -9.82-112.767-12-25.206 -9.16-110.246 -25.206 0.246 0.246 -25.206 0.492 4.323-13-.300073 0.492 0.246 -.300073 0.492 1.621-13-.600146 0.492 0.246 -.600146 0.492 1.592-13-0.90022 0.492 0.246 -0.90022 0.492 2.009-13-1.20029 0.492 0.246 -1.20029 0.492 2.5-13 -1.50037 0.492 0.246 -1.50037 0.492 3.004-13-1.80044 0.492 0.246 -1.80044 0.492 3.51-13 -2.10051 0.492 0.246 -2.10051 0.492 4.016-13-2.40059 0.492 0.246 -2.40059 0.492 4.522-13-2.70066 0.492 0.246 -2.70066 0.492 5.028-13-3.00073 0.492 0.246 -3.00073 0.492 5.534-13-3.30081 0.492 0.246 -3.30081 0.492 6.041-13-3.60088 0.492 0.246 -3.60088 0.492 6.547-13-3.90095 0.492 0.246 -3.90095 0.492 7.053-13-4.20102 0.492 0.246 -4.20102 0.492 7.559-13-4.5011 0.492 0.246 -4.5011 0.492 8.066-13-4.80117 0.492 0.246 -4.80117 0.492 8.572-13-5.10124 0.492 0.246 -5.10124 0.492 9.078-13-5.40132 0.492 0.246 -5.40132 0.492 9.584-13-5.70139 0.492 0.246 -5.70139

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

728 729 730 731 732 733 734 735 736 737 738 739 740 741 742 743 744 745 746 747 748 749 750 751 752 753 754 755 756 757 758 759 760 761 762 763 764 765 766 767 768 769 770 771 772 773 934 935 936 937 938 939 940 941 942 943 944 945 946 947 948 949 950 951 952 953 954 955 956

Altair Engineering

0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492

1.009-12-6.00146 0.246 -6.00146 1.06-12 -6.30154 0.246 -6.30154 1.11-12 -6.60161 0.246 -6.60161 1.161-12-6.90168 0.246 -6.90168 1.212-12-7.20176 0.246 -7.20176 1.262-12-7.50183 0.246 -7.50183 1.313-12-7.8019 0.246 -7.8019 1.363-12-8.10198 0.246 -8.10198 1.414-12-8.40205 0.246 -8.40205 1.465-12-8.70212 0.246 -8.70212 1.515-12-9.0022 0.246 -9.0022 1.566-12-9.30227 0.246 -9.30227 1.616-12-9.60234 0.246 -9.60234 1.667-12-9.90242 0.246 -9.90242 1.718-12-10.2025 0.246 -10.2025 1.768-12-10.5026 0.246 -10.5026 1.819-12-10.8026 0.246 -10.8026 1.87-12 -11.1027 0.246 -11.1027 1.92-12 -11.4028 0.246 -11.4028 1.971-12-11.7029 0.246 -11.7029 2.021-12-12.0029 0.246 -12.0029 2.072-12-12.303 0.246 -12.303 2.123-12-12.6031 0.246 -12.6031 6.223-12-12.903 0.246 -12.903 6.274-12-13.2031 0.246 -13.2031 6.324-12-13.5032 0.246 -13.5032 6.375-12-13.8032 0.246 -13.8032 6.425-12-14.1033 0.246 -14.1033 6.476-12-14.4034 0.246 -14.4034 6.527-12-14.7034 0.246 -14.7034 6.577-12-15.0035 0.246 -15.0035 6.628-12-15.3036 0.246 -15.3036 6.679-12-15.6037 0.246 -15.6037 6.729-12-15.9037 0.246 -15.9037 6.78-12 -16.2038

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

351

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

352

957 958 959 960 961 962 963 964 965 966 967 968 969 970 971 972 973 974 975 976 977 978 979 980 981 982 983 984 985 986 987 988 989 990 991 992 993 994 995 996 997 998 999 1000 1001 1002 1003 1004 1005 1006 1007 1008 1009 1010 1011 1012 1013 1014 1015 1016 1017 1018 1019 1020 1021 1022 1023 1024 1025

0.492 0.246 -16.2038 0.492 6.83-12 -16.5039 0.492 0.246 -16.5039 0.492 6.881-12-16.804 0.492 0.246 -16.804 0.492 6.932-12-17.104 0.492 0.246 -17.104 0.492 6.982-12-17.4041 0.492 0.246 -17.4041 0.492 7.033-12-17.7042 0.492 0.246 -17.7042 0.492 7.083-12-18.0042 0.492 0.246 -18.0042 0.492 7.134-12-18.3043 0.492 0.246 -18.3043 0.492 7.185-12-18.6044 0.492 0.246 -18.6044 0.492 7.235-12-18.9045 0.492 0.246 -18.9045 0.492 7.286-12-19.2045 0.492 0.246 -19.2045 0.492 7.337-12-19.5046 0.492 0.246 -19.5046 0.492 7.387-12-19.8047 0.492 0.246 -19.8047 0.492 7.438-12-20.1048 0.492 0.246 -20.1048 0.492 7.488-12-20.4048 0.492 0.246 -20.4048 0.492 7.539-12-20.7049 0.492 0.246 -20.7049 0.492 7.59-12 -21.005 0.492 0.246 -21.005 0.492 7.64-12 -21.3051 0.492 0.246 -21.3051 0.492 7.691-12-21.6051 0.492 0.246 -21.6051 0.492 7.742-12-21.9052 0.492 0.246 -21.9052 0.492 7.792-12-22.2053 0.492 0.246 -22.2053 0.492 7.843-12-22.5053 0.492 0.246 -22.5053 0.492 7.893-12-22.8054 0.492 0.246 -22.8054 0.492 7.944-12-23.1055 0.492 0.246 -23.1055 0.492 7.995-12-23.4056 0.492 0.246 -23.4056 0.492 8.045-12-23.7056 0.492 0.246 -23.7056 0.492 8.096-12-24.0057 0.492 0.246 -24.0057 0.492 8.146-12-24.3058 0.492 0.246 -24.3058 0.492 8.197-12-24.6059 0.492 0.246 -24.6059 0.492 8.248-12-24.9059 0.492 0.246 -24.9059 0.492 5.534-12-25.206 0.492 0.246 -25.206 -5.24-130.492 -.300073 0.246 0.492 -.300073 -1.05-120.492 -.600146 0.246 0.492 -.600146 -1.57-120.492 -.900219 0.246 0.492 -0.90022 -2.09-120.492 -1.20029 0.246 0.492 -1.20029

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1026 1027 1028 1029 1030 1031 1032 1033 1034 1035 1036 1037 1038 1039 1040 1041 1042 1043 1044 1045 1046 1047 1048 1049 1050 1051 1052 1053 1054 1055 1056 1057 1058 1059 1060 1061 1062 1063 1064 1065 1066 1067 1068 1069 1070 1071 1072 1073 1074 1075 1076 1077 1078 1079 1080 1081 1082 1083 1084 1085 1086 1087 1088 1089 1090 1091 1092 1093 1094

Altair Engineering

-2.63-120.492 0.246 0.492 -3.15-120.492 0.246 0.492 -3.67-120.492 0.246 0.492 -4.19-120.492 0.246 0.492 -4.72-120.492 0.246 0.492 -5.24-120.492 0.246 0.492 -5.76-120.492 0.246 0.492 -6.29-120.492 0.246 0.492 -6.81-120.492 0.246 0.492 -7.33-120.492 0.246 0.492 -7.87-120.492 0.246 0.492 -8.39-120.492 0.246 0.492 -8.91-120.492 0.246 0.492 -9.44-120.492 0.246 0.492 -9.96-120.492 0.246 0.492 -1.05-110.492 0.246 0.492 -1.1-11 0.492 0.246 0.492 -1.15-110.492 0.246 0.492 -1.2-11 0.492 0.246 0.492 -1.26-110.492 0.246 0.492 -1.31-110.492 0.246 0.492 -1.36-110.492 0.246 0.492 -1.41-110.492 0.246 0.492 -1.46-110.492 0.246 0.492 -1.52-110.492 0.246 0.492 -1.57-110.492 0.246 0.492 -1.62-110.492 0.246 0.492 -1.67-110.492 0.246 0.492 -1.73-110.492 0.246 0.492 -1.78-110.492 0.246 0.492 -1.83-110.492 0.246 0.492 -1.88-110.492 0.246 0.492 -1.94-110.492 0.246 0.492 -1.99-110.492 0.246 0.492 -2.04-110.492

-1.50037 -1.50037 -1.80044 -1.80044 -2.10051 -2.10051 -2.40059 -2.40059 -2.70066 -2.70066 -3.00073 -3.00073 -3.30081 -3.30081 -3.60088 -3.60088 -3.90095 -3.90095 -4.20102 -4.20102 -4.5011 -4.5011 -4.80117 -4.80117 -5.10124 -5.10124 -5.40132 -5.40132 -5.70139 -5.70139 -6.00146 -6.00146 -6.30154 -6.30154 -6.60161 -6.60161 -6.90168 -6.90168 -7.20176 -7.20176 -7.50183 -7.50183 -7.8019 -7.8019 -8.10198 -8.10198 -8.40205 -8.40205 -8.70212 -8.70212 -9.0022 -9.0022 -9.30227 -9.30227 -9.60234 -9.60234 -9.90241 -9.90241 -10.2025 -10.2025 -10.5026 -10.5026 -10.8026 -10.8026 -11.1027 -11.1027 -11.4028 -11.4028 -11.7029

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

353

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

354

1095 1096 1097 1098 1099 1100 1101 1262 1263 1264 1265 1266 1267 1268 1269 1270 1271 1272 1273 1274 1275 1276 1277 1278 1279 1280 1281 1282 1283 1284 1285 1286 1287 1288 1289 1290 1291 1292 1293 1294 1295 1296 1297 1298 1299 1300 1301 1302 1303 1304 1305 1306 1307 1308 1309 1310 1311 1312 1313 1314 1315 1316 1317 1318 1319 1320 1321 1322 1323

0.246 0.492 -2.09-110.492 0.246 0.492 -2.14-110.492 0.246 0.492 -2.2-11 0.492 0.246 0.492 -6.43-110.492 0.246 0.492 -6.49-110.492 0.246 0.492 -6.54-110.492 0.246 0.492 -6.59-110.492 0.246 0.492 -6.64-110.492 0.246 0.492 -6.71-110.492 0.246 0.492 -6.76-110.492 0.246 0.492 -6.81-110.492 0.246 0.492 -6.86-110.492 0.246 0.492 -6.91-110.492 0.246 0.492 -6.97-110.492 0.246 0.492 -7.02-110.492 0.246 0.492 -7.07-110.492 0.246 0.492 -7.12-110.492 0.246 0.492 -7.18-110.492 0.246 0.492 -7.23-110.492 0.246 0.492 -7.28-110.492 0.246 0.492 -7.33-110.492 0.246 0.492 -7.39-110.492 0.246 0.492 -7.44-110.492 0.246 0.492 -7.49-110.492 0.246 0.492 -7.54-110.492 0.246 0.492 -7.59-110.492 0.246 0.492 -7.65-110.492 0.246 0.492 -7.7-11 0.492 0.246 0.492 -7.75-110.492 0.246 0.492 -7.8-11 0.492 0.246 0.492 -7.86-110.492 0.246 0.492 -7.91-110.492 0.246 0.492 -7.96-110.492 0.246 0.492 -8.01-110.492 0.246 0.492

-11.7029 -12.0029 -12.0029 -12.303 -12.303 -12.6031 -12.6031 -12.903 -12.903 -13.2031 -13.2031 -13.5032 -13.5032 -13.8032 -13.8032 -14.1033 -14.1033 -14.4034 -14.4034 -14.7034 -14.7034 -15.0035 -15.0035 -15.3036 -15.3036 -15.6037 -15.6037 -15.9037 -15.9037 -16.2038 -16.2038 -16.5039 -16.5039 -16.804 -16.804 -17.104 -17.104 -17.4041 -17.4041 -17.7042 -17.7042 -18.0042 -18.0042 -18.3043 -18.3043 -18.6044 -18.6044 -18.9045 -18.9045 -19.2045 -19.2045 -19.5046 -19.5046 -19.8047 -19.8047 -20.1048 -20.1048 -20.4048 -20.4048 -20.7049 -20.7049 -21.005 -21.005 -21.3051 -21.3051 -21.6051 -21.6051 -21.9052 -21.9052

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1324 1325 1326 1327 1328 1329 1330 1331 1332 1333 1334 1335 1336 1337 1338 1339 1340 1341 1342 1343 1344 1345 1346 1347 1348 1349 1350 1351 1352 1353 1354 1355 1356 1357 1358 1359 1360 1361 1362 1363 1364 1365 1366 1367 1368 1369 1370 1371 1372 1373 1374 1375 1376 1377 1378 1379 1380 1381 1382 1383 1384 1385 1386 1387 1468 1469 1470 1471 1472

Altair Engineering

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

356

1473 1474 1475 1476 1477 1478 1479 1480 1481 1482 1483 1484 1485 1486 1487 1488 1489 1490 1491 1492 1493 1494 1495 1496 1497 1498 1499 1500 1501 1502 1503 1504 1505 1506 1507 1508 1509 1510 1511 1512 1513 1514 1515 1516 1517 1518 1519 1520 1521 1522 1523 1524 1525 1526 1527 1528 1529 1530 1531 1532 1533 1534 1535 1536 1537 1538 1539 1540 1541

0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1542 1543 1544 1545 1546 1547 1548 1549 1550 1551 1552 1553 1554 1555 1556 1557 1558 1559 1560 1561 1562 1563 1564 1565 1566 1567 1568 1569 1570 1571 1572 1573 1574 1575 1576 1577 1578 1579 1580 1581 1582 1583 1584 1585 1586 1587 1588 1589 1590 1591 1592 1593 1594 1595 1596 1597 1598 1599 1600 1601 1602 1603 1604 1605 1606 1607 1608 1609 1610

Altair Engineering

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-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

358

1611 1612 1613 1614 1615 1616 1617 1618 1619 1620 1621 1622 1623 1624 1625 1626 1627 1628 1629 1630 1631 1632 1633 1634 1635 1636 1637 1638 1639 1640 1641 1642 1643 1644 1645 1646 1647 1648 1649 1650 1651 1652 1653 1654 1655 1656 1657 1658 1659 1660 1661 1662 1663 1664 1665 1666 1667 1668 1669 1670 1671 1672 1673 1674 1675 1676 1677 1998 1999

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3.113-27-7.8019 0.246 -7.8019 0.246 -7.8019 0.0 -8.10198 3.067-27-8.10198 0.246 -8.10198 0.246 -8.10198 0.0 -8.40205 2.979-27-8.40205 0.246 -8.40205 0.246 -8.40205 0.0 -8.70212 3.233-27-8.70212 0.246 -8.70212 0.246 -8.70212 0.0 -9.0022 3.323-27-9.00219 0.246 -9.00219 0.246 -9.0022 0.0 -9.30227 3.67-27 -9.30227 0.246 -9.30227 0.246 -9.30227 0.0 -9.60234 3.58-27 -9.60234 0.246 -9.60234 0.246 -9.60234 0.0 -9.90241 3.454-27-9.90241 0.246 -9.90241 0.246 -9.90241 0.0 -10.2025 3.782-27-10.2025 0.246 -10.2025 0.246 -10.2025 0.0 -10.5026 3.659-27-10.5026 0.246 -10.5026 0.246 -10.5026 0.0 -10.8026 4.003-27-10.8026 0.246 -10.8026 0.246 -10.8026 0.0 -11.1027 4.154-27-11.1027 0.246 -11.1027 0.246 -11.1027 0.0 -11.4028 4.274-27-11.4028 0.246 -11.4028 0.246 -11.4028 0.0 -11.7029 4.388-27-11.7028 0.246 -11.7028 0.246 -11.7029 0.0 -12.0029 4.5-27 -12.0029 0.246 -12.0029 0.246 -12.0029 0.0 -12.303 4.358-27-12.303 0.246 -12.303 0.246 -12.303 0.0 -12.6031 4.424-27-12.6031 0.246 -12.6031 0.246 -12.6031 0.0 -12.903 1.381-26-12.903

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022 2023 2024 2025 2026 2027 2028 2029 2030 2031 2032 2033 2034 2035 2036 2037 2038 2039 2040 2041 2042 2043 2044 2045 2046 2047 2048 2049 2050 2051 2052 2053 2054 2055 2056 2057 2058 2059 2060 2061 2062 2063 2064 2065 2066 2067 2068

Altair Engineering

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-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

359

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

360

2069 2070 2071 2072 2073 2074 2075 2076 2077 2078 2079 2080 2081 2082 2083 2084 2085 2086 2087 2088 2089 2090 2091 2092 2093 2094 2095 2096 2097 2098 2099 2100 2101 2102 2103 2104 2105 2106 2107 2108 2109 2110 2111 2112 2113 2114 2115 2116 2117 2118 2119 2120 2121 2122 2123 2124 2125 2126 2127 2128 2129 2130 2131 2132 2133 2134 2135 2136 2137

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0.246 -18.0042 0.0 -18.3043 1.477-26-18.3043 0.246 -18.3043 0.246 -18.3043 0.0 -18.6044 1.58-26 -18.6044 0.246 -18.6044 0.246 -18.6044 0.0 -18.9045 1.606-26-18.9045 0.246 -18.9045 0.246 -18.9045 0.0 -19.2045 1.62-26 -19.2045 0.246 -19.2045 0.246 -19.2045 0.0 -19.5046 1.632-26-19.5046 0.246 -19.5046 0.246 -19.5046 0.0 -19.8047 1.643-26-19.8047 0.246 -19.8047 0.246 -19.8047 0.0 -20.1048 1.655-26-20.1048 0.246 -20.1048 0.246 -20.1048 0.0 -20.4048 1.666-26-20.4048 0.246 -20.4048 0.246 -20.4048 0.0 -20.7049 1.677-26-20.7049 0.246 -20.7049 0.246 -20.7049 0.0 -21.005 1.572-26-21.005 0.246 -21.005 0.246 -21.005 0.0 -21.3051 1.68-26 -21.3051 0.246 -21.3051 0.246 -21.3051 0.0 -21.6051 1.708-26-21.6051 0.246 -21.6051 0.246 -21.6051 0.0 -21.9052 1.722-26-21.9052 0.246 -21.9052 0.246 -21.9052 0.0 -22.2053 1.733-26-22.2053 0.246 -22.2053 0.246 -22.2053 0.0 -22.5053 1.745-26-22.5053 0.246 -22.5053 0.246 -22.5053 0.0 -22.8054 1.756-26-22.8054 0.246 -22.8054 0.246 -22.8054 0.0 -23.1055 1.767-26-23.1055 0.246 -23.1055 0.246 -23.1055

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2138 2139 2140 2141 2142 2143 2144 2145 2146 2147 2148 2149 2150 2151 2152 2153 2154 2155 2156 2157 2158 2159 2160 2161 2162 2163 2164 2165 2166 2167 2168 2169 2170 2171 2172 2173 2174 2175 2176 2177 2178 2179 2180 2181 2182 2183 2184 2185 2186 2187 2188 2189 2190 2191 2192 2193 2194 2195 2196 2197 2198 2199 2200 2201 2202 2203 2204 2205 2206

Altair Engineering

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

361

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

362

2207 2208 2209 2210 2211 2212 2213 2214 2215 2216 2217 2218 2219 2220 2221 2222 2223 2224 2225 2226 2227 2228 2229 2230 2231 2232 2233 2234 2235 2236 2237 2238 2239 2240 2241 2242 2243 2244 2245 2246 2247 2248 2249 2410 2411 2412 2413 2414 2415 2416 2417 2418 2419 2420 2421 2422 2423 2424 2425 2426 2427 2428 2429 2430 2431 2432 2433 2434 2435

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2436 2437 2438 2439 2440 2441 2442 2443 2444 2445 2446 2447 2448 2449 2450 2451 2452 2453 2454 2455 2456 2457 2458 2459 2460 2461 2462 2463 2464 2465 2466 2467 2468 2469 2470 2471 2472 2473 2474 2475 2476 2477 2478 2479 2480 2481 2482 2483 2484 2485 2486 2487 2488 2489 2490 2491 2492 2493 2494 2495 2496 2497 2498 2499 2500 2501 2502 2503 2504

Altair Engineering

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

363

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

364

2505 2506 2507 2508 2509 2510 2511 2512 2513 2514 2515 2516 2517 2518 2519 2520 2521 2522 2523 2524 2525 2526 2527 2528 2529 2530 2531 2532 2533 2534 2535 2536 2537 2538 2539 2540 2541 2542 2543 2544 2545 2546 2547 2548 2549 2550 2551 2552 2553 2554 2555 2556 2557 2558 2559 2560 2561 2562 2563 2564 2565 2566 2567 2568 2569 2570 2571 2572 2573

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-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2574 2575 2576 2577 2738 2739 2740 2741 2742 2743 2744 2745 2746 2747 2748 2749 2750 2751 2752 2753 2754 2755 2756 2757 2758 2759 2760 2761 2762 2763 2764 2765 2766 2767 2768 2769 2770 2771 2772 2773 2774 2775 2776 2777 2778 2779 2780 2781 2782 2783 2784 2785 2786 2787 2788 2789 2790 2791 2792 2793 2794 2795 2796 2797 2798 2799 2800 2801 2802

Altair Engineering

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

365

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

366

2803 2804 2805 2806 2807 2808 2809 2810 2811 2812 2813 2814 2815 2816 2817 2818 2819 2820 2821 2822 2823 2824 2825 2826 2827 2828 2829 2830 2831 2832 2833 2834 2835 2836 2837 2838 2839 2840 2841 2842 2843 2844 2845 2846 2847 2848 2849 2850 2851 2852 2853 2854 2855 2856 2857 2858 2859 2860 2861 2862 2863 2944 2945 2946 2947 2948 2949 2950 2951

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2952 2953 2954 2955 2956 2957 2958 2959 2960 2961 2962 2963 2964 2965 2966 2967 2968 2969 2970 2971 2972 2973 2974 2975 2976 2977 2978 2979 2980 2981 2982 2983 2984 2985 2986 2987 2988 2989 2990 2991 2992 2993 2994 2995 2996 2997 2998 2999 3000 3001 3002 3003 3004 3005 3006 3007 3008 3009 3010 3011 3012 3013 3014 3015 3016 3017 3018 3019 3020

Altair Engineering

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

367

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

368

3021 3022 3023 3024 3025 3026 3027 3028 3029 3030 3031 3032 3033 3034 3035 3036 3037 3038 3039 3040 3041 3042 3043 3044 3045 3046 3047 3048 3049 3050 3051 3052 3053 3054 3055 3056 3057 3058 3059 3060 3061 3062 3063 3064 3065 3066 3067 3068 3069 3230 3231 3232 3233 3234 3235 3236 3237 3238 3239 3240 3241 3242 3243 3244 3245 3246 3247 3248 3249

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3250 3251 3252 3253 3254 3255 3256 3257 3258 3259 3260 3261 3262 3263 3264 3265 3266 3267 3268 3269 3270 3271 3272 3273 3274 3275 3276 3277 3278 3279 3280 3281 3282 3283 3284 3285 3286 3287 3288 3289 3290 3291 3292 3293 3294 3295 3296 3297 3298 3299 3300 3301 3302 3303 3304 3305 3306 3307 3308 3309 3310 3311 3312 3313 3314 3315 3316 3317 3318

Altair Engineering

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

369

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

370

3319 3320 3321 3322 3323 3324 3325 3326 3327 3328 3329 3330 3331 3332 3333 3334 3335 3336 3337 3338 3339 3340 3341 3342 3343 3344 3345 3346 3347 3348 3349 3350 3351 3352 3353 3354 3355 3436 3437 3438 3439 3440 3441 3442 3443 3444 3445 3446 3447 3448 3449 3450 3451 3452 3453 3454 3455 3456 3457 3458 3459 3460 3461 3462 3463 3464 3465 3466 3467

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3468 3469 3470 3471 3472 3473 3474 3475 3476 3477 3478 3479 3480 3481 3482 3483 3484 3485 3486 3487 3488 3489 3490 3491 3492 3493 3494 3495 3496 3497 3498 3499 3500 3501 3502 3503 3504 3505 3506 3507 3508 3509 3510 3511 3512 3513 3514 3515 3516 3517 3518 3519 3520 3521 3522 3523 3524 3525 3526 3527 3528 3529 3530 3531 3532 3533 3534 3535 3536

Altair Engineering

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

371

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

372

3537 3538 3539 3540 3541 3542 3543 3544 3545 3546 3547 3548 3549 3550 3551 3552 3553 3554 3555 3556 3557 3558 3559 3560 3561 3722 3723 3724 3725 3726 3727 3728 3729 3730 3731 3732 3733 3734 3735 3736 3737 3738 3739 3740 3741 3742 3743 3744 3745 3746 3747 3748 3749 3750 3751 3752 3753 3754 3755 3756 3757 3758 3759 3760 3761 3762 3763 3764 3765

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OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3766 3767 3768 3769 3770 3771 3772 3773 3774 3775 3776 3777 3778 3779 3780 3781 3782 3783 3784 3785 3786 3787 3788 3789 3790 3791 3792 3793 3794 3795 3796 3797 3798 3799 3800 3801 3802 3803 3804 3805 3806 3807 3808 3809 3810 3811 3812 3813 3814 3815 3816 3817 3818 3819 3820 3821 3822 3823 3824 3825 3826 3827 3828 3829 3830 3831 3832 3833 3834

Altair Engineering

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-0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492

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-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

373

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

374

3835 3836 3837 3838 3839 3840 3841 3842 3843 3844 3845 3846 3847 3848 3849 3850 3851 3852 3853 3854 3855 3856 3857 3858 3859 3860 3861 3862 3863 3864 3865 3866 3867 3868 3869 3870 3871 3872 3873 3874 3875 3876 3877 3878 3879 3880 3881 3882 3883 3884 3885 3886 3887 3888 3889 4050 4051 4052 4053 4054 4055 4056 4057 4058 4059 4060 4061 4062 4063

0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492

-0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492

-4.5011 -4.80117 -4.80117 -5.10124 -5.10124 -5.40132 -5.40132 -5.70139 -5.70139 -6.00146 -6.00146 -6.30154 -6.30154 -6.60161 -6.60161 -6.90168 -6.90168 -7.20176 -7.20176 -7.50183 -7.50183 -7.8019 -7.8019 -8.10198 -8.10198 -8.40205 -8.40205 -8.70212 -8.70212 -9.0022 -9.0022 -9.30227 -9.30227 -9.60234 -9.60234 -9.90241 -9.90242 -10.2025 -10.2025 -10.5026 -10.5026 -10.8026 -10.8026 -11.1027 -11.1027 -11.4028 -11.4028 -11.7029 -11.7029 -12.0029 -12.0029 -12.303 -12.303 -12.6031 -12.6031 -12.903 -12.903 -13.2031 -13.2031 -13.5032 -13.5032 -13.8032 -13.8032 -14.1033 -14.1033 -14.4034 -14.4034 -14.7034 -14.7034

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

4064 4065 4066 4067 4068 4069 4070 4071 4072 4073 4074 4075 4076 4077 4078 4079 4080 4081 4082 4083 4084 4085 4086 4087 4088 4089 4090 4091 4092 4093 4094 4095 4096 4097 4098 4099 4100 4101 4102 4103 4104 4105 4106 4107 4108 4109 4110 4111 4112 4113 4114 4115 4116 4117 4118 4119 4120 4121 4122 4123 4124 4125 4126 4127 4128 4129 4130 4131 4132

Altair Engineering

0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246

-0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492

-15.0035 -15.0035 -15.3036 -15.3036 -15.6037 -15.6037 -15.9037 -15.9037 -16.2038 -16.2038 -16.5039 -16.5039 -16.804 -16.804 -17.104 -17.104 -17.4041 -17.4041 -17.7042 -17.7042 -18.0042 -18.0042 -18.3043 -18.3043 -18.6044 -18.6044 -18.9045 -18.9045 -19.2045 -19.2045 -19.5046 -19.5046 -19.8047 -19.8047 -20.1048 -20.1048 -20.4048 -20.4048 -20.7049 -20.7049 -21.005 -21.005 -21.3051 -21.3051 -21.6051 -21.6051 -21.9052 -21.9052 -22.2053 -22.2053 -22.5053 -22.5053 -22.8054 -22.8054 -23.1055 -23.1055 -23.4056 -23.4056 -23.7056 -23.7056 -24.0057 -24.0057 -24.3058 -24.3058 -24.6059 -24.6059 -24.9059 -24.9059 -25.206

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

375

GRID 4133 0.492 -0.492 -25.206 GRID 6776 -0.246 -0.246 8.589-16 GRID 6777 0.246 -0.246 -8.59-16 GRID 6778 0.0 -0.246 0.0 GRID 6779 -0.492 -0.246 1.718-15 GRID 6780 -0.492 -0.492 1.718-15 GRID 6781 -0.246 -0.492 8.589-16 GRID 6782 0.0 -0.492 0.0 GRID 6783 0.246 -0.492 -8.59-16 GRID 6784 0.492 -0.492 -1.72-15 GRID 6785 0.492 -0.246 -1.72-15 GRID 6786 0.246 0.246 -8.59-16 GRID 6787 -0.246 0.246 8.589-16 GRID 6788 0.0 0.246 0.0 GRID 6789 0.492 0.246 -1.72-15 GRID 6790 0.492 0.492 -1.72-15 GRID 6791 0.246 0.492 -8.59-16 GRID 6792 0.0 0.492 0.0 GRID 6793 -0.246 0.492 8.589-16 GRID 6794 -0.492 0.492 1.718-15 GRID 6795 -0.492 0.246 1.718-15 GRID 6796 -0.492 0.0 1.718-15 GRID 6797 -0.246 0.0 8.589-16 GRID 6798 0.0 0.0 0.0 GRID 6799 0.246 0.0 -8.59-16 GRID 6800 0.492 0.0 -1.72-15 $$ $$ SPOINT Data $$ $ $ CQUAD4 Elements $ CQUAD4 5627 1 6778 6798 6799 CQUAD4 5629 1 6782 6778 6777 CQUAD4 6116 1 6777 6799 6800 CQUAD4 6122 1 6783 6777 6785 CQUAD4 6125 1 6799 6798 6788 CQUAD4 6520 1 6779 6796 6797 CQUAD4 6521 1 6776 6797 6798 CQUAD4 6523 1 6780 6779 6776 CQUAD4 6528 1 6781 6776 6778 CQUAD4 6954 1 6797 6796 6795 CQUAD4 7220 1 6788 6787 6793 CQUAD4 7647 1 6787 6795 6794 CQUAD4 7652 1 6798 6797 6787 CQUAD4 7945 1 6786 6788 6792 CQUAD4 7948 1 6789 6786 6791 CQUAD4 7955 1 6800 6799 6786 $ $HMMOVE 5 $ 5627 5629 6116 6122 6125 $ 6528 6954 7220 7647 7652 $ $ $ CHEXA Elements: First Order $ CHEXA 17 2 10 11 21 + 36 37 CHEXA 18 2 34 35 36 + 40 41 CHEXA 19 2 38 39 40 + 44 45 CHEXA 20 2 42 43 44 + 48 49 CHEXA 21 2 46 47 48 + 52 53 CHEXA 22 2 50 51 52 + 56 57 CHEXA 23 2 54 55 56

376

-1

6777 6783 6785 6784 6786 6776 6778 6781 6782 6787 6792 6793 6788 6791 6790 6789 6520THRU 7945 7948

6521 7955

23

34

35

37

38

39

41

42

43

45

46

47

49

50

51

53

54

55

57

58

59

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

6523

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

60 24 64 25 68 26 72 27 76 28 80 29 84 30 88 31 92 32 96 33 100 34 104 35 108 36 112 37 116 38 120 39 124 40 128 41 132 42 136 43 140 44 144 45 148 46 152 47 156 48 160 49 164 50 168 51 172 52 176 53 180 54 184 55 188 56 192 57 196

Altair Engineering

61 2 65 2 69 2 73 2 77 2 81 2 85 2 89 2 93 2 97 2 101 2 105 2 109 2 113 2 117 2 121 2 125 2 129 2 133 2 137 2 141 2 145 2 149 2 153 2 157 2 161 2 165 2 169 2 173 2 177 2 181 2 185 2 189 2 193 2 197

58

59

60

61

62

63

62

63

64

65

66

67

66

67

68

69

70

71

70

71

72

73

74

75

74

75

76

77

78

79

78

79

80

81

82

83

82

83

84

85

86

87

86

87

88

89

90

91

90

91

92

93

94

95

94

95

96

97

98

99

98

99

100

101

102

103

102

103

104

105

106

107

106

107

108

109

110

111

110

111

112

113

114

115

114

115

116

117

118

119

118

119

120

121

122

123

122

123

124

125

126

127

126

127

128

129

130

131

130

131

132

133

134

135

134

135

136

137

138

139

138

139

140

141

142

143

142

143

144

145

146

147

146

147

148

149

150

151

150

151

152

153

154

155

154

155

156

157

158

159

158

159

160

161

162

163

162

163

164

165

166

167

166

167

168

169

170

171

170

171

172

173

174

175

174

175

176

177

178

179

178

179

180

181

182

183

182

183

184

185

186

187

186

187

188

189

190

191

190

191

192

193

194

195

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

377

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

378

58 200 139 524 140 528 141 532 142 536 143 540 144 544 145 548 146 552 147 556 148 560 149 564 150 568 151 572 152 576 153 580 154 584 155 588 156 592 157 596 158 600 159 604 160 608 161 612 162 616 163 620 164 624 165 628 166 632 167 636 168 640 169 644 170 648 171 652 172

2 201 2 525 2 529 2 533 2 537 2 541 2 545 2 549 2 553 2 557 2 561 2 565 2 569 2 573 2 577 2 581 2 585 2 589 2 593 2 597 2 601 2 605 2 609 2 613 2 617 2 621 2 625 2 629 2 633 2 637 2 641 2 645 2 649 2 653 2

194

195

196

197

198

199

198

199

200

201

522

523

522

523

524

525

526

527

526

527

528

529

530

531

530

531

532

533

534

535

534

535

536

537

538

539

538

539

540

541

542

543

542

543

544

545

546

547

546

547

548

549

550

551

550

551

552

553

554

555

554

555

556

557

558

559

558

559

560

561

562

563

562

563

564

565

566

567

566

567

568

569

570

571

570

571

572

573

574

575

574

575

576

577

578

579

578

579

580

581

582

583

582

583

584

585

586

587

586

587

588

589

590

591

590

591

592

593

594

595

594

595

596

597

598

599

598

599

600

601

602

603

602

603

604

605

606

607

606

607

608

609

610

611

610

611

612

613

614

615

614

615

616

617

618

619

618

619

620

621

622

623

622

623

624

625

626

627

626

627

628

629

630

631

630

631

632

633

634

635

634

635

636

637

638

639

638

639

640

641

642

643

642

643

644

645

646

647

646

647

648

649

650

651

650

651

652

653

654

655

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

656 173 660 174 664 175 668 176 672 177 676 178 680 179 684 180 688 181 37 182 41 183 45 184 49 185 53 186 57 187 61 188 65 189 69 190 73 191 77 192 81 193 85 194 89 195 93 196 97 197 101 198 105 199 109 200 113 201 117 202 121 203 125 204 129 205 133 206 137

Altair Engineering

657 2 661 2 665 2 669 2 673 2 677 2 681 2 685 2 689 2 691 2 693 2 695 2 697 2 699 2 701 2 703 2 705 2 707 2 709 2 711 2 713 2 715 2 717 2 719 2 721 2 723 2 725 2 727 2 729 2 731 2 733 2 735 2 737 2 739 2 741

654

655

656

657

658

659

658

659

660

661

662

663

662

663

664

665

666

667

666

667

668

669

670

671

670

671

672

673

674

675

674

675

676

677

678

679

678

679

680

681

682

683

682

683

684

685

686

687

9

10

23

20

690

34

690

34

37

691

692

38

692

38

41

693

694

42

694

42

45

695

696

46

696

46

49

697

698

50

698

50

53

699

700

54

700

54

57

701

702

58

702

58

61

703

704

62

704

62

65

705

706

66

706

66

69

707

708

70

708

70

73

709

710

74

710

74

77

711

712

78

712

78

81

713

714

82

714

82

85

715

716

86

716

86

89

717

718

90

718

90

93

719

720

94

720

94

97

721

722

98

722

98

101

723

724

102

724

102

105

725

726

106

726

106

109

727

728

110

728

110

113

729

730

114

730

114

117

731

732

118

732

118

121

733

734

122

734

122

125

735

736

126

736

126

129

737

738

130

738

130

133

739

740

134

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

379

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

380

207 141 208 145 209 149 210 153 211 157 212 161 213 165 214 169 215 173 216 177 217 181 218 185 219 189 220 193 221 197 222 201 303 525 304 529 305 533 306 537 307 541 308 545 309 549 310 553 311 557 312 561 313 565 314 569 315 573 316 577 317 581 318 585 319 589 320 593 321

2 743 2 745 2 747 2 749 2 751 2 753 2 755 2 757 2 759 2 761 2 763 2 765 2 767 2 769 2 771 2 773 2 935 2 937 2 939 2 941 2 943 2 945 2 947 2 949 2 951 2 953 2 955 2 957 2 959 2 961 2 963 2 965 2 967 2 969 2

740

134

137

741

742

138

742

138

141

743

744

142

744

142

145

745

746

146

746

146

149

747

748

150

748

150

153

749

750

154

750

154

157

751

752

158

752

158

161

753

754

162

754

162

165

755

756

166

756

166

169

757

758

170

758

170

173

759

760

174

760

174

177

761

762

178

762

178

181

763

764

182

764

182

185

765

766

186

766

186

189

767

768

190

768

190

193

769

770

194

770

194

197

771

772

198

772

198

201

773

934

522

934

522

525

935

936

526

936

526

529

937

938

530

938

530

533

939

940

534

940

534

537

941

942

538

942

538

541

943

944

542

944

542

545

945

946

546

946

546

549

947

948

550

948

550

553

949

950

554

950

554

557

951

952

558

952

558

561

953

954

562

954

562

565

955

956

566

956

566

569

957

958

570

958

570

573

959

960

574

960

574

577

961

962

578

962

578

581

963

964

582

964

582

585

965

966

586

966

586

589

967

968

590

968

590

593

969

970

594

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

597 322 601 323 605 324 609 325 613 326 617 327 621 328 625 329 629 330 633 331 637 332 641 333 645 334 649 335 653 336 657 337 661 338 665 339 669 340 673 341 677 342 681 343 685 344 689 345 1018 346 1020 347 1022 348 1024 349 1026 350 1028 351 1030 352 1032 353 1034 354 1036 355 1038

Altair Engineering

971 2 973 2 975 2 977 2 979 2 981 2 983 2 985 2 987 2 989 2 991 2 993 2 995 2 997 2 999 2 1001 2 1003 2 1005 2 1007 2 1009 2 1011 2 1013 2 1015 2 1017 2 1019 2 1021 2 1023 2 1025 2 1027 2 1029 2 1031 2 1033 2 1035 2 1037 2 1039

970

594

597

971

972

598

972

598

601

973

974

602

974

602

605

975

976

606

976

606

609

977

978

610

978

610

613

979

980

614

980

614

617

981

982

618

982

618

621

983

984

622

984

622

625

985

986

626

986

626

629

987

988

630

988

630

633

989

990

634

990

634

637

991

992

638

992

638

641

993

994

642

994

642

645

995

996

646

996

646

649

997

998

650

998

650

653

999

1000

654

1000

654

657

1001

1002

658

1002

658

661

1003

1004

662

1004

662

665

1005

1006

666

1006

666

669

1007

1008

670

1008

670

673

1009

1010

674

1010

674

677

1011

1012

678

1012

678

681

1013

1014

682

1014

682

685

1015

1016

686

23

21

17

18

37

36

37

36

1018

1019

41

40

41

40

1020

1021

45

44

45

44

1022

1023

49

48

49

48

1024

1025

53

52

53

52

1026

1027

57

56

57

56

1028

1029

61

60

61

60

1030

1031

65

64

65

64

1032

1033

69

68

69

68

1034

1035

73

72

73

72

1036

1037

77

76

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

381

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

382

356 1040 357 1042 358 1044 359 1046 360 1048 361 1050 362 1052 363 1054 364 1056 365 1058 366 1060 367 1062 368 1064 369 1066 370 1068 371 1070 372 1072 373 1074 374 1076 375 1078 376 1080 377 1082 378 1084 379 1086 380 1088 381 1090 382 1092 383 1094 384 1096 385 1098 386 1100 467 1262 468 1264 469 1266 470

2 1041 2 1043 2 1045 2 1047 2 1049 2 1051 2 1053 2 1055 2 1057 2 1059 2 1061 2 1063 2 1065 2 1067 2 1069 2 1071 2 1073 2 1075 2 1077 2 1079 2 1081 2 1083 2 1085 2 1087 2 1089 2 1091 2 1093 2 1095 2 1097 2 1099 2 1101 2 1263 2 1265 2 1267 2

77

76

1038

1039

81

80

81

80

1040

1041

85

84

85

84

1042

1043

89

88

89

88

1044

1045

93

92

93

92

1046

1047

97

96

97

96

1048

1049

101

100

101

100

1050

1051

105

104

105

104

1052

1053

109

108

109

108

1054

1055

113

112

113

112

1056

1057

117

116

117

116

1058

1059

121

120

121

120

1060

1061

125

124

125

124

1062

1063

129

128

129

128

1064

1065

133

132

133

132

1066

1067

137

136

137

136

1068

1069

141

140

141

140

1070

1071

145

144

145

144

1072

1073

149

148

149

148

1074

1075

153

152

153

152

1076

1077

157

156

157

156

1078

1079

161

160

161

160

1080

1081

165

164

165

164

1082

1083

169

168

169

168

1084

1085

173

172

173

172

1086

1087

177

176

177

176

1088

1089

181

180

181

180

1090

1091

185

184

185

184

1092

1093

189

188

189

188

1094

1095

193

192

193

192

1096

1097

197

196

197

196

1098

1099

201

200

201

200

1100

1101

525

524

525

524

1262

1263

529

528

529

528

1264

1265

533

532

533

532

1266

1267

537

536

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1268 471 1270 472 1272 473 1274 474 1276 475 1278 476 1280 477 1282 478 1284 479 1286 480 1288 481 1290 482 1292 483 1294 484 1296 485 1298 486 1300 487 1302 488 1304 489 1306 490 1308 491 1310 492 1312 493 1314 494 1316 495 1318 496 1320 497 1322 498 1324 499 1326 500 1328 501 1330 502 1332 503 1334 504 1336

Altair Engineering

1269 2 1271 2 1273 2 1275 2 1277 2 1279 2 1281 2 1283 2 1285 2 1287 2 1289 2 1291 2 1293 2 1295 2 1297 2 1299 2 1301 2 1303 2 1305 2 1307 2 1309 2 1311 2 1313 2 1315 2 1317 2 1319 2 1321 2 1323 2 1325 2 1327 2 1329 2 1331 2 1333 2 1335 2 1337

537

536

1268

1269

541

540

541

540

1270

1271

545

544

545

544

1272

1273

549

548

549

548

1274

1275

553

552

553

552

1276

1277

557

556

557

556

1278

1279

561

560

561

560

1280

1281

565

564

565

564

1282

1283

569

568

569

568

1284

1285

573

572

573

572

1286

1287

577

576

577

576

1288

1289

581

580

581

580

1290

1291

585

584

585

584

1292

1293

589

588

589

588

1294

1295

593

592

593

592

1296

1297

597

596

597

596

1298

1299

601

600

601

600

1300

1301

605

604

605

604

1302

1303

609

608

609

608

1304

1305

613

612

613

612

1306

1307

617

616

617

616

1308

1309

621

620

621

620

1310

1311

625

624

625

624

1312

1313

629

628

629

628

1314

1315

633

632

633

632

1316

1317

637

636

637

636

1318

1319

641

640

641

640

1320

1321

645

644

645

644

1322

1323

649

648

649

648

1324

1325

653

652

653

652

1326

1327

657

656

657

656

1328

1329

661

660

661

660

1330

1331

665

664

665

664

1332

1333

669

668

669

668

1334

1335

673

672

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

383

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

384

505 1338 506 1340 507 1342 508 1344 509 1019 510 1021 511 1023 512 1025 513 1027 514 1029 515 1031 516 1033 517 1035 518 1037 519 1039 520 1041 521 1043 522 1045 523 1047 524 1049 525 1051 526 1053 527 1055 528 1057 529 1059 530 1061 531 1063 532 1065 533 1067 534 1069 535 1071 536 1073 537 1075 538 1077 539

2 1339 2 1341 2 1343 2 1345 2 1346 2 1347 2 1348 2 1349 2 1350 2 1351 2 1352 2 1353 2 1354 2 1355 2 1356 2 1357 2 1358 2 1359 2 1360 2 1361 2 1362 2 1363 2 1364 2 1365 2 1366 2 1367 2 1368 2 1369 2 1370 2 1371 2 1372 2 1373 2 1374 2 1375 2

673

672

1336

1337

677

676

677

676

1338

1339

681

680

681

680

1340

1341

685

684

685

684

1342

1343

689

688

20

23

18

19

691

37

691

37

1019

1346

693

41

693

41

1021

1347

695

45

695

45

1023

1348

697

49

697

49

1025

1349

699

53

699

53

1027

1350

701

57

701

57

1029

1351

703

61

703

61

1031

1352

705

65

705

65

1033

1353

707

69

707

69

1035

1354

709

73

709

73

1037

1355

711

77

711

77

1039

1356

713

81

713

81

1041

1357

715

85

715

85

1043

1358

717

89

717

89

1045

1359

719

93

719

93

1047

1360

721

97

721

97

1049

1361

723

101

723

101

1051

1362

725

105

725

105

1053

1363

727

109

727

109

1055

1364

729

113

729

113

1057

1365

731

117

731

117

1059

1366

733

121

733

121

1061

1367

735

125

735

125

1063

1368

737

129

737

129

1065

1369

739

133

739

133

1067

1370

741

137

741

137

1069

1371

743

141

743

141

1071

1372

745

145

745

145

1073

1373

747

149

747

149

1075

1374

749

153

749

153

1077

1375

751

157

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1079 540 1081 541 1083 542 1085 543 1087 544 1089 545 1091 546 1093 547 1095 548 1097 549 1099 550 1101 631 1263 632 1265 633 1267 634 1269 635 1271 636 1273 637 1275 638 1277 639 1279 640 1281 641 1283 642 1285 643 1287 644 1289 645 1291 646 1293 647 1295 648 1297 649 1299 650 1301 651 1303 652 1305 653 1307

Altair Engineering

1376 2 1377 2 1378 2 1379 2 1380 2 1381 2 1382 2 1383 2 1384 2 1385 2 1386 2 1387 2 1468 2 1469 2 1470 2 1471 2 1472 2 1473 2 1474 2 1475 2 1476 2 1477 2 1478 2 1479 2 1480 2 1481 2 1482 2 1483 2 1484 2 1485 2 1486 2 1487 2 1488 2 1489 2 1490

751

157

1079

1376

753

161

753

161

1081

1377

755

165

755

165

1083

1378

757

169

757

169

1085

1379

759

173

759

173

1087

1380

761

177

761

177

1089

1381

763

181

763

181

1091

1382

765

185

765

185

1093

1383

767

189

767

189

1095

1384

769

193

769

193

1097

1385

771

197

771

197

1099

1386

773

201

773

201

1101

1387

935

525

935

525

1263

1468

937

529

937

529

1265

1469

939

533

939

533

1267

1470

941

537

941

537

1269

1471

943

541

943

541

1271

1472

945

545

945

545

1273

1473

947

549

947

549

1275

1474

949

553

949

553

1277

1475

951

557

951

557

1279

1476

953

561

953

561

1281

1477

955

565

955

565

1283

1478

957

569

957

569

1285

1479

959

573

959

573

1287

1480

961

577

961

577

1289

1481

963

581

963

581

1291

1482

965

585

965

585

1293

1483

967

589

967

589

1295

1484

969

593

969

593

1297

1485

971

597

971

597

1299

1486

973

601

973

601

1301

1487

975

605

975

605

1303

1488

977

609

977

609

1305

1489

979

613

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

385

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

386

654 1309 655 1311 656 1313 657 1315 658 1317 659 1319 660 1321 661 1323 662 1325 663 1327 664 1329 665 1331 666 1333 667 1335 668 1337 669 1339 670 1341 671 1343 672 1345 673 1512 674 1516 675 1520 676 1524 677 1528 678 1532 679 1536 680 1540 681 1544 682 1548 683 1552 684 1556 685 1560 686 1564 687 1568 688

2 1491 2 1492 2 1493 2 1494 2 1495 2 1496 2 1497 2 1498 2 1499 2 1500 2 1501 2 1502 2 1503 2 1504 2 1505 2 1506 2 1507 2 1508 2 1509 2 1513 2 1517 2 1521 2 1525 2 1529 2 1533 2 1537 2 1541 2 1545 2 1549 2 1553 2 1557 2 1561 2 1565 2 1569 2

979

613

1307

1490

981

617

981

617

1309

1491

983

621

983

621

1311

1492

985

625

985

625

1313

1493

987

629

987

629

1315

1494

989

633

989

633

1317

1495

991

637

991

637

1319

1496

993

641

993

641

1321

1497

995

645

995

645

1323

1498

997

649

997

649

1325

1499

999

653

999

653

1327

1500

1001

657

1001

657

1329

1501

1003

661

1003

661

1331

1502

1005

665

1005

665

1333

1503

1007

669

1007

669

1335

1504

1009

673

1009

673

1337

1505

1011

677

1011

677

1339

1506

1013

681

1013

681

1341

1507

1015

685

1015

685

1343

1508

1017

689

12

13

14

22

1510

1511

1510

1511

1512

1513

1514

1515

1514

1515

1516

1517

1518

1519

1518

1519

1520

1521

1522

1523

1522

1523

1524

1525

1526

1527

1526

1527

1528

1529

1530

1531

1530

1531

1532

1533

1534

1535

1534

1535

1536

1537

1538

1539

1538

1539

1540

1541

1542

1543

1542

1543

1544

1545

1546

1547

1546

1547

1548

1549

1550

1551

1550

1551

1552

1553

1554

1555

1554

1555

1556

1557

1558

1559

1558

1559

1560

1561

1562

1563

1562

1563

1564

1565

1566

1567

1566

1567

1568

1569

1570

1571

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1572 689 1576 690 1580 691 1584 692 1588 693 1592 694 1596 695 1600 696 1604 697 1608 698 1612 699 1616 700 1620 701 1624 702 1628 703 1632 704 1636 705 1640 706 1644 707 1648 708 1652 709 1656 710 1660 711 1664 712 1668 713 1672 714 1676 795 2000 796 2004 797 2008 798 2012 799 2016 800 2020 801 2024 802 2028

Altair Engineering

1573 2 1577 2 1581 2 1585 2 1589 2 1593 2 1597 2 1601 2 1605 2 1609 2 1613 2 1617 2 1621 2 1625 2 1629 2 1633 2 1637 2 1641 2 1645 2 1649 2 1653 2 1657 2 1661 2 1665 2 1669 2 1673 2 1677 2 2001 2 2005 2 2009 2 2013 2 2017 2 2021 2 2025 2 2029

1570

1571

1572

1573

1574

1575

1574

1575

1576

1577

1578

1579

1578

1579

1580

1581

1582

1583

1582

1583

1584

1585

1586

1587

1586

1587

1588

1589

1590

1591

1590

1591

1592

1593

1594

1595

1594

1595

1596

1597

1598

1599

1598

1599

1600

1601

1602

1603

1602

1603

1604

1605

1606

1607

1606

1607

1608

1609

1610

1611

1610

1611

1612

1613

1614

1615

1614

1615

1616

1617

1618

1619

1618

1619

1620

1621

1622

1623

1622

1623

1624

1625

1626

1627

1626

1627

1628

1629

1630

1631

1630

1631

1632

1633

1634

1635

1634

1635

1636

1637

1638

1639

1638

1639

1640

1641

1642

1643

1642

1643

1644

1645

1646

1647

1646

1647

1648

1649

1650

1651

1650

1651

1652

1653

1654

1655

1654

1655

1656

1657

1658

1659

1658

1659

1660

1661

1662

1663

1662

1663

1664

1665

1666

1667

1666

1667

1668

1669

1670

1671

1670

1671

1672

1673

1674

1675

1674

1675

1676

1677

1998

1999

1998

1999

2000

2001

2002

2003

2002

2003

2004

2005

2006

2007

2006

2007

2008

2009

2010

2011

2010

2011

2012

2013

2014

2015

2014

2015

2016

2017

2018

2019

2018

2019

2020

2021

2022

2023

2022

2023

2024

2025

2026

2027

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

387

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

388

803 2032 804 2036 805 2040 806 2044 807 2048 808 2052 809 2056 810 2060 811 2064 812 2068 813 2072 814 2076 815 2080 816 2084 817 2088 818 2092 819 2096 820 2100 821 2104 822 2108 823 2112 824 2116 825 2120 826 2124 827 2128 828 2132 829 2136 830 2140 831 2144 832 2148 833 2152 834 2156 835 2160 836 2164 837

2 2033 2 2037 2 2041 2 2045 2 2049 2 2053 2 2057 2 2061 2 2065 2 2069 2 2073 2 2077 2 2081 2 2085 2 2089 2 2093 2 2097 2 2101 2 2105 2 2109 2 2113 2 2117 2 2121 2 2125 2 2129 2 2133 2 2137 2 2141 2 2145 2 2149 2 2153 2 2157 2 2161 2 2165 2

2026

2027

2028

2029

2030

2031

2030

2031

2032

2033

2034

2035

2034

2035

2036

2037

2038

2039

2038

2039

2040

2041

2042

2043

2042

2043

2044

2045

2046

2047

2046

2047

2048

2049

2050

2051

2050

2051

2052

2053

2054

2055

2054

2055

2056

2057

2058

2059

2058

2059

2060

2061

2062

2063

2062

2063

2064

2065

2066

2067

2066

2067

2068

2069

2070

2071

2070

2071

2072

2073

2074

2075

2074

2075

2076

2077

2078

2079

2078

2079

2080

2081

2082

2083

2082

2083

2084

2085

2086

2087

2086

2087

2088

2089

2090

2091

2090

2091

2092

2093

2094

2095

2094

2095

2096

2097

2098

2099

2098

2099

2100

2101

2102

2103

2102

2103

2104

2105

2106

2107

2106

2107

2108

2109

2110

2111

2110

2111

2112

2113

2114

2115

2114

2115

2116

2117

2118

2119

2118

2119

2120

2121

2122

2123

2122

2123

2124

2125

2126

2127

2126

2127

2128

2129

2130

2131

2130

2131

2132

2133

2134

2135

2134

2135

2136

2137

2138

2139

2138

2139

2140

2141

2142

2143

2142

2143

2144

2145

2146

2147

2146

2147

2148

2149

2150

2151

2150

2151

2152

2153

2154

2155

2154

2155

2156

2157

2158

2159

2158

2159

2160

2161

2162

2163

11

12

22

21

35

1510

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1513 838 1517 839 1521 840 1525 841 1529 842 1533 843 1537 844 1541 845 1545 846 1549 847 1553 848 1557 849 1561 850 1565 851 1569 852 1573 853 1577 854 1581 855 1585 856 1589 857 1593 858 1597 859 1601 860 1605 861 1609 862 1613 863 1617 864 1621 865 1625 866 1629 867 1633 868 1637 869 1641 870 1645 871 1649

Altair Engineering

36 2 40 2 44 2 48 2 52 2 56 2 60 2 64 2 68 2 72 2 76 2 80 2 84 2 88 2 92 2 96 2 100 2 104 2 108 2 112 2 116 2 120 2 124 2 128 2 132 2 136 2 140 2 144 2 148 2 152 2 156 2 160 2 164 2 168 2 172

35

1510

1513

36

39

1514

39

1514

1517

40

43

1518

43

1518

1521

44

47

1522

47

1522

1525

48

51

1526

51

1526

1529

52

55

1530

55

1530

1533

56

59

1534

59

1534

1537

60

63

1538

63

1538

1541

64

67

1542

67

1542

1545

68

71

1546

71

1546

1549

72

75

1550

75

1550

1553

76

79

1554

79

1554

1557

80

83

1558

83

1558

1561

84

87

1562

87

1562

1565

88

91

1566

91

1566

1569

92

95

1570

95

1570

1573

96

99

1574

99

1574

1577

100

103

1578

103

1578

1581

104

107

1582

107

1582

1585

108

111

1586

111

1586

1589

112

115

1590

115

1590

1593

116

119

1594

119

1594

1597

120

123

1598

123

1598

1601

124

127

1602

127

1602

1605

128

131

1606

131

1606

1609

132

135

1610

135

1610

1613

136

139

1614

139

1614

1617

140

143

1618

143

1618

1621

144

147

1622

147

1622

1625

148

151

1626

151

1626

1629

152

155

1630

155

1630

1633

156

159

1634

159

1634

1637

160

163

1638

163

1638

1641

164

167

1642

167

1642

1645

168

171

1646

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

389

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

390

872 1653 873 1657 874 1661 875 1665 876 1669 877 1673 878 1677 959 2001 960 2005 961 2009 962 2013 963 2017 964 2021 965 2025 966 2029 967 2033 968 2037 969 2041 970 2045 971 2049 972 2053 973 2057 974 2061 975 2065 976 2069 977 2073 978 2077 979 2081 980 2085 981 2089 982 2093 983 2097 984 2101 985 2105 986

2 176 2 180 2 184 2 188 2 192 2 196 2 200 2 524 2 528 2 532 2 536 2 540 2 544 2 548 2 552 2 556 2 560 2 564 2 568 2 572 2 576 2 580 2 584 2 588 2 592 2 596 2 600 2 604 2 608 2 612 2 616 2 620 2 624 2 628 2

171

1646

1649

172

175

1650

175

1650

1653

176

179

1654

179

1654

1657

180

183

1658

183

1658

1661

184

187

1662

187

1662

1665

188

191

1666

191

1666

1669

192

195

1670

195

1670

1673

196

199

1674

199

1674

1677

200

523

1998

523

1998

2001

524

527

2002

527

2002

2005

528

531

2006

531

2006

2009

532

535

2010

535

2010

2013

536

539

2014

539

2014

2017

540

543

2018

543

2018

2021

544

547

2022

547

2022

2025

548

551

2026

551

2026

2029

552

555

2030

555

2030

2033

556

559

2034

559

2034

2037

560

563

2038

563

2038

2041

564

567

2042

567

2042

2045

568

571

2046

571

2046

2049

572

575

2050

575

2050

2053

576

579

2054

579

2054

2057

580

583

2058

583

2058

2061

584

587

2062

587

2062

2065

588

591

2066

591

2066

2069

592

595

2070

595

2070

2073

596

599

2074

599

2074

2077

600

603

2078

603

2078

2081

604

607

2082

607

2082

2085

608

611

2086

611

2086

2089

612

615

2090

615

2090

2093

616

619

2094

619

2094

2097

620

623

2098

623

2098

2101

624

627

2102

627

2102

2105

628

631

2106

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2109 987 2113 988 2117 989 2121 990 2125 991 2129 992 2133 993 2137 994 2141 995 2145 996 2149 997 2153 998 2157 999 2161 1000 2165 1001 2166 1002 2168 1003 2170 1004 2172 1005 2174 1006 2176 1007 2178 1008 2180 1009 2182 1010 2184 1011 2186 1012 2188 1013 2190 1014 2192 1015 2194 1016 2196 1017 2198 1018 2200 1019 2202 1020 2204

Altair Engineering

632 2 636 2 640 2 644 2 648 2 652 2 656 2 660 2 664 2 668 2 672 2 676 2 680 2 684 2 688 2 2167 2 2169 2 2171 2 2173 2 2175 2 2177 2 2179 2 2181 2 2183 2 2185 2 2187 2 2189 2 2191 2 2193 2 2195 2 2197 2 2199 2 2201 2 2203 2 2205

631

2106

2109

632

635

2110

635

2110

2113

636

639

2114

639

2114

2117

640

643

2118

643

2118

2121

644

647

2122

647

2122

2125

648

651

2126

651

2126

2129

652

655

2130

655

2130

2133

656

659

2134

659

2134

2137

660

663

2138

663

2138

2141

664

667

2142

667

2142

2145

668

671

2146

671

2146

2149

672

675

2150

675

2150

2153

676

679

2154

679

2154

2157

680

683

2158

683

2158

2161

684

687

2162

22

14

15

16

1513

1512

1513

1512

2166

2167

1517

1516

1517

1516

2168

2169

1521

1520

1521

1520

2170

2171

1525

1524

1525

1524

2172

2173

1529

1528

1529

1528

2174

2175

1533

1532

1533

1532

2176

2177

1537

1536

1537

1536

2178

2179

1541

1540

1541

1540

2180

2181

1545

1544

1545

1544

2182

2183

1549

1548

1549

1548

2184

2185

1553

1552

1553

1552

2186

2187

1557

1556

1557

1556

2188

2189

1561

1560

1561

1560

2190

2191

1565

1564

1565

1564

2192

2193

1569

1568

1569

1568

2194

2195

1573

1572

1573

1572

2196

2197

1577

1576

1577

1576

2198

2199

1581

1580

1581

1580

2200

2201

1585

1584

1585

1584

2202

2203

1589

1588

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

391

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

392

1021 2206 1022 2208 1023 2210 1024 2212 1025 2214 1026 2216 1027 2218 1028 2220 1029 2222 1030 2224 1031 2226 1032 2228 1033 2230 1034 2232 1035 2234 1036 2236 1037 2238 1038 2240 1039 2242 1040 2244 1041 2246 1042 2248 1123 2410 1124 2412 1125 2414 1126 2416 1127 2418 1128 2420 1129 2422 1130 2424 1131 2426 1132 2428 1133 2430 1134 2432 1135

2 2207 2 2209 2 2211 2 2213 2 2215 2 2217 2 2219 2 2221 2 2223 2 2225 2 2227 2 2229 2 2231 2 2233 2 2235 2 2237 2 2239 2 2241 2 2243 2 2245 2 2247 2 2249 2 2411 2 2413 2 2415 2 2417 2 2419 2 2421 2 2423 2 2425 2 2427 2 2429 2 2431 2 2433 2

1589

1588

2204

2205

1593

1592

1593

1592

2206

2207

1597

1596

1597

1596

2208

2209

1601

1600

1601

1600

2210

2211

1605

1604

1605

1604

2212

2213

1609

1608

1609

1608

2214

2215

1613

1612

1613

1612

2216

2217

1617

1616

1617

1616

2218

2219

1621

1620

1621

1620

2220

2221

1625

1624

1625

1624

2222

2223

1629

1628

1629

1628

2224

2225

1633

1632

1633

1632

2226

2227

1637

1636

1637

1636

2228

2229

1641

1640

1641

1640

2230

2231

1645

1644

1645

1644

2232

2233

1649

1648

1649

1648

2234

2235

1653

1652

1653

1652

2236

2237

1657

1656

1657

1656

2238

2239

1661

1660

1661

1660

2240

2241

1665

1664

1665

1664

2242

2243

1669

1668

1669

1668

2244

2245

1673

1672

1673

1672

2246

2247

1677

1676

1677

1676

2248

2249

2001

2000

2001

2000

2410

2411

2005

2004

2005

2004

2412

2413

2009

2008

2009

2008

2414

2415

2013

2012

2013

2012

2416

2417

2017

2016

2017

2016

2418

2419

2021

2020

2021

2020

2420

2421

2025

2024

2025

2024

2422

2423

2029

2028

2029

2028

2424

2425

2033

2032

2033

2032

2426

2427

2037

2036

2037

2036

2428

2429

2041

2040

2041

2040

2430

2431

2045

2044

2045

2044

2432

2433

2049

2048

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2434 1136 2436 1137 2438 1138 2440 1139 2442 1140 2444 1141 2446 1142 2448 1143 2450 1144 2452 1145 2454 1146 2456 1147 2458 1148 2460 1149 2462 1150 2464 1151 2466 1152 2468 1153 2470 1154 2472 1155 2474 1156 2476 1157 2478 1158 2480 1159 2482 1160 2484 1161 2486 1162 2488 1163 2490 1164 2492 1165 2167 1166 2169 1167 2171 1168 2173 1169 2175

Altair Engineering

2435 2 2437 2 2439 2 2441 2 2443 2 2445 2 2447 2 2449 2 2451 2 2453 2 2455 2 2457 2 2459 2 2461 2 2463 2 2465 2 2467 2 2469 2 2471 2 2473 2 2475 2 2477 2 2479 2 2481 2 2483 2 2485 2 2487 2 2489 2 2491 2 2493 2 1018 2 1020 2 1022 2 1024 2 1026

2049

2048

2434

2435

2053

2052

2053

2052

2436

2437

2057

2056

2057

2056

2438

2439

2061

2060

2061

2060

2440

2441

2065

2064

2065

2064

2442

2443

2069

2068

2069

2068

2444

2445

2073

2072

2073

2072

2446

2447

2077

2076

2077

2076

2448

2449

2081

2080

2081

2080

2450

2451

2085

2084

2085

2084

2452

2453

2089

2088

2089

2088

2454

2455

2093

2092

2093

2092

2456

2457

2097

2096

2097

2096

2458

2459

2101

2100

2101

2100

2460

2461

2105

2104

2105

2104

2462

2463

2109

2108

2109

2108

2464

2465

2113

2112

2113

2112

2466

2467

2117

2116

2117

2116

2468

2469

2121

2120

2121

2120

2470

2471

2125

2124

2125

2124

2472

2473

2129

2128

2129

2128

2474

2475

2133

2132

2133

2132

2476

2477

2137

2136

2137

2136

2478

2479

2141

2140

2141

2140

2480

2481

2145

2144

2145

2144

2482

2483

2149

2148

2149

2148

2484

2485

2153

2152

2153

2152

2486

2487

2157

2156

2157

2156

2488

2489

2161

2160

2161

2160

2490

2491

2165

2164

21

22

16

17

36

1513

36

1513

2167

1018

40

1517

40

1517

2169

1020

44

1521

44

1521

2171

1022

48

1525

48

1525

2173

1024

52

1529

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

393

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

394

1170 2177 1171 2179 1172 2181 1173 2183 1174 2185 1175 2187 1176 2189 1177 2191 1178 2193 1179 2195 1180 2197 1181 2199 1182 2201 1183 2203 1184 2205 1185 2207 1186 2209 1187 2211 1188 2213 1189 2215 1190 2217 1191 2219 1192 2221 1193 2223 1194 2225 1195 2227 1196 2229 1197 2231 1198 2233 1199 2235 1200 2237 1201 2239 1202 2241 1203 2243 1204

2 1028 2 1030 2 1032 2 1034 2 1036 2 1038 2 1040 2 1042 2 1044 2 1046 2 1048 2 1050 2 1052 2 1054 2 1056 2 1058 2 1060 2 1062 2 1064 2 1066 2 1068 2 1070 2 1072 2 1074 2 1076 2 1078 2 1080 2 1082 2 1084 2 1086 2 1088 2 1090 2 1092 2 1094 2

52

1529

2175

1026

56

1533

56

1533

2177

1028

60

1537

60

1537

2179

1030

64

1541

64

1541

2181

1032

68

1545

68

1545

2183

1034

72

1549

72

1549

2185

1036

76

1553

76

1553

2187

1038

80

1557

80

1557

2189

1040

84

1561

84

1561

2191

1042

88

1565

88

1565

2193

1044

92

1569

92

1569

2195

1046

96

1573

96

1573

2197

1048

100

1577

100

1577

2199

1050

104

1581

104

1581

2201

1052

108

1585

108

1585

2203

1054

112

1589

112

1589

2205

1056

116

1593

116

1593

2207

1058

120

1597

120

1597

2209

1060

124

1601

124

1601

2211

1062

128

1605

128

1605

2213

1064

132

1609

132

1609

2215

1066

136

1613

136

1613

2217

1068

140

1617

140

1617

2219

1070

144

1621

144

1621

2221

1072

148

1625

148

1625

2223

1074

152

1629

152

1629

2225

1076

156

1633

156

1633

2227

1078

160

1637

160

1637

2229

1080

164

1641

164

1641

2231

1082

168

1645

168

1645

2233

1084

172

1649

172

1649

2235

1086

176

1653

176

1653

2237

1088

180

1657

180

1657

2239

1090

184

1661

184

1661

2241

1092

188

1665

188

1665

2243

1094

192

1669

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2245 1205 2247 1206 2249 1287 2411 1288 2413 1289 2415 1290 2417 1291 2419 1292 2421 1293 2423 1294 2425 1295 2427 1296 2429 1297 2431 1298 2433 1299 2435 1300 2437 1301 2439 1302 2441 1303 2443 1304 2445 1305 2447 1306 2449 1307 2451 1308 2453 1309 2455 1310 2457 1311 2459 1312 2461 1313 2463 1314 2465 1315 2467 1316 2469 1317 2471 1318 2473

Altair Engineering

1096 2 1098 2 1100 2 1262 2 1264 2 1266 2 1268 2 1270 2 1272 2 1274 2 1276 2 1278 2 1280 2 1282 2 1284 2 1286 2 1288 2 1290 2 1292 2 1294 2 1296 2 1298 2 1300 2 1302 2 1304 2 1306 2 1308 2 1310 2 1312 2 1314 2 1316 2 1318 2 1320 2 1322 2 1324

192

1669

2245

1096

196

1673

196

1673

2247

1098

200

1677

200

1677

2249

1100

524

2001

524

2001

2411

1262

528

2005

528

2005

2413

1264

532

2009

532

2009

2415

1266

536

2013

536

2013

2417

1268

540

2017

540

2017

2419

1270

544

2021

544

2021

2421

1272

548

2025

548

2025

2423

1274

552

2029

552

2029

2425

1276

556

2033

556

2033

2427

1278

560

2037

560

2037

2429

1280

564

2041

564

2041

2431

1282

568

2045

568

2045

2433

1284

572

2049

572

2049

2435

1286

576

2053

576

2053

2437

1288

580

2057

580

2057

2439

1290

584

2061

584

2061

2441

1292

588

2065

588

2065

2443

1294

592

2069

592

2069

2445

1296

596

2073

596

2073

2447

1298

600

2077

600

2077

2449

1300

604

2081

604

2081

2451

1302

608

2085

608

2085

2453

1304

612

2089

612

2089

2455

1306

616

2093

616

2093

2457

1308

620

2097

620

2097

2459

1310

624

2101

624

2101

2461

1312

628

2105

628

2105

2463

1314

632

2109

632

2109

2465

1316

636

2113

636

2113

2467

1318

640

2117

640

2117

2469

1320

644

2121

644

2121

2471

1322

648

2125

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

395

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

396

1319 2475 1320 2477 1321 2479 1322 2481 1323 2483 1324 2485 1325 2487 1326 2489 1327 2491 1328 2493 1329 35 1330 39 1331 43 1332 47 1333 51 1334 55 1335 59 1336 63 1337 67 1338 71 1339 75 1340 79 1341 83 1342 87 1343 91 1344 95 1345 99 1346 103 1347 107 1348 111 1349 115 1350 119 1351 123 1352 127 1353

2 1326 2 1328 2 1330 2 1332 2 1334 2 1336 2 1338 2 1340 2 1342 2 1344 2 2495 2 2497 2 2499 2 2501 2 2503 2 2505 2 2507 2 2509 2 2511 2 2513 2 2515 2 2517 2 2519 2 2521 2 2523 2 2525 2 2527 2 2529 2 2531 2 2533 2 2535 2 2537 2 2539 2 2541 2

648

2125

2473

1324

652

2129

652

2129

2475

1326

656

2133

656

2133

2477

1328

660

2137

660

2137

2479

1330

664

2141

664

2141

2481

1332

668

2145

668

2145

2483

1334

672

2149

672

2149

2485

1336

676

2153

676

2153

2487

1338

680

2157

680

2157

2489

1340

684

2161

684

2161

2491

1342

688

2165

33

12

11

31

2494

1510

2494

1510

35

2495

2496

1514

2496

1514

39

2497

2498

1518

2498

1518

43

2499

2500

1522

2500

1522

47

2501

2502

1526

2502

1526

51

2503

2504

1530

2504

1530

55

2505

2506

1534

2506

1534

59

2507

2508

1538

2508

1538

63

2509

2510

1542

2510

1542

67

2511

2512

1546

2512

1546

71

2513

2514

1550

2514

1550

75

2515

2516

1554

2516

1554

79

2517

2518

1558

2518

1558

83

2519

2520

1562

2520

1562

87

2521

2522

1566

2522

1566

91

2523

2524

1570

2524

1570

95

2525

2526

1574

2526

1574

99

2527

2528

1578

2528

1578

103

2529

2530

1582

2530

1582

107

2531

2532

1586

2532

1586

111

2533

2534

1590

2534

1590

115

2535

2536

1594

2536

1594

119

2537

2538

1598

2538

1598

123

2539

2540

1602

2540

1602

127

2541

2542

1606

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

131 1354 135 1355 139 1356 143 1357 147 1358 151 1359 155 1360 159 1361 163 1362 167 1363 171 1364 175 1365 179 1366 183 1367 187 1368 191 1369 195 1370 199 1451 523 1452 527 1453 531 1454 535 1455 539 1456 543 1457 547 1458 551 1459 555 1460 559 1461 563 1462 567 1463 571 1464 575 1465 579 1466 583 1467 587

Altair Engineering

2543 2 2545 2 2547 2 2549 2 2551 2 2553 2 2555 2 2557 2 2559 2 2561 2 2563 2 2565 2 2567 2 2569 2 2571 2 2573 2 2575 2 2577 2 2739 2 2741 2 2743 2 2745 2 2747 2 2749 2 2751 2 2753 2 2755 2 2757 2 2759 2 2761 2 2763 2 2765 2 2767 2 2769 2 2771

2542

1606

131

2543

2544

1610

2544

1610

135

2545

2546

1614

2546

1614

139

2547

2548

1618

2548

1618

143

2549

2550

1622

2550

1622

147

2551

2552

1626

2552

1626

151

2553

2554

1630

2554

1630

155

2555

2556

1634

2556

1634

159

2557

2558

1638

2558

1638

163

2559

2560

1642

2560

1642

167

2561

2562

1646

2562

1646

171

2563

2564

1650

2564

1650

175

2565

2566

1654

2566

1654

179

2567

2568

1658

2568

1658

183

2569

2570

1662

2570

1662

187

2571

2572

1666

2572

1666

191

2573

2574

1670

2574

1670

195

2575

2576

1674

2576

1674

199

2577

2738

1998

2738

1998

523

2739

2740

2002

2740

2002

527

2741

2742

2006

2742

2006

531

2743

2744

2010

2744

2010

535

2745

2746

2014

2746

2014

539

2747

2748

2018

2748

2018

543

2749

2750

2022

2750

2022

547

2751

2752

2026

2752

2026

551

2753

2754

2030

2754

2030

555

2755

2756

2034

2756

2034

559

2757

2758

2038

2758

2038

563

2759

2760

2042

2760

2042

567

2761

2762

2046

2762

2046

571

2763

2764

2050

2764

2050

575

2765

2766

2054

2766

2054

579

2767

2768

2058

2768

2058

583

2769

2770

2062

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

397

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

398

1468 591 1469 595 1470 599 1471 603 1472 607 1473 611 1474 615 1475 619 1476 623 1477 627 1478 631 1479 635 1480 639 1481 643 1482 647 1483 651 1484 655 1485 659 1486 663 1487 667 1488 671 1489 675 1490 679 1491 683 1492 687 1493 1510 1494 1514 1495 1518 1496 1522 1497 1526 1498 1530 1499 1534 1500 1538 1501 1542 1502

2 2773 2 2775 2 2777 2 2779 2 2781 2 2783 2 2785 2 2787 2 2789 2 2791 2 2793 2 2795 2 2797 2 2799 2 2801 2 2803 2 2805 2 2807 2 2809 2 2811 2 2813 2 2815 2 2817 2 2819 2 2821 2 2494 2 2496 2 2498 2 2500 2 2502 2 2504 2 2506 2 2508 2 2510 2

2770

2062

587

2771

2772

2066

2772

2066

591

2773

2774

2070

2774

2070

595

2775

2776

2074

2776

2074

599

2777

2778

2078

2778

2078

603

2779

2780

2082

2780

2082

607

2781

2782

2086

2782

2086

611

2783

2784

2090

2784

2090

615

2785

2786

2094

2786

2094

619

2787

2788

2098

2788

2098

623

2789

2790

2102

2790

2102

627

2791

2792

2106

2792

2106

631

2793

2794

2110

2794

2110

635

2795

2796

2114

2796

2114

639

2797

2798

2118

2798

2118

643

2799

2800

2122

2800

2122

647

2801

2802

2126

2802

2126

651

2803

2804

2130

2804

2130

655

2805

2806

2134

2806

2134

659

2807

2808

2138

2808

2138

663

2809

2810

2142

2810

2142

667

2811

2812

2146

2812

2146

671

2813

2814

2150

2814

2150

675

2815

2816

2154

2816

2154

679

2817

2818

2158

2818

2158

683

2819

2820

2162

30

13

12

33

2822

1511

2822

1511

1510

2494

2823

1515

2823

1515

1514

2496

2824

1519

2824

1519

1518

2498

2825

1523

2825

1523

1522

2500

2826

1527

2826

1527

1526

2502

2827

1531

2827

1531

1530

2504

2828

1535

2828

1535

1534

2506

2829

1539

2829

1539

1538

2508

2830

1543

2830

1543

1542

2510

2831

1547

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1546 1503 1550 1504 1554 1505 1558 1506 1562 1507 1566 1508 1570 1509 1574 1510 1578 1511 1582 1512 1586 1513 1590 1514 1594 1515 1598 1516 1602 1517 1606 1518 1610 1519 1614 1520 1618 1521 1622 1522 1626 1523 1630 1524 1634 1525 1638 1526 1642 1527 1646 1528 1650 1529 1654 1530 1658 1531 1662 1532 1666 1533 1670 1534 1674 1615 1998 1616 2002

Altair Engineering

2512 2 2514 2 2516 2 2518 2 2520 2 2522 2 2524 2 2526 2 2528 2 2530 2 2532 2 2534 2 2536 2 2538 2 2540 2 2542 2 2544 2 2546 2 2548 2 2550 2 2552 2 2554 2 2556 2 2558 2 2560 2 2562 2 2564 2 2566 2 2568 2 2570 2 2572 2 2574 2 2576 2 2738 2 2740

2831

1547

1546

2512

2832

1551

2832

1551

1550

2514

2833

1555

2833

1555

1554

2516

2834

1559

2834

1559

1558

2518

2835

1563

2835

1563

1562

2520

2836

1567

2836

1567

1566

2522

2837

1571

2837

1571

1570

2524

2838

1575

2838

1575

1574

2526

2839

1579

2839

1579

1578

2528

2840

1583

2840

1583

1582

2530

2841

1587

2841

1587

1586

2532

2842

1591

2842

1591

1590

2534

2843

1595

2843

1595

1594

2536

2844

1599

2844

1599

1598

2538

2845

1603

2845

1603

1602

2540

2846

1607

2846

1607

1606

2542

2847

1611

2847

1611

1610

2544

2848

1615

2848

1615

1614

2546

2849

1619

2849

1619

1618

2548

2850

1623

2850

1623

1622

2550

2851

1627

2851

1627

1626

2552

2852

1631

2852

1631

1630

2554

2853

1635

2853

1635

1634

2556

2854

1639

2854

1639

1638

2558

2855

1643

2855

1643

1642

2560

2856

1647

2856

1647

1646

2562

2857

1651

2857

1651

1650

2564

2858

1655

2858

1655

1654

2566

2859

1659

2859

1659

1658

2568

2860

1663

2860

1663

1662

2570

2861

1667

2861

1667

1666

2572

2862

1671

2862

1671

1670

2574

2863

1675

2863

1675

1674

2576

2944

1999

2944

1999

1998

2738

2945

2003

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

399

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

400

1617 2006 1618 2010 1619 2014 1620 2018 1621 2022 1622 2026 1623 2030 1624 2034 1625 2038 1626 2042 1627 2046 1628 2050 1629 2054 1630 2058 1631 2062 1632 2066 1633 2070 1634 2074 1635 2078 1636 2082 1637 2086 1638 2090 1639 2094 1640 2098 1641 2102 1642 2106 1643 2110 1644 2114 1645 2118 1646 2122 1647 2126 1648 2130 1649 2134 1650 2138 1651

2 2742 2 2744 2 2746 2 2748 2 2750 2 2752 2 2754 2 2756 2 2758 2 2760 2 2762 2 2764 2 2766 2 2768 2 2770 2 2772 2 2774 2 2776 2 2778 2 2780 2 2782 2 2784 2 2786 2 2788 2 2790 2 2792 2 2794 2 2796 2 2798 2 2800 2 2802 2 2804 2 2806 2 2808 2

2945

2003

2002

2740

2946

2007

2946

2007

2006

2742

2947

2011

2947

2011

2010

2744

2948

2015

2948

2015

2014

2746

2949

2019

2949

2019

2018

2748

2950

2023

2950

2023

2022

2750

2951

2027

2951

2027

2026

2752

2952

2031

2952

2031

2030

2754

2953

2035

2953

2035

2034

2756

2954

2039

2954

2039

2038

2758

2955

2043

2955

2043

2042

2760

2956

2047

2956

2047

2046

2762

2957

2051

2957

2051

2050

2764

2958

2055

2958

2055

2054

2766

2959

2059

2959

2059

2058

2768

2960

2063

2960

2063

2062

2770

2961

2067

2961

2067

2066

2772

2962

2071

2962

2071

2070

2774

2963

2075

2963

2075

2074

2776

2964

2079

2964

2079

2078

2778

2965

2083

2965

2083

2082

2780

2966

2087

2966

2087

2086

2782

2967

2091

2967

2091

2090

2784

2968

2095

2968

2095

2094

2786

2969

2099

2969

2099

2098

2788

2970

2103

2970

2103

2102

2790

2971

2107

2971

2107

2106

2792

2972

2111

2972

2111

2110

2794

2973

2115

2973

2115

2114

2796

2974

2119

2974

2119

2118

2798

2975

2123

2975

2123

2122

2800

2976

2127

2976

2127

2126

2802

2977

2131

2977

2131

2130

2804

2978

2135

2978

2135

2134

2806

2979

2139

2979

2139

2138

2808

2980

2143

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2142 1652 2146 1653 2150 1654 2154 1655 2158 1656 2162 1657 2495 1658 2497 1659 2499 1660 2501 1661 2503 1662 2505 1663 2507 1664 2509 1665 2511 1666 2513 1667 2515 1668 2517 1669 2519 1670 2521 1671 2523 1672 2525 1673 2527 1674 2529 1675 2531 1676 2533 1677 2535 1678 2537 1679 2539 1680 2541 1681 2543 1682 2545 1683 2547 1684 2549 1685 2551

Altair Engineering

2810 2 2812 2 2814 2 2816 2 2818 2 2820 2 2987 2 2989 2 2991 2 2993 2 2995 2 2997 2 2999 2 3001 2 3003 2 3005 2 3007 2 3009 2 3011 2 3013 2 3015 2 3017 2 3019 2 3021 2 3023 2 3025 2 3027 2 3029 2 3031 2 3033 2 3035 2 3037 2 3039 2 3041 2 3043

2980

2143

2142

2810

2981

2147

2981

2147

2146

2812

2982

2151

2982

2151

2150

2814

2983

2155

2983

2155

2154

2816

2984

2159

2984

2159

2158

2818

2985

2163

28

33

31

27

2986

2494

2986

2494

2495

2987

2988

2496

2988

2496

2497

2989

2990

2498

2990

2498

2499

2991

2992

2500

2992

2500

2501

2993

2994

2502

2994

2502

2503

2995

2996

2504

2996

2504

2505

2997

2998

2506

2998

2506

2507

2999

3000

2508

3000

2508

2509

3001

3002

2510

3002

2510

2511

3003

3004

2512

3004

2512

2513

3005

3006

2514

3006

2514

2515

3007

3008

2516

3008

2516

2517

3009

3010

2518

3010

2518

2519

3011

3012

2520

3012

2520

2521

3013

3014

2522

3014

2522

2523

3015

3016

2524

3016

2524

2525

3017

3018

2526

3018

2526

2527

3019

3020

2528

3020

2528

2529

3021

3022

2530

3022

2530

2531

3023

3024

2532

3024

2532

2533

3025

3026

2534

3026

2534

2535

3027

3028

2536

3028

2536

2537

3029

3030

2538

3030

2538

2539

3031

3032

2540

3032

2540

2541

3033

3034

2542

3034

2542

2543

3035

3036

2544

3036

2544

2545

3037

3038

2546

3038

2546

2547

3039

3040

2548

3040

2548

2549

3041

3042

2550

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

401

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

402

1686 2553 1687 2555 1688 2557 1689 2559 1690 2561 1691 2563 1692 2565 1693 2567 1694 2569 1695 2571 1696 2573 1697 2575 1698 2577 1779 2739 1780 2741 1781 2743 1782 2745 1783 2747 1784 2749 1785 2751 1786 2753 1787 2755 1788 2757 1789 2759 1790 2761 1791 2763 1792 2765 1793 2767 1794 2769 1795 2771 1796 2773 1797 2775 1798 2777 1799 2779 1800

2 3045 2 3047 2 3049 2 3051 2 3053 2 3055 2 3057 2 3059 2 3061 2 3063 2 3065 2 3067 2 3069 2 3231 2 3233 2 3235 2 3237 2 3239 2 3241 2 3243 2 3245 2 3247 2 3249 2 3251 2 3253 2 3255 2 3257 2 3259 2 3261 2 3263 2 3265 2 3267 2 3269 2 3271 2

3042

2550

2551

3043

3044

2552

3044

2552

2553

3045

3046

2554

3046

2554

2555

3047

3048

2556

3048

2556

2557

3049

3050

2558

3050

2558

2559

3051

3052

2560

3052

2560

2561

3053

3054

2562

3054

2562

2563

3055

3056

2564

3056

2564

2565

3057

3058

2566

3058

2566

2567

3059

3060

2568

3060

2568

2569

3061

3062

2570

3062

2570

2571

3063

3064

2572

3064

2572

2573

3065

3066

2574

3066

2574

2575

3067

3068

2576

3068

2576

2577

3069

3230

2738

3230

2738

2739

3231

3232

2740

3232

2740

2741

3233

3234

2742

3234

2742

2743

3235

3236

2744

3236

2744

2745

3237

3238

2746

3238

2746

2747

3239

3240

2748

3240

2748

2749

3241

3242

2750

3242

2750

2751

3243

3244

2752

3244

2752

2753

3245

3246

2754

3246

2754

2755

3247

3248

2756

3248

2756

2757

3249

3250

2758

3250

2758

2759

3251

3252

2760

3252

2760

2761

3253

3254

2762

3254

2762

2763

3255

3256

2764

3256

2764

2765

3257

3258

2766

3258

2766

2767

3259

3260

2768

3260

2768

2769

3261

3262

2770

3262

2770

2771

3263

3264

2772

3264

2772

2773

3265

3266

2774

3266

2774

2775

3267

3268

2776

3268

2776

2777

3269

3270

2778

3270

2778

2779

3271

3272

2780

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2781 1801 2783 1802 2785 1803 2787 1804 2789 1805 2791 1806 2793 1807 2795 1808 2797 1809 2799 1810 2801 1811 2803 1812 2805 1813 2807 1814 2809 1815 2811 1816 2813 1817 2815 1818 2817 1819 2819 1820 2821 1821 2494 1822 2496 1823 2498 1824 2500 1825 2502 1826 2504 1827 2506 1828 2508 1829 2510 1830 2512 1831 2514 1832 2516 1833 2518 1834 2520

Altair Engineering

3273 2 3275 2 3277 2 3279 2 3281 2 3283 2 3285 2 3287 2 3289 2 3291 2 3293 2 3295 2 3297 2 3299 2 3301 2 3303 2 3305 2 3307 2 3309 2 3311 2 3313 2 2986 2 2988 2 2990 2 2992 2 2994 2 2996 2 2998 2 3000 2 3002 2 3004 2 3006 2 3008 2 3010 2 3012

3272

2780

2781

3273

3274

2782

3274

2782

2783

3275

3276

2784

3276

2784

2785

3277

3278

2786

3278

2786

2787

3279

3280

2788

3280

2788

2789

3281

3282

2790

3282

2790

2791

3283

3284

2792

3284

2792

2793

3285

3286

2794

3286

2794

2795

3287

3288

2796

3288

2796

2797

3289

3290

2798

3290

2798

2799

3291

3292

2800

3292

2800

2801

3293

3294

2802

3294

2802

2803

3295

3296

2804

3296

2804

2805

3297

3298

2806

3298

2806

2807

3299

3300

2808

3300

2808

2809

3301

3302

2810

3302

2810

2811

3303

3304

2812

3304

2812

2813

3305

3306

2814

3306

2814

2815

3307

3308

2816

3308

2816

2817

3309

3310

2818

3310

2818

2819

3311

3312

2820

29

30

33

28

3314

2822

3314

2822

2494

2986

3315

2823

3315

2823

2496

2988

3316

2824

3316

2824

2498

2990

3317

2825

3317

2825

2500

2992

3318

2826

3318

2826

2502

2994

3319

2827

3319

2827

2504

2996

3320

2828

3320

2828

2506

2998

3321

2829

3321

2829

2508

3000

3322

2830

3322

2830

2510

3002

3323

2831

3323

2831

2512

3004

3324

2832

3324

2832

2514

3006

3325

2833

3325

2833

2516

3008

3326

2834

3326

2834

2518

3010

3327

2835

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

403

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

404

1835 2522 1836 2524 1837 2526 1838 2528 1839 2530 1840 2532 1841 2534 1842 2536 1843 2538 1844 2540 1845 2542 1846 2544 1847 2546 1848 2548 1849 2550 1850 2552 1851 2554 1852 2556 1853 2558 1854 2560 1855 2562 1856 2564 1857 2566 1858 2568 1859 2570 1860 2572 1861 2574 1862 2576 1943 2738 1944 2740 1945 2742 1946 2744 1947 2746 1948 2748 1949

2 3014 2 3016 2 3018 2 3020 2 3022 2 3024 2 3026 2 3028 2 3030 2 3032 2 3034 2 3036 2 3038 2 3040 2 3042 2 3044 2 3046 2 3048 2 3050 2 3052 2 3054 2 3056 2 3058 2 3060 2 3062 2 3064 2 3066 2 3068 2 3230 2 3232 2 3234 2 3236 2 3238 2 3240 2

3327

2835

2520

3012

3328

2836

3328

2836

2522

3014

3329

2837

3329

2837

2524

3016

3330

2838

3330

2838

2526

3018

3331

2839

3331

2839

2528

3020

3332

2840

3332

2840

2530

3022

3333

2841

3333

2841

2532

3024

3334

2842

3334

2842

2534

3026

3335

2843

3335

2843

2536

3028

3336

2844

3336

2844

2538

3030

3337

2845

3337

2845

2540

3032

3338

2846

3338

2846

2542

3034

3339

2847

3339

2847

2544

3036

3340

2848

3340

2848

2546

3038

3341

2849

3341

2849

2548

3040

3342

2850

3342

2850

2550

3042

3343

2851

3343

2851

2552

3044

3344

2852

3344

2852

2554

3046

3345

2853

3345

2853

2556

3048

3346

2854

3346

2854

2558

3050

3347

2855

3347

2855

2560

3052

3348

2856

3348

2856

2562

3054

3349

2857

3349

2857

2564

3056

3350

2858

3350

2858

2566

3058

3351

2859

3351

2859

2568

3060

3352

2860

3352

2860

2570

3062

3353

2861

3353

2861

2572

3064

3354

2862

3354

2862

2574

3066

3355

2863

3355

2863

2576

3068

3436

2944

3436

2944

2738

3230

3437

2945

3437

2945

2740

3232

3438

2946

3438

2946

2742

3234

3439

2947

3439

2947

2744

3236

3440

2948

3440

2948

2746

3238

3441

2949

3441

2949

2748

3240

3442

2950

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2750 1950 2752 1951 2754 1952 2756 1953 2758 1954 2760 1955 2762 1956 2764 1957 2766 1958 2768 1959 2770 1960 2772 1961 2774 1962 2776 1963 2778 1964 2780 1965 2782 1966 2784 1967 2786 1968 2788 1969 2790 1970 2792 1971 2794 1972 2796 1973 2798 1974 2800 1975 2802 1976 2804 1977 2806 1978 2808 1979 2810 1980 2812 1981 2814 1982 2816 1983 2818

Altair Engineering

3242 2 3244 2 3246 2 3248 2 3250 2 3252 2 3254 2 3256 2 3258 2 3260 2 3262 2 3264 2 3266 2 3268 2 3270 2 3272 2 3274 2 3276 2 3278 2 3280 2 3282 2 3284 2 3286 2 3288 2 3290 2 3292 2 3294 2 3296 2 3298 2 3300 2 3302 2 3304 2 3306 2 3308 2 3310

3442

2950

2750

3242

3443

2951

3443

2951

2752

3244

3444

2952

3444

2952

2754

3246

3445

2953

3445

2953

2756

3248

3446

2954

3446

2954

2758

3250

3447

2955

3447

2955

2760

3252

3448

2956

3448

2956

2762

3254

3449

2957

3449

2957

2764

3256

3450

2958

3450

2958

2766

3258

3451

2959

3451

2959

2768

3260

3452

2960

3452

2960

2770

3262

3453

2961

3453

2961

2772

3264

3454

2962

3454

2962

2774

3266

3455

2963

3455

2963

2776

3268

3456

2964

3456

2964

2778

3270

3457

2965

3457

2965

2780

3272

3458

2966

3458

2966

2782

3274

3459

2967

3459

2967

2784

3276

3460

2968

3460

2968

2786

3278

3461

2969

3461

2969

2788

3280

3462

2970

3462

2970

2790

3282

3463

2971

3463

2971

2792

3284

3464

2972

3464

2972

2794

3286

3465

2973

3465

2973

2796

3288

3466

2974

3466

2974

2798

3290

3467

2975

3467

2975

2800

3292

3468

2976

3468

2976

2802

3294

3469

2977

3469

2977

2804

3296

3470

2978

3470

2978

2806

3298

3471

2979

3471

2979

2808

3300

3472

2980

3472

2980

2810

3302

3473

2981

3473

2981

2812

3304

3474

2982

3474

2982

2814

3306

3475

2983

3475

2983

2816

3308

3476

2984

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

405

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

406

1984 2820 1985 690 1986 692 1987 694 1988 696 1989 698 1990 700 1991 702 1992 704 1993 706 1994 708 1995 710 1996 712 1997 714 1998 716 1999 718 2000 720 2001 722 2002 724 2003 726 2004 728 2005 730 2006 732 2007 734 2008 736 2009 738 2010 740 2011 742 2012 744 2013 746 2014 748 2015 750 2016 752 2017 754 2018

2 3312 2 3479 2 3481 2 3483 2 3485 2 3487 2 3489 2 3491 2 3493 2 3495 2 3497 2 3499 2 3501 2 3503 2 3505 2 3507 2 3509 2 3511 2 3513 2 3515 2 3517 2 3519 2 3521 2 3523 2 3525 2 3527 2 3529 2 3531 2 3533 2 3535 2 3537 2 3539 2 3541 2 3543 2

3476

2984

2818

3310

3477

2985

32

10

9

24

3478

34

3478

34

690

3479

3480

38

3480

38

692

3481

3482

42

3482

42

694

3483

3484

46

3484

46

696

3485

3486

50

3486

50

698

3487

3488

54

3488

54

700

3489

3490

58

3490

58

702

3491

3492

62

3492

62

704

3493

3494

66

3494

66

706

3495

3496

70

3496

70

708

3497

3498

74

3498

74

710

3499

3500

78

3500

78

712

3501

3502

82

3502

82

714

3503

3504

86

3504

86

716

3505

3506

90

3506

90

718

3507

3508

94

3508

94

720

3509

3510

98

3510

98

722

3511

3512

102

3512

102

724

3513

3514

106

3514

106

726

3515

3516

110

3516

110

728

3517

3518

114

3518

114

730

3519

3520

118

3520

118

732

3521

3522

122

3522

122

734

3523

3524

126

3524

126

736

3525

3526

130

3526

130

738

3527

3528

134

3528

134

740

3529

3530

138

3530

138

742

3531

3532

142

3532

142

744

3533

3534

146

3534

146

746

3535

3536

150

3536

150

748

3537

3538

154

3538

154

750

3539

3540

158

3540

158

752

3541

3542

162

3542

162

754

3543

3544

166

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

756 2019 758 2020 760 2021 762 2022 764 2023 766 2024 768 2025 770 2026 772 2107 934 2108 936 2109 938 2110 940 2111 942 2112 944 2113 946 2114 948 2115 950 2116 952 2117 954 2118 956 2119 958 2120 960 2121 962 2122 964 2123 966 2124 968 2125 970 2126 972 2127 974 2128 976 2129 978 2130 980 2131 982 2132 984

Altair Engineering

3545 2 3547 2 3549 2 3551 2 3553 2 3555 2 3557 2 3559 2 3561 2 3723 2 3725 2 3727 2 3729 2 3731 2 3733 2 3735 2 3737 2 3739 2 3741 2 3743 2 3745 2 3747 2 3749 2 3751 2 3753 2 3755 2 3757 2 3759 2 3761 2 3763 2 3765 2 3767 2 3769 2 3771 2 3773

3544

166

756

3545

3546

170

3546

170

758

3547

3548

174

3548

174

760

3549

3550

178

3550

178

762

3551

3552

182

3552

182

764

3553

3554

186

3554

186

766

3555

3556

190

3556

190

768

3557

3558

194

3558

194

770

3559

3560

198

3560

198

772

3561

3722

522

3722

522

934

3723

3724

526

3724

526

936

3725

3726

530

3726

530

938

3727

3728

534

3728

534

940

3729

3730

538

3730

538

942

3731

3732

542

3732

542

944

3733

3734

546

3734

546

946

3735

3736

550

3736

550

948

3737

3738

554

3738

554

950

3739

3740

558

3740

558

952

3741

3742

562

3742

562

954

3743

3744

566

3744

566

956

3745

3746

570

3746

570

958

3747

3748

574

3748

574

960

3749

3750

578

3750

578

962

3751

3752

582

3752

582

964

3753

3754

586

3754

586

966

3755

3756

590

3756

590

968

3757

3758

594

3758

594

970

3759

3760

598

3760

598

972

3761

3762

602

3762

602

974

3763

3764

606

3764

606

976

3765

3766

610

3766

610

978

3767

3768

614

3768

614

980

3769

3770

618

3770

618

982

3771

3772

622

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

407

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

408

2133 986 2134 988 2135 990 2136 992 2137 994 2138 996 2139 998 2140 1000 2141 1002 2142 1004 2143 1006 2144 1008 2145 1010 2146 1012 2147 1014 2148 1016 2149 34 2150 38 2151 42 2152 46 2153 50 2154 54 2155 58 2156 62 2157 66 2158 70 2159 74 2160 78 2161 82 2162 86 2163 90 2164 94 2165 98 2166 102 2167

2 3775 2 3777 2 3779 2 3781 2 3783 2 3785 2 3787 2 3789 2 3791 2 3793 2 3795 2 3797 2 3799 2 3801 2 3803 2 3805 2 3478 2 3480 2 3482 2 3484 2 3486 2 3488 2 3490 2 3492 2 3494 2 3496 2 3498 2 3500 2 3502 2 3504 2 3506 2 3508 2 3510 2 3512 2

3772

622

984

3773

3774

626

3774

626

986

3775

3776

630

3776

630

988

3777

3778

634

3778

634

990

3779

3780

638

3780

638

992

3781

3782

642

3782

642

994

3783

3784

646

3784

646

996

3785

3786

650

3786

650

998

3787

3788

654

3788

654

1000

3789

3790

658

3790

658

1002

3791

3792

662

3792

662

1004

3793

3794

666

3794

666

1006

3795

3796

670

3796

670

1008

3797

3798

674

3798

674

1010

3799

3800

678

3800

678

1012

3801

3802

682

3802

682

1014

3803

3804

686

31

11

10

32

2495

35

2495

35

34

3478

2497

39

2497

39

38

3480

2499

43

2499

43

42

3482

2501

47

2501

47

46

3484

2503

51

2503

51

50

3486

2505

55

2505

55

54

3488

2507

59

2507

59

58

3490

2509

63

2509

63

62

3492

2511

67

2511

67

66

3494

2513

71

2513

71

70

3496

2515

75

2515

75

74

3498

2517

79

2517

79

78

3500

2519

83

2519

83

82

3502

2521

87

2521

87

86

3504

2523

91

2523

91

90

3506

2525

95

2525

95

94

3508

2527

99

2527

99

98

3510

2529

103

2529

103

102

3512

2531

107

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

106 2168 110 2169 114 2170 118 2171 122 2172 126 2173 130 2174 134 2175 138 2176 142 2177 146 2178 150 2179 154 2180 158 2181 162 2182 166 2183 170 2184 174 2185 178 2186 182 2187 186 2188 190 2189 194 2190 198 2271 522 2272 526 2273 530 2274 534 2275 538 2276 542 2277 546 2278 550 2279 554 2280 558 2281 562

Altair Engineering

3514 2 3516 2 3518 2 3520 2 3522 2 3524 2 3526 2 3528 2 3530 2 3532 2 3534 2 3536 2 3538 2 3540 2 3542 2 3544 2 3546 2 3548 2 3550 2 3552 2 3554 2 3556 2 3558 2 3560 2 3722 2 3724 2 3726 2 3728 2 3730 2 3732 2 3734 2 3736 2 3738 2 3740 2 3742

2531

107

106

3514

2533

111

2533

111

110

3516

2535

115

2535

115

114

3518

2537

119

2537

119

118

3520

2539

123

2539

123

122

3522

2541

127

2541

127

126

3524

2543

131

2543

131

130

3526

2545

135

2545

135

134

3528

2547

139

2547

139

138

3530

2549

143

2549

143

142

3532

2551

147

2551

147

146

3534

2553

151

2553

151

150

3536

2555

155

2555

155

154

3538

2557

159

2557

159

158

3540

2559

163

2559

163

162

3542

2561

167

2561

167

166

3544

2563

171

2563

171

170

3546

2565

175

2565

175

174

3548

2567

179

2567

179

178

3550

2569

183

2569

183

182

3552

2571

187

2571

187

186

3554

2573

191

2573

191

190

3556

2575

195

2575

195

194

3558

2577

199

2577

199

198

3560

2739

523

2739

523

522

3722

2741

527

2741

527

526

3724

2743

531

2743

531

530

3726

2745

535

2745

535

534

3728

2747

539

2747

539

538

3730

2749

543

2749

543

542

3732

2751

547

2751

547

546

3734

2753

551

2753

551

550

3736

2755

555

2755

555

554

3738

2757

559

2757

559

558

3740

2759

563

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

409

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

410

2282 566 2283 570 2284 574 2285 578 2286 582 2287 586 2288 590 2289 594 2290 598 2291 602 2292 606 2293 610 2294 614 2295 618 2296 622 2297 626 2298 630 2299 634 2300 638 2301 642 2302 646 2303 650 2304 654 2305 658 2306 662 2307 666 2308 670 2309 674 2310 678 2311 682 2312 686 2313 3479 2314 3481 2315 3483 2316

2 3744 2 3746 2 3748 2 3750 2 3752 2 3754 2 3756 2 3758 2 3760 2 3762 2 3764 2 3766 2 3768 2 3770 2 3772 2 3774 2 3776 2 3778 2 3780 2 3782 2 3784 2 3786 2 3788 2 3790 2 3792 2 3794 2 3796 2 3798 2 3800 2 3802 2 3804 2 3807 2 3809 2 3811 2

2759

563

562

3742

2761

567

2761

567

566

3744

2763

571

2763

571

570

3746

2765

575

2765

575

574

3748

2767

579

2767

579

578

3750

2769

583

2769

583

582

3752

2771

587

2771

587

586

3754

2773

591

2773

591

590

3756

2775

595

2775

595

594

3758

2777

599

2777

599

598

3760

2779

603

2779

603

602

3762

2781

607

2781

607

606

3764

2783

611

2783

611

610

3766

2785

615

2785

615

614

3768

2787

619

2787

619

618

3770

2789

623

2789

623

622

3772

2791

627

2791

627

626

3774

2793

631

2793

631

630

3776

2795

635

2795

635

634

3778

2797

639

2797

639

638

3780

2799

643

2799

643

642

3782

2801

647

2801

647

646

3784

2803

651

2803

651

650

3786

2805

655

2805

655

654

3788

2807

659

2807

659

658

3790

2809

663

2809

663

662

3792

2811

667

2811

667

666

3794

2813

671

2813

671

670

3796

2815

675

2815

675

674

3798

2817

679

2817

679

678

3800

2819

683

2819

683

682

3802

2821

687

26

32

24

25

3806

3478

3806

3478

3479

3807

3808

3480

3808

3480

3481

3809

3810

3482

3810

3482

3483

3811

3812

3484

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

3485 2317 3487 2318 3489 2319 3491 2320 3493 2321 3495 2322 3497 2323 3499 2324 3501 2325 3503 2326 3505 2327 3507 2328 3509 2329 3511 2330 3513 2331 3515 2332 3517 2333 3519 2334 3521 2335 3523 2336 3525 2337 3527 2338 3529 2339 3531 2340 3533 2341 3535 2342 3537 2343 3539 2344 3541 2345 3543 2346 3545 2347 3547 2348 3549 2349 3551 2350 3553

Altair Engineering

3813 2 3815 2 3817 2 3819 2 3821 2 3823 2 3825 2 3827 2 3829 2 3831 2 3833 2 3835 2 3837 2 3839 2 3841 2 3843 2 3845 2 3847 2 3849 2 3851 2 3853 2 3855 2 3857 2 3859 2 3861 2 3863 2 3865 2 3867 2 3869 2 3871 2 3873 2 3875 2 3877 2 3879 2 3881

3812

3484

3485

3813

3814

3486

3814

3486

3487

3815

3816

3488

3816

3488

3489

3817

3818

3490

3818

3490

3491

3819

3820

3492

3820

3492

3493

3821

3822

3494

3822

3494

3495

3823

3824

3496

3824

3496

3497

3825

3826

3498

3826

3498

3499

3827

3828

3500

3828

3500

3501

3829

3830

3502

3830

3502

3503

3831

3832

3504

3832

3504

3505

3833

3834

3506

3834

3506

3507

3835

3836

3508

3836

3508

3509

3837

3838

3510

3838

3510

3511

3839

3840

3512

3840

3512

3513

3841

3842

3514

3842

3514

3515

3843

3844

3516

3844

3516

3517

3845

3846

3518

3846

3518

3519

3847

3848

3520

3848

3520

3521

3849

3850

3522

3850

3522

3523

3851

3852

3524

3852

3524

3525

3853

3854

3526

3854

3526

3527

3855

3856

3528

3856

3528

3529

3857

3858

3530

3858

3530

3531

3859

3860

3532

3860

3532

3533

3861

3862

3534

3862

3534

3535

3863

3864

3536

3864

3536

3537

3865

3866

3538

3866

3538

3539

3867

3868

3540

3868

3540

3541

3869

3870

3542

3870

3542

3543

3871

3872

3544

3872

3544

3545

3873

3874

3546

3874

3546

3547

3875

3876

3548

3876

3548

3549

3877

3878

3550

3878

3550

3551

3879

3880

3552

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

411

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

412

2351 3555 2352 3557 2353 3559 2354 3561 2435 3723 2436 3725 2437 3727 2438 3729 2439 3731 2440 3733 2441 3735 2442 3737 2443 3739 2444 3741 2445 3743 2446 3745 2447 3747 2448 3749 2449 3751 2450 3753 2451 3755 2452 3757 2453 3759 2454 3761 2455 3763 2456 3765 2457 3767 2458 3769 2459 3771 2460 3773 2461 3775 2462 3777 2463 3779 2464 3781 2465

2 3883 2 3885 2 3887 2 3889 2 4051 2 4053 2 4055 2 4057 2 4059 2 4061 2 4063 2 4065 2 4067 2 4069 2 4071 2 4073 2 4075 2 4077 2 4079 2 4081 2 4083 2 4085 2 4087 2 4089 2 4091 2 4093 2 4095 2 4097 2 4099 2 4101 2 4103 2 4105 2 4107 2 4109 2

3880

3552

3553

3881

3882

3554

3882

3554

3555

3883

3884

3556

3884

3556

3557

3885

3886

3558

3886

3558

3559

3887

3888

3560

3888

3560

3561

3889

4050

3722

4050

3722

3723

4051

4052

3724

4052

3724

3725

4053

4054

3726

4054

3726

3727

4055

4056

3728

4056

3728

3729

4057

4058

3730

4058

3730

3731

4059

4060

3732

4060

3732

3733

4061

4062

3734

4062

3734

3735

4063

4064

3736

4064

3736

3737

4065

4066

3738

4066

3738

3739

4067

4068

3740

4068

3740

3741

4069

4070

3742

4070

3742

3743

4071

4072

3744

4072

3744

3745

4073

4074

3746

4074

3746

3747

4075

4076

3748

4076

3748

3749

4077

4078

3750

4078

3750

3751

4079

4080

3752

4080

3752

3753

4081

4082

3754

4082

3754

3755

4083

4084

3756

4084

3756

3757

4085

4086

3758

4086

3758

3759

4087

4088

3760

4088

3760

3761

4089

4090

3762

4090

3762

3763

4091

4092

3764

4092

3764

3765

4093

4094

3766

4094

3766

3767

4095

4096

3768

4096

3768

3769

4097

4098

3770

4098

3770

3771

4099

4100

3772

4100

3772

3773

4101

4102

3774

4102

3774

3775

4103

4104

3776

4104

3776

3777

4105

4106

3778

4106

3778

3779

4107

4108

3780

4108

3780

3781

4109

4110

3782

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

3783 2466 3785 2467 3787 2468 3789 2469 3791 2470 3793 2471 3795 2472 3797 2473 3799 2474 3801 2475 3803 2476 3805 2477 3478 2478 3480 2479 3482 2480 3484 2481 3486 2482 3488 2483 3490 2484 3492 2485 3494 2486 3496 2487 3498 2488 3500 2489 3502 2490 3504 2491 3506 2492 3508 2493 3510 2494 3512 2495 3514 2496 3516 2497 3518 2498 3520 2499 3522

Altair Engineering

4111 2 4113 2 4115 2 4117 2 4119 2 4121 2 4123 2 4125 2 4127 2 4129 2 4131 2 4133 2 3806 2 3808 2 3810 2 3812 2 3814 2 3816 2 3818 2 3820 2 3822 2 3824 2 3826 2 3828 2 3830 2 3832 2 3834 2 3836 2 3838 2 3840 2 3842 2 3844 2 3846 2 3848 2 3850

4110

3782

3783

4111

4112

3784

4112

3784

3785

4113

4114

3786

4114

3786

3787

4115

4116

3788

4116

3788

3789

4117

4118

3790

4118

3790

3791

4119

4120

3792

4120

3792

3793

4121

4122

3794

4122

3794

3795

4123

4124

3796

4124

3796

3797

4125

4126

3798

4126

3798

3799

4127

4128

3800

4128

3800

3801

4129

4130

3802

4130

3802

3803

4131

4132

3804

27

31

32

26

2987

2495

2987

2495

3478

3806

2989

2497

2989

2497

3480

3808

2991

2499

2991

2499

3482

3810

2993

2501

2993

2501

3484

3812

2995

2503

2995

2503

3486

3814

2997

2505

2997

2505

3488

3816

2999

2507

2999

2507

3490

3818

3001

2509

3001

2509

3492

3820

3003

2511

3003

2511

3494

3822

3005

2513

3005

2513

3496

3824

3007

2515

3007

2515

3498

3826

3009

2517

3009

2517

3500

3828

3011

2519

3011

2519

3502

3830

3013

2521

3013

2521

3504

3832

3015

2523

3015

2523

3506

3834

3017

2525

3017

2525

3508

3836

3019

2527

3019

2527

3510

3838

3021

2529

3021

2529

3512

3840

3023

2531

3023

2531

3514

3842

3025

2533

3025

2533

3516

3844

3027

2535

3027

2535

3518

3846

3029

2537

3029

2537

3520

3848

3031

2539

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

413

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

414

2500 3524 2501 3526 2502 3528 2503 3530 2504 3532 2505 3534 2506 3536 2507 3538 2508 3540 2509 3542 2510 3544 2511 3546 2512 3548 2513 3550 2514 3552 2515 3554 2516 3556 2517 3558 2518 3560 2599 3722 2600 3724 2601 3726 2602 3728 2603 3730 2604 3732 2605 3734 2606 3736 2607 3738 2608 3740 2609 3742 2610 3744 2611 3746 2612 3748 2613 3750 2614

2 3852 2 3854 2 3856 2 3858 2 3860 2 3862 2 3864 2 3866 2 3868 2 3870 2 3872 2 3874 2 3876 2 3878 2 3880 2 3882 2 3884 2 3886 2 3888 2 4050 2 4052 2 4054 2 4056 2 4058 2 4060 2 4062 2 4064 2 4066 2 4068 2 4070 2 4072 2 4074 2 4076 2 4078 2

3031

2539

3522

3850

3033

2541

3033

2541

3524

3852

3035

2543

3035

2543

3526

3854

3037

2545

3037

2545

3528

3856

3039

2547

3039

2547

3530

3858

3041

2549

3041

2549

3532

3860

3043

2551

3043

2551

3534

3862

3045

2553

3045

2553

3536

3864

3047

2555

3047

2555

3538

3866

3049

2557

3049

2557

3540

3868

3051

2559

3051

2559

3542

3870

3053

2561

3053

2561

3544

3872

3055

2563

3055

2563

3546

3874

3057

2565

3057

2565

3548

3876

3059

2567

3059

2567

3550

3878

3061

2569

3061

2569

3552

3880

3063

2571

3063

2571

3554

3882

3065

2573

3065

2573

3556

3884

3067

2575

3067

2575

3558

3886

3069

2577

3069

2577

3560

3888

3231

2739

3231

2739

3722

4050

3233

2741

3233

2741

3724

4052

3235

2743

3235

2743

3726

4054

3237

2745

3237

2745

3728

4056

3239

2747

3239

2747

3730

4058

3241

2749

3241

2749

3732

4060

3243

2751

3243

2751

3734

4062

3245

2753

3245

2753

3736

4064

3247

2755

3247

2755

3738

4066

3249

2757

3249

2757

3740

4068

3251

2759

3251

2759

3742

4070

3253

2761

3253

2761

3744

4072

3255

2763

3255

2763

3746

4074

3257

2765

3257

2765

3748

4076

3259

2767

3259

2767

3750

4078

3261

2769

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ 3752 4080 CHEXA 2615 2 3261 2769 3752 4080 3263 2771 + 3754 4082 CHEXA 2616 2 3263 2771 3754 4082 3265 2773 + 3756 4084 CHEXA 2617 2 3265 2773 3756 4084 3267 2775 + 3758 4086 CHEXA 2618 2 3267 2775 3758 4086 3269 2777 + 3760 4088 CHEXA 2619 2 3269 2777 3760 4088 3271 2779 + 3762 4090 CHEXA 2620 2 3271 2779 3762 4090 3273 2781 + 3764 4092 CHEXA 2621 2 3273 2781 3764 4092 3275 2783 + 3766 4094 CHEXA 2622 2 3275 2783 3766 4094 3277 2785 + 3768 4096 CHEXA 2623 2 3277 2785 3768 4096 3279 2787 + 3770 4098 CHEXA 2624 2 3279 2787 3770 4098 3281 2789 + 3772 4100 CHEXA 2625 2 3281 2789 3772 4100 3283 2791 + 3774 4102 CHEXA 2626 2 3283 2791 3774 4102 3285 2793 + 3776 4104 CHEXA 2627 2 3285 2793 3776 4104 3287 2795 + 3778 4106 CHEXA 2628 2 3287 2795 3778 4106 3289 2797 + 3780 4108 CHEXA 2629 2 3289 2797 3780 4108 3291 2799 + 3782 4110 CHEXA 2630 2 3291 2799 3782 4110 3293 2801 + 3784 4112 CHEXA 2631 2 3293 2801 3784 4112 3295 2803 + 3786 4114 CHEXA 2632 2 3295 2803 3786 4114 3297 2805 + 3788 4116 CHEXA 2633 2 3297 2805 3788 4116 3299 2807 + 3790 4118 CHEXA 2634 2 3299 2807 3790 4118 3301 2809 + 3792 4120 CHEXA 2635 2 3301 2809 3792 4120 3303 2811 + 3794 4122 CHEXA 2636 2 3303 2811 3794 4122 3305 2813 + 3796 4124 CHEXA 2637 2 3305 2813 3796 4124 3307 2815 + 3798 4126 CHEXA 2638 2 3307 2815 3798 4126 3309 2817 + 3800 4128 CHEXA 2639 2 3309 2817 3800 4128 3311 2819 + 3802 4130 CHEXA 2640 2 3311 2819 3802 4130 3313 2821 + 3804 4132 $ $HMMOVE 2 $ 17THRU 58 139THRU 222 303THRU 386 $ 467THRU 550 631THRU 714 795THRU 878 $ 959THRU 1042 1123THRU 1206 1287THRU 1370 $ 1451THRU 1534 1615THRU 1698 1779THRU 1862 $ 1943THRU 2026 2107THRU 2190 2271THRU 2354 $ 2435THRU 2518 2599THRU 2640 $ $$ $$------------------------------------------------------------------------------$ $$ HyperMesh name and color information for generic components $ $$------------------------------------------------------------------------------$ $HMNAME COMP 2"Air" 2 "Air" 5 $HWCOLOR COMP 2 5 $

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

415

$HMNAME COMP $HWCOLOR COMP $ $HMNAME COMP $HWCOLOR COMP $ $ $HMDPRP $ 17THRU $ 467THRU $ 959THRU $ 1451THRU $ 1943THRU $ 2435THRU $ 6122 6125 $ 7647 7652 $

5"Piston" 5 8 6"absorber" 6 3

58 139THRU 550 631THRU 1042 1123THRU 1534 1615THRU 2026 2107THRU 2518 2599THRU 6520THRU 6521 7945 7948 7955

222 714 1206 1698 2190 2640 6523

303THRU 795THRU 1287THRU 1779THRU 2271THRU 5627 5629 6528 6954

386 878 1370 1862 2354 6116 7220

$ $$ $$ PSHELL Data $$ $ $ $ $ $ $ $ $HMNAME PROP 1"tube" 4 $HWCOLOR PROP 1 52 PSHELL 1 20.1 2 2 0.0 $$ $$ PSOLID Data $$ $HMNAME PROP 2"Air" 5 $HWCOLOR PROP 2 4 PSOLID 2 1 PFLUID $$ $$ MAT1 Data $$ $HMNAME MAT 2"alum" "MAT1" $HWCOLOR MAT 2 3 MAT1 21.0+7 0.3 0.000254 $$ $$ MAT10 Data $HMNAME MAT 1"Air" "MAT10" $HWCOLOR MAT 1 3 MAT10 1 1.21-7 13000.0 $$ $$------------------------------------------------------------------------------$ $$ HyperMesh Commands for loadcollectors name and color information $ $$------------------------------------------------------------------------------$ $HMNAME LOADCOL 2"spc" $HWCOLOR LOADCOL 2 6 $$ $HMNAME LOADCOL 8"Force" $HWCOLOR LOADCOL 8 7 $$ $HMNAME LOADCOL 12"SPC" $HWCOLOR LOADCOL 12 5 $$ $$ $$ FREQi cards $$ $HMNAME LOADCOL 3"Freq" $HWCOLOR LOADCOL 3 6 $FREQ1 3 0.0 5.0 600 FREQ 3480.

416

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

$ $$ $$ RLOAD1 cards $$ $HMNAME LOADCOL 6"Rload" $HWCOLOR LOADCOL 6 6 RLOAD1 6 8 $$ $$ $$ TABLED1 cards $$ $HMNAME LOADCOL 7"Table" $HWCOLOR LOADCOL 7 6 TABLED1 7 LINEAR LINEAR + 0.0 1.0 3000.0 1.0ENDT $$ $HMNAME LOADCOL 10"reactance" $HWCOLOR LOADCOL 10 5 TABLED1 10 LINEAR LINEAR + 0.0 0.00154 3000.0 0.00154ENDT $$ $HMNAME LOADCOL 11"Impedance" $HWCOLOR LOADCOL 11 5 TABLED1 11 LINEAR LINEAR + 0.0 0.0 3000.0 0.0ENDT $$ $$ $$ DLOAD cards $$ $HMNAME LOADCOL 9"Dload" $HWCOLOR LOADCOL 9 6 DLOAD 91.0 1.0 6 $$ $$ EIGRL cards $$ $HMNAME LOADCOL 4"EigrlTube" $HWCOLOR LOADCOL 4 6 EIGRL 4 5 $HMNAME LOADCOL 5"EigrlAir" $HWCOLOR LOADCOL 5 6 EIGRL 5 30 $$ $$ SPC Data $$ SPC1 12123456 6776 thru 6800 spcd 86776 3 1.0 spcd 86777 3 1.0 spcd 86778 3 1.0 spcd 86779 3 1.0 spcd 86780 3 1.0 spcd 86781 3 1.0 spcd 86782 3 1.0 spcd 86783 3 1.0 spcd 86784 3 1.0 spcd 86785 3 1.0 spcd 86786 3 1.0 spcd 86788 3 1.0 spcd 86789 3 1.0 spcd 86790 3 1.0 spcd 86791 3 1.0 spcd 86792 3 1.0 spcd 86793 3 1.0 spcd 86794 3 1.0 spcd 86795 3 1.0 spcd 86796 3 1.0 spcd 86797 3 1.0 spcd 86798 3 1.0 spcd 86799 3 1.0 spcd 86800 3 1.0

Altair Engineering

7

0

VELO

MASS MASS

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$ $ DAREA Data $ $$ $$ DAREA Data $$ DAREA 8 6798 3-15.0 $$ $$ CAABSF 7957 5 689 688 687 686 CAABSF 7960 5 1017 689 686 1016 CAABSF 7964 5 1345 1344 688 689 CAABSF 7969 5 1509 1345 689 1017 CAABSF 7972 5 2165 2164 2163 2162 CAABSF 7977 5 688 2165 2162 687 CAABSF 7978 5 4133 3805 3804 4132 CAABSF 7980 5 2493 2492 2164 2165 CAABSF 7984 5 1344 2493 2165 688 CAABSF 7985 5 2821 687 2162 2820 CAABSF 7988 5 2820 2162 2163 2985 CAABSF 7990 5 3313 2821 2820 3312 CAABSF 7994 5 3312 2820 2985 3477 CAABSF 7996 5 3805 1016 686 3804 CAABSF 7998 5 3804 686 687 2821 CAABSF 8003 5 4132 3804 2821 3313 PAABSF 5 11 10 ENDDATA $$ $$------------------------------------------------------------------------------$$ $$ Data Definition for AutoDV $$ $$------------------------------------------------------------------------------$$ $$ $$-----------------------------------------------------------------------------$$ $$ Design Variables Card for Control Perturbations $$ $$-----------------------------------------------------------------------------$$ $ $------------------------------------------------------------------------------$ $ Domain Element Definitions $ $------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$$ $$ Nodeset Definitions $$ $$------------------------------------------------------------------------------$$ $$ Design domain node sets $$ $$------------------------------------------------------------------------------$$ $$ Control Perturbation $$ $$------------------------------------------------------------------------------$$ $$ $$ $$ CONTROL PERTURBATION Data $$

ALTDOCTAG "0mjpRI@DXd^3_0ASnbi`;l;q6A23R@9_67hgW8R?OiZ] Eq:PeN``A;WXh3ITgJeq5NZRd5jSHQK3X@:`a12;n4qD_I^RYMo" ADI0.1.0 2011-02-11T20:16:20 0of1 OSQA ENDDOCTAG

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Comments 1.

Element identification numbers should be unique with respect to all other element identification numbers.

2.

If only G1 is specified, then a point impedance is assumed. If G1 and G2 are specified, then a line impedance is assumed. If G1, G2 and G3 are specified, then an impedance is associated with the area of the triangular face. If G1 through G4 are specified, then an impedance is associated with the quadrilateral face.

3.

The CAABSF element must connect entirely to fluid points on the fluid-structure boundary.

4.

This card is represented as a CAABSF element in HyperMesh.

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CAALOAD Bulk Data Entry CAALOAD – Pressure from CFD Analysis Description The CAALOAD bulk data entry defines the CFD pressure that is transferred to the structural side for frequency response analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

C AALOAD

SID

C AAID

SRFID

AC SC AL

PSC AL

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C AALOAD

110

5

20

1.0

(6)

Field

Contents

SID

Identification number of a dynamic load set.

(7)

(8)

(9)

(10)

No default (Integer > 0) CAAID

Identification number of the H3D file (loadID) specified by ASSIGN,H3DCAA (See comments 1 and 2). Default = no default (Integer > 0)

SRFID

Identification number of a SURF bulk data entry that defines the surface where CFD pressure is applicable (See comment 1). Default = 0 (Integer > 0)

ACSCAL Scale factor of the acoustic source term. Default = 1.0 (Real > 0)

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Field

Contents

PSCAL

Scale factor of CFD pressure. Default = 1.0 (Real > 0)

Comments 1.

The surface GRIDs associated with the CFD pressure must be fluid grids. The pressures from CFD analysis at each loading frequency are stored in an H3D file. This H3D file can be referenced using the ASSIGN I/O Options Entry (ASSIGN, H3DCAA, loadID, and filename).

2.

The pressure from the fluid grids will be transferred to structural grids for frequency response analysis.

3.

CAALOAD can be chosen as a dynamic load in the I/O Options or Subcase Information sections with the command DLOAD = SID.

4.

The SID field in this CAALOAD entry must be unique with respect to other dynamic load sets (ACSRCE, DLOAD, RLOAD1, RLOAD2, TLOAD1, and TLOAD2 entries).

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CBAR Bulk Data Entry CBAR – Simple Beam Element Connection Description The CBAR bulk data entry defines a simple beam element (BAR) of the structural model. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C BAR

EID

PID

GA

GB

X1/G0

X2

X3

OFFT

PA

PB

W1A

W2A

W3A

W1B

W2B

W3B

Example

(1)

(2)

(3)

(4)

(5)

(6)

C BAR

2

39

7

3

13

(7)

(8)

(9)

(10)

513

Field

Contents

EID

Unique element identification number. No default (Integer > 0)

PID

Identification number of a PBAR or PBARL property entry. Default = EID (Integer > 0)

GA,GB

422

Grid point identification numbers of connection points.

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Field

Contents

X1,X2,X3

Components of vector v, at end A, measured at end A, parallel to the components of the displacement coordinate system for GA, or the basic coordinate system, to determine (with the vector from end A to end B) the orientation of the element coordinate system for the BAR element. See comment 5. No default (Real)

G0

Grid point identification number to optionally supply X1, X2, X3. Direction of orientation vector is GA to G0. No default (Integer > 0)

OFFT

Character String specifying the interpretation of the offset vector specification. See comment 5. Default = GGG (Character or blank)

PA,PB

Pin flags for bar ends A and B, respectively. Used to remove connections between the grid point and selected degrees-offreedom of the bar. The degrees-of-freedom are defined in the element’s coordinate system. The bar must have stiffness associated with the PA and PB degrees-of-freedom to be released by the pin flags. For example, if PA=4 is specified, the PBAR entry must have a value for J, the torsion stiffness. No default (Integer > 0; up to 5 of the unique digits 1-6 with no embedded blanks)

W1A,W2A,W3A W1B,W2B,W3B

Components of offset vectors wa and wb in displacement coordinate systems at points GA and GB, respectively, or in the element coordinate system. See comment 5. Default = blank (Real or blank)

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Fig 1: Bar element coordinate system (for C BAR element)

Fig 2: Moments and Internal Forces in the x-y Plane (for a C BAR element)

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Fig 3: Moments and Internal Forces in the x-z Plane (for a C BAR element)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

If there are no pin flags or offsets, the continuation may be omitted.

3.

G0 cannot be located at GA or GB.

4.

If X1/G0 is a positive integer and X2 and X3 are blank, then G0 is used to orient the element, otherwise X1, X2, X3 is used.

5.

The OFFT character string specifies how the offset and orientation vector components are computed. By default, the offset vectors are specified in the Global (local displacement) coordinate system of each grid A and B, and the orientation vector is specified in the Global coordinate system of grid A. Using the codes below, the offset vector can be specified in the element coordinate system and the orientation vector can be specified in the basic coordinate system. The valid character strings and their meanings are shown below: OFFT

Orientation Vector

End A Offset

End B Offset

GGG

Global

Global

Global

BGG

Basic

Global

Global

GGO

Global

Global

Element

BGO

Basic

Global

Element

GOG

Global

Element

Global

BOG

Basic

Element

Global

GOO

Global

Element

Element

BOO

Basic

Element

Element

The element system x-axis is defined from GA to GB. The orientation vector and the element system x-axis are then used to define the z and y axes of the element system. A vector is formed from the cross product of a vector going from Grid A to Grid B and the orientation vector to create the element coordinate z-direction. 6.

Offset vectors are treated like rigid elements. The length of the offset vectors is not affected by thermal loads.

7.

This card is represented as a bar2 element in HyperMesh.

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CBEAM Bulk Data Entry CBEAM – Beam Element Connection Description The CBEAM bulk data entry defines a beam element (BEAM) of the structural model. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C BEAM

EID

PID

GA

GB

X1/G0

X2

X3

OFFT

PA

PB

W1A

W2A

W3A

W1B

W2B

W3B

Example

(1)

(2)

(3)

(4)

(5)

(6)

C BEAM

2

39

7

3

13

513

(7)

(8)

(9)

(10)

3.0

Field

Contents

EID

Unique element identification number. No default (Integer > 0)

PID

Identification number of PBEAM or PBEAML property entry. Default = EID (Integer > 0)

GA,GB

426

Grid point identification numbers of connection points.

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Field

Contents

X1,X2,X3

Components of vector v, at end A, measured at the offset point for end A, parallel to the components of the displacement coordinate system for GA, or the basic coordinate system, to determine (with the vector from offset end A to offset end B) the orientation of the element coordinate system for the beam element. See comment 5. No default (Real; See comment 2)

G0

Grid point identification number to optionally supply X1, X2, X3. Direction of orientation vector is GA to G0. No default (Integer > 0; See comment 2).

OFFT

Character string specifying the interpretation of the offset vector specification. See comment 5. Default = GGG (Character or blank)

PA, PB

Pin flags for beam ends A and B respectively. Used to remove connections between the grid point and selected degrees-of-freedom of the beam. The degrees-of-freedom are defined in the element’s coordinate system and the pin flags are applied at the offset ends of the beam. The beam must have stiffness associated with the PA and PB degrees-of-freedom to be released by the pin flags. For example, if PA=4, the PBEAM entry must have a non-zero value for J, the torsion stiffness. No default (Integer > 0; up to 5 of the unique digits 1-6 with no embedded blanks)

W1A,W2A,W3A, Components of offset vectors, measured in the displacement coordinate systems at grid points A and B or in the element W1B,W2B,W3B coordinate system, from the grid points to the end points of the axis of shear center. See comment 5. Default = blank (Real or blank)

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Fig 1: Beam element coordinate system.

Fig 2: Direction of Internal Forces and Moments (for C BEAM entry)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

If X1/G0 is a positive integer and X2 and X3 are blank, then G0 is used to orient the element, otherwise X1, X2, X3 is used.

3.

G0

4.

If there are no pin flags or offsets the continuation may be omitted.

428

GA or GB.

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5.

The OFFT character string specifies how the offset and orientation vector components are computed. By default, the offset vectors are specified in the Global (local displacement) coordinate system of each grid A and B, and the orientation vector is specified in the Global coordinate system of grid A. Using the codes below, the offset vector can be specified in the element coordinate system and the orientation vector can be specified in the basic coordinate system. The valid character strings and their meanings are shown below: OFFT

Orientation Vector

End A Offset

End B Offset

GGG

Global

Global

Global

BGG

Basic

Global

Global

GGO

Global

Global

Element

BGO

Basic

Global

Element

GOG

Global

Element

Global

BOG

Basic

Element

Global

GOO

Global

Element

Element

BOO

Basic

Element

Element

The element system x-axis is defined from GA to GB. The orientation vector and the element system x-axis are then used to define the z and y axes of the element system. A vector is formed from the cross product of a vector going from Grid A to Grid B and the orientation vector to create the element coordinate z-direction. 6.

Offset vectors are treated like rigid elements. The length of the offset vectors is not affected by thermal loads.

7.

Torsional stiffness due to warping of the cross-section is not considered.

8.

This card is represented as a bar2 element in HyperMesh.

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CBUSH Bulk Data Entry CBUSH – Bushing Element Description Defines a generalized spring-damper structural element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C BUSH

EID

PID

GA

GB

G0/X1

X2

X3

C ID

S

OC ID

S1

S2

S3

(10)

Example 1

Spring-damper element defined with default orientation and location; default orientation is only valid when only K1, and/or K4 are defined on referenced PBUSH. (1)

(2)

(3)

(4)

(5)

C BUSH

2

6

8

1

(6)

(7)

(8)

(9)

(10)

(7)

(8)

(9)

(10)

Example 2

Spring-damper location is offset from mid-point of GA-GB. (1)

(2)

(3)

(4)

(5)

(6)

C BUSH

19

7

1

2

4

0.3

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Example 3

Spring-damper is oriented by referencing coordinate system 5, and spring-damper location is explicitly defined using OCID, S1, S2, and S3. (1)

(2)

(3)

(4)

(5)

C BUSH

41

9

1

2

7

1.0

0.5

Field

Contents

EID

Element identification number.

(6)

(7)

(8)

(9)

(10)

5

-0.7

No default (Integer > 0) PID

Property identification number of a PBUSH entry. Default = EID (Integer > 0)

GA,GB

Grid point identification number of connection points. No default (Integer > 0 or ) See comments 6, 9 and 10.

Xi

Components of orientation vector coordinate system of GA.

, from GA, in the displacement

(Real)

G0

Alternate method to supply vector is from GA to GO.

using grid point GO. Direction of

is then transferred to End A.

(Integer > 0 or ) See comments 3 and 9. CID

Element coordinate system identification. A 0 means the basic coordinate system. If CID is blank, then the element coordinate system is determined from GO or Xi. (Integer > 0 or blank) See comments 2 and 3.

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Field

Contents

S

Location of spring-damper as a fraction along the line segment between GA and GB. Default = 0.5 (0.0 < Real < 1.0)

OCID

Coordinate system identification for spring-damper offset. See comment 7. Default = -1 (Integer > -1; -1 indicates that the offset is along GA-GB)

Si

Components of the spring-damper offset in the OCID coordinate system, ignored if OCID is -1. (Real)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

C BUSH element

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Alternate C BUSH element definition

2.

CID > 0 overrides GO and Xi. Then the element x-axis is along T1, the element y-axis is along T2, and the element z-axis is along T3 of the CID coordinate system. If the CID refers to a cylindrical coordinate system or a spherical coordinate system, the grid GA is used to locate the system. If for cylindrical or spherical coordinate, GA falls on the z-axis used to define them, it is recommended that another CID be selected to define the element x-axis.

3. specified, the line AB is the element x-axis and the orientation vector plane (similar to the CBEAM element).

lies in the x-y

4. specified, the line AB is the element x-axis. This option is valid only when K1 or K4 or both on the PBUSH entry are specified (but K2, K3, K5, and K6 are not specified). If K2, K3, K5, or K6 are specified, the solver will terminate with an error. 5.

If GA and GB are coincident, or if GB is blank, then CID must be specified.

6.

If OCID refers to a cylindrical or spherical coordinate system, then grid GA is used to locate the system.

7.

A CBUSH element, referencing a PBUSH property with a single stiffness term, is equivalent to a CELAS1 or CELAS2 element, only when the elements have zero length. A non-zero length CBUSH assumes rigid body connections from the connection points, GA and GB, to the spring-damper location, as defined either by S or the OCID and Si fields.

8.

Bushing elements are ignored in heat transfer analysis.

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9.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on CBUSH entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

10. The CBUSH element force is calculated as follows: F = K(UGB - UGA ) Therefore, the sign of the force will depend on the grids GA and GB. If the grids are switched, then the element force will be reversed. 11. This card is represented as a spring element in HyperMesh.

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CBUSH1D Bulk Data Entry CBUSH1D – Rod-type Spring-Damper Element Description Defines a one-dimensional spring-damper structural element. Format (1)

(2)

(3)

(4)

(5)

(6)

C BUSH1D

EID

PID

GA

GB

C ID

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C BUSH1D

2

6

8

1

Field

Contents

EID

Element identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Property identification number of a PBUSH1D entry. Default = EID (Integer > 0)

GA,GB

Grid point identification numbers of connection points. No default (Integer > 0 or ) See comments 2 and 7.

CID

Element coordinate system identification number. If a value of 0 is input, the basic coordinate system is selected. (Integer > 0 or blank) See comments 2 through 4.

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Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2. axis. In geometric nonlinear analysis, the element axis (line GA to GB) follows the deformation of grids GA and GB. 3.

If GA and GB are coincident, or if GB is blank, then CID must be specified.

4.

If CID > 0, the x-axis of CID is the element axis. In geometric nonlinear analysis, depending on the referenced system being movable or fixed, the axis of the element will move or not move with the axes of the system, respectively. Geometric nonlinear analysis is selected by an ANALYSIS = NLGEOM, IMPDYN or EXPDYN subcase entry.

5.

In all linear subcases, as well as small displacement nonlinear quasi-static (ANALYSIS=NLSTAT) subcases, PBUSH1D and CBUSH1D are converted internally to the equivalent PBUSH (with PBUSHT, if necessary) and CBUSH.

6.

Rod-type spring-damper elements are ignored in heat transfer analysis.

7.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on CBUSH1D entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN bulk data entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

8.

This card is represented as a spring element in HyperMesh.

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CDAMP1 Bulk Data Entry CDAMP1 – Scalar Damper Connection Description Defines a scalar damper element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

C DAMP1

EID

PID

G1

C1

G2

C2

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

C DAMP1

2

10

0

(5)

(6)

(7)

26

3

Field

Contents

EID

Unique element identification number.

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PDAMP property entry. Default = EID (Integer > 0)

G1, G2

Geometric grid point or scalar point identification number. Default = 0 (Integer > 0)

C1, C2

Component number in the displacement coordinate system specified by the CD entry of the GRID data. Default = 0 (0 < Integer < 6)

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Comments 1.

Zero or blank may be used to indicate a grounded terminal G1 or G2 with a corresponding blank or zero C1 or C2. A grounded terminal is a point whose displacement is constrained to zero.

2.

Scalar points may be used for G1 and/or G2, (with corresponding C1 and/or C2 of zero or blank). If only scalar points and/or grounded terminals are involved, it is more efficient to use the CDAMP3 entry.

3.

Element identification numbers must be unique with respect to all other element identification numbers.

4.

The two connection points (G1, C1) and (G2, C2) must be distinct.

5.

A scalar point specified on this entry need not be defined on an SPOINT entry.

6.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

7.

Scalar damper elements are ignored in heat transfer analysis.

8.

This card is represented as a spring or mass element in HyperMesh.

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CDAMP2 Bulk Data Entry CDAMP2 – Scalar Damper Property and Connection Description Defines a scalar damper element without reference to a property entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

C DAMP2

EID

B

G1

C1

G2

C2

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C DAMP2

2

3.12

12

2

(6)

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) B

Value of the scalar damper. No default (Real)

G1, G2

Geometric grid point identification number. Default = blank (Integer > 0)

C1, C2

Component number in the displacement coordinate system specified by the CD entry of the GRID data. Default = 0 (0 < Integer < 6)

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Comments 1.

Zero or blank may be used to indicate a grounded terminal G1 or G2 with a corresponding blank or zero C1 or C2. A grounded terminal is a point whose displacement is constrained to zero.

2.

Scalar points may be used for G1 and/or G2, (with a corresponding C1 and/or C2 of zero or blank). If only scalar points and/or grounded terminals are involved, it is more efficient to use the CDAMP4 entry.

3.

Element identification numbers must be unique with respect to all other element identification numbers.

4.

This single entry completely defines the element since no material or geometric properties are required.

5.

The two connection points (G1, C1) and (G2, C2) must be distinct.

6.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

7.

Scalar damper elements are ignored in heat transfer analysis.

8.

This card is represented as a spring or mass element in HyperMesh.

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CDAMP3 Bulk Data Entry CDAMP3 – Scalar Damper Connection to Scalar Points Only Description Defines a scalar damper element that is connected only to scalar points. Format (1)

(2)

(3)

(4)

(5)

C DAMP3

EID

PID

S1

S2

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C DAMP3

16

978

24

36

Field

Contents

EID

Unique element identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Property identification number of a PDAMP property entry. Default = EID (Integer > 0)

S1, S2

Scalar point identification numbers. Default = 0 (Integer >

Comments 1.

S1 or S2, but not both, may be blank or zero, indicating a constrained coordinate.

2.

Element identification numbers should be unique with respect to all other element identification numbers.

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3.

Only one scalar damper element may be defined on a single entry.

4.

A scalar point specified on this entry need not be defined on an SPOINT entry.

5.

Scalar damper elements are ignored in heat transfer analysis.

6.

This card is represented as a spring or mass element in HyperMesh.

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CDAMP4 Bulk Data Entry CDAMP4 – Scalar Damper Property and Connection to Scalar Points Only Description Defines a scalar damper element that is connected only to scalar points and is without reference to a material or property entry. Format (1)

(2)

(3)

(4)

(5)

C DAMP4

EID

B

S1

S2

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C DAMP4

16

-2.6

4

9

Field

Contents

EID

Unique element identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) B

Scalar damper value. No default (Real)

S1, S2

Scalar point identification numbers. Default = 0 (Integer >

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Comments 1.

S1 or S2, but not both, may be blank or zero, indicating a constrained coordinate.

2.

Element identification numbers should be unique with respect to all other element identification numbers.

3.

This single entry completely defines the element since no material or geometric properties are required.

4.

Only one scalar damper element may be defined on a single entry.

5.

A scalar point specified on this entry need not be defined on an SPOINT entry.

6.

Scalar damper elements are ignored in heat transfer analysis.

7.

This card is represented as a spring or mass element in HyperMesh.

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CDSMETH Bulk Data Entry CDSMETH - Run Control Description The CDSMETH command can be used in the component dynamic synthesis method for generating component dynamic matrices at each loading frequency. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C DSMETH

C DSID

GTYPE

TF

OSET

TOL

SSF

RSF

C MSOUT

SPID

SPID_F

GP_RC

(10)

Example

(1)

(2)

(3)

(4)

C DSMETH

10

SVDNP

YES

C MSOUT

9000001

9000001

(5)

(6)

(7)

(8)

(10)

YES

Argumen Options t

Description

CDSID

Identification number of CDSMETH.



(9)

Default = NONE

GTYPE

Default =

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SVDNP:

Dynamic Stiffness Matrix is calculated by singular value decomposition of transfer function after scaling rotational DOF’s (Comment 6).

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Argumen Options t SVDNP

TF

Description BME:

Dynamic Stiffness Matrix is calculated by block matrix elimination (Comment 6).

Generate transfer functions at the connection and interior points at each loading frequency.

Default = NO

OSET

Default = BLANK

TOL

Default = 1.0e-20

SSF

Default = 1.0

RSF

Default = 1.0e-3

CMSOUT

Default = BLANK

446

Grid set for interior grids. The responses corresponding to interior grids may be recovered in the residual run (Comment 5).

Tolerance value for the Singular Value Decomposition (SVD) operation that involves pseudo–inversion of the transfer function matrix to obtain the dynamic stiffness matrix.

Structural scale factor used to scale transfer function terms associated with the structural degrees of freedom prior to the singular value decomposition (SVD) operation.

Rotational scale factor used to scale transfer function terms associated with the rotational degrees of freedom prior to the singular value decomposition (SVD) operation.

This is an optional keyword to specify the creation of the component model synthesis (CMS) super element generated using the General Modal method with free – free boundary (Craig-Chang method).

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Argumen Options t

Description

SPID



The starting SPOINT ID to be used in CMS matrix output for the structural eigenmodes. There is no default. This is only valid, if CMSOUT is specified.

SPID_F



The starting SPOINT ID to be used in CMS matrix output for the fluid eigenmodes. There is no default, if fluid grids are present in the model. However, this must be used, if there are fluid grids in the model. This is only valid, if CMSOUT is specified.

GP_RC



Grid participation recovery control. If YES, the fluidstructural interface connection matrix is calculated and stored as a part of the CMS super element. This is only valid, if CMSOUT is specified.

Default = NO

Comments 1.

The responses available for recovery, and the attachment points available for connection in the residual structure, must be specified on a BNDFRE1, BNDFREE, CSET or CSET1 data entry for a modal frequency response analysis in which CDSMETH has been specified.

2.

Frequencies available for recovery must be specified, using the FREQ or FREQ# (# ranges from 1 to 5) data entries, in the modal frequency response analysis in which CDSMETH has been specified.

3.

A MODEL card may be used for additional response output for the optional CMS superelement output.

4.

Reasonable speedup may be achieved by reducing the number of ASET points in the residual run when CDSMETH is used.

5.

If OSET is specified, TF is automatically set to YES.

6.

Performance may be an issue with the Block Matrix Elimination (BME) method for large models. The BME option for the GTYPE field is only recommended for small models or when other methods fail to work.

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CELAS1 Bulk Data Entry CELAS1 – Scalar Spring Connection Description Defines a scalar spring element of the structural model. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

C ELAS1

EID

PID

G1

C1

G2

C2

(8)

(9)

(10)

Example

(1)

(2)

(3)

C ELAS1

2

6

(4)

(5)

Field

Contents

EID

Unique element identification number.

(6)

(7)

8

1

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PELAS property entry. Default = EID (Integer > 0)

G1,G2

Geometric grid point or scalar point identification number. Default = 0 (Integer > 0)

C1,C2

Component number in the displacement coordinate system specified by the CD entry of the GRID data. Default = 0 (0 < Integer < 6)

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Comments 1.

Zero or blank may be used to indicate a grounded terminal G1 or G2 with a corresponding blank or zero C1 or C2. A grounded terminal is a point whose displacement is constrained to zero.

2.

Scalar points may be used for G1 and/or G2 (with a corresponding C1 and/or C2 of zero or blank). If only scalar points and/or grounded terminals are involved, it is more efficient to use the CELAS3 entry.

3.

Element identification numbers must be unique with respect to all other element identification numbers.

4.

The two connection points (G1, C1) and (G2, C2) must be distinct.

5.

A scalar point specified on this entry need not be defined on an SPOINT entry.

6.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

7.

A CBUSH element, referencing a PBUSH property with a single stiffness term, is equivalent to a CELAS1 or CELAS2 element, only when the elements have zero length. A non-zero length CBUSH assumes rigid body connections from the connection points, GA and GB, to the spring-damper location, as defined either by S or the OCID and Si fields.

8.

This card is represented as a spring or mass element in HyperMesh.

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CELAS2 Bulk Data Entry CELAS2 – Scalar Spring Property and Connection Description Defines a scalar spring element of the structural model without reference to a property entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ELAS2

EID

K

G1

C1

G2

C2

GE

S

(10)

Example

(1)

(2)

(3)

C ELAS2

28

6.2+3

(4)

(5)

Field

Contents

EID

Unique element identification number.

(6)

(7)

19

4

(8)

(9)

(10)

No default (Integer > 0) K

Spring stiffness. No default (Real)

G1, G2

Geometric grid point or scalar point identification number. Default = 0 (Integer > 0)

C1, C2

Component number in the displacement coordinate system specified by the CD entry of the GRID data. Default = 0 (0 < Integer < 6)

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Field

Contents

GE

Damping coefficient. (See comment 7). Default = 0.0 (Real)

S

Stress coefficient. Default = 0.0 (Real)

Comments 1.

Zero or blank may be used to indicate a grounded terminal G1 or G2 with a corresponding blank or zero C1 or C2. A grounded terminal is a point whose displacement is constrained to zero.

2.

Scalar points may be used for G1 and/or G2 (with a corresponding C1 and/or C2 of zero or blank). If only scalar points and/or grounded terminals are involved, it is more efficient to use the CELAS4 entry.

3.

Element identification numbers must be unique with respect to all other element identification numbers.

4.

This single entry completely defines the element since no material or geometric properties are required.

5.

The two connection points (G1, C1) and (G2, C2) must be distinct.

6.

To obtain the damping coefficient GE, multiply the critical damping ratio, C/C0, by 2.

7.

If PARAM, W4 is not specified, GE is ignored in transient analysis.

8.

A scalar point specified on this entry need not be defined on an SPOINT entry.

9.

The element force of a spring is calculated from the equation: F = k * (u1 – u2) Where, k is the stiffness coefficient for the scalar element and u1 is the displacement of the first degree-of-freedom listed on the CELAS entry. Element stresses are calculated from the equation: s = S * F, where, S is the stress coefficient as defined above.

10. When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID). 11. A CBUSH element, referencing a PBUSH property with a single stiffness term, is equivalent to a CELAS1 or CELAS2 element, only when the elements have zero length. A non-zero length CBUSH assumes rigid body connections from the connection points, GA and GB, to the spring-damper location, as defined either by S or the OCID and Si fields.

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12. This card is represented as a spring or mass element in HyperMesh.

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CELAS3 Bulk Data Entry CELAS3 – Scalar Spring Connection to Scalar Points Only Description Defines a scalar spring element that connects only to scalar points. Format (1)

(2)

(3)

(4)

(5)

C ELAS3

EID

PID

S1

S2

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C ELAS3

19

2

14

15

Field

Contents

EID

Unique element identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Property identification number of a PELAS entry.

S1, S2

Scalar point identification numbers. Default = 0 (Integer >

Comments 1.

S1 or S2 may be blank or zero indicating a constrained coordinate.

2.

Element identification numbers should be unique with respect to all other element identification numbers.

3.

Only one scalar spring element may be defined on a single entry.

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4.

A scalar point specified on this entry need not be defined on an SPOINT entry.

5.

This card is represented as a spring or mass element in HyperMesh.

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CELAS4 Bulk Data Entry CELAS4 – Scalar Spring Property and Connection to Scalar Points Only Description Defines a scalar spring element that is connected only to scalar points without reference to a property entry. Format (1)

(2)

(3)

(4)

(5)

C ELAS4

EID

K

S1

S2

(6)

(7)

(8)

(9)

GE

S

(10)

Example

(1)

(2)

(3)

(4)

C ELAS4

42

6.2-3

2

(5)

Field

Contents

EID

Unique element identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) K

Stiffness of the scalar spring. No default (Real)

S1, S2

Scalar point identification numbers. Default = 0 (Integer >

GE

Damping coefficient. See comment 7. Default = 0.0 (Real)

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Field

Contents

S

Stress coefficient Default = 0.0 (Real)

Comments 1.

S1 or S2, but not both, may be blank or zero indicating a constrained coordinate.

2.

Element identification numbers should be unique with respect to all other element identification numbers.

3.

This single entry completely defines the element since no material or geometric properties are required.

4.

Only one scalar spring element may be defined on a single entry.

5.

A scalar point specified on this entry need not be defined on an SPOINT entry.

6.

The element force of a spring is calculated from the equation: F = k * (u1 – u2) Where, k is the stiffness coefficient for the scalar element and u1 is the displacement of the first degree-of-freedom listed on the CELAS entry. Element stresses are calculated from the equation: s = S * F, where, S is the stress coefficient as defined above.

7.

If PARAM, W4 is not specified, GE is ignored in transient analysis.

8.

This card is represented as a spring or mass element in HyperMesh.

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CFAST Bulk Data Entry CFAST – Fastener Element Connection Description Define a fastener with material orientation connecting two shell surfaces. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C FAST

EID

PID

C TYPE

PIDA/ SHIDA

PIDB/ SHIDB

GS

GA

GB

XS

YS

ZS

(10)

Example 1

(1)

(2)

(3)

(4)

(5)

(6)

C FAST

22

1

PROP

2

3

0.2

0.3

0.3

(1)

(2)

(3)

(4)

(5)

(6)

C FAST

22

1

ELEM

101

201

(7)

(8)

(9)

(10)

(7)

(8)

(9)

(10)

21

30

Example 2

Field

Contents

EID

Unique element identification number. No default (Integer > 0)

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Field

Contents

PID

Identification number of a PFAST entry. Default = EID (Integer > 0)

CTYPE

The type of connection between the patches. Either format connects up to 3 x 3 elements per patch (possibly more for triangular elements). For PROP, the connection of surface patch to surface patch is defined by specifying the property numbers of shells on side A and B, PIDA and PIDB, respectively. For ELEM, the connection of surface patch to surface patch is defined by specifying IDs of shells SHIDA and SHIDB, respectively. No default

PIDA,PIDB

Property identification numbers of PSHELL entries defining surface A and B, respectively. Required when CTYPE = PROP.

SHIDA, SHIDB

Element identification numbers of shells defining fastener ends A and B, respectively. Required when CTYPE = ELEM.

GS

Identification number of a grid point which defines the location of the connector. See comment 2. (Integer > 0)

GA, GB

These represent grid identification numbers of piercing points on surface A and surface B respectively. See comment 3. (Integer > 0)

XS, YS, ZS

Coordinates of point that defines the location of the fastener in the basic coordinate system. It is an alternative way of specifying the location of GS. (Real)

Comments 1.

458

CFAST defines a flexible connection between two shell surface patches. An internallygenerated CBUSH element will be created automatically for a CFAST, and the end points of this bushing will be connected to the grids of corresponding shell elements. Then the

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stiffness, mass and structural damping of the CBUSH will be transferred to the corresponding shell grids. GS, GA and GB do not hold any independent DOF. See the figure below:

2.

A CFAST element connects Shell A and Shell B. An internal CBUSH is generated for the CFAST and supported by fictitious auxiliary points. Auxiliary points, in turn, are constrained by corresponding shell grids. (To have a clear view, only one of these kind of constraint relationships is shown with dotted lines).

3.

The end points of the internally-generated CBUSH element are defined from GS, GA, and GB (not all are required). If GA or GB is not specified, they are generated from the normal projection of GS onto the surface patches. If GA and GB (or, GA only) are (is) specified, they take precedence over GS in defining the respective end points (If only GA is specified, then GA is used as a normal projection point (similar to GS) to generate GB on Shell B). Also, their locations will be corrected so that they lie on surface patch A and B, respectively. If neither GS nor GA is specified, then (XS, YS, and ZS), in the basic coordinate system, must be specified. The length of the connector is the distance between projected points GA and GB.

4.

The connections of the internally-generated bushing to surface patches A and B are defined in the following way: the axis GA-GB is used to define four pairs of auxiliary points GAHi, GBHi, i=1,4 that are located on patches A and B, respectively. The cross-section area of the resulting hexahedral is equivalent to the area of the connector, defined from diameter D on PFAST card. The connector stiffness matrix is first built by connecting the internally-generated bushing element to the auxiliary points, and then constraining them to supporting shell nodes using respective shape functions. Similarly, the mass of the fastener is divided by ½ to each side and then distributed via auxiliary points to supporting shell nodes.

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5.

460

Since the geometry for finding the correct projection could be various and complicated, sometimes the default projection algorithm may fail. However, the default projection rules and tolerances can be modified to some extent via the SWLDPRM card.

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CGAP Bulk Data Entry CGAP – Gap Element Connection Description Defines a gap or friction element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GAP

EID

PID

GA

GB

GO/X1

X2

X3

C ID

(10)

Examples

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

C GAP

6

6

233

223

3.0

-1.0

1.0

(9)

(10)

Minimum necessary data when GA and GB are not coincident: C GAP

247

1

233

223

Field

Contents

EID

Unique element identification number. No default (Integer > 0)

PID

Identification number of a PGAP entry. Default = EID (Integer > 0)

GA,GB

Connected grid points at ends A and B.

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Field

Contents

X1, X2, X3

Components of the orientation vector, from GA, in the displacement coordinate system at GA. Default determined automatically - See comment 7. (Real)

G0

Alternate method to supply orientation vector, using grid point G0. Direction of orientation vector is from GA to G0. No default (Integer > 0)

CID

Element coordinate system identification number. CID must be specified if GA and GB are coincident (distance from GA to GB < 10-4). Alternatively: FLIP – reverses the direction of the gap axis (See comment 5). Default = blank (Integer > 0 or flip or blank) - See comments 2 through 6.

Comments 1.

For linear subcases, the CGAP element will produce a linear stiffness matrix which remains linear with the initial stiffness. The stiffness used depends on the value for the initial gap opening (U0 field in the PGAP entry).

2.

The gap element coordinate system is defined by one of the following methods: Prescribed CID: If the coordinate system CID is specified, the element coordinate system is established using that coordinate system. In this case, the element x-axis is in the coordinate system’s 1-direction, and the y-axis is in the coordinate system’s 2direction (for rectangular coordinate systems; the 1-direction is the x-direction and the 2-direction is the y-direction). The orientation vector will be ignored in this case. CID field blank: If the CID field is blank and the grid points GA and GB are not coincident (distance from GA to GB > 10-4), then the line GA-GB is the element x-axis and the orientation vector lies in the x-y plane (as with the CBEAM element). FLIP option: the x-axis of the gap coordinate system is reversed with respect to the default orientation described above. This option is useful when meshes of bodies A and B overlap, rather than have a gap between them (See comment 5). For gaps with coincident nodes (the distance between GA and GB < 1.0e-4), the gap coordinate system must be specified.

3.

462

In typical applications, leaving the CID field blank is appropriate when the nodes GA and GB obstacle are initially separated. If the meshes of bodies A and B overlap, then a coordinate system CID should be specified or the FLIP option should be used as discussed below.

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4.

When prescribing the gap coordinate system CID, it is essential to assure that its x-axis points in the general direction from body A (the one associated with node GA) towards the body B (the one associated with node GB). This will assure that the gap element acts to prevent contact/overlap of these bodies. An incorrect orientation of the x-axis will result in gap elements being ineffective, or will even act to "glue" the bodies together, rather than prevent them from overlapping. The solver checks for such misalignment and prints respective error and warning messages. For more information, see the GAPPRM bulk data card.

5.

The FLIP option in the CID field is useful when meshes of bodies A and B overlap, rather than have a gap between them. In such cases, the defaults gap axis vector GA-GB would be opposite to the overall direction from body A to body B and therefore would produce a "gluing" effect, rather than a resolution of the contact condition. The FLIP option reverses the default gap direction so that the gap axis correctly points from the bulk of body A towards body B in such cases. The effect of FLIP is equivalent to defining a coordinate system with axis 1 pointing in direction GB-GA, rather then GA-GB. Aside from setting the FLIP option to correctly resolve the cases with initial penetration, U0 on the PGAP card needs to be properly set to a negative value, or an AUTO option needs to be used in the U0 field. Alternatively, FLIP can be used to define a simple cable element. If such an arrangement is used, then it should be noted that: a) F0 corresponds to a pair of forces acting on the ends of the cable (pointing inwards), while U0 corresponds to pre-existing “slack” or extra length in the cable. b) Gap “open” status corresponds to the cable being “shortened”, while “closed” gap status corresponds to the cable being “elongated.” c) Positive gap force reported in the results corresponds to the cable being in tension (note that the force also includes the effect of F0).

6.

The element coordinate system does not rotate as a result of deflections.

7.

If neither coordinate system nor orientation vector are specified, the orientation vector is defined automatically as a vector aligned with the axis of the basic coordinate system that makes the largest angle with the gap direction (gap x-axis).

8.

Initial gap openings are specified on the PGAP entry and not derived from the separation distance between GA and GB.

9.

Forces, which are requested with the FORCE card in the I/O Options or Subcase Information sections, are output in the element coordinate system. F x is positive for compression.

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C GAP Element C oordinate System

10. For more information on using nonlinear gaps, refer to the Nonlinear Quasi-Static Analysis section of the User's Guide. 11. Heat transfer properties can be defined for Gap elements using the PGAPHT bulk data entry. 12. This card is represented as a gap or mass element in HyperMesh.

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CGAPG Bulk Data Entry CGAPG – General Node-to-Obstacle Gap Element Description Defines a node-to-obstacle gap element. The obstacle may be an element face or a patch of nodes. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GAPG

EID

PID

GA

TYP

X1/G0

X2

X3

C ID

GB1/ELIDB

GB2/G1

GB3/G3 or G4

GB4/

GB5

GB6

GB7

GB8

(10)

Example 1

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

C GAPG

6

6

233

ELEM

3.0

-1.0

1.0

(6)

(7)

(8)

(9)

(10)

(9)

(10)

257

Example 2

(1)

(2)

(3)

(4)

(5)

C GAPG

6

6

233

QUAD

110

111

114

113

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Field

Contents

EID

Unique element identification number. No default (Integer > 0)

PID

Identification number of a PGAP entry. Default = EID (Integer > 0)

GA

Grid point serving as end A of CGAPG. No default (Integer > 0)

TYP

Character string indicating the type of obstacle on the B end of CGAPG (opposing node GA): QUAD indicates that the obstacle is defined as a quadrilateral patch of grid points. The patch is defined with grid identification numbers GB#. TRIA indicates that the obstacle is defined as a triangular patch of grid points. The patch is defined with grid identification numbers GB#. ELEM indicates that the obstacle is defined as element face. No default (QUAD, TRIA or ELEM)

X1, X2, X3 Components of the orientation vector, from GA, in the displacement coordinate system at GA. Default determined automatically – See comment 6. (Real) G0

Alternate method to supply orientation vector, using grid point G0. Direction of orientation vector is from GA to G0. No default (Integer > 0)

CID

Prescribed element coordinate system identification number. CID, when prescribed, is used to define both the gap axis and orientation vector. Additional keywords that can be used in this field: FLIP – reverses the default orientation of gap axis, so it points from obstacle B towards GA. PUSHOUT – for obstacles defined as solid elements using ELIDB, gap axis is automatically defined so as to create “pushout” force that prevents GA

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Field

Contents from entering the interior of the element ELIDB. PUSHNORM – gap axis is automatically defined so as to create “pushout” force from obstacle B towards GA along the default vector normal to the obstacle B. PUSHREVN – creates pushout force reversed relative to the PUSHNORM option. Default = blank (Integer > 0, FLIP, PUSHOUT, PUSHNORM, PUSHREVN, or blank). See comments 2 through 5.

GB#

Grid identification number of the grid surface patch on the B (obstacle) end of the CGAPG element. GB1 to GB3 are required. No default (Integer > 0). See comment 7.

ELIDB

Element identification number of the element on the B (obstacle) end of the CGAPG element. No default (Integer > 0)

G1

For solid element ELIDB: identification number of a grid point connected to a corner of the face that defines the second end of the CGAPG element. For PYRA elements, this grid must be on an edge of the quadrilateral face. Default = blank (Integer > 0 or blank). See comments 8 through 11.

G3

For solid element ELIDB: identification number of a grid point connected to a corner diagonally opposite to G1 on the same face of a HEXA or PENTA element. Needed only if G1 has been specified. It is required data for quadrilateral faces of HEXA and PENTA elements only (Integer or blank). G3 must be omitted for a triangular surface on a PENTA element and the quadrilateral face on a PYRA element. For triangular faces of PYRA elements, this grid must be on the edge next to the quadrilateral face. G1 and G3 must define a positive direction into the element using the right hand rule. Default = blank (Integer > 0 or blank). See comments 8 through 11.

G4

For solid element ELIDB: identification number of the TETRA grid point located at the corner, not on the face being loaded. This is used for TETRA elements only. It is required data if G1 has been specified. Default = blank (Integer > 0 or blank)

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Comments 1.

CGAPG defines a contact element between a point and an obstacle. The obstacle may be defined as a patch of nodes or as an element face. See figure below:

Typical configuration of C GAPG between node GA and a grid patch GB1…GB4.

2.

The gap element coordinate system is defined via one of the following methods: Prescribed CID: if the coordinate system CID is specified, the element coordinate system is established using that coordinate system. In this case, the element x-axis is in the coordinate system’s 1-direction, and the y-axis is in the coordinate system’s 2direction (for rectangular coordinate systems; the 1-direction is the x-direction and the 2-direction is the y-direction). The orientation vector will be ignored in this case. CID field blank: if the CID field is blank and the grid point GA does not lie on the element face or node patch (distance from GA to the surface > 10-4), then the x-axis is defined along the shortest distance from GA to the element face or node patch. The orientation of gap x-axis points from GA towards the patch or element face (see figure above). The orientation vector defines the x-y plane of the gap coordinate system (similarly as for the CGAP element). If the grid point GA lies on the element face or node patch (distance from GA to the surface < 10-4), then CID must be prescribed. FLIP option: the x-axis of the gap coordinate system is reversed with respect to the default orientation described above. This option is useful when meshes of bodies A and B overlap rather than have a gap between them (See comment 5). PUSHOUT option: the x-axis of the gap coordinate system is oriented so as to prevent GA from entering interior of body B. This is only available for obstacles defined as 3D solid elements with ELIDB.

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With the PUSHNORM option, the gap axis is so oriented so as to produce “pushout” force from obstacle B towards GA along the default normal vector to the obstacle – element face or node patch. (Note that this pushout force direction is opposite to the gap axis, which points from GA towards the obstacle.) In cases when GA does not have a direct normal projection onto the obstacle B, and the "shortest distance" projection is used (GAPGPRJ set to SHORT on the GAPPRM card), the pushout force is oriented along the shortest distance line, yet with the orientation aligned with the normal vector. PUSHREVN creates pushout force reversed relative to the PUSHNORM option. Note that for faces on solid elements, the default normal is pointing inwards, so that it is the PUSHREVN option that will prevent penetration (PUSHOUT is a more straightforward option to use on solid faces). 3.

In typical applications, leaving the CID field blank is appropriate when the node GA and the obstacle are initially separated; that is, there is a gap between respective bodies A and B (see figure above). If the meshes of bodies A and B overlap, then a coordinate system CID should be specified (See comment 4). Alternatively, and usually more intuitively, one of the FLIP, PUSHOUT, PUSHNORM, or PUSHREVN options may be used.

4.

When prescribing the gap coordinate system CID, it is essential to assure that the resulting gap x-axis points in the general direction from body A (the one associated with node GA) towards body B (the one associated with element ELIDB or patch GB#). This assures that the gap element will act to prevent the contact/overlap of these bodies. An incorrect orientation of the x-axis will result in the gap element being ineffective or can even act to "glue" the bodies together rather than prevent their overlap. The solver checks for such misalignment and prints respective error and warning messages. For more information, see the GAPPRM bulk data card.

5.

The FLIP option in the CID field is useful when the meshes of bodies A and B overlap rather than have a gap between them. In such cases, the default gap axis vector would be opposite to the overall direction from body A to body B, and therefore would produce a "gluing" effect rather than a resolution of the contact condition. The FLIP option reverses the default gap direction so that the gap axis correctly points from the bulk of body A towards body B in such cases. Aside from setting the FLIP option or prescribing CID to correctly resolve the cases with initial penetration, U0 on the PGAP card needs to be properly set to a negative value or an AUTO option needs to be used in the U0 field.

6.

If neither coordinate system CID nor orientation vector is specified, the orientation vector is defined automatically as a vector aligned with the axis of the basic coordinate system that makes the largest angle with the gap direction (gap x-axis).

7.

GB# are required when TYP is QUAD or TRIA. At least 3, and at most 8, grid IDs may be specified for GB#. Triangular and quadrilateral element definition sequences apply for the order of GB# (see below). Missing mid-side nodes are allowed.

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Quadrilateral and triangular surface patches as defined when TYP is QUAD or TRIA.

8.

If ELIDB represents a solid element and G1, G3/G4 fields are blank, then the element face closest to the grid GA is selected as the respective obstacle face. Note that if the meshes are overlapping (such as in the case of initial penetration), this option should not be used, and the contact face should be explicitly prescribed. Otherwise, the face closest to GA may be an internal face within the solid body, rather than the outside surface of body B.

9.

G1 and G3 are ignored for shell elements (TRIA3, QUAD4, TRIA6 and QUAD8).

10. For triangular faces of PENTA elements, G1 is an identification number of a corner grid point that is on the face being loaded and the G3 or G4 field is left blank. For faces of TETRA elements, G1 is an identification number of a corner grid point that is on the face being loaded and G4 is an identification number of the corner grid point that is not on the face being loaded. Since a TETRA has only four corner points, this point, G4, is unique and different for each of the four faces of a TETRA element. 11. For the quadrilateral face of the PYRA element, G1 is an identification number of a corner grid point on the face and the G3 or G4 field is left blank. For the triangular faces, G1 and G3 must specify the grids on the edge of the face that borders the quadrilateral face and the grids must be ordered so that they define an inward normal using the right hand rule. 12. The element coordinate system does not rotate as a result of deformation. 13. Initial gap openings are specified on the PGAP entry and not derived from the separation distance between GA and GB, unless the AUTO option is used on the PGAP card. 14. Gap forces, which are requested with the FORCE card in the I/O Options or Subcase Information sections, are output in the gap element coordinate system. F x is positive for compression. 15. For linear subcases, the CGAPG element will produce a linear stiffness matrix which remains linear with the initial stiffness. The stiffness used depends on the value for the initial gap opening (U0 field in the PGAP entry). 16. For more information on using nonlinear gaps, refer to the Nonlinear Quasi-Static Analysis section of the User's Guide.

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17. This card is represented as a gap or mass element in HyperMesh.

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CGASK6 Bulk Data Entry CGASK6 – Five-sided Solid Gasket Element with Six Grid Nodes Description Defining the connections of the GASK6 solid gasket element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GASK6

EID

PID

G1

G2

G3

G4

G5

G6

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GASK6

71

4

3

4

5

6

7

8

Field

Contents

EID

Unique element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PGASK property entry. Default = EID (Integer > 0)

G#

Grid point identification number of connection points. No default (Integer > 0)

Comments 1.

472

Element identification numbers must be unique with respect to all other element identification numbers.

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2.

Grid points G1, …, G3 must be given in consecutive order at the bottom face of the gasket element. G4, …, G6 must be on the top face with G4 opposite G1, G5 opposite G2, and so on.

3.

If the user-prescribed node numbering on the bottom and top faces is reversed as compared to the sequence shown above, then the nodes are renumbered to produce right-handed orientation of numbering. This is accomplished by swapping nodes G1 with G3 and G4 with G6. In such cases, the element local coordinate system will be built on the renumbered node sequence.

4.

The element coordinate system for the CGASK6 element is defined below. The local 3-direction (the gasket material thickness direction in default) is defined as the simple average of the unit normal directions on the top and bottom surfaces of the element. After the local 3-direction is defined, a local 1-2 plane is generated accordingly. Then, the local 1-direction and 2-direction are defined as follows: Project the basic x-axis onto the local 1-2 plane, and set it to be the default local 1-direction. If the basic x-axis is within 0.1° difference as the local 3-direction, project the basic z-axis onto the local 12 plane and set it to be the local 1-direction. The local 2-direction is determined then.

5.

The gasket material coordinate system is the same as the element coordinate system in default and can be defined as a prescribed system through PGASK entry.

6.

This card is represented as a gask6 element in HyperMesh.

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CGASK8 Bulk Data Entry CGASK8 – Six-sided Solid Gasket Element with Eight Grid Nodes Description Defining the connections of the GASK8 solid gasket element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GASK8

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GASK8

71

4

3

4

5

6

7

8

9

10

Field

Contents

EID

Unique element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PGASK property entry. Default = EID (Integer > 0)

G#

Grid point identification number of connection points. No default (Integer > 0)

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Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

Grid points G1, …, G4 must be given in consecutive order at the bottom face of the gasket element. G5, …, G8 must be on the top face with G5 opposite G1, G6 opposite G2, and so on.

3.

If the user-prescribed node numbering on the bottom and top faces is reversed as compared to the sequence shown above, then the nodes are renumbered to produce right-handed orientation of numbering. This is accomplished by swapping nodes G1 with G3 and G5 with G7. In such cases, the element local coordinate system will be built on the renumbered node sequence.

4.

The element coordinate system for the CGASK8 element is defined below. The local 3-direction (the gasket material thickness direction in default) is defined as the simple average of the unit normal directions on the top and bottom surfaces of the element. After the local 3-direction is defined, a local 1-2 plane is generated accordingly. Then, the local 1-direction and 2-direction are defined as follows: Project the basic x-axis onto the local 1-2 plane, and set it to be the default local 1-direction. If the basic x-axis is within 0.1° difference as the local 3-direction, project the basic z-axis onto the local 12 plane and set it to be the local 1-direction. The local 2-direction is determined then.

5.

The gasket material coordinate system is the same as the element coordinate system in default and can be defined as a prescribed system through PGASK entry.

6.

This card is represented as a gask8 element in HyperMesh.

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CGASK12 Bulk Data Entry CGASK12 – Five-sided Solid Gasket Element with Twelve Grid Nodes Description Defining the connections of the GASK12 solid gasket element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GASK12

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

G9

G10

G11

G12

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GASK12

71

4

3

4

5

6

7

8

9

10

11

12

13

14

Field

Contents

EID

Unique element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PGASK property entry. Default = EID (Integer > 0)

G#

Grid point identification number of connection points. No default (Integer > 0)

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Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

Corner grid points G1, …, G3 must be given in consecutive order at the bottom face of the gasket element. Corner grid points G4, …, G6 must be on the top face with G4 opposite G1, G5 opposite G2, and so on. Edge grid points G7, …, G9 must be given in consecutive order at the bottom face of the gasket element. Edge grid points G10, …, G12 must be on the top face with G10 opposite G7, G11 opposite G8, and so on.

3.

If the user-prescribed node numbering on the bottom and top faces is reversed as compared to the sequence shown above, then the nodes are renumbered to produce right-handed orientation of numbering. This is accomplished by swapping nodes G1 with G3 and G4 with G6. In such cases, the element local coordinate system will be built on the renumbered node sequence.

4.

The element coordinate system for the CGASK12 element is defined below. The local 3-direction (the gasket material thickness direction in default) is defined as the simple average of the unit normal directions on the top and bottom surfaces of the element. After the local 3-direction is defined, a local 1-2 plane is generated accordingly. Then, the local 1-direction and 2-direction are defined as follows: Project the basic x-axis onto the local 1-2 plane, and set it to be the default local 1-direction. If the basic x-axis is within 0.1° difference as the local 3-direction, project the basic z-axis onto the local 12 plane and set it to be the local 1-direction. The local 2-direction is determined then.

5.

The gasket material coordinate system is the same as the element coordinate system in default and can be defined as a prescribed system through PGASK entry.

6.

This card is represented as a gask12 element in HyperMesh.

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CGASK16 Bulk Data Entry CGASK16 – Six-sided Solid Gasket Element with Sixteen Grid Nodes Description Defining the connections of the GASK16 solid gasket element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GASK16

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

G9

G10

G11

G12

G13

G14

G15

G16

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C GASK16

71

4

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

Field

Contents

EID

Unique element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PGASK property entry. Default = EID (Integer > 0)

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Field

Contents

G#

Grid point identification number of connection points. No default (Integer > 0)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

Corner grid points G1, …, G4 must be given in consecutive order at the bottom face of the gasket element. Corner grid points G5, …, G8 must be on the top face with G5 opposite G1, G6 opposite G2, and so on. Edge grid points G9, …, G12 must be given in consecutive order at the bottom face of the gasket element. Edge grid points G13, …, G16 must be on the top face with G13 opposite G9, G14 opposite G10, and so on.

3.

If the user-prescribed node numbering on the bottom and top faces is reversed as compared to the sequence shown above, then the nodes are renumbered to produce right-handed orientation of numbering. This is accomplished by swapping nodes G1 with G3 and G5 with G7. In such cases, the element local coordinate system will be built on the renumbered node sequence.

4.

The element coordinate system for the CGASK16 element is defined below. The local 3-direction (the gasket material thickness direction in default) is defined as the simple average of the unit normal directions on the top and bottom surfaces of the element. After the local 3-direction is defined, a local 1-2 plane is generated accordingly. Then, the local 1-direction and 2-direction are defined as follows: Project the basic x-axis onto the local 1-2 plane, and set it to be the default local 1-direction. If the basic x-axis is within 0.1° difference as the local 3-direction, project the basic z-axis onto the local 12 plane and set it to be the local 1-direction. The local 2-direction is determined then.

5.

The gasket material coordinate system is the same as the element coordinate system in default and can be defined as a prescribed system through PGASK entry.

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6.

480

This card is represented as a gask16 element in HyperMesh.

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CHACAB Bulk Data Entry CHACAB – Six-sided, Frequency-dependent Structural Acoustic Absorber Element Description Defines the frequency-dependent structural acoustic absorber element in coupled fluidstructural analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C HAC AB

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

G9

G10

G11

G12

G17

G18

G19

G20

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C HAC AB

71

4

3

4

5

6

7

8

9

10

Field

Contents

EID

Unique element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PACABS property entry. No default (Integer > 0)

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Field

Contents

Gi

Grid point identification numbers of connection points. Default = blank (Integer > 0 or blank)

Input File - chacab.fem $$------------------------------------------------------------------------------$ $$ $ $$ NASTRAN Input Deck Generated by HyperMesh Version : 8.0SR1 $ $$ Generated using HyperMesh-Nastran Template Version : 8.0sr1 $$ $ $$ Template: general $ $$ $ $$------------------------------------------------------------------------------$ $$------------------------------------------------------------------------------$ $$ Executive Control Cards $ $$------------------------------------------------------------------------------$ SOL 111 CEND $$------------------------------------------------------------------------------$ $$ Case Control Cards $ $$------------------------------------------------------------------------------$ SET 1 = 1734 DISPLACEMENT = 1 $ $HMNAME LOADSTEP 1"Load2" SUBCASE 1 LABEL= Load2 SPC = 4 FREQUENCY = 5 DLOAD = 2 $$------------------------------------------------------------------------------$ $$ Bulk Data Cards $ $$------------------------------------------------------------------------------$ BEGIN BULK $CHEXA 1056 2 1650 1661 1662 $+ 1683 1672 CHACAB 1056 100 1650 1645 1657 + 1671 1672 PACABS,100,YES,1,2,3,1.5,10.0,2.0 PARAM,G,0.001 PARAM,COUPMASS,-1 PARAM,POST,-1 $ACMODL DIFF 0.1 $$ EIGRL,20,,,300 EIGRL,21,,,300 $$ GRID Data $$ GRID 1 2.0 2.0 0.0 GRID 2 2.0 1.5 0.0 GRID 3 2.0 1.0 0.0 GRID 4 2.0 0.5 0.0 GRID 5 2.0 0.0 0.0 GRID 6 2.0 -0.5 0.0 GRID 7 2.0 -1.0 0.0 GRID 8 2.0 -1.5 0.0 GRID 9 2.0 -2.0 0.0

482

1651 1658

1671 1676

1682+ 1675+

-1 -1 -1 -1 -1 -1 -1 -1 -1

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GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

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1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0

2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5

0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

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GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

484

79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 727 728 729 730 731 732 733 734 735 736 737 738 739 740 741 742 743 744 745 746 747 748 749 750 751 752

-2.0 -2.0 -2.0 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 2.5 2.5 2.0 2.0 1.5 1.5 1.0 1.0 0.5 0.5 0.0 0.0 -0.5 -0.5 -1.0 -1.0 -1.5 -1.5 -2.0 -2.0 -2.5 -2.5 2.5 2.5 2.0 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 1.5 1.5 1.5 1.5

-1.0 0.0 -1.5 0.0 -2.0 0.0 2.0 0.0 1.5 0.0 1.0 0.0 0.5 0.0 0.0 0.0 -0.5 0.0 -1.0 0.0 -1.5 0.0 -2.0 0.0 2.0 0.0 1.5 0.0 1.0 0.0 0.5 0.0 0.0 0.0 -0.5 0.0 -1.0 0.0 -1.5 0.0 -2.0 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 0.0 -2.5 0.0 2.5 1.0 2.0 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.5 1.0 1.0 1.0 1.0 1.0 0.5 1.0 0.5 1.0 -4.2E-191.0 -6.5E-201.0 -0.5 1.0 -0.5 1.0 -1.0 1.0 -1.0 1.0 -1.5 1.0 -1.5 1.0 -2.0 1.0 -2.0 1.0 -2.5 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

753 754 755 756 757 758 759 760 761 762 763 764 765 766 767 768 769 770 771 772 773 774 775 776 777 778 779 780 781 782 783 784 785 786 787 788 789 790 791 792 793 794 795 796 797 798 799 800 801 802 803 804 805 806 807 808 809 810 811 812 813 814 815 816 817 818 819 820 821

Altair Engineering

1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5

0.5 1.0 -9.8E-211.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -1.5E-211.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -2.3E-221.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -3.5E-231.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -5.3E-241.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -8.1E-251.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -9.3E-181.0 -0.5 1.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

485

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

486

822 823 824 825 826 827 828 829 830 831 832 833 834 835 836 837 838 839 840 841 842 843 844 845 846 847 848 849 850 851 852 853 854 855 856 857 858 859 860 861 862 863 864 865 866 867 868 869 870 871 872 873 874 875 876 877 878 879 880 881 882 883 884 885 886 887 888 889 890

-1.5 -1.5 -1.5 -1.5 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 2.5 2.5 2.0 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0

-1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -2.0E-181.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -1.0E-181.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.5 2.0 2.0 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.5 2.0 1.0 2.0 1.0 2.0 0.5 2.0 0.5 2.0 -6.0E-192.0 -1.2E-192.0 -0.5 2.0 -0.5 2.0 -1.0 2.0 -1.0 2.0 -1.5 2.0 -1.5 2.0 -2.0 2.0 -2.0 2.0 -2.5 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -2.1E-202.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -3.8E-212.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

891 892 893 894 895 896 897 898 899 900 901 902 903 904 905 906 907 908 909 910 911 912 913 914 915 916 917 918 919 920 921 922 923 924 925 926 927 928 929 930 931 932 933 934 935 936 937 938 939 940 941 942 943 944 945 946 947 948 949 950 951 952 953 954 955 956 957 958 959

Altair Engineering

1.0 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.5 -2.5

-2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -6.7E-222.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -1.2E-222.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -2.0E-232.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -1.4E-182.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -1.3E-172.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -4.1E-182.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

487

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

488

960 961 962 963 964 965 966 967 968 969 970 971 972 973 974 975 976 977 978 979 980 981 982 983 984 985 986 987 988 989 990 991 992 993 994 995 996 997 998 999 1000 1001 1002 1003 1004 1005 1006 1007 1008 1009 1010 1011 1012 1013 1014 1015 1016 1017 1018 1019 1020 1021 1022 1023 1024 1025 1026 1027 1028

-2.5 1.5 2.0 -2.5 1.0 2.0 -2.5 0.5 2.0 -2.5 -2.5E-182.0 -2.5 -0.5 2.0 -2.5 -1.0 2.0 -2.5 -1.5 2.0 -2.5 -2.0 2.0 -2.5 -2.5 2.0 2.5 2.5 3.0 2.5 2.0 3.0 2.0 2.0 3.0 2.0 2.5 3.0 2.5 1.5 3.0 2.0 1.5 3.0 2.5 1.0 3.0 2.0 1.0 3.0 2.5 0.5 3.0 2.0 0.5 3.0 2.5 -6.7E-193.0 2.0 -1.5E-193.0 2.5 -0.5 3.0 2.0 -0.5 3.0 2.5 -1.0 3.0 2.0 -1.0 3.0 2.5 -1.5 3.0 2.0 -1.5 3.0 2.5 -2.0 3.0 2.0 -2.0 3.0 2.5 -2.5 3.0 2.0 -2.5 3.0 1.5 2.0 3.0 1.5 2.5 3.0 1.5 1.5 3.0 1.5 1.0 3.0 1.5 0.5 3.0 1.5 -3.1E-203.0 1.5 -0.5 3.0 1.5 -1.0 3.0 1.5 -1.5 3.0 1.5 -2.0 3.0 1.5 -2.5 3.0 1.0 2.0 3.0 1.0 2.5 3.0 1.0 1.5 3.0 1.0 1.0 3.0 1.0 0.5 3.0 1.0 -6.2E-213.0 1.0 -0.5 3.0 1.0 -1.0 3.0 1.0 -1.5 3.0 1.0 -2.0 3.0 1.0 -2.5 3.0 0.5 2.0 3.0 0.5 2.5 3.0 0.5 1.5 3.0 0.5 1.0 3.0 0.5 0.5 3.0 0.5 -1.2E-213.0 0.5 -0.5 3.0 0.5 -1.0 3.0 0.5 -1.5 3.0 0.5 -2.0 3.0 0.5 -2.5 3.0 1.50E-322.0 3.0 3.80E-332.5 3.0 2.67E-331.5 3.0 4.07E-341.0 3.0 6.20E-350.5 3.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1029 1030 1031 1032 1033 1034 1035 1036 1037 1038 1039 1040 1041 1042 1043 1044 1045 1046 1047 1048 1049 1050 1051 1052 1053 1054 1055 1056 1057 1058 1059 1060 1061 1062 1063 1064 1065 1066 1067 1068 1069 1070 1071 1072 1073 1074 1075 1076 1077 1078 1079 1080 1081 1082 1083 1084 1085 1086 1087 1088 1089 1090 1091 1092 1093 1094 1095 1096 1097

Altair Engineering

6.35E-32-2.3E-223.0 1.29E-31-0.5 3.0 -4.0E-32-1.0 3.0 -5.5E-32-1.5 3.0 -3.2E-32-2.0 3.0 -4.8E-33-2.5 3.0 -0.5 2.0 3.0 -0.5 2.5 3.0 -0.5 1.5 3.0 -0.5 1.0 3.0 -0.5 0.5 3.0 -0.5 -2.2E-193.0 -0.5 -0.5 3.0 -0.5 -1.0 3.0 -0.5 -1.5 3.0 -0.5 -2.0 3.0 -0.5 -2.5 3.0 -1.0 2.0 3.0 -1.0 2.5 3.0 -1.0 1.5 3.0 -1.0 1.0 3.0 -1.0 0.5 3.0 -1.0 -2.6E-183.0 -1.0 -0.5 3.0 -1.0 -1.0 3.0 -1.0 -1.5 3.0 -1.0 -2.0 3.0 -1.0 -2.5 3.0 -1.5 2.0 3.0 -1.5 2.5 3.0 -1.5 1.5 3.0 -1.5 1.0 3.0 -1.5 0.5 3.0 -1.5 -1.5E-173.0 -1.5 -0.5 3.0 -1.5 -1.0 3.0 -1.5 -1.5 3.0 -1.5 -2.0 3.0 -1.5 -2.5 3.0 -2.0 2.0 3.0 -2.0 2.5 3.0 -2.0 1.5 3.0 -2.0 1.0 3.0 -2.0 0.5 3.0 -2.0 -5.3E-183.0 -2.0 -0.5 3.0 -2.0 -1.0 3.0 -2.0 -1.5 3.0 -2.0 -2.0 3.0 -2.0 -2.5 3.0 -2.5 2.0 3.0 -2.5 2.5 3.0 -2.5 1.5 3.0 -2.5 1.0 3.0 -2.5 0.5 3.0 -2.5 -3.3E-183.0 -2.5 -0.5 3.0 -2.5 -1.0 3.0 -2.5 -1.5 3.0 -2.5 -2.0 3.0 -2.5 -2.5 3.0 2.5 2.5 4.0 2.5 2.0 4.0 2.0 2.0 4.0 2.0 2.5 4.0 2.5 1.5 4.0 2.0 1.5 4.0 2.5 1.0 4.0 2.0 1.0 4.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

489

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

490

1098 1099 1100 1101 1102 1103 1104 1105 1106 1107 1108 1109 1110 1111 1112 1113 1114 1115 1116 1117 1118 1119 1120 1121 1122 1123 1124 1125 1126 1127 1128 1129 1130 1131 1132 1133 1134 1135 1136 1137 1138 1139 1140 1141 1142 1143 1144 1145 1146 1147 1148 1149 1150 1151 1152 1153 1154 1155 1156 1157 1158 1159 1160 1161 1162 1163 1164 1165 1166

2.5 0.5 4.0 2.0 0.5 4.0 2.5 -1.0E-164.0 2.0 -1.8E-164.0 2.5 -0.5 4.0 2.0 -0.5 4.0 2.5 -1.0 4.0 2.0 -1.0 4.0 2.5 -1.5 4.0 2.0 -1.5 4.0 2.5 -2.0 4.0 2.0 -2.0 4.0 2.5 -2.5 4.0 2.0 -2.5 4.0 1.5 2.0 4.0 1.5 2.5 4.0 1.5 1.5 4.0 1.5 1.0 4.0 1.5 0.5 4.0 1.5 -3.1E-164.0 1.5 -0.5 4.0 1.5 -1.0 4.0 1.5 -1.5 4.0 1.5 -2.0 4.0 1.5 -2.5 4.0 1.0 2.0 4.0 1.0 2.5 4.0 1.0 1.5 4.0 1.0 1.0 4.0 1.0 0.5 4.0 1.0 -3.6E-164.0 1.0 -0.5 4.0 1.0 -1.0 4.0 1.0 -1.5 4.0 1.0 -2.0 4.0 1.0 -2.5 4.0 0.5 2.0 4.0 0.5 2.5 4.0 0.5 1.5 4.0 0.5 1.0 4.0 0.5 0.5 4.0 0.5 -2.8E-164.0 0.5 -0.5 4.0 0.5 -1.0 4.0 0.5 -1.5 4.0 0.5 -2.0 4.0 0.5 -2.5 4.0 -1.7E-162.0 4.0 -2.3E-162.5 4.0 -2.7E-171.5 4.0 -3.0E-171.0 4.0 -7.0E-170.5 4.0 2.16E-17-1.4E-164.0 1.65E-16-0.5 4.0 3.53E-16-1.0 4.0 2.86E-16-1.5 4.0 -5.5E-17-2.0 4.0 -2.5E-16-2.5 4.0 -0.5 2.0 4.0 -0.5 2.5 4.0 -0.5 1.5 4.0 -0.5 1.0 4.0 -0.5 0.5 4.0 -0.5 -2.5E-174.0 -0.5 -0.5 4.0 -0.5 -1.0 4.0 -0.5 -1.5 4.0 -0.5 -2.0 4.0 -0.5 -2.5 4.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1167 1168 1169 1170 1171 1172 1173 1174 1175 1176 1177 1178 1179 1180 1181 1182 1183 1184 1185 1186 1187 1188 1189 1190 1191 1192 1193 1194 1195 1196 1197 1198 1199 1200 1201 1202 1203 1204 1205 1206 1207 1208 1209 1210 1211 1212 1213 1214 1215 1216 1217 1218 1219 1220 1221 1222 1223 1224 1225 1226 1227 1228 1229 1230 1231 1232 1233 1234 1235

Altair Engineering

-1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 2.5 2.5 2.0 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 1.5 1.5 1.5

2.0 4.0 2.5 4.0 1.5 4.0 1.0 4.0 0.5 4.0 9.63E-174.0 -0.5 4.0 -1.0 4.0 -1.5 4.0 -2.0 4.0 -2.5 4.0 2.0 4.0 2.5 4.0 1.5 4.0 1.0 4.0 0.5 4.0 2.14E-164.0 -0.5 4.0 -1.0 4.0 -1.5 4.0 -2.0 4.0 -2.5 4.0 2.0 4.0 2.5 4.0 1.5 4.0 1.0 4.0 0.5 4.0 1.84E-164.0 -0.5 4.0 -1.0 4.0 -1.5 4.0 -2.0 4.0 -2.5 4.0 2.0 4.0 2.5 4.0 1.5 4.0 1.0 4.0 0.5 4.0 1.10E-164.0 -0.5 4.0 -1.0 4.0 -1.5 4.0 -2.0 4.0 -2.5 4.0 2.5 5.0 2.0 5.0 2.0 5.0 2.5 5.0 1.5 5.0 1.5 5.0 1.0 5.0 1.0 5.0 0.5 5.0 0.5 5.0 -1.8E-165.0 -2.4E-165.0 -0.5 5.0 -0.5 5.0 -1.0 5.0 -1.0 5.0 -1.5 5.0 -1.5 5.0 -2.0 5.0 -2.0 5.0 -2.5 5.0 -2.5 5.0 2.0 5.0 2.5 5.0 1.5 5.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

491

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

492

1236 1237 1238 1239 1240 1241 1242 1243 1244 1245 1246 1247 1248 1249 1250 1251 1252 1253 1254 1255 1256 1257 1258 1259 1260 1261 1262 1263 1264 1265 1266 1267 1268 1269 1270 1271 1272 1273 1274 1275 1276 1277 1278 1279 1280 1281 1282 1283 1284 1285 1286 1287 1288 1289 1290 1291 1292 1293 1294 1295 1296 1297 1298 1299 1300 1301 1302 1303 1304

1.5 1.0 5.0 1.5 0.5 5.0 1.5 -2.8E-165.0 1.5 -0.5 5.0 1.5 -1.0 5.0 1.5 -1.5 5.0 1.5 -2.0 5.0 1.5 -2.5 5.0 1.0 2.0 5.0 1.0 2.5 5.0 1.0 1.5 5.0 1.0 1.0 5.0 1.0 0.5 5.0 1.0 -3.0E-165.0 1.0 -0.5 5.0 1.0 -1.0 5.0 1.0 -1.5 5.0 1.0 -2.0 5.0 1.0 -2.5 5.0 0.5 2.0 5.0 0.5 2.5 5.0 0.5 1.5 5.0 0.5 1.0 5.0 0.5 0.5 5.0 0.5 -2.4E-165.0 0.5 -0.5 5.0 0.5 -1.0 5.0 0.5 -1.5 5.0 0.5 -2.0 5.0 0.5 -2.5 5.0 -2.4E-162.0 5.0 -2.4E-162.5 5.0 -1.4E-161.5 5.0 -1.1E-161.0 5.0 -6.8E-170.5 5.0 -2.1E-17-1.4E-165.0 1.13E-16-0.5 5.0 2.64E-16-1.0 5.0 2.07E-16-1.5 5.0 -8.9E-18-2.0 5.0 -1.0E-16-2.5 5.0 -0.5 2.0 5.0 -0.5 2.5 5.0 -0.5 1.5 5.0 -0.5 1.0 5.0 -0.5 0.5 5.0 -0.5 -2.9E-175.0 -0.5 -0.5 5.0 -0.5 -1.0 5.0 -0.5 -1.5 5.0 -0.5 -2.0 5.0 -0.5 -2.5 5.0 -1.0 2.0 5.0 -1.0 2.5 5.0 -1.0 1.5 5.0 -1.0 1.0 5.0 -1.0 0.5 5.0 -1.0 8.84E-175.0 -1.0 -0.5 5.0 -1.0 -1.0 5.0 -1.0 -1.5 5.0 -1.0 -2.0 5.0 -1.0 -2.5 5.0 -1.5 2.0 5.0 -1.5 2.5 5.0 -1.5 1.5 5.0 -1.5 1.0 5.0 -1.5 0.5 5.0 -1.5 1.34E-165.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1305 1306 1307 1308 1309 1310 1311 1312 1313 1314 1315 1316 1317 1318 1319 1320 1321 1322 1323 1324 1325 1326 1327 1328 1329 1330 1331 1332 1333 1334 1335 1336 1337 1338 1339 1340 1341 1342 1343 1344 1345 1346 1347 1348 1349 1350 1351 1352 1353 1354 1355 1356 1357 1358 1359 1360 1361 1362 1363 1364 1365 1366 1367 1368 1369 1370 1371 1372 1373

Altair Engineering

-1.5 -0.5 5.0 -1.5 -1.0 5.0 -1.5 -1.5 5.0 -1.5 -2.0 5.0 -1.5 -2.5 5.0 -2.0 2.0 5.0 -2.0 2.5 5.0 -2.0 1.5 5.0 -2.0 1.0 5.0 -2.0 0.5 5.0 -2.0 1.09E-165.0 -2.0 -0.5 5.0 -2.0 -1.0 5.0 -2.0 -1.5 5.0 -2.0 -2.0 5.0 -2.0 -2.5 5.0 -2.5 2.0 5.0 -2.5 2.5 5.0 -2.5 1.5 5.0 -2.5 1.0 5.0 -2.5 0.5 5.0 -2.5 5.75E-175.0 -2.5 -0.5 5.0 -2.5 -1.0 5.0 -2.5 -1.5 5.0 -2.5 -2.0 5.0 -2.5 -2.5 5.0 2.0 2.0 0.0 2.0 1.5 0.0 2.0 1.0 0.0 2.0 0.5 0.0 2.0 -2.2E-180.0 2.0 -0.5 0.0 2.0 -1.0 0.0 2.0 -1.5 0.0 2.0 -2.0 0.0 1.5 2.0 0.0 1.5 1.5 0.0 1.5 1.0 0.0 1.5 0.5 0.0 1.5 -1.9E-180.0 1.5 -0.5 0.0 1.5 -1.0 0.0 1.5 -1.5 0.0 1.5 -2.0 0.0 1.0 2.0 0.0 1.0 1.5 0.0 1.0 1.0 0.0 1.0 0.5 0.0 1.0 -1.9E-180.0 1.0 -0.5 0.0 1.0 -1.0 0.0 1.0 -1.5 0.0 1.0 -2.0 0.0 0.5 2.0 0.0 0.5 1.5 0.0 0.5 1.0 0.0 0.5 0.5 0.0 0.5 -1.9E-180.0 0.5 -0.5 0.0 0.5 -1.0 0.0 0.5 -1.5 0.0 0.5 -2.0 0.0 -2.8E-182.0 0.0 -2.8E-181.5 0.0 -2.5E-181.0 0.0 -2.8E-180.5 0.0 -3.1E-18-1.7E-180.0 -2.8E-18-0.5 0.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

493

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

494

1374 1375 1376 1377 1378 1379 1380 1381 1382 1383 1384 1385 1386 1387 1388 1389 1390 1391 1392 1393 1394 1395 1396 1397 1398 1399 1400 1401 1402 1403 1404 1405 1406 1407 1408 1409 1410 1411 1412 1413 1414 1415 1416 1417 1418 1419 1420 1421 1422 1423 1424 1425 1426 1427 1428 1429 1430 1431 1432 1433 1434 1435 1436 1437 1438 1439 1440 1441 1442

-3.1E-18-1.0 0.0 -1.9E-18-1.5 0.0 -2.8E-18-2.0 0.0 -0.5 2.0 0.0 -0.5 1.5 0.0 -0.5 1.0 0.0 -0.5 0.5 0.0 -0.5 -1.7E-180.0 -0.5 -0.5 0.0 -0.5 -1.0 0.0 -0.5 -1.5 0.0 -0.5 -2.0 0.0 -1.0 2.0 0.0 -1.0 1.5 0.0 -1.0 1.0 0.0 -1.0 0.5 0.0 -1.0 -1.9E-180.0 -1.0 -0.5 0.0 -1.0 -1.0 0.0 -1.0 -1.5 0.0 -1.0 -2.0 0.0 -1.5 2.0 0.0 -1.5 1.5 0.0 -1.5 1.0 0.0 -1.5 0.5 0.0 -1.5 -1.7E-180.0 -1.5 -0.5 0.0 -1.5 -1.0 0.0 -1.5 -1.5 0.0 -1.5 -2.0 0.0 -2.0 2.0 0.0 -2.0 1.5 0.0 -2.0 1.0 0.0 -2.0 0.5 0.0 -2.0 -2.2E-180.0 -2.0 -0.5 0.0 -2.0 -1.0 0.0 -2.0 -1.5 0.0 -2.0 -2.0 0.0 2.4964642.0 0.004472 2.4964641.5 0.004472 2.4964641.0 0.004472 2.4964640.5 0.004472 2.496464-2.6E-180.004472 2.496464-0.5 0.004472 2.496464-1.0 0.004472 2.496464-1.5 0.004472 2.496464-2.0 0.004472 -2.496462.0 0.004472 -2.496461.5 0.004472 -2.496461.0 0.004472 -2.496460.5 0.004472 -2.49646-2.6E-180.004472 -2.49646-0.5 0.004472 -2.49646-1.0 0.004472 -2.49646-1.5 0.004472 -2.49646-2.0 0.004472 2.4961522.4961520.005963 2.496152-2.496150.005963 2.0 2.4964640.004472 2.0 -2.496460.004472 1.5 2.4964640.004472 1.5 -2.496460.004472 1.0 2.4964640.004472 1.0 -2.496460.004472 0.5 2.4964640.004472 0.5 -2.496460.004472 -2.6E-182.4964640.004472 -2.6E-18-2.496460.004472

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1443 1444 1445 1446 1447 1448 1449 1450 1451 1452 1453 1454 1455 1456 1457 1458 1459 1460 1461 1462 1463 1464 1465 1466 1467 1468 1469 1470 1471 1472 1473 1474 1475 1476 1477 1478 1479 1480 1481 1482 1483 1484 1485 1486 1487 1488 1489 1493 1494 1495 1496 1497 1498 1499 1500 1504 1505 1506 1507 1508 1509 1510 1511 1515 1516 1517 1518 1519 1520

Altair Engineering

-0.5 2.4964640.004472 -0.5 -2.496460.004472 -1.0 2.4964640.004472 -1.0 -2.496460.004472 -1.5 2.4964640.004472 -1.5 -2.496460.004472 -2.0 2.4964640.004472 -2.0 -2.496460.004472 -2.496152.4961520.005963 -2.49615-2.496150.005963 -2.49615-2.496154.994037 -2.49646-2.0 4.995528 -2.49646-1.5 4.995528 -2.49646-1.0 4.995528 -2.49646-0.5 4.995528 -2.496465.58E-174.995528 -2.496460.5 4.995528 -2.496461.0 4.995528 -2.496461.5 4.995528 -2.496152.4961524.994037 -2.496462.0 4.995528 -2.0 -2.496464.995528 -2.0 -2.0 5.0 -2.0 -1.5 5.0 -2.0 -1.0 5.0 -2.0 -0.5 5.0 -2.0 1.05E-165.0 -2.0 0.5 5.0 -2.0 1.0 5.0 -2.0 1.5 5.0 -2.0 2.4964644.995528 -2.0 2.0 5.0 -1.5 -2.496464.995528 -1.5 -2.0 5.0 -1.5 -1.5 5.0 -1.5 -1.0 5.0 -1.5 -0.5 5.0 -1.5 1.32E-165.0 -1.5 0.5 5.0 -1.5 1.0 5.0 -1.5 1.5 5.0 -1.5 2.4964644.995528 -1.5 2.0 5.0 -1.0 -2.496464.995528 -1.0 -2.0 5.0 -1.0 -1.5 5.0 -1.0 -1.0 5.0 -1.0 1.0 5.0 -1.0 1.5 5.0 -1.0 2.4964644.995528 -1.0 2.0 5.0 -0.5 -2.496464.995528 -0.5 -2.0 5.0 -0.5 -1.5 5.0 -0.5 -1.0 5.0 -0.5 1.0 5.0 -0.5 1.5 5.0 -0.5 2.4964644.995528 -0.5 2.0 5.0 -1.0E-16-2.496464.995528 -1.1E-17-2.0 5.0 2.04E-16-1.5 5.0 2.61E-16-1.0 5.0 -1.2E-161.0 5.0 -1.4E-161.5 5.0 -2.4E-162.4964644.995528 -2.4E-162.0 5.0 0.5 -2.496464.995528 0.5 -2.0 5.0

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

495

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

496

1521 1522 1526 1527 1528 1529 1530 1531 1532 1533 1534 1535 1536 1537 1538 1539 1540 1541 1542 1543 1544 1545 1546 1547 1548 1549 1550 1551 1552 1553 1554 1555 1556 1557 1558 1559 1560 1561 1562 1563 1564 1565 1566 1567 1568 1569 1570 1571 1572 1573 1574 1575 1576 1577 1578 1579 1580 1581 1582 1583 1584 1585 1586 1587 1588 1589 1590 1591 1592

0.5 -1.5 5.0 0.5 -1.0 5.0 0.5 1.0 5.0 0.5 1.5 5.0 0.5 2.4964644.995528 0.5 2.0 5.0 1.0 -2.496464.995528 1.0 -2.0 5.0 1.0 -1.5 5.0 1.0 -1.0 5.0 1.0 -0.5 5.0 1.0 -3.0E-165.0 1.0 0.5 5.0 1.0 1.0 5.0 1.0 1.5 5.0 1.0 2.4964644.995528 1.0 2.0 5.0 1.5 -2.496464.995528 1.5 -2.0 5.0 1.5 -1.5 5.0 1.5 -1.0 5.0 1.5 -0.5 5.0 1.5 -2.8E-165.0 1.5 0.5 5.0 1.5 1.0 5.0 1.5 1.5 5.0 1.5 2.4964644.995528 1.5 2.0 5.0 2.0 -2.496464.995528 2.496152-2.496154.994037 2.0 -2.0 5.0 2.496464-2.0 4.995528 2.0 -1.5 5.0 2.496464-1.5 4.995528 2.0 -1.0 5.0 2.496464-1.0 4.995528 2.0 -0.5 5.0 2.496464-0.5 4.995528 2.0 -2.4E-165.0 2.496464-1.8E-164.995528 2.0 0.5 5.0 2.4964640.5 4.995528 2.0 1.0 5.0 2.4964641.0 4.995528 2.0 1.5 5.0 2.4964641.5 4.995528 2.0 2.4964644.995528 2.0 2.0 5.0 2.4964642.0 4.995528 2.4961522.4961524.994037 -2.49776-2.497764.0 -2.5 -2.0 4.0 -2.5 -1.5 4.0 -2.5 -1.0 4.0 -2.5 -0.5 4.0 -2.5 1.07E-164.0 -2.5 0.5 4.0 -2.5 1.0 4.0 -2.5 1.5 4.0 -2.497762.4977644.0 -2.5 2.0 4.0 -2.0 -2.5 4.0 -2.0 2.5 4.0 -1.5 -2.5 4.0 -1.5 2.5 4.0 -1.0 -2.5 4.0 -1.0 2.5 4.0 -0.5 -2.5 4.0 -0.5 2.5 4.0

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1593 1594 1595 1596 1597 1598 1599 1600 1601 1602 1603 1604 1605 1606 1607 1608 1609 1610 1611 1612 1613 1614 1615 1616 1617 1618 1619 1620 1621 1622 1623 1624 1625 1626 1627 1628 1629 1630 1631 1632 1633 1634 1635 1636 1637 1638 1639 1640 1641 1642 1643 1644 1645 1646 1647 1648 1649 1650 1651 1652 1653 1654 1655 1656 1657 1658 1659 1660 1661

Altair Engineering

-2.5E-16-2.5 4.0 -2.3E-162.5 4.0 0.5 -2.5 4.0 0.5 2.5 4.0 1.0 -2.5 4.0 1.0 2.5 4.0 1.5 -2.5 4.0 1.5 2.5 4.0 2.0 -2.5 4.0 2.497764-2.497764.0 2.5 -2.0 4.0 2.5 -1.5 4.0 2.5 -1.0 4.0 2.5 -0.5 4.0 2.5 -1.0E-164.0 2.5 0.5 4.0 2.5 1.0 4.0 2.5 1.5 4.0 2.0 2.5 4.0 2.5 2.0 4.0 2.4977642.4977644.0 -2.49776-2.497763.0 -2.5 -2.0 3.0 -2.5 -1.5 3.0 -2.5 -1.0 3.0 -2.5 -0.5 3.0 -2.5 -5.4E-183.0 -2.5 0.5 3.0 -2.5 1.0 3.0 -2.5 1.5 3.0 -2.497762.4977643.0 -2.5 2.0 3.0 -2.0 -2.5 3.0 -2.0 2.5 3.0 -1.5 -2.5 3.0 -1.5 2.5 3.0 -1.0 -2.5 3.0 -1.0 2.5 3.0 -0.5 -2.5 3.0 -0.5 2.5 3.0 -2.9E-18-2.5 3.0 -3.1E-182.5 3.0 0.5 -2.5 3.0 0.5 2.5 3.0 1.0 -2.5 3.0 1.0 2.5 3.0 1.5 -2.5 3.0 1.5 2.5 3.0 2.0 -2.5 3.0 2.497764-2.497763.0 2.5 -2.0 3.0 2.5 -1.5 3.0 2.5 -1.0 3.0 2.5 -0.5 3.0 2.5 -3.4E-183.0 2.5 0.5 3.0 2.5 1.0 3.0 2.5 1.5 3.0 2.0 2.5 3.0 2.5 2.0 3.0 2.4977642.4977643.0 -2.49776-2.497762.0 -2.5 -2.0 2.0 -2.5 -1.5 2.0 -2.5 -1.0 2.0 -2.5 -0.5 2.0 -2.5 -5.0E-182.0 -2.5 0.5 2.0 -2.5 1.0 2.0

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

497

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

498

1662 1663 1664 1665 1666 1667 1668 1669 1670 1671 1672 1673 1674 1675 1676 1677 1678 1679 1680 1681 1682 1683 1684 1685 1686 1687 1688 1689 1690 1691 1692 1693 1694 1695 1696 1697 1698 1699 1700 1701 1702 1703 1704 1705 1706 1707 1708 1709 1710 1711 1712 1713 1714 1715 1716 1717 1718 1719 1720 1721 1722 1723 1724 1725 1726 1727 1728 1729 1730

-2.5 1.5 2.0 -2.497762.4977642.0 -2.5 2.0 2.0 -2.0 -2.5 2.0 -2.0 2.5 2.0 -1.5 -2.5 2.0 -1.5 2.5 2.0 -1.0 -2.5 2.0 -1.0 2.5 2.0 -0.5 -2.5 2.0 -0.5 2.5 2.0 -2.5E-18-2.5 2.0 -2.5E-182.5 2.0 0.5 -2.5 2.0 0.5 2.5 2.0 1.0 -2.5 2.0 1.0 2.5 2.0 1.5 -2.5 2.0 1.5 2.5 2.0 2.0 -2.5 2.0 2.497764-2.497762.0 2.5 -2.0 2.0 2.5 -1.5 2.0 2.5 -1.0 2.0 2.5 -0.5 2.0 2.5 -3.1E-182.0 2.5 0.5 2.0 2.5 1.0 2.0 2.5 1.5 2.0 2.0 2.5 2.0 2.5 2.0 2.0 2.4977642.4977642.0 -2.49776-2.497761.0 -2.5 -2.0 1.0 -2.5 -1.5 1.0 -2.5 -1.0 1.0 -2.5 -0.5 1.0 -2.5 -3.5E-181.0 -2.5 0.5 1.0 -2.5 1.0 1.0 -2.5 1.5 1.0 -2.497762.4977641.0 -2.5 2.0 1.0 -2.0 -2.5 1.0 -2.0 2.5 1.0 -1.5 -2.5 1.0 -1.5 2.5 1.0 -1.0 -2.5 1.0 -1.0 2.5 1.0 -0.5 -2.5 1.0 -0.5 2.5 1.0 -2.5E-18-2.5 1.0 -2.5E-182.5 1.0 0.5 -2.5 1.0 0.5 2.5 1.0 1.0 -2.5 1.0 1.0 2.5 1.0 1.5 -2.5 1.0 1.5 2.5 1.0 2.0 -2.5 1.0 2.497764-2.497761.0 2.5 -2.0 1.0 2.5 -1.5 1.0 2.5 -1.0 1.0 2.5 -0.5 1.0 2.5 -2.9E-181.0 2.5 0.5 1.0 2.5 1.0 1.0 2.5 1.5 1.0

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID 1731 2.0 2.5 1.0 GRID 1732 2.5 2.0 1.0 GRID 1733 2.4977642.4977641.0 GRID 1734 -0.25 3.33E-165.0 $$ $$ SPOINT Data $$ $$ $$------------------------------------------------------------------------------$ $$ Group Definitions $ $$------------------------------------------------------------------------------$ $$ $$ RBE2 Elements - Multiple dependent nodes $$ RBE2 1553 1734 123456 1478 1479 1480 1481 1482+ + 1489 1493 1500 1504 1511 1515 1522 1526+ + 1533 1534 1535 1536 1537 $ $HMMOVE 6 $ 1553 $ $ CQUAD4 Elements $ CQUAD4 1101 4 1332 1341 1342 1333 CQUAD4 1102 4 1333 1342 1343 1334 CQUAD4 1103 4 1334 1343 1344 1335 CQUAD4 1104 4 1335 1344 1345 1336 CQUAD4 1105 4 1336 1345 1346 1337 CQUAD4 1106 4 1337 1346 1347 1338 CQUAD4 1107 4 1338 1347 1348 1339 CQUAD4 1108 4 1339 1348 1349 1340 CQUAD4 1109 4 1341 1350 1351 1342 CQUAD4 1110 4 1342 1351 1352 1343 CQUAD4 1111 4 1343 1352 1353 1344 CQUAD4 1112 4 1344 1353 1354 1345 CQUAD4 1113 4 1345 1354 1355 1346 CQUAD4 1114 4 1346 1355 1356 1347 CQUAD4 1115 4 1347 1356 1357 1348 CQUAD4 1116 4 1348 1357 1358 1349 CQUAD4 1117 4 1350 1359 1360 1351 CQUAD4 1118 4 1351 1360 1361 1352 CQUAD4 1119 4 1352 1361 1362 1353 CQUAD4 1120 4 1353 1362 1363 1354 CQUAD4 1121 4 1354 1363 1364 1355 CQUAD4 1122 4 1355 1364 1365 1356 CQUAD4 1123 4 1356 1365 1366 1357 CQUAD4 1124 4 1357 1366 1367 1358 CQUAD4 1125 4 1359 1368 1369 1360 CQUAD4 1126 4 1360 1369 1370 1361 CQUAD4 1127 4 1361 1370 1371 1362 CQUAD4 1128 4 1362 1371 1372 1363 CQUAD4 1129 4 1363 1372 1373 1364 CQUAD4 1130 4 1364 1373 1374 1365 CQUAD4 1131 4 1365 1374 1375 1366 CQUAD4 1132 4 1366 1375 1376 1367 CQUAD4 1133 4 1368 1377 1378 1369 CQUAD4 1134 4 1369 1378 1379 1370 CQUAD4 1135 4 1370 1379 1380 1371 CQUAD4 1136 4 1371 1380 1381 1372 CQUAD4 1137 4 1372 1381 1382 1373 CQUAD4 1138 4 1373 1382 1383 1374 CQUAD4 1139 4 1374 1383 1384 1375 CQUAD4 1140 4 1375 1384 1385 1376 CQUAD4 1141 4 1377 1386 1387 1378 CQUAD4 1142 4 1378 1387 1388 1379 CQUAD4 1143 4 1379 1388 1389 1380 CQUAD4 1144 4 1380 1389 1390 1381 CQUAD4 1145 4 1381 1390 1391 1382 CQUAD4 1146 4 1382 1391 1392 1383

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

499

CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4

500

1147 1148 1149 1150 1151 1152 1153 1154 1155 1156 1157 1158 1159 1160 1161 1162 1163 1164 1165 1166 1167 1168 1169 1170 1171 1172 1173 1174 1175 1176 1177 1178 1179 1180 1181 1182 1183 1184 1185 1186 1187 1188 1189 1190 1191 1192 1193 1194 1195 1196 1197 1198 1199 1200 1201 1202 1203 1204 1205 1206 1207 1208 1209 1210 1211 1212 1213 1214 1215

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

1383 1384 1386 1387 1388 1389 1390 1391 1392 1393 1395 1396 1397 1398 1399 1400 1401 1402 1413 1414 1415 1416 1417 1418 1419 1420 1404 1405 1406 1407 1408 1409 1410 1411 1431 1433 1421 1340 1435 1349 1437 1358 1439 1367 1441 1376 1443 1385 1445 1394 1447 1403 1449 1412 1431 1413 1414 1433 1415 1416 1417 1418 1419 1420 1421 1432 1434 1436 1435

1392 1393 1395 1396 1397 1398 1399 1400 1401 1402 1404 1405 1406 1407 1408 1409 1410 1411 1332 1333 1334 1335 1336 1337 1338 1339 1422 1423 1424 1425 1426 1427 1428 1429 1433 1435 1340 1349 1437 1358 1439 1367 1441 1376 1443 1385 1445 1394 1447 1403 1449 1412 1451 1430 1733 1732 1730 1731 1729 1728 1727 1726 1725 1724 1723 1722 1721 1719 1720

1393 1394 1396 1397 1398 1399 1400 1401 1402 1403 1405 1406 1407 1408 1409 1410 1411 1412 1333 1334 1335 1336 1337 1338 1339 1340 1423 1424 1425 1426 1427 1428 1429 1430 1332 1341 1434 1436 1350 1438 1359 1440 1368 1442 1377 1444 1386 1446 1395 1448 1404 1450 1422 1452 1731 1733 1732 1720 1730 1729 1728 1727 1726 1725 1724 1723 1722 1721 1718

1384 1385 1387 1388 1389 1390 1391 1392 1393 1394 1396 1397 1398 1399 1400 1401 1402 1403 1414 1415 1416 1417 1418 1419 1420 1421 1405 1406 1407 1408 1409 1410 1411 1412 1413 1332 1432 1434 1341 1436 1350 1438 1359 1440 1368 1442 1377 1444 1386 1446 1395 1448 1404 1450 1433 1431 1413 1435 1414 1415 1416 1417 1418 1419 1420 1421 1432 1434 1437

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4

1216 1217 1218 1219 1220 1221 1222 1223 1224 1225 1226 1227 1228 1229 1230 1231 1232 1233 1234 1235 1236 1237 1238 1239 1240 1241 1242 1243 1244 1245 1246 1247 1248 1249 1250 1251 1252 1253 1254 1255 1256 1257 1258 1259 1260 1261 1262 1263 1264 1265 1266 1267 1268 1269 1270 1271 1272 1273 1274 1275 1276 1277 1278 1279 1280 1281 1282 1283 1284

Altair Engineering

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

1438 1437 1440 1439 1442 1441 1444 1443 1446 1445 1448 1447 1450 1449 1452 1451 1422 1423 1424 1425 1426 1427 1428 1429 1430 1732 1733 1730 1731 1729 1728 1727 1726 1725 1724 1723 1722 1721 1719 1720 1717 1718 1715 1716 1713 1714 1711 1712 1709 1710 1707 1708 1705 1706 1694 1703 1704 1702 1701 1700 1699 1698 1697 1696 1695 1692 1693 1690 1691

1717 1718 1715 1716 1713 1714 1711 1712 1709 1710 1707 1708 1705 1706 1694 1703 1704 1702 1701 1700 1699 1698 1697 1696 1695 1692 1693 1690 1691 1689 1688 1687 1686 1685 1684 1683 1682 1681 1679 1680 1677 1678 1675 1676 1673 1674 1671 1672 1669 1670 1667 1668 1665 1666 1654 1663 1664 1662 1661 1660 1659 1658 1657 1656 1655 1652 1653 1650 1651

1719 1716 1717 1714 1715 1712 1713 1710 1711 1708 1709 1706 1707 1703 1705 1704 1702 1701 1700 1699 1698 1697 1696 1695 1694 1693 1691 1692 1680 1690 1689 1688 1687 1686 1685 1684 1683 1682 1681 1678 1679 1676 1677 1674 1675 1672 1673 1670 1671 1668 1669 1666 1667 1663 1665 1664 1662 1661 1660 1659 1658 1657 1656 1655 1654 1653 1651 1652 1640

1436 1439 1438 1441 1440 1443 1442 1445 1444 1447 1446 1449 1448 1451 1450 1422 1423 1424 1425 1426 1427 1428 1429 1430 1452 1733 1731 1732 1720 1730 1729 1728 1727 1726 1725 1724 1723 1722 1721 1718 1719 1716 1717 1714 1715 1712 1713 1710 1711 1708 1709 1706 1707 1703 1705 1704 1702 1701 1700 1699 1698 1697 1696 1695 1694 1693 1691 1692 1680

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

501

CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4

502

1285 1286 1287 1288 1289 1290 1291 1292 1293 1294 1295 1296 1297 1298 1299 1300 1301 1302 1303 1304 1305 1306 1307 1308 1309 1310 1311 1312 1313 1314 1315 1316 1317 1318 1319 1320 1321 1322 1323 1324 1325 1326 1327 1328 1329 1330 1331 1332 1333 1334 1335 1336 1337 1338 1339 1340 1341 1342 1343 1344 1345 1346 1347 1348 1349 1350 1351 1352 1353

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

1689 1688 1687 1686 1685 1684 1683 1682 1681 1679 1680 1677 1678 1675 1676 1673 1674 1671 1672 1669 1670 1667 1668 1665 1666 1654 1663 1664 1662 1661 1660 1659 1658 1657 1656 1655 1652 1653 1650 1651 1649 1648 1647 1646 1645 1644 1643 1642 1641 1639 1640 1637 1638 1635 1636 1633 1634 1631 1632 1629 1630 1627 1628 1625 1626 1614 1623 1624 1622

1649 1648 1647 1646 1645 1644 1643 1642 1641 1639 1640 1637 1638 1635 1636 1633 1634 1631 1632 1629 1630 1627 1628 1625 1626 1614 1623 1624 1622 1621 1620 1619 1618 1617 1616 1615 1612 1613 1610 1611 1609 1608 1607 1606 1605 1604 1603 1602 1601 1599 1600 1597 1598 1595 1596 1593 1594 1591 1592 1589 1590 1587 1588 1585 1586 1574 1583 1584 1582

1650 1649 1648 1647 1646 1645 1644 1643 1642 1641 1638 1639 1636 1637 1634 1635 1632 1633 1630 1631 1628 1629 1626 1627 1623 1625 1624 1622 1621 1620 1619 1618 1617 1616 1615 1614 1613 1611 1612 1600 1610 1609 1608 1607 1606 1605 1604 1603 1602 1601 1598 1599 1596 1597 1594 1595 1592 1593 1590 1591 1588 1589 1586 1587 1583 1585 1584 1582 1581

1690 1689 1688 1687 1686 1685 1684 1683 1682 1681 1678 1679 1676 1677 1674 1675 1672 1673 1670 1671 1668 1669 1666 1667 1663 1665 1664 1662 1661 1660 1659 1658 1657 1656 1655 1654 1653 1651 1652 1640 1650 1649 1648 1647 1646 1645 1644 1643 1642 1641 1638 1639 1636 1637 1634 1635 1632 1633 1630 1631 1628 1629 1626 1627 1623 1625 1624 1622 1621

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4

1354 1355 1356 1357 1358 1359 1360 1361 1362 1363 1364 1365 1366 1367 1368 1369 1370 1371 1372 1373 1374 1375 1376 1377 1378 1379 1380 1381 1382 1383 1384 1385 1386 1387 1388 1389 1390 1391 1392 1393 1394 1395 1396 1397 1398 1399 1400 1401 1402 1403 1404 1405 1406 1407 1408 1409 1410 1411 1412 1417 1418 1419 1420 1421 1422 1423 1424 1429 1430

Altair Engineering

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

1621 1620 1619 1618 1617 1616 1615 1612 1613 1610 1572 1611 1569 1609 1567 1608 1565 1607 1563 1606 1561 1605 1559 1604 1557 1603 1555 1602 1601 1553 1599 1571 1568 1600 1566 1564 1562 1560 1558 1556 1554 1552 1597 1551 1549 1598 1548 1547 1546 1545 1544 1543 1542 1541 1595 1540 1538 1596 1537 1532 1531 1530 1593 1529 1527 1594 1526 1521 1520

1581 1580 1579 1578 1577 1576 1575 1572 1573 1569 1571 1570 1568 1567 1566 1565 1564 1563 1562 1561 1560 1559 1558 1557 1556 1555 1554 1553 1552 1552 1541 1551 1549 1550 1548 1547 1546 1545 1544 1543 1542 1541 1530 1540 1538 1539 1537 1536 1535 1534 1533 1532 1531 1530 1519 1529 1527 1528 1526 1521 1520 1519 1508 1518 1516 1517 1515 1510 1509

1580 1579 1578 1577 1576 1575 1574 1573 1570 1572 1570 1550 1571 1569 1568 1567 1566 1565 1564 1563 1562 1561 1560 1559 1558 1557 1556 1555 1553 1554 1552 1550 1551 1539 1549 1548 1547 1546 1545 1544 1543 1542 1541 1539 1540 1528 1538 1537 1536 1535 1534 1533 1532 1531 1530 1528 1529 1517 1527 1522 1521 1520 1519 1517 1518 1506 1516 1511 1510

1620 1619 1618 1617 1616 1615 1614 1613 1611 1612 1573 1600 1572 1610 1569 1609 1567 1608 1565 1607 1563 1606 1561 1605 1559 1604 1557 1603 1602 1555 1601 1570 1571 1598 1568 1566 1564 1562 1560 1558 1556 1554 1599 1550 1551 1596 1549 1548 1547 1546 1545 1544 1543 1542 1597 1539 1540 1594 1538 1533 1532 1531 1595 1528 1529 1592 1527 1522 1521

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

503

CQUAD4 1431 4 1519 CQUAD4 1432 4 1591 CQUAD4 1433 4 1518 CQUAD4 1434 4 1516 CQUAD4 1435 4 1592 CQUAD4 1436 4 1515 CQUAD4 1441 4 1510 CQUAD4 1442 4 1509 CQUAD4 1443 4 1508 CQUAD4 1444 4 1589 CQUAD4 1445 4 1507 CQUAD4 1446 4 1505 CQUAD4 1447 4 1590 CQUAD4 1448 4 1504 CQUAD4 1453 4 1499 CQUAD4 1454 4 1498 CQUAD4 1455 4 1497 CQUAD4 1456 4 1587 CQUAD4 1457 4 1496 CQUAD4 1458 4 1494 CQUAD4 1459 4 1588 CQUAD4 1460 4 1493 CQUAD4 1465 4 1488 CQUAD4 1466 4 1487 CQUAD4 1467 4 1486 CQUAD4 1468 4 1585 CQUAD4 1469 4 1485 CQUAD4 1470 4 1483 CQUAD4 1471 4 1586 CQUAD4 1472 4 1482 CQUAD4 1473 4 1481 CQUAD4 1474 4 1480 CQUAD4 1475 4 1479 CQUAD4 1476 4 1478 CQUAD4 1477 4 1477 CQUAD4 1478 4 1476 CQUAD4 1479 4 1475 CQUAD4 1480 4 1574 CQUAD4 1481 4 1583 CQUAD4 1482 4 1474 CQUAD4 1483 4 1584 CQUAD4 1484 4 1472 CQUAD4 1485 4 1582 CQUAD4 1486 4 1471 CQUAD4 1487 4 1581 CQUAD4 1488 4 1470 CQUAD4 1489 4 1580 CQUAD4 1490 4 1469 CQUAD4 1491 4 1579 CQUAD4 1492 4 1468 CQUAD4 1493 4 1578 CQUAD4 1494 4 1467 CQUAD4 1495 4 1577 CQUAD4 1496 4 1466 CQUAD4 1497 4 1576 CQUAD4 1498 4 1465 CQUAD4 1499 4 1575 CQUAD4 1500 4 1464 $ $ CHEXA Elements: First Order $ CHEXA 601 1 100 + 729 728 CHEXA 602 1 82 + 732 731 CHEXA 603 1 83 + 734 733 CHEXA 604 1 84 + 736 735

504

1508 1497 1507 1505 1506 1504 1499 1498 1497 1486 1496 1494 1495 1493 1488 1487 1486 1475 1485 1483 1484 1482 1477 1476 1475 1464 1474 1472 1473 1471 1470 1469 1468 1467 1466 1465 1464 1453 1462 1463 1463 1461 1461 1460 1460 1459 1459 1458 1458 1457 1457 1456 1456 1455 1455 1454 1454 1453

1509 1508 1506 1507 1495 1505 1500 1499 1498 1497 1495 1496 1484 1494 1489 1488 1487 1486 1484 1485 1473 1483 1478 1477 1476 1475 1473 1474 1462 1472 1471 1470 1469 1468 1467 1466 1465 1464 1463 1462 1461 1463 1460 1461 1459 1460 1458 1459 1457 1458 1456 1457 1455 1456 1454 1455 1453 1454

1520 1593 1517 1518 1590 1516 1511 1510 1509 1591 1506 1507 1588 1505 1500 1499 1498 1589 1495 1496 1586 1494 1489 1488 1487 1587 1484 1485 1583 1483 1482 1481 1480 1479 1478 1477 1476 1585 1584 1473 1582 1474 1581 1472 1580 1471 1579 1470 1578 1469 1577 1468 1576 1467 1575 1466 1574 1465

102

1

82

727

730+

1

2

83

728

729+

2

3

84

731

732+

3

4

85

733

734+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

605 738 606 740 607 742 608 744 609 746 610 748 611 749 612 751 613 752 614 753 615 754 616 755 617 756 618 757 619 758 620 759 621 760 622 762 623 763 624 764 625 765 626 766 627 767 628 768 629 769 630 770 631 771 632 773 633 774 634 775 635 776 636 777 637 778 638 779 639

Altair Engineering

1 737 1 739 1 741 1 743 1 745 1 747 1 729 1 732 1 734 1 736 1 738 1 740 1 742 1 744 1 746 1 748 1 749 1 751 1 752 1 753 1 754 1 755 1 756 1 757 1 758 1 759 1 760 1 762 1 763 1 764 1 765 1 766 1 767 1 768 1

85

4

5

86

735

736+

86

5

6

87

737

738+

87

6

7

88

739

740+

88

7

8

89

741

742+

89

8

9

90

743

744+

90

9

103

101

745

746+

102

104

10

1

730

750+

1

10

11

2

729

749+

2

11

12

3

732

751+

3

12

13

4

734

752+

4

13

14

5

736

753+

5

14

15

6

738

754+

6

15

16

7

740

755+

7

16

17

8

742

756+

8

17

18

9

744

757+

9

18

105

103

746

758+

104

106

19

10

750

761+

10

19

20

11

749

760+

11

20

21

12

751

762+

12

21

22

13

752

763+

13

22

23

14

753

764+

14

23

24

15

754

765+

15

24

25

16

755

766+

16

25

26

17

756

767+

17

26

27

18

757

768+

18

27

107

105

758

769+

106

108

28

19

761

772+

19

28

29

20

760

771+

20

29

30

21

762

773+

21

30

31

22

763

774+

22

31

32

23

764

775+

23

32

33

24

765

776+

24

33

34

25

766

777+

25

34

35

26

767

778+

26

35

36

27

768

779+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

505

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

506

780 640 781 641 782 642 784 643 785 644 786 645 787 646 788 647 789 648 790 649 791 650 792 651 793 652 795 653 796 654 797 655 798 656 799 657 800 658 801 659 802 660 803 661 804 662 806 663 807 664 808 665 809 666 810 667 811 668 812 669 813 670 814 671 815 672 817 673 818

769 1 770 1 771 1 773 1 774 1 775 1 776 1 777 1 778 1 779 1 780 1 781 1 782 1 784 1 785 1 786 1 787 1 788 1 789 1 790 1 791 1 792 1 793 1 795 1 796 1 797 1 798 1 799 1 800 1 801 1 802 1 803 1 804 1 806 1 807

27

36

109

107

769

780+

108

110

37

28

772

783+

28

37

38

29

771

782+

29

38

39

30

773

784+

30

39

40

31

774

785+

31

40

41

32

775

786+

32

41

42

33

776

787+

33

42

43

34

777

788+

34

43

44

35

778

789+

35

44

45

36

779

790+

36

45

111

109

780

791+

110

112

46

37

783

794+

37

46

47

38

782

793+

38

47

48

39

784

795+

39

48

49

40

785

796+

40

49

50

41

786

797+

41

50

51

42

787

798+

42

51

52

43

788

799+

43

52

53

44

789

800+

44

53

54

45

790

801+

45

54

113

111

791

802+

112

114

55

46

794

805+

46

55

56

47

793

804+

47

56

57

48

795

806+

48

57

58

49

796

807+

49

58

59

50

797

808+

50

59

60

51

798

809+

51

60

61

52

799

810+

52

61

62

53

800

811+

53

62

63

54

801

812+

54

63

115

113

802

813+

114

116

64

55

805

816+

55

64

65

56

804

815+

56

65

66

57

806

817+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

674 819 675 820 676 821 677 822 678 823 679 824 680 825 681 826 682 828 683 829 684 830 685 831 686 832 687 833 688 834 689 835 690 836 691 837 692 839 693 840 694 841 695 842 696 843 697 844 698 845 699 846 700 847 701 850 702 853 703 855 704 857 705 859 706 861 707 863 708

Altair Engineering

1 808 1 809 1 810 1 811 1 812 1 813 1 814 1 815 1 817 1 818 1 819 1 820 1 821 1 822 1 823 1 824 1 825 1 826 1 828 1 829 1 830 1 831 1 832 1 833 1 834 1 835 1 836 1 849 1 852 1 854 1 856 1 858 1 860 1 862 1

57

66

67

58

807

818+

58

67

68

59

808

819+

59

68

69

60

809

820+

60

69

70

61

810

821+

61

70

71

62

811

822+

62

71

72

63

812

823+

63

72

117

115

813

824+

116

118

73

64

816

827+

64

73

74

65

815

826+

65

74

75

66

817

828+

66

75

76

67

818

829+

67

76

77

68

819

830+

68

77

78

69

820

831+

69

78

79

70

821

832+

70

79

80

71

822

833+

71

80

81

72

823

834+

72

81

119

117

824

835+

118

120

91

73

827

838+

73

91

92

74

826

837+

74

92

93

75

828

839+

75

93

94

76

829

840+

76

94

95

77

830

841+

77

95

96

78

831

842+

78

96

97

79

832

843+

79

97

98

80

833

844+

80

98

99

81

834

845+

81

99

121

119

835

846+

727

730

729

728

848

851+

728

729

732

731

849

850+

731

732

734

733

852

853+

733

734

736

735

854

855+

735

736

738

737

856

857+

737

738

740

739

858

859+

739

740

742

741

860

861+

741

742

744

743

862

863+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

507

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

508

865 709 867 710 869 711 870 712 872 713 873 714 874 715 875 716 876 717 877 718 878 719 879 720 880 721 881 722 883 723 884 724 885 725 886 726 887 727 888 728 889 729 890 730 891 731 892 732 894 733 895 734 896 735 897 736 898 737 899 738 900 739 901 740 902 741 903 742 905

864 1 866 1 868 1 850 1 853 1 855 1 857 1 859 1 861 1 863 1 865 1 867 1 869 1 870 1 872 1 873 1 874 1 875 1 876 1 877 1 878 1 879 1 880 1 881 1 883 1 884 1 885 1 886 1 887 1 888 1 889 1 890 1 891 1 892 1 894

743

744

746

745

864

865+

745

746

748

747

866

867+

730

750

749

729

851

871+

729

749

751

732

850

870+

732

751

752

734

853

872+

734

752

753

736

855

873+

736

753

754

738

857

874+

738

754

755

740

859

875+

740

755

756

742

861

876+

742

756

757

744

863

877+

744

757

758

746

865

878+

746

758

759

748

867

879+

750

761

760

749

871

882+

749

760

762

751

870

881+

751

762

763

752

872

883+

752

763

764

753

873

884+

753

764

765

754

874

885+

754

765

766

755

875

886+

755

766

767

756

876

887+

756

767

768

757

877

888+

757

768

769

758

878

889+

758

769

770

759

879

890+

761

772

771

760

882

893+

760

771

773

762

881

892+

762

773

774

763

883

894+

763

774

775

764

884

895+

764

775

776

765

885

896+

765

776

777

766

886

897+

766

777

778

767

887

898+

767

778

779

768

888

899+

768

779

780

769

889

900+

769

780

781

770

890

901+

772

783

782

771

893

904+

771

782

784

773

892

903+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

743 906 744 907 745 908 746 909 747 910 748 911 749 912 750 913 751 914 752 916 753 917 754 918 755 919 756 920 757 921 758 922 759 923 760 924 761 925 762 927 763 928 764 929 765 930 766 931 767 932 768 933 769 934 770 935 771 936 772 938 773 939 774 940 775 941 776 942 777

Altair Engineering

1 895 1 896 1 897 1 898 1 899 1 900 1 901 1 902 1 903 1 905 1 906 1 907 1 908 1 909 1 910 1 911 1 912 1 913 1 914 1 916 1 917 1 918 1 919 1 920 1 921 1 922 1 923 1 924 1 925 1 927 1 928 1 929 1 930 1 931 1

773

784

785

774

894

905+

774

785

786

775

895

906+

775

786

787

776

896

907+

776

787

788

777

897

908+

777

788

789

778

898

909+

778

789

790

779

899

910+

779

790

791

780

900

911+

780

791

792

781

901

912+

783

794

793

782

904

915+

782

793

795

784

903

914+

784

795

796

785

905

916+

785

796

797

786

906

917+

786

797

798

787

907

918+

787

798

799

788

908

919+

788

799

800

789

909

920+

789

800

801

790

910

921+

790

801

802

791

911

922+

791

802

803

792

912

923+

794

805

804

793

915

926+

793

804

806

795

914

925+

795

806

807

796

916

927+

796

807

808

797

917

928+

797

808

809

798

918

929+

798

809

810

799

919

930+

799

810

811

800

920

931+

800

811

812

801

921

932+

801

812

813

802

922

933+

802

813

814

803

923

934+

805

816

815

804

926

937+

804

815

817

806

925

936+

806

817

818

807

927

938+

807

818

819

808

928

939+

808

819

820

809

929

940+

809

820

821

810

930

941+

810

821

822

811

931

942+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

509

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

510

943 778 944 779 945 780 946 781 947 782 949 783 950 784 951 785 952 786 953 787 954 788 955 789 956 790 957 791 958 792 960 793 961 794 962 795 963 796 964 797 965 798 966 799 967 800 968 801 971 802 974 803 976 804 978 805 980 806 982 807 984 808 986 809 988 810 990 811 991

932 1 933 1 934 1 935 1 936 1 938 1 939 1 940 1 941 1 942 1 943 1 944 1 945 1 946 1 947 1 949 1 950 1 951 1 952 1 953 1 954 1 955 1 956 1 957 1 970 1 973 1 975 1 977 1 979 1 981 1 983 1 985 1 987 1 989 1 971

811

822

823

812

932

943+

812

823

824

813

933

944+

813

824

825

814

934

945+

816

827

826

815

937

948+

815

826

828

817

936

947+

817

828

829

818

938

949+

818

829

830

819

939

950+

819

830

831

820

940

951+

820

831

832

821

941

952+

821

832

833

822

942

953+

822

833

834

823

943

954+

823

834

835

824

944

955+

824

835

836

825

945

956+

827

838

837

826

948

959+

826

837

839

828

947

958+

828

839

840

829

949

960+

829

840

841

830

950

961+

830

841

842

831

951

962+

831

842

843

832

952

963+

832

843

844

833

953

964+

833

844

845

834

954

965+

834

845

846

835

955

966+

835

846

847

836

956

967+

848

851

850

849

969

972+

849

850

853

852

970

971+

852

853

855

854

973

974+

854

855

857

856

975

976+

856

857

859

858

977

978+

858

859

861

860

979

980+

860

861

863

862

981

982+

862

863

865

864

983

984+

864

865

867

866

985

986+

866

867

869

868

987

988+

851

871

870

850

972

992+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

812 993 813 994 814 995 815 996 816 997 817 998 818 999 819 1000 820 1001 821 1002 822 1004 823 1005 824 1006 825 1007 826 1008 827 1009 828 1010 829 1011 830 1012 831 1013 832 1015 833 1016 834 1017 835 1018 836 1019 837 1020 838 1021 839 1022 840 1023 841 1024 842 1026 843 1027 844 1028 845 1029 846

Altair Engineering

1 974 1 976 1 978 1 980 1 982 1 984 1 986 1 988 1 990 1 991 1 993 1 994 1 995 1 996 1 997 1 998 1 999 1 1000 1 1001 1 1002 1 1004 1 1005 1 1006 1 1007 1 1008 1 1009 1 1010 1 1011 1 1012 1 1013 1 1015 1 1016 1 1017 1 1018 1

850

870

872

853

971

991+

853

872

873

855

974

993+

855

873

874

857

976

994+

857

874

875

859

978

995+

859

875

876

861

980

996+

861

876

877

863

982

997+

863

877

878

865

984

998+

865

878

879

867

986

999+

867

879

880

869

988

1000+

871

882

881

870

992

1003+

870

881

883

872

991

1002+

872

883

884

873

993

1004+

873

884

885

874

994

1005+

874

885

886

875

995

1006+

875

886

887

876

996

1007+

876

887

888

877

997

1008+

877

888

889

878

998

1009+

878

889

890

879

999

1010+

879

890

891

880

1000

1011+

882

893

892

881

1003

1014+

881

892

894

883

1002

1013+

883

894

895

884

1004

1015+

884

895

896

885

1005

1016+

885

896

897

886

1006

1017+

886

897

898

887

1007

1018+

887

898

899

888

1008

1019+

888

899

900

889

1009

1020+

889

900

901

890

1010

1021+

890

901

902

891

1011

1022+

893

904

903

892

1014

1025+

892

903

905

894

1013

1024+

894

905

906

895

1015

1026+

895

906

907

896

1016

1027+

896

907

908

897

1017

1028+

897

908

909

898

1018

1029+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

511

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

512

1030 847 1031 848 1032 849 1033 850 1034 851 1035 852 1037 853 1038 854 1039 855 1040 856 1041 857 1042 858 1043 859 1044 860 1045 861 1046 862 1048 863 1049 864 1050 865 1051 866 1052 867 1053 868 1054 869 1055 870 1056 871 1057 872 1059 873 1060 874 1061 875 1062 876 1063 877 1064 878 1065 879 1066 880 1067

1019 1 1020 1 1021 1 1022 1 1023 1 1024 1 1026 1 1027 1 1028 1 1029 1 1030 1 1031 1 1032 1 1033 1 1034 1 1035 1 1037 1 1038 1 1039 1 1040 1 1041 1 1042 1 1043 1 1044 1 1045 1 1046 1 1048 1 1049 1 1050 1 1051 1 1052 1 1053 1 1054 1 1055 1 1056

898

909

910

899

1019

1030+

899

910

911

900

1020

1031+

900

911

912

901

1021

1032+

901

912

913

902

1022

1033+

904

915

914

903

1025

1036+

903

914

916

905

1024

1035+

905

916

917

906

1026

1037+

906

917

918

907

1027

1038+

907

918

919

908

1028

1039+

908

919

920

909

1029

1040+

909

920

921

910

1030

1041+

910

921

922

911

1031

1042+

911

922

923

912

1032

1043+

912

923

924

913

1033

1044+

915

926

925

914

1036

1047+

914

925

927

916

1035

1046+

916

927

928

917

1037

1048+

917

928

929

918

1038

1049+

918

929

930

919

1039

1050+

919

930

931

920

1040

1051+

920

931

932

921

1041

1052+

921

932

933

922

1042

1053+

922

933

934

923

1043

1054+

923

934

935

924

1044

1055+

926

937

936

925

1047

1058+

925

936

938

927

1046

1057+

927

938

939

928

1048

1059+

928

939

940

929

1049

1060+

929

940

941

930

1050

1061+

930

941

942

931

1051

1062+

931

942

943

932

1052

1063+

932

943

944

933

1053

1064+

933

944

945

934

1054

1065+

934

945

946

935

1055

1066+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

881 1068 882 1070 883 1071 884 1072 885 1073 886 1074 887 1075 888 1076 889 1077 890 1078 891 1079 892 1081 893 1082 894 1083 895 1084 896 1085 897 1086 898 1087 899 1088 900 1089 901 1092 902 1095 903 1097 904 1099 905 1101 906 1103 907 1105 908 1107 909 1109 910 1111 911 1112 912 1114 913 1115 914 1116 915

Altair Engineering

1 1057 1 1059 1 1060 1 1061 1 1062 1 1063 1 1064 1 1065 1 1066 1 1067 1 1068 1 1070 1 1071 1 1072 1 1073 1 1074 1 1075 1 1076 1 1077 1 1078 1 1091 1 1094 1 1096 1 1098 1 1100 1 1102 1 1104 1 1106 1 1108 1 1110 1 1092 1 1095 1 1097 1 1099 1

937

948

947

936

1058

1069+

936

947

949

938

1057

1068+

938

949

950

939

1059

1070+

939

950

951

940

1060

1071+

940

951

952

941

1061

1072+

941

952

953

942

1062

1073+

942

953

954

943

1063

1074+

943

954

955

944

1064

1075+

944

955

956

945

1065

1076+

945

956

957

946

1066

1077+

948

959

958

947

1069

1080+

947

958

960

949

1068

1079+

949

960

961

950

1070

1081+

950

961

962

951

1071

1082+

951

962

963

952

1072

1083+

952

963

964

953

1073

1084+

953

964

965

954

1074

1085+

954

965

966

955

1075

1086+

955

966

967

956

1076

1087+

956

967

968

957

1077

1088+

969

972

971

970

1090

1093+

970

971

974

973

1091

1092+

973

974

976

975

1094

1095+

975

976

978

977

1096

1097+

977

978

980

979

1098

1099+

979

980

982

981

1100

1101+

981

982

984

983

1102

1103+

983

984

986

985

1104

1105+

985

986

988

987

1106

1107+

987

988

990

989

1108

1109+

972

992

991

971

1093

1113+

971

991

993

974

1092

1112+

974

993

994

976

1095

1114+

976

994

995

978

1097

1115+

978

995

996

980

1099

1116+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

513

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

514

1117 916 1118 917 1119 918 1120 919 1121 920 1122 921 1123 922 1125 923 1126 924 1127 925 1128 926 1129 927 1130 928 1131 929 1132 930 1133 931 1134 932 1136 933 1137 934 1138 935 1139 936 1140 937 1141 938 1142 939 1143 940 1144 941 1145 942 1147 943 1148 944 1149 945 1150 946 1151 947 1152 948 1153 949 1154

1101 1 1103 1 1105 1 1107 1 1109 1 1111 1 1112 1 1114 1 1115 1 1116 1 1117 1 1118 1 1119 1 1120 1 1121 1 1122 1 1123 1 1125 1 1126 1 1127 1 1128 1 1129 1 1130 1 1131 1 1132 1 1133 1 1134 1 1136 1 1137 1 1138 1 1139 1 1140 1 1141 1 1142 1 1143

980

996

997

982

1101

1117+

982

997

998

984

1103

1118+

984

998

999

986

1105

1119+

986

999

1000

988

1107

1120+

988

1000

1001

990

1109

1121+

992

1003

1002

991

1113

1124+

991

1002

1004

993

1112

1123+

993

1004

1005

994

1114

1125+

994

1005

1006

995

1115

1126+

995

1006

1007

996

1116

1127+

996

1007

1008

997

1117

1128+

997

1008

1009

998

1118

1129+

998

1009

1010

999

1119

1130+

999

1010

1011

1000

1120

1131+

1000

1011

1012

1001

1121

1132+

1003

1014

1013

1002

1124

1135+

1002

1013

1015

1004

1123

1134+

1004

1015

1016

1005

1125

1136+

1005

1016

1017

1006

1126

1137+

1006

1017

1018

1007

1127

1138+

1007

1018

1019

1008

1128

1139+

1008

1019

1020

1009

1129

1140+

1009

1020

1021

1010

1130

1141+

1010

1021

1022

1011

1131

1142+

1011

1022

1023

1012

1132

1143+

1014

1025

1024

1013

1135

1146+

1013

1024

1026

1015

1134

1145+

1015

1026

1027

1016

1136

1147+

1016

1027

1028

1017

1137

1148+

1017

1028

1029

1018

1138

1149+

1018

1029

1030

1019

1139

1150+

1019

1030

1031

1020

1140

1151+

1020

1031

1032

1021

1141

1152+

1021

1032

1033

1022

1142

1153+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

950 1155 951 1156 952 1158 953 1159 954 1160 955 1161 956 1162 957 1163 958 1164 959 1165 960 1166 961 1167 962 1169 963 1170 964 1171 965 1172 966 1173 967 1174 968 1175 969 1176 970 1177 971 1178 972 1180 973 1181 974 1182 975 1183 976 1184 977 1185 978 1186 979 1187 980 1188 981 1189 982 1191 983 1192 984

Altair Engineering

1 1144 1 1145 1 1147 1 1148 1 1149 1 1150 1 1151 1 1152 1 1153 1 1154 1 1155 1 1156 1 1158 1 1159 1 1160 1 1161 1 1162 1 1163 1 1164 1 1165 1 1166 1 1167 1 1169 1 1170 1 1171 1 1172 1 1173 1 1174 1 1175 1 1176 1 1177 1 1178 1 1180 1 1181 1

1022

1033

1034

1023

1143

1154+

1025

1036

1035

1024

1146

1157+

1024

1035

1037

1026

1145

1156+

1026

1037

1038

1027

1147

1158+

1027

1038

1039

1028

1148

1159+

1028

1039

1040

1029

1149

1160+

1029

1040

1041

1030

1150

1161+

1030

1041

1042

1031

1151

1162+

1031

1042

1043

1032

1152

1163+

1032

1043

1044

1033

1153

1164+

1033

1044

1045

1034

1154

1165+

1036

1047

1046

1035

1157

1168+

1035

1046

1048

1037

1156

1167+

1037

1048

1049

1038

1158

1169+

1038

1049

1050

1039

1159

1170+

1039

1050

1051

1040

1160

1171+

1040

1051

1052

1041

1161

1172+

1041

1052

1053

1042

1162

1173+

1042

1053

1054

1043

1163

1174+

1043

1054

1055

1044

1164

1175+

1044

1055

1056

1045

1165

1176+

1047

1058

1057

1046

1168

1179+

1046

1057

1059

1048

1167

1178+

1048

1059

1060

1049

1169

1180+

1049

1060

1061

1050

1170

1181+

1050

1061

1062

1051

1171

1182+

1051

1062

1063

1052

1172

1183+

1052

1063

1064

1053

1173

1184+

1053

1064

1065

1054

1174

1185+

1054

1065

1066

1055

1175

1186+

1055

1066

1067

1056

1176

1187+

1058

1069

1068

1057

1179

1190+

1057

1068

1070

1059

1178

1189+

1059

1070

1071

1060

1180

1191+

1060

1071

1072

1061

1181

1192+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

515

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

516

1193 985 1194 986 1195 987 1196 988 1197 989 1198 990 1199 991 1200 992 1202 993 1203 994 1204 995 1205 996 1206 997 1207 998 1208 999 1209 1000 1210 1001 1213 1002 1216 1003 1218 1004 1220 1005 1222 1006 1224 1007 1226 1008 1228 1009 1230 1010 1232 1011 1233 1012 1235 1013 1236 1014 1237 1015 1238 1016 1239 1017 1240 1018 1241

1182 1 1183 1 1184 1 1185 1 1186 1 1187 1 1188 1 1189 1 1191 1 1192 1 1193 1 1194 1 1195 1 1196 1 1197 1 1198 1 1199 1 1212 1 1215 1 1217 1 1219 1 1221 1 1223 1 1225 1 1227 1 1229 1 1231 1 1213 1 1216 1 1218 1 1220 1 1222 1 1224 1 1226 1 1228

1061

1072

1073

1062

1182

1193+

1062

1073

1074

1063

1183

1194+

1063

1074

1075

1064

1184

1195+

1064

1075

1076

1065

1185

1196+

1065

1076

1077

1066

1186

1197+

1066

1077

1078

1067

1187

1198+

1069

1080

1079

1068

1190

1201+

1068

1079

1081

1070

1189

1200+

1070

1081

1082

1071

1191

1202+

1071

1082

1083

1072

1192

1203+

1072

1083

1084

1073

1193

1204+

1073

1084

1085

1074

1194

1205+

1074

1085

1086

1075

1195

1206+

1075

1086

1087

1076

1196

1207+

1076

1087

1088

1077

1197

1208+

1077

1088

1089

1078

1198

1209+

1090

1093

1092

1091

1211

1214+

1091

1092

1095

1094

1212

1213+

1094

1095

1097

1096

1215

1216+

1096

1097

1099

1098

1217

1218+

1098

1099

1101

1100

1219

1220+

1100

1101

1103

1102

1221

1222+

1102

1103

1105

1104

1223

1224+

1104

1105

1107

1106

1225

1226+

1106

1107

1109

1108

1227

1228+

1108

1109

1111

1110

1229

1230+

1093

1113

1112

1092

1214

1234+

1092

1112

1114

1095

1213

1233+

1095

1114

1115

1097

1216

1235+

1097

1115

1116

1099

1218

1236+

1099

1116

1117

1101

1220

1237+

1101

1117

1118

1103

1222

1238+

1103

1118

1119

1105

1224

1239+

1105

1119

1120

1107

1226

1240+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1019 1242 1020 1243 1021 1244 1022 1246 1023 1247 1024 1248 1025 1249 1026 1250 1027 1251 1028 1252 1029 1253 1030 1254 1031 1255 1032 1257 1033 1258 1034 1259 1035 1260 1036 1261 1037 1262 1038 1263 1039 1264 1040 1265 1041 1266 1042 1268 1043 1269 1044 1270 1045 1271 1046 1272 1047 1273 1048 1274 1049 1275 1050 1276 1051 1277 1052 1279 1053

Altair Engineering

1 1230 1 1232 1 1233 1 1235 1 1236 1 1237 1 1238 1 1239 1 1240 1 1241 1 1242 1 1243 1 1244 1 1246 1 1247 1 1248 1 1249 1 1250 1 1251 1 1252 1 1253 1 1254 1 1255 1 1257 1 1258 1 1259 1 1260 1 1261 1 1262 1 1263 1 1264 1 1265 1 1266 1 1268 1

1107

1120

1121

1109

1228

1241+

1109

1121

1122

1111

1230

1242+

1113

1124

1123

1112

1234

1245+

1112

1123

1125

1114

1233

1244+

1114

1125

1126

1115

1235

1246+

1115

1126

1127

1116

1236

1247+

1116

1127

1128

1117

1237

1248+

1117

1128

1129

1118

1238

1249+

1118

1129

1130

1119

1239

1250+

1119

1130

1131

1120

1240

1251+

1120

1131

1132

1121

1241

1252+

1121

1132

1133

1122

1242

1253+

1124

1135

1134

1123

1245

1256+

1123

1134

1136

1125

1244

1255+

1125

1136

1137

1126

1246

1257+

1126

1137

1138

1127

1247

1258+

1127

1138

1139

1128

1248

1259+

1128

1139

1140

1129

1249

1260+

1129

1140

1141

1130

1250

1261+

1130

1141

1142

1131

1251

1262+

1131

1142

1143

1132

1252

1263+

1132

1143

1144

1133

1253

1264+

1135

1146

1145

1134

1256

1267+

1134

1145

1147

1136

1255

1266+

1136

1147

1148

1137

1257

1268+

1137

1148

1149

1138

1258

1269+

1138

1149

1150

1139

1259

1270+

1139

1150

1151

1140

1260

1271+

1140

1151

1152

1141

1261

1272+

1141

1152

1153

1142

1262

1273+

1142

1153

1154

1143

1263

1274+

1143

1154

1155

1144

1264

1275+

1146

1157

1156

1145

1267

1278+

1145

1156

1158

1147

1266

1277+

1147

1158

1159

1148

1268

1279+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

517

+ CHEXA + CHEXA +

1280 1054 1281 1055 1282

1269 1 1270 1 1271

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1057 1284 1058 1285 1059 1286 1060 1287 1061 1288 1062 1290 1063 1291 1064 1292 1065 1293 1066 1294 1067 1295 1068 1296 1069 1297 1070 1298 1071 1299 1072 1301 1073 1302 1074 1303 1075 1304 1076 1305 1077 1306 1078 1307 1079 1308 1080 1309 1081 1310 1082 1312 1083 1313 1084 1314 1085 1315 1086 1316 1087 1317 1088

1 1273 1 1274 1 1275 1 1276 1 1277 1 1279 1 1280 1 1281 1 1282 1 1283 1 1284 1 1285 1 1286 1 1287 1 1288 1 1290 1 1291 1 1292 1 1293 1 1294 1 1295 1 1296 1 1297 1 1298 1 1299 1 1301 1 1302 1 1303 1 1304 1 1305 1 1306 1

518

1148

1159

1160

1149

1269

1280+

1149

1160

1161

1150

1270

1281+

1151

1162

1163

1152

1272

1283+

1152

1163

1164

1153

1273

1284+

1153

1164

1165

1154

1274

1285+

1154

1165

1166

1155

1275

1286+

1157

1168

1167

1156

1278

1289+

1156

1167

1169

1158

1277

1288+

1158

1169

1170

1159

1279

1290+

1159

1170

1171

1160

1280

1291+

1160

1171

1172

1161

1281

1292+

1161

1172

1173

1162

1282

1293+

1162

1173

1174

1163

1283

1294+

1163

1174

1175

1164

1284

1295+

1164

1175

1176

1165

1285

1296+

1165

1176

1177

1166

1286

1297+

1168

1179

1178

1167

1289

1300+

1167

1178

1180

1169

1288

1299+

1169

1180

1181

1170

1290

1301+

1170

1181

1182

1171

1291

1302+

1171

1182

1183

1172

1292

1303+

1172

1183

1184

1173

1293

1304+

1173

1184

1185

1174

1294

1305+

1174

1185

1186

1175

1295

1306+

1175

1186

1187

1176

1296

1307+

1176

1187

1188

1177

1297

1308+

1179

1190

1189

1178

1300

1311+

1178

1189

1191

1180

1299

1310+

1180

1191

1192

1181

1301

1312+

1181

1192

1193

1182

1302

1313+

1182

1193

1194

1183

1303

1314+

1183

1194

1195

1184

1304

1315+

1184

1195

1196

1185

1305

1316+

1185

1196

1197

1186

1306

1317+

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ 1318 1307 CHEXA 1089 1 1186 1197 1198 1187 1307 1318+ + 1319 1308 CHEXA 1090 1 1187 1198 1199 1188 1308 1319+ + 1320 1309 CHEXA 1091 1 1190 1201 1200 1189 1311 1322+ + 1321 1310 CHEXA 1092 1 1189 1200 1202 1191 1310 1321+ + 1323 1312 CHEXA 1093 1 1191 1202 1203 1192 1312 1323+ + 1324 1313 CHEXA 1094 1 1192 1203 1204 1193 1313 1324+ + 1325 1314 CHEXA 1095 1 1193 1204 1205 1194 1314 1325+ + 1326 1315 CHEXA 1096 1 1194 1205 1206 1195 1315 1326+ + 1327 1316 CHEXA 1097 1 1195 1206 1207 1196 1316 1327+ + 1328 1317 CHEXA 1098 1 1196 1207 1208 1197 1317 1328+ + 1329 1318 CHEXA 1099 1 1197 1208 1209 1198 1318 1329+ + 1330 1319 CHEXA 1100 1 1198 1209 1210 1199 1319 1330+ + 1331 1320 $$ $$------------------------------------------------------------------------------$ $$ HyperMesh name information for generic property collectors $ $$------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$ $$ Property Definition for 1-D Elements $ $$------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$ $$ HyperMesh name and color information for generic components $ $$------------------------------------------------------------------------------$ $HMNAME COMP 6"auto1" $HWCOLOR COMP 6 3 $ $$ $$------------------------------------------------------------------------------$ $$ Property Definition for Surface and Volume Elements $ $$------------------------------------------------------------------------------$ $$ $$ PSHELL Data $ $HMNAME COMP 4"shells" $HWCOLOR COMP 4 7 PSHELL 4 20.2 2 2 $$ $$ PSOLID Data $ $HMNAME COMP 1"solids" $HWCOLOR COMP 1 26 PSOLID 1 1 PFLUID PSOLID 2 2 $$ $$------------------------------------------------------------------------------$ $$ Material Definition Cards $ $$------------------------------------------------------------------------------$ $$-------------------------------------------------------------$$ HYPERMESH TAGS $$-------------------------------------------------------------$$BEGIN TAGS $$END TAGS $$ $$ MAT1 Data $

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

519

$HMNAME MAT 2"MAT1" $HWCOLOR MAT 2 18 MAT1 2200000.0 0.3 0.9e-5 $$ $$ $$ MAT10 Data $HMNAME MAT 1"MAT10_1" $HWCOLOR MAT 1 3 MAT10 11.0 0.01 $$ $$ $$------------------------------------------------------------------------------$ $$ HyperMesh name information for generic materials $ $$------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$ $$ Material Definition Cards $ $$------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$ $$ Loads and Boundary Conditions $ $$------------------------------------------------------------------------------$ $$ $$HyperMesh name and color information for generic loadcollectors $$ $HMNAME LOADCOL 4"SPC" $HWCOLOR LOADCOL 4 3 $ $HMNAME LOADCOL 6"spcd" $HWCOLOR LOADCOL 6 4 $ $$ $$ $$ $$ $$ FREQ1 cards $$ $HMNAME LOADCOL 5"freq" $HWCOLOR LOADCOL 5 4 FREQ1 50.1 10.0 5 $$ $$ $$ $$ $$ $$ RLOAD2 cards $$ $HMNAME LOADCOL 2"rload2" $HWCOLOR LOADCOL 2 5 RLOAD2 2 6 1 0 ACCE $$ $HMNAME LOADCOL 3"darea" $HWCOLOR LOADCOL 3 5 RLOAD2 3 3 1 0 LOAD $$ $$ $$ $$ TABLED1 cards $$ $HMNAME LOADCOL 1"tab" $HWCOLOR LOADCOL 1 41 TABLED1 1 LINEAR LINEAR + 0.0 0.0 1000.0 1.0ENDT $$ TABLED1 2 LINEAR LINEAR + 0.0 0.0 1000.0 1.0ENDT $$ TABLED1 3 LINEAR LINEAR + 0.0 5.0 1000.0 5.0ENDT

520

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

$$ DLOAD cards $$ $HMNAME LOADCOL $HWCOLOR LOADCOL DLOAD 111.0 $$ $$ $$ $$ $$ $$ $$ $$ SPC Data $$ SPC 4 SPC 4 SPC 4 SPC 4 SPC 4 $$ $$ SPCD Data $$ SPCD 6 $ $ DAREA Data $ $$ $$ DAREA Data $$ DAREA 3 ENDDATA

11"DLOAD11" 11 3 1.0 2

1431 1432 1451 1452 1734

1234560.0 1234560.0 1234560.0 1234560.0 3 0.0

1734

3

1734

1.0

3

3.0

3-10.0

ALTDOCTAG "HqTD_ARNMI\S\pMpN13G;5oANN]l[enE7fmSbTJro20LOpNriZFOQfUk] _`5hfS5ATf6pT7RXMjA3e@k_r^K?GP;?OeEbD0" ADI0.1.0 2011-05-13T19:57:45 0of1 OSQA ENDDOCTAG

Comments 1.

Element identification numbers should be unique with respect to all other element identification numbers.

2.

Grid points G1 through G4 must be given in consecutive order about one quadrilateral face. G5 through G8 must be on the opposite face with G5 opposite G1, G6 opposite G2, and so on.

3.

The edge points, G9 to G20 are optional. All or none of them may exist. The corner grid points cannot be deleted. The edge points should be in the middle third of the edges.

4.

The second continuation is optional.

5.

The face consisting of grid points G1 through G4 and G9 through G12 is assumed to be in contact with the structure.

6.

The mass is lumped to the face formed by grid points G5 through G8 and G17 through G20 and defined to be in contact with the fluid. The opposite face has no mass contribution due to the absorber element. Also, the face in contact with the fluid has only

Altair Engineering

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translational stiffness in the direction normal to the face. 7.

522

This card is represented as a CHACAB8 or CHACAB20 element in HyperMesh.

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CHBDYE Bulk Data Entry CHBDYE – Thermal Surface Element (Element Form) Description Defines a surface element for application of thermal boundary condition. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

C HBDYE

EID

EID2

SIDE

Field

Contents

EID

Unique surface element identification number. See comments.

(9)

(10)

No default (Integer > 0) EID2

A heat conduction element identification number. See comments. No default (Integer > 0)

SIDE

Element side identification number. No default (1 < Integer < 6)

Comments 1.

EID is unique with respect to other surface element IDs.

2.

EID2 identifies the heat conduction element associated with this surface element. 1D

2D

3D

CBAR CBEAM CONROD CROD

CQUAD4 CQUAD8 CTRIA3 CTIRA6

CHEXA CPENTA CPYRA CTETRA

C onduction elements for heat transfer analysis

3.

All conduction elements that are to have a boundary condition applied must be individually identified with the application of a surface element entry CHBDYE.

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4.

Side conventions for 3D elements: Sides are numbered consecutively according to the order of the grid point numbers on the 3D element entry. The sides of 3D elements are either quadrilaterals or triangles. For each element type, the side numbers are shown here:

Side convention for C HEXA element (1st or 2nd order)

Side convention for C PENTA element (1st or 2nd order)

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Side convention for C PYRA element (1st or 2nd order)

Side convention for C TETRA element (1st or 2nd order)

5.

Side conventions for 2D elements. 2D elements have one side of type AREA (this is Side 1) and 3 or 4 sides of type LINE. AREA type: Side 1 is that given by the right hand rule on the shell’s gird points. LINE type: The second side (first line) is from grid point 1 to grid point 2, and the remaining lines are numbered consecutively. The thickness of the line is that of the shell, and the normal to the line is outward from the shell in the plane of the shell. Note that midside nodes are ignored in the specification.

6.

Side conventions for 1D elements. 1D elements have one linear side (Side 1) with geometry that is the same as that of the element and two POINT type sides, corresponding to the two points bounding the linear element (first grid point side 2; second grid point side 3).

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POINT type: Point sides may be used with any linear element. The direction of the outward normals of these points is in line with the element axis, but pointing away from the element. The area assigned to these POINT type sides is consistent with the element geometry. Boundary conditions (QBDY1) are applied to CHBDYE through reference of the EID. 7.

526

This card is represented as slave3 and slave4 element in HyperMesh.

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CHEXA Bulk Data Entry CHEXA – Six-sided Solid Element with Eight or Twenty Grid Points Description Defines the connections of the HEXA solid element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C HEXA

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

G9

G10

G11

G12

G13

G14

G15

G16

G17

G18

G19

G20

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C HEXA

71

4

3

4

5

6

7

8

9

10

Field

Contents

EID

Unique element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PSOLID property entry. Default = EID (Integer > 0)

G#

Grid point identification numbers of connection points. Default = blank (Integer > 0 or blank)

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Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

Grid points G1,…,G4 must be given in consecutive order about one quadrilateral face. G5,…,G8 must be on the opposite face with G5 opposite G1, G6 opposite G2, and so on. The edge points, G9 through G20, are optional. If any of the edge points are present, they all must be used. The second continuation must not be present for the 8-noded version of this element. It is recommended that the edge points be placed near the middle of the edge.

C HEXA definition

3.

If the user-prescribed node numbering on the bottom and top faces is reversed as compared to the sequence shown above, then the nodes are renumbered to produce right-handed orientation of numbering. This is accomplished by swapping nodes G1 with G3 and G5 with G7. For 20-noded CHEXA, appropriate changes to mid-side node numbering are also performed. In such cases, the element coordinate system will be built on the renumbered node sequence.

4.

Stresses are output in the material coordinate system. The material coordinate system is defined on the referenced PSOLID entry. It may be defined as the basic coordinate system (CORDM = 0), a defined system (CORDM = Integer > 0), or the element coordinate system (CORDM = -1).

5.

The element coordinate system for the CHEXA element is defined as follows: Three intermediate vectors R, S, and T are chosen by the following rules:

528

R

Joins the centroids of the faces described by the grid points G4, G1, G5, G8 and the grid points G3, G2, G6, G7.

S

Joins the centroids of the faces described by the grid points G1, G2, G6, G5 and the grid points G4, G3, G7, G8

T

Joins the centroids of the faces described by the grid points G1, G2, G3, G4 and the grid pints G5, G6, G7, G8.

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C HEXA element coordinate systems

The origin of the element coordinate system is at the intersection of these three vectors. If the vectors do not all intersect at one point, then the average location of the intersection points is used. The element z-axis corresponds to the T vector. The element y-axis is the cross product of the T and R vectors. The element x-axis is the cross product of the element y-axis and the element z-axis. 6.

This card is represented as a hexa8 or hex20 element in HyperMesh.

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CMASS1 Bulk Data Entry CMASS1 – Scalar Mass Connection Description Defines a scalar mass element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

C MASS1

EID

PID

G1

C1

G2

C2

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C MASS1

45

4

653

2

Field

Contents

EID

Unique element identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Property identification number of a PMASS entry. Default = EID (Integer > 0)

G1, G2

Geometric grid point or scalar point identification number. Default = 0 (Integer > 0)

C1, C2

Component number in the displacement coordinate system specified by the CD entry of the GRID data. No default (0 < Integer < 6)

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Comments 1.

Zero or blank may be used to indicate a grounded terminal G1 or G2 with a corresponding blank or zero C1 or C2. A grounded terminal is a point with a displacement that is constrained to zero.

2.

Scalar points may be used for G1 and/or G2, (with a corresponding C1 and/or C2 of zero or blank). If only scalar points and/or grounded terminals are involved, it is more efficient to use the CMASS3 entry.

3.

Element identification numbers should be unique with respect to all other element identification numbers.

4.

The two connection points (G1, C1) and (G2, C2) must not be coincident. Except in unusual circumstances, one of them will be a grounded terminal with blank entries for Gi and Ci.

5.

A scalar point specified on this entry need not be defined on an SPOINT entry.

6.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

7.

Scalar mass elements are ignored in heat transfer analysis.

8.

This card is represented as a spring or mass element in HyperMesh.

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CMASS2 Bulk Data Entry CMASS2 – Scalar Mass Property and Connection Description Defines a scalar mass element without reference to a property entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

C MASS2

EID

M

G1

C1

G2

C2

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C MASS2

2

1.1

56

3

(6)

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) M

Value of the scalar mass. No default (Real)

G1, G2

Geometric grid or identification number. No default (Integer > 0)

C1, C2

Component number in the displacement coordinate system specified by the CD entry of the GRID data. No default (0 < Integer < 6)

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Comments 1.

Zero or blank may be used to indicate a grounded terminal G1 or G2 with a corresponding blank or zero C1 or C2. A grounded terminal is a point with a displacement that is constrained to zero.

2.

Scalar points may be used for G1 and/or G2, (with a corresponding C1 and/or C2 of zero or blank). If only scalar points and/or grounded terminals are involved, it is more efficient to use the CMASS4 entry.

3.

Element identification numbers should be unique with respect to all other element identification numbers.

4.

This single entry completely defines the element since no material or geometric properties are required.

5.

The two connection points (G1, C1) and (G2, C2) must be distinct. Except in unusual circumstances, one of them will be a grounded terminal with blank entries for Gi and Ci.

6.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

7.

Scalar mass elements are ignored in heat transfer analysis.

8.

This card is represented as a spring or mass element in HyperMesh.

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CMASS3 Bulk Data Entry CMASS3 – Scalar Mass Connection to Scalar Points Only Description Defines a scalar mass element that is connected only to scalar points. Format (1)

(2)

(3)

(4)

(5)

C MASS3

EID

PID

S1

S2

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

C MASS3

13

42

62

(5)

(6)

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Property identification number of a PMASS entry. Default = EID (Integer > 0)

S1, S2

Scalar point identification numbers. Default = 0 (Integer >

Comments 1.

S1 or S2, but not both, may be blank or zero, indicating a constrained coordinate.

2.

Element identification numbers should be unique with respect to all other element identification numbers.

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3.

Only one scalar mass element may be defined on a single entry.

4.

A scalar point specified on this entry need not be defined on an SPOINT entry.

5.

Scalar mass elements are ignored in heat transfer analysis.

6.

This card is represented as a spring or mass element in HyperMesh.

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CMASS4 Bulk Data Entry CMASS4 – Scalar Mass Property and Connection to Scalar Points Only Description Defines a scalar mass element that is connected only to scalar points, without reference to a property entry. Format (1)

(2)

(3)

(4)

(5)

C MASS4

EID

M

S1

S2

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

C MASS4

23

14.92

(4)

(5)

(6)

(7)

(8)

(9)

(10)

23

Field

Contents

EID

Unique element identification number. No default (Integer > 0)

M

Scalar mass value. No default (Real)

S1, S2

Scalar point identification numbers. Default = 0 (Integer >

Comments 1.

536

S1 or S2, but not both, may be blank or zero, indicating a constrained coordinate. This is the usual case.

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2.

Element identification numbers should be unique with respect to all other element identification numbers.

3.

Only one scalar mass element may be defined on a single entry.

4.

A scalar point specified on this entry need not be defined on an SPOINT entry.

5.

This single entry completely defines the element since no material or geometric properties are required.

6.

Scalar mass elements are ignored in heat transfer analysis.

7.

This card is represented as a spring or mass element in HyperMesh.

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CMBEAM Bulk Data Entry CMBEAM – Beam Element for MBD Description Defines a beam element for multi-body dynamics solution sequence without reference to a property entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C MBEAM

EID

MID

GA

GB

X1, G0

Y1

Z1

L

A

I1

I2

J

K1

K2

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C MBEAM

1

2

123

125

0.0

0.0

1.0

5.0

100.0

833.3

833.3

1485.3

Field

Contents

EID

Element identification number.

(10)

(Integer > 0) MID

Material identification number. See comment 5. (Integer > 0)

GA, GB

538

Grid point identification number of connection points.

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Field

Contents

X1, Y1, Z1

Components of vector v at end A, measured at end A, parallel to the components of the displacement coordinate system for GA, to determine (with the vector from end A to end B) the orientation of the element coordinate system for the BEAM element. (Real)

G0

Grid point identification number to optionally supply X1, X2, and X3 (Integer > 0). Direction of orientation vector is GA to G0. (Integer > 0)

L

Undeformed length along the X-axis of the beam. (Real)

A

Area of the beam cross-section. No default (Real > 0.0)

I1

Area moment inertia in plane 1 about the neutral axis. No default (Real > 0.0)

I2

Area moment inertia in plane 2 about the neutral axis. No default (Real > 0.0)

J

Torsional constant. (Real > 0.0)

K1, K2

Area factor for shear. Default = 0.0 (Real)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

The X-axis of the beam is always along the line connecting G1 and G2. The Z-axis of the beam is determined based on the X-axis and the Y-axis provided by G3/X1, Y1, and Z1.

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3.

The moments of inertia are defined as follows:

The beam coordinates must be aligned with the principal axes of the cross-section. 4.

The transverse shear stiffness in planes 1 and 2 are (K1)AG and (K2)AG, respectively. If a value of 0.0 is used for K1 and K2, the transverse shear flexibilities are set to 0.0 (K1 and K2 are interpreted as infinite).

5.

Only MAT1 material definitions may be referenced by this element.

6.

This card is represented as a bar2 element in HyperMesh.

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CMBEAMM Bulk Data Entry CMBEAMM – Beam Element for MBD based on Markers Description Defines a beam element for multi-body dynamic solution sequence without reference to a property entry based on markers. Format (1)

(2)

(3)

(4)

(5)

C MBEAMM

EID

MID

M1

M2

A

I1

I2

J

(6)

(7)

(8)

(9)

(10)

L

K1

K2

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C MBEAMM

1

2

123

125

0.0

0.0

1.0

5.0

100.0

833.3

833.3

1485.3

Field

Contents

EID

Element identification number.

(10)

(Integer > 0) MID

Material identification number. (Integer > 0)

M1

Marker identification number. (Integer > 0)

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Field

Contents

M2

Marker identification number. (Integer > 0)

L

Undeformed length along the X-axis of the beam. (Real)

A

Area of the beam cross-section. (Real)

I1

Area moment inertia in plane 1 about the neutral axis. No default (Real > 0.0)

I2

Area moment inertia in plane 2 about the neutral axis. No default (Real > 0.0)

J

Torsional constant. (Real > 0.0)

K1, K2

Area factor for shear. Default = 0.0 (Real)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

The X-axis of the markers M1 and M2 should always be along the axis of the beam.

3.

The moments of inertia are defined as follows:

The beam coordinates must be aligned with the principal axes of the cross-section. 4.

The transverse shear stiffness in planes 1 and 2 are (K1)AG and (K2)AG, respectively. If a value of 0.0 is used for K1 and K2, the transverse shear flexibilities are set to 0.0 (K1 and K2 are interpreted as infinite).

5.

This card is represented as a bar element in HyperMesh.

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CMBUSH Bulk Data Entry CMBUSH – Bushing Element for MBD Description Defines a bushing element without reference to a property entry. Format (1)

(2)

C MBUSH

EID

(3)

(4)

(5)

(6)

(7)

(8)

(9)

G1

G2

X1, G3

Y1

Z1

"K"

K1

K2

K3

K4

K5

K6

"B"

B1

B2

B3

B4

B5

B6

"P"

P1

P2

P3

P4

P5

P6

(10)

Example

(1)

(2)

C MBUSH

4

(3)

(4)

(5)

(6)

(7)

(8)

1

2

1.0

0.0

0.0

K

100

100

100

1

1

1

B

1

1

1

0.1

0.1

0.1

P

0

0

0

0

0

0

Field

Contents

EID

Element identification number.

(9)

(10)

(Integer > 0)

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Field

Contents

G1

Grid point identification number. (Integer > 0)

G2

Grid point identification number. (Integer > 0)

G3

Grid point identification number to optionally supply X1, Y1, and Z1 in conjunction with G1. (Integer > 0)

X1, Y1, Z1

Orientation vector of the bushing. (Real)

K

Stiffness specifier.

K1, K2, K3

Translational stiffness.

K4, K5, K6

Rotational stiffness.

B

Damping specifier.

B1, B2, B3

Translational damping.

B4, B5, B6

Rotational damping.

P

Preload specifier.

P1, P2, P3

Translational preload.

P4, P5, P6

Rotational preload.

Comments 1.

544

Element identification numbers must be unique with respect to all other element identification numbers.

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CMBUSHC Bulk Data Entry CMBUSHC – Nonlinear Bushing Element for MBD using Curve Description Defines a bushing element without reference to a property entry. Format (1)

(2)

C MBUSHC

EID

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

G1

G2

X1, G3

Y1

Z1

"K"

K1C ID

K2C ID

K3C ID

K4C ID

K5C ID

K6C ID

"B"

B1C ID

B2C ID

B3C ID

B4C ID

B5C ID

B6C ID

"P"

P1

P2

P3

P4

P5

P6

”KE”

K1EID

K2EID

K3EID

K4EID

K5EID

K6EID

“BE”

B1EID

B2EID

B3EID

B4EID

B5EID

B6EID

KINT

BINT

Example

(1)

(2)

C MBUSHC

4

Altair Engineering

(3)

(4)

(5)

(6)

(7)

(8)

(9)

1

2

1.0

0.0

0.0

K

100

100

100

1

1

1

B

1

1

1

1

1

1

P

0

0

0

0

0

0

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(10)

545

AKIMA

AKIMA

Field

Contents

EID

Element identification number (Integer > 0)

G1

Grid point identification number. (Integer > 0)

G2

Grid point identification number. (Integer > 0)

G3

Grid point identification number to optionally supply X1, Y1, and Z1 in conjunction with G1. (Integer > 0)

X1, Y1, Z1

Orientation vector of the bushing. (Real)

K

Stiffness specifier.

K1CID, K2CID, K3CID

Translational stiffness curve ID.

K4CID, K5CID, K6CID

Rotational stiffness curve ID.

B

Damping specifier.

B1CID, B2CID, B3CID

Translational damping curve ID.

B4CID, B5CID,

Rotational damping curve ID.

546

Default = 0 (Integer > 0 or blank)

Default = 0 (Integer > 0 or blank)

Default = 0 (Integer > 0 or blank)

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Field

Contents

B6CID

Default = 0 (Integer > 0 or blank)

P

Preload specifier.

P1, P2, P3 Translational preload. P4, P5, P6 Rotational preload. K1EID, K2EID, K3EID

Translational stiffness independent variable expression ID.

K4EID, K5EID, K6EID

Rotational stiffness independent variable expression ID.

B1EID, B2EID, B3EID

Translational damping independent variable expression ID.

B4EID, B5EID, B6EID

Rotational damping independent variable expression ID.

KINT

Stiffness interpolation type (Character: LINEAR, CUBIC, AKIMA).

Default = 0 (Integer > 0 or blank) implies deflection as the independent variable

Default = 0 (Integer > 0 or blank) implies deflection as the independent variable

Default = 0 (Integer > 0 or blank) implies velocity as the independent variable

Default = 0 (Integer > 0 or blank) implies velocity as the independent variable

Default = AKIMA BINT

Damping interpolation type (Character: LINEAR, CUBIC, AKIMA). Default = AKIMA

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

This card is represented as a spring element in HyperMesh.

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CMBUSHE Bulk Data Entry CMBUSHE – Nonlinear Bushing Element for MBD using Expression Defined in MBVAR Description Defines a bushing element without reference to a property entry. Format (1)

(2)

C MBUSHE

EID

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

G1

G2

X1, G3

Y1

Z1

"K"

K1EID

K2EID

K3EID

K4EID

K5EID

K6EID

"B"

B1EID

B2EID

B3EID

B4EID

B5EID

B6EID

"P"

P1

P2

P3

P4

P5

P6

Example

(1)

(2)

C MBUSHE

4

(3)

(4)

(5)

(6)

(7)

(8)

1

2

1.0

0.0

0.0

K

100

100

100

1

1

1

B

1

1

1

1

1

1

P

0

0

0

0

0

0

Field

Contents

EID

Element identification number.

(9)

(10)

(Integer > 0)

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Field

Contents

G1

Grid point identification number. (Integer > 0)

G2

Grid point identification number. (Integer > 0)

G3

Grid point identification number to optionally supply X1, Y1, and Z1 in conjunction with G1. (Integer > 0)

X1, Y1, Z1

Orientation vector of the bushing. (Real)

K

Stiffness specifier.

K1EID, K2EID, K3EID

Translational stiffness MBVAR ID. Default = 0 (Integer > 0 or blank)

K4EID, K5EID, K6EID

Rotational stiffness MBVAR ID. Default = 0 (Integer > 0 or blank)

B

Damping specifier.

B1EID, B2EID, B3EID

Translational damping MBVAR ID. Default = 0 (Integer > 0 or blank)

B4EID, B5EID, B6EID

Rotational damping MBVAR ID. Default = 0 (Integer > 0 or blank)

P

Preload specifier.

P1, P2, P3

Translational preload.

P4, P5, P6

Rotational preload.

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Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

This card is represented as a spring element in HyperMesh.

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CMBUSHM Bulk Data Entry CMBUSHM – Bushing Element for MBD based on Markers Description Defines a bushing element without reference to a property entry based on markers. Format (1)

(2)

C MBUSHM

EID

(3)

(4)

(5)

(6)

(7)

(8)

(9)

M1

M2

"K"

K1

K2

K3

K4

K5

K6

"B"

B1

B2

B3

B4

B5

B6

"P"

P1

P2

P3

P4

P5

P6

(10)

Example

(1)

(2)

C MBUSHM

1

(3)

(4)

(5)

(6)

(7)

(8)

(9)

12

13

K

100

100

100

1

1

1

B

1

1

1

0.1

0.1

0.1

P

0

0

0

0

0

0

Field

Contents

EID

Element identification number.

(10)

(Integer > 0)

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Field

Contents

M1

Marker identification number. (Integer > 0)

M2

Marker identification number. (Integer > 0)

K

Stiffness specifier.

K1, K2, K3

Translational stiffness. (Real)

K4, K5, K6

Rotational stiffness. (Real)

B

Damping specifier.

B1, B2, B3

Translational damping. (Real)

B4, B5, B6

Rotational damping. (Real)

P

Preload specifier.

P1, P2, P3

Translational preload. (Real)

P4, P5, P6

Rotational preload. (Real)

Comments 1.

552

Element identification numbers must be unique with respect to all other element identification numbers.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CMBUSHT Bulk Data Entry CMBUSHT – Nonlinear Bushing Element for MBD using Table Description Defines a bushing element without reference to a property entry. Format (1)

(2)

(3)

C MBUSHT

EID

(4)

(5)

(6)

(7)

(8)

(9)

(10)

G1

G2

X1, G3

Y1

Z1

"K"

K1TID

K2TID

K3TID

K4TID

K5TID

K6TID

"B"

B1TID

B2TID

B3TID

B4TID

B5TID

B6TID

"P"

P1

P2

P3

P4

P5

P6

Example

(1)

(2)

C MBUSHT

4

(3)

(4)

(5)

(6)

(7)

(8)

1

2

1.0

0.0

0.0

K

100

100

100

1

1

1

B

1

1

1

1

1

1

P

0

0

0

0

0

0

Field

Contents

EID

Element identification number.

(9)

(10)

(Integer > 0)

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Field

Contents

G1

Grid point identification number. (Integer > 0)

G2

Grid point identification number. (Integer > 0)

G3

Grid point identification number to optionally supply X1, Y1, and Z1 in conjunction with G1. (Integer > 0)

X1, Y1, Z1

Orientation vector of the bushing. (Real)

K

Stiffness specifier.

K1TID, K2TID, K3TID

Translational stiffness TABLEDi ID. Default = 0 (Integer > 0 or blank)

K4TID, K5TID, K6TID

Rotational stiffness TABLEDi ID. Default = 0 (Integer > 0 or blank)

B

Damping specifier.

B1TID, B2TID, B3TID

Translational damping TABLEDi ID. Default = 0 (Integer > 0 or blank)

B4TID, B5TID, B6TID

Rotational damping TABLEDi ID. Default = 0 (Integer > 0 or blank)

P

Preload specifier.

P1, P2, P3

Translational preload.

P4, P5, P6

Rotational preload.

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Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

This card is represented as a spring element in HyperMesh.

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CMSMETH Bulk Data Entry CMSMETH – Component Mode Synthesis Method Definition Description CMSMETH defines the CMS method, frequency upper limit, number of modes, and starting SPOINT ID to be used in a component mode synthesis solution. The eigenvalue solver is also specified. In addition, preload as well as loads for reduction and residual vector generation can be defined. Also, an ASCII file containing CELAS4 and CDAMP3 element data and/or their corresponding design variable definitions can be generated for DMIG to allow the use of the component modes in optimization runs. Format (1)

(2)

(3)

C MSMETH C MSID METHOD

(4)

(5)

(6)

(7)

(8)

(9)

UB_FRE Q

NMODES

SPID

SOLVER

AMPFFA CT

SHFSC L

UB_FRE Q_F

NMODES _F

SPID_F

GPRC

(8)

(9)

(10)

Optional continuation lines for preload definition (1)

(2)

(3)

(4)

PRELOAD

SPC ID

PLSID

(5)

(6)

(7)

(10)

Optional continuation lines for LOAD SET definition (1)

(2)

(3)

LOADSET USETYPE

(4)

(5)

(6)

LSID1

LSID2

LSID3

(7)

(8)

(9)

(10)

Optional continuation lines for DMIGDV definition (1)

556

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DMIGDV

S/F

OUTOPT

NMODE

DVKUPFAC

DVGEUP

DVBUP

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(9)

(10)

Altair Engineering

Example

(1)

(2)

(3)

(4)

(5)

(6)

C MSMETH

5

C BN

1000

200

100000

600

100

200000

Field

Contents

CMSID

CMSMETH identification number.

(7)

(8)

(9)

(10)

(Integer > 0) METHOD

Component mode synthesis method to be employed. See comment 2. No default (Character = CB, CC, CBN, GM, or GUYAN)

UB_FREQ

Upper bound frequency for the eigenvalue analysis for the structural part. If 0.0 or blank, no upper bound is used. See comments 3 and 4. Default = blank (Real > 0.0, or blank)

NMODES

Number of modes to be extracted from structural eigenvalue analysis. If set to -1 or blank, number of modes is limitless. See comments 3 and 4. Default = blank (Integer > -1, or blank)

SPID

The starting SPOINT ID to be used in DMIG matrix output for the structural eigenmodes. No default. See comment 6.

SOLVER

The eigenvalue solver. Either blank or LAN for Lanzos. AMSES for AMSES. Default = LAN (Character = LAN or AMSES, or blank)

AMPFFACT

AMSES Amplification Factor. The substructure modes are solved up to the frequency of AMPFFACT*V2. Higher values of AMPFFACT will lead to more accurate results and longer running times. See comment 9. Default = 5.0 (Real or blank)

SHFSCL

For vibration analysis, it is the estimate of the frequency of the first flexible mode. See comment 12.

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Field

Contents Default = blank (Real or blank)

UB_FREQ_F

Upper bound frequency for the eigenvalue analysis for the fluid part. If 0.0 or blank, no upper bound is used. See comments 3 and 4. Default = blank (Real > 0.0, or blank)

NMODES_F

Number of modes to be extracted from fluid eigenvalue analysis. If set to -1 or blank, number of modes is limitless. See comments 3 and 4. Default = blank (Integer > -1, or blank)

SPID_F

The starting SPOINT ID to be used in DMIG matrix output for the fluid eigenmodes. No default. See comment 6.

GPRC

Grid participation recovery control. Allows fluid-structure interface grid shape data (that is the modes associated with the fluid-structure interface) to be calculated and stored with the external superelement. Only applicable when GM (general modal formulation) is input in the METHOD field and when all boundary degrees of freedom are free (BNDFREE). If any boundary degrees of freedom are fixed and GPRC is set to YES, the program will be terminated with an error. Default = NO (YES, NO)

PRELOAD

PRELOAD flag indicates that a preload will be used in the CMS analysis

SPCID

SPC SET ID for the preload

PLSID

LOAD SET ID for defining the preload.

LOADSET

LOADSET flag indicates that static load sets will be used in CMS analysis.

USETYPE

RESVEC/REDLOAD/BOTH defines the use type for the load sets RESVEC – the load set is used for generating residual vectors to improve the modal space REDLOAD – the load set is used for generating reduced loads BOTH – both RESVEC and REDLOAD options are selected Default = BOTH (see comment 11)

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Field

Contents

LSIDi

The load set IDs for generating residual vectors and/or reduced loads.

S/F

S – Selects the structural part of the model. Default = S

DMIGDV

DMIGDV flag indicates that an ASCII file containing CELAS4 and CDAMP3 element data and/or their corresponding design variable definitions is generated for DMIG (see comment 13).

OUTOPT

OUTOPT defines how design variable definitions are written for DMIG. (see comments 13 to 17) If OUTOPT is: 1 – Only CELAS4 and CDAMP3 element data and PDAMP properties (if any) are written. Design variable definitions are not written. 2 – All data from Option-1 and design variable definitions are written (Default, see comment 14). 3 – All data from Option-2 and constraint (f1 0 then “NMODE” number of design variables will be written to control the first “NMODE” eigenvalue changes (∆K), damping coefficient changes (∆GE) and scalar damping value changes (∆B). If NMODE is not specified (the NMODE field is blank) then as many design variables as the total number of modes are written.

DVKUPFAC

DVKUPFAC is used to determine the upper bound of ∆K (which is (maximum eigenvalue)*DVKUPFAC). If DVKUPFAC is not specified (DVKUPFAC field is blank) then it is set to 0.1 by default (See comment 16). Default: DVKUPFAC=0.1

DVGEUP

Upper bound of ∆GE. This applies to all the design variables for ∆GE. If DVGEUP is not specified (DVGEUP field is blank) then it is set to 2*DVBUP by default (See comment 16). Default: DVGEUP=2*DVBUP

DVBUP

Upper bound of ∆B. This applies to all the design variables for ∆B. If DVBUP is not specified (DVBUP field is blank) then it is set to 0.4 by

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Field

Contents default (See comment 16). Default: DVBUP=0.4

Comments 1.

This definition will be ignored unless referenced in the I/O Options section by a CMSMETH run control.

2.

Several methods are available for Component Mode Synthesis, these are: CB, CC, CBN, GM and GUYAN (see descriptions below). The first two methods (CB and CC) are used for generating flexible bodies for use with multi-body dynamics analysis software, such as Altair’s MotionSolve. The remaining methods (CBN, GM and GUYAN) are used primarily to generate external superelements (stored in DMIG format) for use in subsequent finite element analyses. Flexible body methods: CB – Craig-Bampton formulation CC – Craig-Chang formulation External superelement methods: CBN – Craig-Bampton Nodal formulation GM – General Modal formulation GUYAN – GUYAN reduction: GUYAN is the same as CBN without including structural eigenmodes; when GUYAN is used, UB_FREQ & NMODES are ignored.

3.

UB_FREQ, NMODES, UB_FREQ_F and NMODES_F cannot all be blank. Additionally, when structural elements are present in the model, UB_FREQ and NMODES cannot both be blank, and when fluid elements are present in the model, UB_FREQ_F and NMODES_F cannot both be blank.

4.

When UB_FREQ = 0.0 and NMODES = 0, this is a special case where no structural eigenmodes will be included in CMS mode generation. If both UB_FREQ and NMODES are specified, lowest NMODES below UB_FREQ will be accepted as structural SPOINTs. Similarly things are applied to fluid part.

5.

If PARAM, EXTOUT, DMIGPCH (or DMGBIN) is defined when using the CB method, then a DMIG matrix corresponding to the reduced stiffness and mass matrices will be output. The stiffness and mass corresponding to the eigenmodes will be assigned to the generated SPOINTs.

6.

The SPOINT IDs of the structure and fluid should have distinct IDs. Any fluid SPOINT ID cannot be in between structural SPOINT IDs.

7.

When PARAM,EXTOUT is used to output DMIG matrices, then it is possible to disable the

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output of a flexh3d file by specifying “OUTPUT,H3D,NONE” in the input file. 8.

The nodal flexh3d file output from the CBN method can be used as the DMIG input (using ASSIGN,H3DDMIG). In this way, the model set output in flexh3d file will be recovered as the interior points of the DMIG matrix in the residual structure run. The displacements of these interior points will be included in the output.

9.

AMPFFACT is used to increase the accuracy of the eigenvalue and eigenvectors at the expense of slightly longer run times. It is recommended to use higher values of AMPFFACT for solid structures like engine blocks and suspension components. If AMPFFACT is not specified by you and the model contains a large number of solid elements, then the value of AMPFFACT is automatically reset to 10.

10. The mass properties of the super element (Mass, Center of Gravity, and Moments of Inertia) are written to the H3D file. In the residual run, these mass properties are included in the mass properties of the structure printed in the .out file. 11. The USETYPE field should always be set to BOTH or blank for flexible body generation (METHOD=CB or CC, see comment 2). 12. A specification of SHFSCL may improve the performance of a vibration analysis. 13. If you define the DMIGDV optional continuation card, a text file (ASCII) filename_dmig_dv.inc is created after the run. You can include this file in the original input deck to study how changes in the eigenvalues/damping of superelements affect the performance of the residual structure. 14. In addition to the data included in option 1, the ASCII file now also contains design variable definitions. These design variables can control available eigenvalues, structural damping, and viscous damping of the superelement. You can set up an optimization problem by including this file in the original input deck. 15. In addition to the data included in option 2, the ASCII file now includes data required for the creation of constraints. These constraints ensure that the eigenvalue of the nth mode is less than the eigenvalue of the (n+1)th mode during optimization. 16. The lower bound of ∆K, ∆B and ∆GE is set such that K, B and GE are always greater than or equal to zero. 17. The DMIGDV continuation line works only for METHOD = GM (General Modal formulation) in field 3 of CMSMETH (See comment 2). 18. Where, ∆K, ∆GE and ∆B represent increments/decrements to the eigenvalues (K), damping coefficients (GE) and scalar damping values (B) respectively. You are required to include the .h3d file containing the values of K, GE and B using ASSIGN, H3DDMIG. 19. For further information on creating flex bodies for third party software, refer to Coupling OptiStruct with Third Party Software in the User’s Guide. 20. This card is represented as a loadcollector in HyperMesh.

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CMSPDP Bulk Data Entry CMSPDP – Multi-body Spring Damper Element Description Defines a spring damper element without reference to a property entry for multi-body solution sequence. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C MSPDP

EID

K

G1

G2

B

L

PF

TYPE

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C MSPDP

3

34.5

223

324

0.0

1.0

Field

Contents

EID

Element identification number.

(8)

(9)

(10)

TRANS

(Integer > 0) K

Stiffness value. Default = 0.0 (Real or blank)

G1

Grid point identification number. (Integer > 0)

G2

Grid point identification number. (Integer > 0)

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Field

Contents

B

Damping value. Default = 0.0 (Real or blank)

L

Unstretched length/angle of spring damper. See comment 4. Default = 0 (Real > 0.0 or blank)

PF

Preload force. Default = 0 (Real or blank)

TYPE

Type (TRANS or ROT; if blank, default: TRANS)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

The spring damper force is along the line segment connecting the grids G1 and G2.

3.

The positive preload force is a stretching force.

4.

If the unstretched length/angle of spring damper field (L) is blank: (a) For a translational spring, OptiStruct calculates the length between the two grid points (G1, G2) of the spring damper for the value of L. (b) For a rotational spring, L is set to 0.0.

5.

This card is represented as a spring element in HyperMesh.

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CMSPDPC Bulk Data Entry CMSPDPC – Nonlinear Multi-body Spring Damper Element using Curve Description Defines a spring damper element without reference to a property entry for multi-body solution sequence. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C MSPDPC

EID

KC ID

G1

G2

BC ID

L

PF

TYPE

KINT

KEID

BINT

BEID

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C MSPDPC

3

34

223

324

0

1.0

AKIMA

1

Field

Contents

EID

Element identification number.

(8)

(9)

(10)

TRANS

(Integer > 0) KCID

Stiffness curve ID. Default = 0 (Integer > 0 or blank)

G1

Grid point identification number. (Integer > 0)

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Field

Contents

G2

Grid point identification number. (Integer > 0)

B

Damping Curve ID. Default = 0 (Integer > 0 or blank)

L

Unstretched length of spring damper. Default = 0 (Real > 0.0 or blank)

PF

Preload force. Default = 0 (Real or blank)

TYPE

Type. (TRANS or ROT; if blank, default: TRANS)

KINT

Stiffness Interpolation type (Character: LINEAR, CUBIC, AKIMA). Default = AKIMA

KEID

MBVAR ID for independent variable ID for stiffness. Default = Deflection (Integer > 0 or blank)

BINT

Damping Interpolation type (Character: LINEAR, CUBIC, AKIMA). Default = AKIMA

BEID

MBVAR ID for independent variable ID for damping. Default = Velocity (Integer > 0 or blank)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

The spring damper force is along the line segment connecting the grids, G1 and G2.

3.

The positive preload force is a stretching force.

4.

This card is represented as a spring element in HyperMesh.

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CMSPDPE Bulk Data Entry CMSPDPE – Nonlinear Multi-body Spring Damper Element using Expression defined in MBVAR Description Defines a spring damper element without reference to a property entry for multi-body solution sequence. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C MSPDPE

EID

KEID

G1

G2

BEID

L

PF

TYPE

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C MSPDPE

3

3

223

324

4

1.0

Field

Contents

EID

Element identification number.

(8)

(9)

(10)

TRANS

(Integer > 0) KEID

MBVAR ID for stiffness expression. Default = 0 (Integer > 0 or blank)

G1

Grid point identification number. (Integer > 0)

G2

Grid point identification number. (Integer > 0)

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Field

Contents

BEID

MBVAR ID for Damping expression. Default = 0 (Integer > 0 or blank)

L

Unstretched length of spring damper. Default = 0 (Real > 0.0 or blank)

PF

Preload force. Default = 0 (Real or blank)

TYPE

Type. (TRANS or ROT; if blank, default: TRANS)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

The spring damper force is along the line segment connecting the grids G1 and G2.

3.

The positive preload force is a stretching force.

4.

This card is represented as a spring element in HyperMesh.

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CMSPDPM Bulk Data Entry CMSPDPM – Multi-body Spring Damper Element based on Marker Description Defines a spring damper element without reference to a property entry for multi-body solution sequence based on marker. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C MSPDPM

EID

K

M1

M2

B

L

PF

TYPE

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C MSPDPM

3

34.5

223

324

0.0

1.0

Field

Contents

EID

Element identification number.

(8)

(9)

(10)

TRANS

(Integer > 0) K

Stiffness value. Default = 0.0 (Real or blank)

M1

Marker identification number. (Integer > 0)

M2

Marker identification number. (Integer > 0)

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Field

Contents

B

Damping value. Default = 0.0 (Real or blank)

L

Unstretched length of spring damper. Default = 0 (Real > 0.0 or blank)

PF

Preload force. Default = 0 (Real or blank)

TYPE

Type. (TRANS or ROT; if blank, default: TRANS)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

The spring damper force is along the line segment connecting the marker M1 and M2.

3.

The positive preload force is a stretching force.

4.

This card is represented as a spring element in HyperMesh.

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CMSPDPT Bulk Data Entry CMSPDPT – Nonlinear Multi-body Spring Damper Element using Table Description Defines a spring damper element without reference to a property entry for multi-body solution sequence. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C MSPDPT

EID

KTID

G1

G2

BTID

L

PF

TYPE

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C MSPDPT

3

3

223

324

4

1.0

Field

Contents

EID

Element identification number.

(8)

(9)

(10)

TRANS

(Integer > 0) KTID

TABLEDi ID for stiffness. Default = 0 (Integer > 0 or blank)

G1

Grid point identification number. (Integer > 0)

G2

Grid point identification number. (Integer > 0)

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Field

Contents

BTID

TABLEDi ID for Damping. Default = 0 (Integer > 0 or blank)

L

Unstretched length of spring damper. Default = 0 (Real > 0.0 or blank)

PF

Preload force. Default = 0 (Real or blank)

TYPE

Type. (TRANS or ROT; if blank, default: TRANS)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

The spring damper force is along the line segment connecting the grids G1 and G2.

3.

The positive preload force is a stretching force.

4.

This card is represented as a spring element in HyperMesh.

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CONM1 Bulk Data Entry CONM1 – Concentrated Mass Element Connection, General Form Description Defines a 6x6 mass matrix at a geometric grid point. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ONM1

EID

G

C ID

M11

M21

M22

M31

M32

M33

M41

M42

M43

M44

M51

M52

M53

M54

M55

M61

M62

M63

M64

M65

M66

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

C ONM1

2

22

2

2.9

6.3

4.8

28.6

(7)

(8)

28.6

Field

Contents

EID

Unique element identification number.

(9)

(10)

28.6

(Integer > 0) G

Grid point identification number. (Integer > 0)

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Field

Contents

CID

Coordinate system identification number for the mass matrix. (Integer > 0)

Mij

Mass matrix values. (Real)

Comments 1.

This card is represented as a mass element in HyperMesh.

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CONM2 Bulk Data Entry CONM2 – Concentrated Mass Element Connection, Rigid Body Form Description Defines a concentrated mass at a grid point of the structural model. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

C ONM2

EID

G

C ID

M

X1

X2

X3

I11

I21

I22

I31

I32

I33

(9)

(10)

Example

(1)

(2)

(3)

C ONM2

2

15

16.2

(4)

(5)

(6)

(7)

(8)

(9)

(10)

49.7

16.2

Field

Contents

EID

Unique element identification number.

7.8

No default (Integer > 0) G

Grid point identification number. No default (Integer > 0)

CID

Coordinate system identification number. Default = 0 (Integer > -1)

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Field

Contents

M

Mass value. No default (Real)

X1, X2, X3

Offset distance from the grid point to the center of gravity of the mass in the coordinate system defined by CID, unless CID = -1, in which case X1, X2, and X3 are the coordinates (not offsets) of the center of gravity of the mass in the basic coordinate system.

Iij

Mass moments of inertia measured at the mass c.g. If CID is zero, then Iij is defined in the basic coordinate system. If CID > 1, then Iij refers to the local coordinate system. If CID is -1, then Iij refers to the basic coordinate system. Default = 0.0 (Real)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

If the continuation is omitted, all rotary inertia is assigned zero values.

3.

The form of the inertia matrix about its c.g. is taken as:

where M =

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and X1, X2, and X3 are components of distance from the c.g. The negative signs for the off-diagonal terms are supplied by the program. 4.

If CID = -1, then the offsets are computed internally as the difference between the grid point location and X1, X2, and X3. The grid points may be defined in a local coordinate system, in which case the values of basic coordinate system.

must be in a coordinate system that parallels the

5.

If CID > 0, then X1, X2, and X3 are defined by a local Cartesian system, even if CID references a spherical or cylindrical coordinate system.

6.

This card is represented as a mass element in HyperMesh.

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CONNECT Bulk Data Entry CONNECT – Connects two parts Description The CONNECT bulk data entry can be used to define equivalence for all degrees of freedom of grid points of two different parts within a specified tolerance. The tolerance is defined as the maximum distance between two grid points within which equivalence is allowed. Two formats can be used to either select all grid points or a few grid points for equivalence. Format (1)

(2)

(3)

(4)

C ONNEC T name_a name_b

(5)

(6)

(7)

(8)

(9)

(10)

tol

Example

(1)

(2)

(3)

(4)

(5)

C ONNEC T

C yl_Head

Gaskt

0.01

(6)

(7)

(8)

(9)

(10)

Alternate Format (1)

(2)

(3)

(4)

C ONNEC T

name_a

name_b

tol

GRID

GID1

GID2

(5)

(6)

(7)

(8)

GID3

...

GIDn

(9)

(10)

Alternate Example

(1)

(2)

C ONNEC T C yl_Head

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(3)

(4)

Gaskt

0.01

(5)

(6)

(7)

(8)

(9)

(10)

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GRID

1201

1212

192

115

Field

Contents

name_a

Name of a part selected for equivalencing. Part “name_a” is the reference part. All grid points in part “name_a” are considered during the search; if OptiStruct finds grid points in part “name_b” within the specified maximum distance (tol), then such grid point pairs are equivalent. (Character String)

name_b

Name of a part selected for equivalencing. All grid points in part “name_a” are considered during the search; if OptiStruct finds grid points in part “name_b” within the specified maximum distance (tol), then such grid point pairs are equivalent. (Character String)

tol

Specifies the numeric value defining the maximum distance between two grid points to allow equivalence. All grid points in part “name_a” are considered during the search; if OptiStruct finds grid points in part “name_b” within the specified maximum distance (tol), then such grid point pairs are equivalent. (Real > 0.0)

GRID

GRID flag indicating that a list of grid point ID’s is to follow. These grid point locations are used to define locations to search for matching nodes.

GID#

Identification numbers of grid points that define locations at which a search for matching nodes is conducted. GID# do not need to belong to either part “name_a” or part “name_b”. (Integer > 0)

Comments 1.

Parts can be connected in two different ways, using the CONNECT entry or by using rigid elements. The RELOC and INSTNCE entries can be used to position the part appropriately within the full model and the CONNECT entry or rigid elements can be used to connect the requisite number of grid points of one part to the other.

2.

In an alternate form, grid point ID’s can be specified anywhere in the model, it is not mandatory for a grid point ID to belong to a part. Equivalencing takes place between any matching grids in both parts if they coincide with the location of any grid in the list.

3.

Searches defined by this entry are performed after all parts are located at their final positions.

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CONROD Bulk Data Entry CONROD – Rod Element Property and Connection Description Defines a rod element without reference to a property entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C ONROD

EID

G1

G2

MID

A

J

C

NSM

Example

(1)

(2)

(3)

(4)

(5)

(6)

C ONROD

2

16

17

4

269

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

(Integer > 0) G1,G2

Grid point identification numbers of connection points.

MID

Material identification number. See comment 1. (Integer > 0)

A

Area of the rod. (Real)

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Field

Contents

J

Torsional constant. (Real)

C

Coefficient for torsional stress determination. (Real)

NSM

Nonstructural mass per unit length. (Real)

Comments 1.

For structural problems, MID may reference only a MAT1 material entry. For heat transfer problems, MID may reference only a MAT4 material entry.

C ONROD Element Forces and Moments

2.

580

This card is represented as a rod element in HyperMesh.

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CONTACT Bulk Data Entry CONTACT – Contact Interface Definition Description Defines a contact interface. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C ONTAC T

C TID

PID/ TYPE/ MU1

SSID

MSID

MORIENT

SRC HDI S

ADJUST

C LEARANC E

DISC RET

Example

(1)

(2)

(3)

(4)

(5)

C ONTAC T

5

SLIDE

7

8

(6)

(7)

(8)

(9)

(10)

N25

Field

Contents

CTID

Contact interface identification number. (Integer > 0)

PID

Property identification number of a PCONT, PCONTX entry. (Integer > 0)

TYPE

Choose type of contact without pointing to contact property – respective default property settings will be used. Default settings can be changed using CONTPRM. SLIDE – Sliding contact.

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Field

Contents STICK – Contact with stick condition (stick applies to closed contacts only). FREEZE – Enforced zero relative displacements on the contact interface (applies to both closed and open contacts). See comments 5 and 15. Default = SLIDE (SLIDE, STICK, FREEZE)

MU1

Coefficient of static friction (µs). See comment 6. (0.0 < Real < 1.0)

SSID

Identification number of slave entity. See comments 2 and 14. (Integer > 0)

MSID

Identification number of master entity. See comments 3 and 15. (Integer > 0)

MORIENT

Orientation of contact “pushout” force from master surface. This only applies to masters that consist of shell elements or patches of grids. Masters defined on solid elements always push outwards irrespective of this flag. OPENGAP – The contact interface is assumed open. OVERLAP – Slave and master bodies overlap. NORM – Contact force is oriented along the vector normal to the master surface. REVNORM – Contact force is oriented opposite to the default vector normal to the master surface. Default = OPENGAP (OPENGAP, OVERLAP, NORM or REVNORM). See comments 7, 8, and 17.

SRCHDIS

Search distance criterion for creating contact condition. When specified, only slave nodes that are within SRCHDIS distance from master surface will have contact condition checked. Default = twice the average edge length on the master surface. For FREEZE contact, half the average edge length. (Real > 0 or blank)

ADJUST

Adjustment of slave nodes onto the master surface at the start of a simulation. 0.0, or Integer > 0>

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Field

Contents Default = NO. NO – no adjustment. AUTO – A real value equal to 5% of the average edge length on the master surface is internally assigned as the depth criterion (see comment 10). Real > 0.0 – value of the depth criterion which defines the zone in which a search is conducted for slave nodes (for which contact elements have been created). These slave nodes (with created contact elements) are then adjusted onto the master surface. The assigned depth criterion is used to define the searching zone in the pushout direction (see comment 10). Integer > 0 – identification number of a SET entry with TYPE = “GRID”. Only the nodes on the slave entity which also belong to this SET will be selected for adjustment. Note: See comment 10 for more information.

CLEARANCE Prescribed initial gap opening between master and slave, irrespective of the actual distance between the nodes (see comment 11). Default = blank (Real or blank) DISCRET

Discretization approach type for the construction of contact elements. Default = N2S. N2S – node-to-surface discretization S2S – surface-to-surface discretization

Comments for nonlinear quasi-static analysis 1.

If the node-to-surface (DISCRET=N2S) discretization approach is selected, the CONTACT interface is constructed by searching, for each slave node, a respective facet of the master surface, which contains the normal projection of the slave and is within SRCHDIS distance from the slave node. If no master segment with normal projection is found, then the nearest segment is picked if the direction from slave to master is within a certain angle (30 degrees) relative to the normal to the master segment. Having found a feasible master segment for the slave node, a contact element is created of a similar structure as the CGAPG element (Figure 1).

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Figure 1: C reation of a contact element

If the surface-to-surface (DISCRET=S2S) discretization approach is selected, the CONTACT interface is constructed by searching, for each facet of the slave surface, respective facets of the master surface which contain the normal projection of sample points on the slave facet and is within SRCHDIS distance from the sample points. For a slave node, a contact element is created with the surrounding slave facets and the master facets found by projection of the sample points on the slave facets (Figure 2).

Figure 2: C reation of a contact element (surface-to-surface discretization)

2.

The slave entity (SSID) always consists of grid nodes. It may be specified as: a set of grid nodes defined using SET(GRID,..) command. a surface defined using SURF command (the slave nodes are picked from the respective nodes of the SURF faces). a set of elements (shells or solids) defined using SET(ELEM,..) command. Slave nodes are picked from the respective nodes of the elements in the set. For 3D solids, only nodes on the surface of the solid body are selected; internal nodes are not considered. DISCRET = N2S is recommended if the slave entity is a set of grids (nodes) or a set of solid elements.

3.

The master entity (MSID) may be defined as: a surface defined using SURF command.

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a set of elements (shells or solids) defined using SET(ELEM,..) command. For sets of 3D solids, element faces on the surface are automatically found and selected as master surface. 4.

Prescribing TYPE=STICK is interpreted in OptiStruct as an enforced stick condition - such contact interfaces will not enter the sliding phase. Of course, the enforced stick only applies to contacts that are closed. Note that, in order to effectively enforce the stick condition, frictional offset may need to be turned off (See comment 8 on PCONT).

5.

Prescribing TYPE=FREEZE enforces zero relative motion on the contact surface – the contact gap opening remains fixed at the original value and the sliding distance is forced to be zero. Also, rotations at the slave node are matched to the rotations of the master patch. The FREEZE condition applies to all respective contact elements, no matter whether open or closed.

6.

Prescribing MU1 directly on the CONTACT card allows for simplified specification of frictional contacts. Note that this implies MU2=MU1, unless MU2 is specified explicitly on the CONTPRM card. Also note that the value of MU1 prescribed on the CONTACT card must be less than 1.0 – to specify higher values of static coefficient of friction, PCONT card must be used. If FRIC is not explicitly defined on the PCONTX/PCNTX# entries, the MU1 value on the CONTACT or PCONT entry is used for FRIC in the /INTER entries for Geometric Nonlinear Analysis. Otherwise, FRIC on PCONTX/PCNTX# overwrites the MU1 value on CONTACT/ PCONT.

7.

MORIENT defines the master pushout direction, which is the direction of contact force that master surface exerts on slave nodes. It is important to note that, in most practical applications, leaving this field blank will provide correct resolution of contact, irrespective of the orientation of surface normals. Only in cases of master surfaces defined as shells or patches of grids, and combined with initial pre-penetration, is MORIENT needed. By default, MORIENT is ignored for solid elements – it applies only to master surfaces that consist of shell elements or patches of grids. (Master surfaces defined as faces of solid elements always push outwards, irrespective of the surface normals, or whether the contact gap is initially open or closed. See comment 7 for additional options). a) In default behavior (OPENGAP), the pushout direction is defined using the assumption that the gap between slave and master is initially open, and the contact condition should prevent their contact (gap “padding” GPAD from the PCONT card is ignored in defining the pushout direction – this direction is based strictly on the positions of master and slave nodes). The following example shows a typical use of OPENGAP:

Figure 3: Example for the use of OPENGAP

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b) OVERLAP assumes the reverse, namely that the slave and master bodies are already overlapping and the contact condition should push them apart (this is useful in case of pre-penetrating models when the entire slave set is pre-penetrating into the master object). The following example shows a typical use of OVERLAP:

Figure 4: Example for the use of OVERLAP

c) With the NORM option, the pushout force is oriented along the normal vector to the master surface. (Note that the surface normal may be reversed relative to the default normal to a shell element if a FLIP flag is present on the master SURF definition. This behavior corresponds to that of the reverse normals checkbox on the contactsurfs panel in HyperMesh). In cases when the slave node does not have a direct normal projection onto the master surface, and the "shortest distance" projection is used (GAPGPRJ set to SHORT on the GAPPRM card), the pushout force is oriented along the shortest distance line, yet with the orientation aligned with the normal vector. The following example shows a typical use of NORM:

Figure 5: Example for the use of NORM

d) REVNORM creates pushout force reversed relative to the NORM option. 8.

By default, MORIENT does not apply to masters that are defined on solid elements – such masters always push outwards. This can be changed by choosing CONTPRM,CORIENT,ONALL which extends the meaning of MORIENT to all contact surfaces. In which case, it should be noted that the default normal is pointing inwards unless a FLIP flag appears on the master SURF definition for surfaces on solid elements, making the surface normal point outwards. (When creating contact surfaces in HyperMesh, this behavior corresponds to that of the reverse normals checkbox on the contactsurfs panel).

9.

Presently one CONTACT element is created for each slave node. This assures reasonably efficient numerical computations without creating an excessive number of contact elements. However, this may require special handling in some cases, such as when a master surface wraps around the slave set. In such cases, switching the role of slave and master may be recommended. Alternatively, multiple CONTACT interfaces can be

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created in order to cover all possible directions of relative motion (a simplified illustration is shown in the figure below). Additionally, individual GAP(G) elements can be used to handle such special situations.

Figure 6: Special case - Master surface wraps around a slave node set

10. The adjustment of slave nodes doesn’t create any strain in the model. If DISCRET=N2S is selected, it is treated as a change in the initial model geometry. If DISCRET=S2S is selected, it is treated as a change in the initial contact opening/penetration. If a node on the slave entity lies outside the projection zone of the master surface, it will always be skipped during adjustment since no contact element has been constructed for it. Contact interface padding will be accounted for during the nodal adjustment. If the MORIENT field is “OPENGAP” or “OVERLAP” while the GPAD field in the referred PCONT entry is “NONE” or zero, the nodal adjustment will be skipped, since for “OPENGAP” or “OVERLAP” there is no way to decide the master pushout direction if slave nodes are adjusted to be exactly on the master face. If different contact interfaces involve the same nodes, nodal adjustment definitions are processed sequentially in the order of identification numbers of the contact interfaces. Care must be taken to avoid conflicts between the nodal adjustments; otherwise, contact element errors or lack of compliance may occur. a) The ADJUST field must be set to “NO” for self-contact. b) If a real value (the searching depth criterion for adjustment) is input for the ADJUST field, a searching zone for adjustment is defined. The slave nodes in this searching zone, for which contact elements have been created, will be adjusted. If ADJUST is larger than or equal to SRCHDIS, all the slave nodes for which contact elements have been created, will be adjusted.

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Figure 7: An illustration depicting how ADJUST works.

Depth Criterion The depth criterion (A non-negative real value for ADJUST) is used to define the searching zone for adjustment, as shown in Figure 7. This searching zone is created in the pushout direction up to a distance equal to the value of the ADJUST field. The slave nodes within the searching zone (with defined contact elements) are then considered for adjustment based on the rules specified within this comment (Comment 10). c) If the ADJUST field is set to an integer value (the identification number of a grid SET entry), the nodes shared by the slave entity and the grid SET will be checked for contact creation, that is, SRCHDIS will be ignored for these nodes, and then adjusted if a projection is found. The nodes belonging to the grid SET but not to the slave entity will be simply ignored. 11. Using CLEARANCE overrides the default contact behavior of calculating initial gap opening from the actual distance between Slave and Master. CLEARANCE is now equal to the distance that Slave and Master have to move towards each other in order to close the contact. Negative value of CLEARANCE indicates that the bodies have initial prepenetration. Warning:

588

If CLEARANCE is used, it is important to correctly restrict the contact zones and pick search distance SRCHDIS so that only desired Slave-Master pairs are involved. Using CLEARANCE, all contact elements created on a given interface, even those where Slaves are geometrically distant from the

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respective Master surface, will be considered to be at given initial gap and participate in resolving the contact condition. Note: 1.

CLEARANCE cannot be used in conjunction with PID of PCONT entry. In such a case, clearance must be specified on the PCONT entry.

2.

The CLEARANCE field value on the CONTACT entry will be ignored for ANALYSIS=NLGEOM subcases

Comments for geometric nonlinear analysis (ANALYSIS = NLGEOM subcases) 12. CONTACT models an interface between a master surface and a set of slave grid points. A grid point can be at the same time as a slave and a master node. Each slave grid point can impact each master segment; except if it is connected to the impacted master segment. A grid point can impact on more than one segment. A grid point can impact on the two sides, on the edges, and on the corners of each segment. The contact uses a fast search algorithm without limitations. The main limitations of this interface follow: a) the time step in an explicit analysis is reduced in case of high impact speed or contacts with small gap; b) the contact may not work properly if used with a rigid body at high impact speed or rigid body with small gap; c) the contact does not solve edge to edge contact. 13. Additional control can be applied to the CONTACT definition in geometric nonlinear subcases through CONTPRM and PCONTX. These definitions are ignored in all other subcases. A geometric nonlinear subcase is one that has an ANALYSIS = NLGEOM entry in the subcase definition. 14. The slave entity (SSID) always consists of grid nodes. It may be specified as: a set of grid nodes defined using SET(GRID,..) command. a surface defined using SURF command (the slave nodes are picked from the respective nodes of the SURF faces). a set of elements (shells or solids) defined using SET(ELEM,..) command. Slave nodes are picked from the respective nodes of the elements in the set. For 3D solids, only nodes on the surface of the solid body are selected; internal nodes are not considered. 15. The master entity (MSID) may be defined as: a surface defined using SURF command. a set of elements (shells or solids), TYPE = FREEZE is implemented as a TIE kinematic condition for large deformation subcases. 16. For implicit analysis, modified settings that improve the contact convergence are recommended. See CONTPRM and PCONTX. 17. This card defined using SET(ELEM,..) command.

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Comment for Contact-based Thermal Analysis 18. Thermal-structural analysis problems involving contact are fully coupled since contact status changes thermal conductivity. Refer to Contact-based Thermal Analysis in the User’s Guide for more information. 19. This card is represented as a group in HyperMesh.

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CONTPRM Bulk Data Entry CONTPRM – Default Contact Properties Description Defines the default properties of all contacts and sets parameters that affect all contacts. The default values set here can be overridden by values explicitly specified on PCONT, PCONTX, and CONTACT cards. Note: These defaults do not apply to properties of individual gap elements that are specified on PGAP cards.

Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ONTPRM PARAM1

VALUE1

PARAM2

VALUE2

PARAM3

VALUE3

PARAM4

VALUE4

PARAM5

VALUE5

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C ONTPR M

GPAD

0.5

STIFF

AUTO

MU1

0.3

Field

Contents

PARAMi

Name of parameter.

VALi

Value of parameter.

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(10)

591

Parameters for nonlinear quasi-static analysis Name

Values

GPAD

“Padding” of master or slave objects to account for additional layers, such as shell thickness, and so on. This value is subtracted from contact gap opening as calculated from location of nodes. See comment 1. Default = THICK (Real or NONE or THICK)

STIFF

Relative stiffness of gap. See comment 2. Default = AUTO (AUTO, SOFT, HARD or Real > 0.0)

MU1

Coefficient of static friction ( s). See comments 3 and 4. Default = 0.0 (Real > 0.0 or STICK or FREEZE)

MU2

Coefficient of kinetic friction ( k ). Default = MU1 (0.0 < Real < MU1)

CONTGAP

Create a bulk data file that contains internally created node-to-surface contact elements represented as CGAPG elements. The file name is: filename_root.contgap.fem. See comment 6. Default = NO (YES or NO)

CORIENT

Indicates whether the master orientation field MORIENT on the CONTACT card applies to all surfaces or if it excludes solid elements. Default = ONSHELL (ONSHELL or ONALL) ONSHELL – MORIENT applies only to contact masters that consist of shell elements or patches of grids. Master surfaces defined as faces of solid elements always push outwards, irrespective of initially open or prepenetrating contact. ONALL – MORIENT applies to all contact masters including, in particular, solid elements.

SFPRPEN

Indicates whether initial pre-penetrations are recognized and resolved in self-contact areas. (This only affects self-contact areas, wherein Master and Slave belong to the same set or surface). Default = YES (YES or NO) YES – Initial self-penetrations are recognized and resolved in self-contact areas. There is some danger of finding false self-penetrations across solids thinner than SRCHDIS (See comment 7). NO – There are no pre-penetrations to be resolved in self-contact areas,

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except maybe minimal intrusions due to meshing, and so on. Any selfpenetrations larger than minimum element size will be ignored in those areas (See comment 7). FRICESL

Frictional elastic slip – distance of sliding up to which the frictional transverse force increases linearly with slip distance. Specified in physical distance units (similar to U0 and GPAD). See comment 8. •

Non-zero value or blank activates respective friction model based on Elastic Slip Distance.

•

Zero value activates friction model based on fixed transverse stiffness KT.

Default = AUTO (Real > 0.0 or AUTO)

Parameters for geometric nonlinear analysis (ANALYSIS = NLGEOM / IMPDYN / EXPDYN in subcase) Name

Values

STFAC

Interface stiffness scale factor. Default = 1.0 in implicit analysis Default = 0.1 in explicit analysis (Real > 0)

FRIC

Coulomb friction. Default = 0.0 (Real > 0)

GAP

Gap for impact activation (See comments 10 and 11). (Real > 0)

IDEL

Flag for node and segment deletion. Default = 0 (Integer = 0, …, 2) 0 - No deletion. 1 - When all of the elements (shells, solids) associated to one segment are deleted, the segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface. 2 - When a shell or a solid element is deleted, the corresponding segment is removed from the master side of the interface. Additionally, nonconnected nodes are removed from the slave side of the interface.

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INACTI

Flag for handling of initial penetrations (See comment 13). Default as defined by CONTPRM (Integer = 0, …, 5) 0 - No action. 1 - Deactivation of stiffness on nodes. 2 - Deactivation of stiffness on elements. 3 - Change slave node coordinates to avoid small initial penetrations. 4 - Change master node coordinates to avoid small initial penetrations. 5 - Gap is variable with time but initial gap is slightly de-penetrated as follows: gap0 = gap - P0 – 0.05*(gap - P0) Valid in explicit analysis: 0, 1, 2, 3 and 5. Valid in implicit analysis: 0, 3 and 4. Invalid entries are ignored.

CORIENT

Indicates whether the master orientation field MORIENT on the CONTACT card applies to all surfaces, or if it excludes solid elements. Default = ONSHELL (ONSHELL or ONALL) ONSHELL – MORIENT applies only to contact masters that consist of shell elements or patches of grids. Master surfaces defined as faces of solid elements always push outwards, irrespective of initially open or prepenetrating contact. ONALL – MORIENT applies to all contact masters including, in particular, solid elements.

IFRIC

Friction formulation flag (See comment 15). Default = COUL (Character = COUL, GEN, DARM, REN) COUL - Static Coulomb friction law. GEN - Generalized viscous friction law. DARM - Darmstad friction law. REN - Renard friction law. In implicit computation, only IFRIC = COUL is implemented.

IFILT

Friction filtering flag (See comment 14). Default = NO (Character = NO, SIMP, PER, CUTF) NO - No filter is used. SIMP - Simple numerical filter. PER - Standard -3dB filter with filtering period. CUTF - Standard -3dB filter with cutting frequency.

FFAC

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(0.0 < Real < 1.0) IFORM

Type of friction penalty formulation (See comments 16 and 17). Default = VISC (Character = VISC, STIFF) VISC - Viscous (total) formulation. STIFF - Stiffness (incremental) formulation.

C1, C2, C3, C4, C5, C6

Friction law coefficients.

IGNORE

Flag to ignore slave nodes if no master segment is found for TIE contact (See comment 18).

(Real > 0)

Default = 1 (Integer = 0, 1, 2) 0 - No deletion of slave nodes; 1 - Slave nodes with no master segment found are deleted from the interface; 2 - Slave nodes with no master segment found are deleted from the interface; if SRCHDIS is blank, then it would be newly calculated internally. MTET10

Flag for second order CTETRA as contact master surface. Default = 0 (Integer = 0, 1) 0 - TETRA 10 is degenerated on the surface (middle nodes are removed from contact); 1 - Four triangular segments are used on each tetra face.

The following entries are relevant for explicit analysis only. ISYM

Flag for symmetric contact. Default = SYM (Character = SYM, UNSYM) SYM – Symmetric contact. UNSYM – Master-slave contact. If SSID defines a grid set, the contact is always a master-slave contact.

IEDGE

Flag for edge generation from slave and master surfaces. Default = NO (Character = NO, ALL, BORD, FEAT) NO – No edge generation. ALL – All segment edges are included. BORD – External border of slave and master surface is used.

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FEAT – External border as well as features defined by FANG are used. FANG

Feature angle for edge generation in degrees (Only with IEDGE = FEAT). Default = 91.0 (Real > 0)

IGAP

Flag for gap definition. Default = CONST (Character = CONST, VAR) CONST - Gap is constant and equal to GAP (See comments 11 and 12). VAR - Gap is variable (in space, not in time) according to the characteristics of the impacting surfaces and nodes (See comment 11).

ISTF

Flag for stiffness definition (See comment 9). Default = 0 (Integer = 0, …, 5) 0 - The stiffness is computed according to the master side characteristics. 1 - STIF1 is used as interface stiffness. 2, 3, 4 and 5 - The interface stiffness is computed from both master and slave characteristics.

STIF1

Interface stiffness (Only with ISTF = 1). Default = 0.0 (Real > 0)

STMIN

Minimum interface stiffness (Only with ISTF > 1). (Real > 0)

STMAX

Maximum interface stiffness (Only with ISTF > 1). Default = 1030 (Real > 0)

IBC

Flag for deactivation of boundary conditions at impact. (Character = X, Y, Z, XY, XZ, YZ, XYZ)

VISS

Critical damping coefficient on interface stiffness. Default = 0.05 (Real > 0)

VISF

Critical damping coefficient on interface friction. Default = 1.0 (Real > 0)

BMULT

Sorting factor. Default = 0.20 (Real > 0)

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Comments for quasi-static analysis 1.

The initial gap opening is calculated automatically based on the relative location of slave and master nodes (in the original, undeformed mesh). To account for additional material layers covering master or slave objects (such as half of shell thickness), the GPAD entry can be used. GPAD option THICK automatically accounts for shell thickness on both sides of the contact interface (this also includes the effects of shell element offset ZOFFS or composite offset Z0).

2.

Option STIFF=AUTO determines the value of normal stiffness for each contact element using the stiffness of surrounding elements. Additional options SOFT and HARD create respectively softer or harder penalties. SOFT can be used in cases of convergence difficulties and HARD can be used if undesirable penetration is detected in the solution.

3.

Prescribing MU1=STICK is interpreted in OptiStruct as an enforced stick condition - such contact interfaces will not enter the sliding phase. Of course, the enforced stick only applies to contacts that are closed.

4.

Prescribing MU1=FREEZE enforces zero relative displacements on the contact surface – the contact gap opening remains fixed at the original value and the sliding distance is zero. The FREEZE condition applies to all slave nodes, no matter whether their initial gap is open or closed.

5.

This card is represented as a control card in HyperMesh.

6.

The file filename_root.contgap.fem, produced using the CONTGAP parameter, can be imported into HyperMesh in order to visualize internally created node-to-surface contact elements (now converted to GAPG entities). Note that during optimization, this file shows node-to-surface contact elements for the latest optimization iteration. In order to correctly visualize this configuration in HyperMesh for shape optimization problems, the FEA mesh shape needs to be updated by applying "Shape change" results. Furthermore, if GAPPRM,HMGAPST,YES is activated together with CONTPRM,CONTGAP,YES, then the gap status command file, filename_root.HM.gapstat.cmf, will also include the open/closed status of these additional GAPG’s that represent node-to-surface contact elements. For correct visualization of their status in HyperMesh, file filename_root.contgap.fem needs to be imported before running the gap status command file.

7.

The CONTACT capability in NLSTAT solution is designed to correctly resolve initial prepenetration, such as happens in press fit, and so on. This usually works reliably with correct identification of Master and Slave surfaces. However, in some cases users create contact surfaces by property for convenience, which results in contact surfaces enveloping the entire solid bodies. Also, sometimes the Slave and Master receive the same ID, which is known as self-contact (and is not a recommended practice, in spite of the convenience factor). In such cases, it is possible to encounter false selfpenetrations, as illustrated below:

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In the case above, the Slave node will be identified as if pre-penetrating the Master face, while in reality it is on the other side of the same solid body. The result from nonlinear CONTACT solution will be such that this portion of the body will be “squeezed” to have practically zero thickness, with very high stresses obviously resulting. Apart from correctly identifying potential Slave and Master sets, a possible remedy to avoid such situations is to make sure that SRCHDIS is smaller than minimum thickness of the solid bodies which are enveloped by self-contacting surfaces. An alternative, viable when there are no actual pre-penetrations in the problem, is to choose SFPRPEN = NO, which will ignore initial pre-penetrations on self-contacting surfaces (some minor pre-penetrations due to variations of nodal positions will still be correctly resolved – up to the minimum element size on the respective contact surfaces). Note that SFPRPEN affects only surfaces that actually have self-penetration, as in a case where the Slave Node and Master Face belong to the same contact set or surface. On properly defined, disjoint Slave and Master surfaces, the initial pre-penetrations will be resolved irrespective of this parameter. 8.

Effective in Release 12.0, two models of friction are available in nonlinear analysis: (a) Model based on fixed slope KT (previously existing), (b) Model based on Elastic Slip Distance FRICESL (introduced in v12.0 and current default). This latter model typically shows better performance in solution of frictional problems thanks to more stable handling of transitions from stick to slip. Key differences between the two available models are illustrated in the figure below (F 1 and F 2 represent two different values of normal force F x ):

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C omparison of the two available friction models for contact elements.

Model (a), based on fixed stiffness KT, is relatively simple, yet has certain drawback in modeling nonlinear friction. Namely, in Coulomb friction the frictional resistance depends upon normal force. Using fixed KT will predict different range of stick/slip boundary for different normal forces, and thus may qualify the same configuration as stick or slip, depending on normal force. Model (b), based on Elastic Slip Distance, provides unique identification of stick or slip and generally performs better in solution of problems with friction. This model does require prescribing elastic slip distance FRICESL – for contact interfaces this value is determined automatically as 0.5% of typical element size on all Master contact surfaces. The model (b), which is currently the default, is recommended for solution of nonlinear problems with friction. For backwards compatibility, the model based on fixed KT can be activated by prescribing FRICESL=0 on PCONT or CONTPRM card. Comments for geometric nonlinear analysis (ANALYSIS = NLGEOM / IMPDYN / EXPDYN in subcase) 9. and/or the slave segment stiffness Ks. The master stiffness is computed from Km = STFAC * B * S * S/V for solids, Km = 0.5 * STFAC * E * t for shells as well as when the master segment is shared by a shell and solid. The slave stiffness is an equivalent nodal stiffness computed as Ks = STFAC * B * V-3 for solids, Ks = 0.5 * STFAC * E * t for shells. In these equations, B is the Bulk Modulus, S is the segment area, E is the modulus of elasticity, t is shell thickness, and V is the volume of a solid. There is no limitation to the value of stiffness factor (but a value larger than 1.0 can reduce the initial time step). ISTF = 0, the interface stiffness K = Km ISTF > 1, the interface stiffness is then K = max (STMIN, min (STMAX, K1)) with ISTF = 2, K1 = 0.5 * (Km + Ks)

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ISTF = 3, K1 = max (Km, Ks) ISTF = 4, K1 = min (Km, Ks) ISTF = 5, K1 = Km * Ks / (Km + Ks) 10. In an implicit analysis, the contact stiffness plays a very important role in convergence. ISTF = 4 (which takes the minimum of master and slave stiffness’s for contact) is recommended. This is because the penalty contact force will be balanced with the internal force of the deformable impacted part. That means the stiffness near the effective stiffness one will converge easier than a higher one. For small initial gaps in implicit analysis, the convergence will be more stable if a GAP is defined that is larger than the initial gap. In implicit analysis, sometimes a stiffness with scaling factor reduction (for example: STFAC = 0.01) or reduction in impacted thickness (if rigid one) might reduce unbalanced forces and improve convergence, particularly in shell structures under bending where the effective stiffness is much lower than membrane stiffness; but it should be noted that too low of a value could also lead to divergence. 11. The default for the constant gap (IGAP = CONST) is the minimum of t, average thickness of the master shell elements; l/10, l – average side length of the master solid elements; lmin/2, lmin – smallest side length of all master segments (shell or solid). 12. The variable gap (IGAP = VAR) is computed as gs + gm with: gm - master element gap with gm = t/2, t: thickness of the master element for shell elements. gm = 0 for solid elements. gs - slave node gap: gs = 0 if the slave node is not connected to any element or is only connected to solid or spring elements. gs = t/2, t - largest thickness of the shell elements connected to the slave node. and beam elements, with S being the cross-section of the element. If the slave node is connected to multiple shells and/or beams or trusses, the largest computed slave gap is used. The variable gap is always at least equal to GAPMIN. 13. INACTI = 3, 4 are only recommended for small initial penetrations and should be used with caution because: the coordinate change is irreversible. it may create other initial penetrations if several surface layers are defined in the interfaces.

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it may create initial energy if the node belongs to a spring element. INACTI = 5 works as follows:

14. the tangential friction forces are smoothed using a filter: F T = α * F'T + (1 - α) * F'T -1 where, F T - Tangential force F'T - Tangential force at time t F'T - 1 - Tangential force at time t-1 α - filtering coefficient IFILT = SIMP – α = FFAC IFILT = PER – α = 2π dt/FFAC, where dt/T = FFAC, T is the filtering period IFILT = CUTF – α = 2π * FFAC * dt, where FFAC is the cutting frequency 15. IFRIC defines the friction model. IFRIC = COUL – Coulomb friction with F T <

* F N with

= FRIC

For IFRIC is not COUL, the friction coefficient is set by a function ( = (p, V)), where p is the pressure of the normal force on the master segment and V is the tangential velocity of the slave node. The following formulations are available: IFRIC = GEN - Generalized viscous friction law = Fric + C1 * p + C2 * V + C3 * p * V + C4 * p2 + C5 * V2 IFRIC = DARM - Darmstad law = C1

e(C 2 V )

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p2 + C3

e(C 4 V )

p + C5

e(C 6 V )

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IFRIC = REN - Renard law

The first critical velocity Vcr1 than the second critical velocity Vcr2 (C5 < C6). The static friction coefficient C1 and the dynamic friction coefficient C2 must be lower than the maximum friction C3 (C1 < C3 ) and C2 < C3 ). The minimum friction coefficient C4 , must be lower than the static friction coefficient C1 and the dynamic friction coefficient C2 (C4 < C1 and C4 < C2 ). 16. IFROM selects two types of contact friction penalty formulation. The viscous (total) formulation (IFORM = VISC) computes an adhesive force as F adh = VISF * Sqrt(2Km) * VTF T = min (µF N, F adh) The stiffness (incremental) formulation (IFORM = STIFF) computes an adhesive force as F adh = F Told + ∆F T ∆F T = K * VT * dt

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F Tnew = min (µF N, F adh ) 17. For nonlinear implicit contact with friction, the stiffness formulation (IFORM = STIFF) is recommended. 18. If IGNORE = 1 or 2, the slave nodes without a master segment found during the searching are deleted from the interface. If IGNORE = 1 and SRCHDIS is blank, then the default value of the distance for searching closest master segment is the average size of the master segments. If IGNORE = 2 and SRCHDIS is blank, then the distance for searching closest master segment is computed as follows for each slave node: d1 = 0.6 * (T s + T m) d2 = 0.05 * T md SRCHDIS = max(d1, d2 ) where, T s is the thickness of the element connected to the slave node, for solids T s = 0.0 T m is the thickness of master segment, for solids T m = Element volume / Segment area T md is the master segment diagonal 19. This card is represented as a control card in HyperMesh.

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CONTX11 Bulk Data Entry CONTX11 – Edge to Edge or Line to Line Contact Interface Definition for Geometric Nonlinear Analysis Description Defines a edge to edge or line to line contact interface. Format (1)

(2)

(3)

(4)

(5)

(6)

C ONTX11

C TID

PID

SLID

MLID

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C ONTX11

5

10

7

8

(6)

Field

Contents

CTID

Contact interface identification number.

(7)

(8)

(9)

(10)

(Integer > 0) PID

Property identification number of a PCONT entry. See comment 2. (Integer > 0)

SLID

Identification number of slave LINE entity. See comments 3 and 4. (Integer > 0)

MLID

Identification number of master LINE entity. See comments 3 and 4. (Integer > 0)

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Comments 1.

CONTX11 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

2.

The property of CONTX11(PID) only can be defined by PCONT and its extended card PCNTX11.

3.

CONTX11 defines contact interface type 11, it describes the edge to edge or line to line interface. This interface simulates impact between lines, a line can be a beam or truss element or a shell edge or spring elements. The interface properties are: impacts occur between a master and a slave line; a slave line can impact on one or more master lines; a line can belong to the master and the slave side. This allows self impact; this interface can be used in addition to the interface type 7 PCNTX7 to solve the edge to edge limitation of interface type 7.

4.

The slave line entity SLID and master line set entity MLID must be defined via LINE: a set of edges or lines of 1-D, 2-D or 3-D elements; a set of elements (bars, beams, springs or shells), defined using SET(ELEM,...) command;

5.

This card is represented as a group in HyperMesh.

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CONV Bulk Data Entry CONV – Free Convection Description Defines a free convection boundary condition for heat transfer analysis through connection to a surface element (CHBDYE card). Format (1)

(2)

(3)

C ONV

EID

PC ONID

(4)

(5)

(6)

(7)

(8)

(9)

(10)

TA

Field

Contents

EID

CHBDYE surface element identification number. No default (Integer > 0)

PCONID

Convection property identification number of a PCONV card. No default (Integer > 0)

TA

Ambient points used to specify ambient temperature. No default (Integer > 0)

Comments 1.

The basic exchange relationship is expressed as:

q = H * (T - TAMB) Where, H is the free convection heat transfer coefficient specified on a MAT4 card referred by a PCONV card, T is the grid temperature, and TAMB is the ambient temperature. 2.

CONV is used with a CHBDYE card having the same EID.

3.

In linear steady-state heat transfer analysis, ambient temperature is specified by SPC of the TA point.

4.

This card is represented as a slave element in HyperMesh.

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CORD1C Bulk Data Entry CORD1C – Cylindrical Coordinate System Definition, Form 1 Description This entry defines a cylindrical coordinate system using three grid points. The first point is the origin, the second lies on the Z-axis, and the third lies in the X-Z plane (see Figure 1). Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ORD1C

C ID

G1

G2

G3

C ID

G1

G2

G3

(10)

Example

(1)

(2)

(3)

(4)

(5)

C ORD1C

3

16

32

19

(6)

(7)

Field

Contents

CID

Unique coordinate system identification number.

(8)

(9)

(10)

(Integer > 0) G1, G2, G3

Grid point identification numbers of points used to uniquely define the cylindrical coordinate system (see Figure 1).

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Figure 1: Defining a C ylindrical C oordinate System (C ID) using grid points G1, G2 and G3.

Comments 1.

Coordinate system identification numbers (CID) on all CORD1R, CORD1C, CORD1S, CORD2R, CORD2C, CORD2S, CORD3R, and CORD4R entries must all be unique.

2.

A duplicate identification number is allowed if the CID and GID are identical and the coordinates are within the value set by PARAM, DUPTOL (see Guidelines for Bulk Data Entries for further information).

3.

The three points G1, G2, G3 must be non-collinear. Non-collinearity is checked by the geometry processor.

4.

The location of a grid point (P in Figure 1) in this cylindrical coordinate system is given by (R, θ, and Z) where, θ is measured in degrees.

5.

The displacement coordinate directions at P are dependent on the location of P (ur, uθ, and uz) as shown in Figure 1. The displacements in all three of these directions at the grid point are specified in units of length. In OptiStruct, the cylindrical and spherical coordinate systems are internally resolved to entity-position-dependent (example: GRID) rectangular systems. Therefore, when a grid point is located in a cylindrical system, OptiStruct constructs a rectangular system at that location for the grid point. The R-direction corresponds to the X-axis, the Z-axis is the same, and the θ axis is tangential to the X (or R) axis. Now the various degrees of freedom can be resolved (vis-à-vis constraints) similar to a general rectangular system. Care must be taken to observe that the internally generated rectangular systems are dependent on the grid point location in the cylindrical system. So they may be different for different grid point locations within the same cylindrical system.

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6.

Points on the Z-axis should not have their displacement directions defined in this coordinate system due to ambiguity. In this case, the defining rectangular system is used.

7.

A maximum of two coordinate systems may be defined on a single entry.

8.

This card is represented as a system in HyperMesh.

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CORD1R Bulk Data Entry CORD1R – Rectangular Coordinate System Definition, Form 1 Description This entry defines a rectangular coordinate system using three grid points. The first point is the origin, the second lies on the Z-axis, and the third lies on the X-Z plane (see Figure 1). Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ORD1R

C ID

G1

G2

G3

C ID

G1

G2

G3

(10)

Example

(1)

(2)

(3)

(4)

(5)

C ORD1R

3

16

32

19

(6)

(7)

Field

Contents

CID

Unique coordinate system identification number.

(8)

(9)

(10)

(Integer > 0) G1, G2, G3

610

Grid point identification numbers of points used to uniquely define the rectangular coordinate system (see Figure 1).

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Figure 1: Defining a Rectangular C oordinate System (C ID) using grid points G1, G2 and G3.

Comments 1.

Coordinate system identification numbers on all CORD1R, CORD1C, CORD1S, CORD2R, CORD2C, CORD2S, CORD3R, and CORD4R entries must all be unique.

2.

A duplicate identification number is allowed if the CID and GID are identical and the coordinates are within the value set by PARAM, DUPTOL (see Guidelines for Bulk Data Entries for further information).

3.

The three points G1, G2, and G3 must be non-collinear. Non-collinearity is checked by the geometry processor.

4.

The location of a grid point (P in Figure 1) in this rectangular coordinate system is given by (X, Y, and Z).

5.

The displacement coordinate directions at P are (Ux , Uv , and Uz) as shown in Figure 1.

6.

A maximum of two coordinate systems may be defined on a single entry.

7.

In geometric nonlinear analysis, CORD1R is a moving coordinate system. It moves with GRID points defining the system.

8.

This card is represented as a system in HyperMesh.

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CORD1S Bulk Data Entry CORD1S – Spherical Coordinate System Definition, Form 1 Description This entry defines a spherical coordinate system using three grid points. The first point is the origin, the second lies on the polar (Z) axis, and the third lies in the X-Z plane (see Figure 1). Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ORD1S

C ID

G1

G2

G3

C ID

G1

G2

G3

(10)

Example

(1)

(2)

(3)

(4)

(5)

C ORD1S

3

16

32

19

(6)

(7)

Field

Contents

CID

Unique coordinate system identification number.

(8)

(9)

(10)

(Integer > 0) G1, G2, G3

612

Grid point identification number.

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Figure 1: Defining a Spherical C oordinate System (C ID) using grid points G1, G2 and G3.

Comments 1.

Coordinate system identification numbers on all CORD1R, CORD1C, CORD1S, CORD2R, CORD2C, CORD2S, CORD3R, and CORD4R entries must all be unique.

2.

A duplicate identification number is allowed if the CID and GID are identical and the coordinates are within the value set by PARAM, DUPTOL (see Guidelines for Bulk Data Entries for further information).

3.

The three points G1, G2, and G3 must be non-collinear. Non-collinearity is checked by the geometry processor.

4.

The location of a grid point (P in Figure 1) in this spherical coordinate system is given by (R, θ, and ). Where, θ and are measured in degrees.

5.

The displacement coordinate directions at P are dependent on the location of P (ur, uθ, and u ) as shown in Figure 1. The displacements in all three of these directions at the grid point are specified in units of length.

6.

Points on the polar axis may not have their displacement directions defined in this coordinate system due to ambiguity. In this case, the defining rectangular system is used.

7.

A maximum of two coordinate systems may be defined on a single entry.

8.

This card is represented as a system in HyperMesh.

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CORD2C Bulk Data Entry CORD2C – Cylindrical Coordinate System Definition, Form 2 Description This entry defines a cylindrical coordinate system using three grid points specified with respect to a reference coordinate system. The coordinates of the three non-collinear grid points are used to uniquely define the coordinate system. The first point defines the origin. The second point defines the direction of the Z-axis. The third lies in the X-Z plane (see Figure 1). Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ORD2C

C ID

RID

A1

A2

A3

B1

B2

B3

C1

C2

C3

(10)

Example

(1)

(2)

C ORD2C

3

5.2

(3)

1.0

(4)

(5)

(6)

(7)

(8)

(9)

-2.9

1.0

0.0

3.6

0.0

1.0

(10)

-2.9

Field

Contents

CID

Unique coordinate system identification number. (Integer > 0)

RID

Identification number of a reference coordinate system that is defined independently from this coordinate system (see comment 7). Default = 0 (Integer > 0)

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Field

Contents

A1,A2,A3 B1,B2,B3 C1,C2,C3

Coordinates of three points in the reference coordinate system (RID). If RID is blank or 0, then the reference coordinate system is the default basic coordinate system. (Real)

Figure 1: Defining a C ylindrical C oordinate System (C ID) using points A, B and C with reference to another coordinate system (RID).

Comments 1.

The three points (A1, A2, A3), (B1, B2, B3), (C1, C2, C3) must be unique and noncollinear. Non-collinearity is checked by the geometry processor.

2.

Coordinate system identification numbers (CID) on all CORD1R, CORD1C, CORD1S, CORD2R, CORD2C, CORD2S, CORD3R, and CORD4R entries must be unique.

3.

A duplicate identification number is allowed if the CID and GID are identical and the coordinates are within the value set by PARAM, DUPTOL (see Guidelines for Bulk Data Entries for further information).

4.

The location of a grid point (P in Figure 1) in this cylindrical coordinate system is given by (R, θ, and Z). Where, θ is measured in degrees.

5.

The displacement coordinate directions at P are dependent on the location of P (Ur, Uθ, and Uz) as shown in Figure 1. The displacements in these three directions at the grid point are specified in units of length.

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In OptiStruct, the cylindrical and spherical coordinate systems are internally resolved to entity-position-dependent (example: GRID) rectangular systems. Therefore, when a grid point is located in a cylindrical system, OptiStruct constructs a rectangular system at that location for the grid point. The R-direction corresponds to the X-axis, the Z-axis is the same, and the θ axis is tangential to the X (or R) axis. Now the various degrees of freedom can be resolved (vis-à-vis constraints) similar to a general rectangular system. Care must be taken to observe that the internally generated rectangular systems are dependent on the grid point location in the cylindrical system. So they may be different for different grid point locations within the same cylindrical system. 6.

Points on the Z-axis should not have their displacement directions defined in this coordinate system due to ambiguity.

7.

The reference coordinate system (RID) should be independently defined or left blank. If blank (or 0), the reference coordinate system is the default basic coordinate system. In such cases, A, B and C are defined with respect to the basic coordinate system.

8.

This card is represented as a system in HyperMesh.

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CORD2R Bulk Data Entry CORD2R – Rectangular Coordinate System Definition, Form 2 Description The entry defines a rectangular coordinate system by using three grid points. The coordinates of the three non-collinear grid points are used to uniquely define the coordinate system. The first point defines the origin. The second defines the direction of the Z-axis. The third point defines a vector, which, with the Z-axis, defines the X-Z plane (see Figure 1). Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ORD2R

C ID

RID

A1

A2

A3

B1

B2

B3

C1

C2

C3

(10)

Example

(1)

(2)

C ORD2R

3

5.2

(3)

1.0

(4)

(5)

(6)

(7)

(8)

(9)

-2.9

1.0

0.0

3.6

0.0

1.0

(10)

-2.9

Field

Contents

CID

Unique coordinate system identification number. (Integer > 0)

RID

Identification number of a coordinate system that is defined independently from this coordinate system (see comment 6). Default = 0 (Integer > 0)

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Field

Contents

A1,A2,A3 B1,B2,B3 C1,C2,C3

Coordinates of three points in the reference coordinate system (RID). If RID is blank or 0, then the reference coordinate system is the default basic coordinate system. (Real)

Figure 1: Defining a Rectangular C oordinate System (C ID) using points A, B and C with reference to another coordinate system (RID).

Comments 1.

The three points (A1, A2, and A3), (B1, B2, and B3), and (C1, C2, and C3) must be unique and non-collinear. Non-collinearity is checked by the geometry processor.

2.

Coordinate system identification numbers on all CORD1R, CORD1C, CORD1S, CORD2R, CORD2C, CORD2S, CORD3R, and CORD4R entries must all be unique.

3.

A duplicate identification number is allowed if the CID and GID are identical and the coordinates are within the value set by PARAM, DUPTOL (see Guidelines for Bulk Data Entries for further information).

4.

The location of a grid point (P in Figure 1) in this rectangular coordinate system is given by (X, Y, and Z).

5.

The displacement coordinate directions at P are (Ux , Uv , and Uz) as shown in Figure 1.

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6.

The reference coordinate system (RID) should be independently defined or left blank. If blank (or 0), the reference coordinate system is the default basic coordinate system. In such cases, A, B and C are defined with respect to the basic coordinate system.

7.

This card is represented as a system in HyperMesh.

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CORD2S Bulk Data Entry CORD2S – Spherical Coordinate System Definition, Form 2 Description This entry defines a spherical coordinate system three grid points. The coordinates of the three non-collinear grid points are used to uniquely define the coordinate system. The first point defines the origin. The second point defines the direction of the Z-axis. The third lies in the X-Z plane (see Figure 1). Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ORD2S

C ID

RID

A1

A2

A3

B1

B2

B3

C1

C2

C3

(10)

Example

(1)

(2)

C ORD2S

3

5.2

(3)

1.0

(4)

(5)

(6)

(7)

(8)

(9)

-2.9

1.0

0.0

3.6

0.0

1.0

(10)

-2.9

Field

Contents

CID

Unique coordinate system identification number. (Integer > 0)

RID

Identification number of a coordinate system that is defined independently from this coordinate system (see comment 7). Default = 0 (Integer > 0)

A1,A2,A3

620

Coordinates of three points in the reference coordinate system (RID). If

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Field

Contents

B1,B2,B3 C1,C2,C3

RID is blank or 0, then the reference coordinate system is the default basic coordinate system. (Real)

Figure 1: Defining a Spherical C oordinate System (C ID) using grid points A, B and C .

Comments 1.

The three points (A1, A2, and A3), (B1, B2, and B3), and (C1, C2, and C3) must be unique and non-collinear. Non-collinearity is checked by the geometry processor.

2.

Coordinate system identification numbers on all CORD1R, CORD1C, CORD1S, CORD2R, CORD2C, CORD2S, CORD3R, and CORD4R entries must all be unique.

3.

A duplicate identification number is allowed if the CID and GID are identical and the coordinates are within the value set by PARAM, DUPTOL (see Guidelines for Bulk Data Entries for further information).

4.

The location of a grid point (P in Figure 1) in this spherical coordinate system is given by (R, θ, and ). Where, θ and are measured in degrees.

5.

The displacement coordinate directions at P are (ur, uθ, and u ) as shown in Figure 1. The displacements in all three of these directions at the grid point are specified in units of length.

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6.

Points on the polar axis may not have their displacement directions defined in this coordinate system due to ambiguity.

7.

The reference coordinate system (RID) should be independently defined or left blank. If blank (or 0), the reference coordinate system is the default basic coordinate system. In such cases, A, B and C are defined with respect to the basic coordinate system.

8.

This card is represented as a system in HyperMesh.

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CORD3R Bulk Data Entry CORD3R – Rectangular Coordinate System Definition, Form 3 Description The entry defines a rectangular coordinate system using three grid points. The first point is the origin, the second lies on the X-axis, and the third lies on the X-Y plane (see Figure 1). Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ORD3R

C ID

G1

G2

G3

C ID

G1

G2

G3

(10)

Example

(1)

(2)

(3)

(4)

(5)

C ORD3R

3

16

32

19

(6)

(7)

Field

Contents

CID

Unique coordinate system identification number.

(8)

(9)

(10)

(Integer > 0) G1, G2, G3

Grid point identification numbers of points used to uniquely define the rectangular coordinate system (see Figure 1).

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Figure 1: Defining a Rectangular C oordinate System (C ID) using grid points G1, G2 and G3.

Comments 1.

Coordinate system identification numbers on all CORD1R, CORD1C, CORD1S, CORD2R, CORD2C, CORD2S, CORD3R, and CORD4R entries must all be unique.

2.

A duplicate identification number is allowed if the CID and GID are identical and the coordinates are within the value set by PARAM, DUPTOL. Refer to Guidelines for Bulk Data Entries.

3.

The three points G1, G2, and G3 must be non-collinear. Non-collinearity is checked by the geometry processor.

4.

The location of a grid point (P in Figure 1) in this rectangular coordinate system is given by (X, Y, and Z).

5.

The displacement coordinate directions at P are (Ux , Uv , and Uz) as shown in Figure 1.

6.

A maximum of two coordinate systems may be defined on a single entry.

7.

In geometric nonlinear analysis, CORD3R is a moving coordinate system. It moves with grid points defining the system.

8.

The implementation of CORD3R in OptiStruct is different from that of NASTRAN. A CORD3R coordinate system in OptiStruct can be defined by specifying grid point identification numbers for the Origin, X-axis and the XY plane, whereas CORD3R in NASTRAN is specified with reference to the Origin, Z-axis and the XZ plane.

9.

This card is represented as a system in HyperMesh.

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CORD4R Bulk Data Entry CORD4R – Rectangular Coordinate System Definition, Form 4 Description This entry defines a rectangular coordinate system using three grid points specified with respect to the basic coordinate system. The coordinates of the three non-collinear grid points are used to uniquely define the coordinate system. The first point is the origin, the second lies on the X-axis, and the third lies on the X-Y plane (see Figure 1). Format (1)

(2)

(3)

C ORD4R

C ID

C1

C2

(4)

(5)

(6)

(7)

(8)

(9)

A1

A2

A3

B1

B2

B3

(10)

C3

Example

(1)

(2)

C ORD4R

3

5.2

(3)

1.0

(4)

(5)

(6)

(7)

(8)

(9)

-2.9

1.0

0.0

3.6

0.0

1.0

(10)

-2.9

Field

Contents

CID

Unique coordinate system identification number. (Integer > 0)

A1,A2,A3 B1,B2,B3 C1,C2,C3

Coordinates of three points in the basic coordinate system. (Real)

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Figure 1: C ORD4R definition.

Comments 1.

Coordinate system identification numbers on all CORD1R, CORD1C, CORD1S, CORD2R, CORD2C, CORD2S, CORD3R, and CORD4R entries must all be unique.

2.

A duplicate identification number is allowed if the CID and GID are identical and the coordinates are within the value set by PARAM, DUPTOL (see Guidelines for Bulk Data Entries for further information).

3.

The three points (A1, A2, and A3), (B1, B2, and B3), and (C1, C2, and C3) must be unique and non-collinear. Non-collinearity is checked by the geometry processor.

4.

The location of a grid point (P in Figure 1) in this rectangular coordinate system is given by (X, Y, and Z).

5.

The displacement coordinate directions at P are (Ux , Uv , and Uz) as shown in Figure 1.

6.

A maximum of two coordinate systems may be defined on a single entry.

7.

This card is represented as a system in HyperMesh.

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COUPLER Bulk Data Entry COUPLER – Coupler Definition for Multi-body Solution Sequence Description Defines a coupler connecting two or three joints. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C OUPLER

C OID

JID1

TYPE1

RATIO1

JID2

TYPE2

RATIO2

JID3

TYPE3

RATIO3

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

C OUPLER

3

1

T

2.0

4

R

1.0

Field

Contents

COID

Unique coupler identification number.

(9)

(10)

(Integer > 0) JIDi

Joint identification numbers. No default (Integer > 0)

TYPEi

Type. No default (TRA or ROT) – See comment 3.

RATIOi

Coefficients of the coupler constraint equation. (Real; Default = 1.0)

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Comments 1.

COUPLERs are only valid in a multi-body solution sequence.

2.

At least JID1 and JID2 need to be defined.

3.

The type is optional if the Joint is revolute or translation. But if the joint is cylindrical, the type should be set to TRA to denote that the translational motion is coupled or ROT to specify that the rotational motion is coupled.

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CPENTA Bulk Data Entry CPENTA – Five-sided Solid Element with six or fifteen grid points Description Defines the connections of the CPENTA element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C PENTA

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

G9

G10

G11

G12

G13

G14

G15

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C PENTA

112

2

3

15

14

4

103

115

Field

Contents

EID

Unique element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PSOLID property entry. Default = EID (Integer > 0)

G#

Identification numbers of connected grid points. Default = blank (Integer > 0 or blank)

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Comments 1.

Element ID numbers must be unique with respect to all other element ID numbers.

2.

The topology of the diagram must be preserved, that is, G1, G2, and G3 define a triangular face, G1-G4, G2-G5, and G3-G6 each form one edge. The edge points, G7-G15, are optional. If any of the edge points are present, they all must be used. The second and third continuation is not needed for the six node version of this element. It is recommended that the edge points be placed near the middle of the edge.

C PENTA definition

3.

If the user-prescribed node numbering on the bottom and top faces is reversed as compared to the sequence shown above, then the nodes are renumbered to produce right-handed orientation of numbering. This is accomplished by swapping nodes G1 with G3 and G4 with G6. For 15-noded CPENTA, appropriate changes to mid-side node numbering are also performed. In such cases, the element coordinate system will be built on the renumbered node sequence.

4.

Stresses are output in the material coordinate system. The material coordinate system is defined on the referenced PSOLID entry. It may be defined as the basic coordinate system (CORDM = 0), a defined system (CORDM = Integer > 0), or the element coordinate system (CORDM = -1).

5.

The element coordinate system for the CPENTA element is defined as follows:

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C PENTA element coordinate system

The origin of the element coordinate system is located at the mid-point of a straight line from G1 to G4. The element z-axis corresponds to the average of the vector connecting the centroid of triangular face G1-G2-G3 to the centroid of the triangular face G4-G5-G6 and the normal vector of the mid-plane (the plane on which the mid-points of the straight lines G1-G4, G2-G5, and G3-G6 lie). The positive sense of the z-axis is toward the triangular face G4G5-G6. The element y-axis is perpendicular to the element z-axis and lies on the plane created by the element z-axis and the line connecting the origin and the mid-point of a straight line from G3 to G6. The positive sense of the y-axis is toward the straight line from G3 to G6. The element x-axis is the cross product of the element y-axis and the element z-axis. 6.

This card is represented as a penta6 or penta15 element in HyperMesh.

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CPYRA Bulk Data Entry CPYRA – Five-sided Solid Element with five or thirteen grid points Description Defines the connections of the PYRA solid element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C PYRA

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

G9

G10

G11

G12

G13

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

C PYRA

71

4

3

4

5

6

7

Field

Contents

EID

Unique element identification number.

(9)

(10)

No default (Integer > 0) PID

Identification number of a PSOLID property entry. Default = EID (Integer > 0)

G#

Grid point identification numbers of connection points. Default = blank (Integer > 0 or blank)

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Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

Grid points G1,…,G4 must be given in consecutive order about the quadrilateral face. The edge points, G6 through G13, are optional. If any of the edge points are present, they all must be used. The continuation must not be present for the 5-noded version of this element. It is recommended that the edge points be placed near the middle of the edge.

C PYRA definition

3.

Stresses are output in the material coordinate system. The material coordinate system is defined on the referenced PSOLID entry. It may be defined as the basic coordinate system (CORDM = 0), a defined system (CORDM = Integer > 0), or the element coordinate system (CORDM = -1).

4.

The element coordinate system for the CPYRA element is defined as follows: Three intermediate vectors R, S, and T are chosen by the following rules: R

Joins the midpoints of the edges from G1 to G4 and G2 to G3.

S

Joins the midpoints of the edges from G1 to G2 and G3 to G4.

T

Joins the intersection of R and S to G5.

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C PYRA element coordinate system

The origin of the element coordinate system is located at the intersection of the vectors R and S. The element z-axis corresponds to the T vector. The element y-axis is the cross product of the T and R vectors. The element x-axis is the cross product of the element y-axis and the element z-axis. 5.

634

This card is represented as a pyra5 or pyra13 element in HyperMesh.

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CQUAD4 Bulk Data Entry CQUAD4 – Quadrilateral Element Connection Description Defines a quadrilateral plate element (QUAD4) of the structural model. This element uses a 6 degree-of-freedom per node formulation. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C QUAD4

EID

PID

G1

G2

G3

G4

Theta or MC ID

ZOFFS

T1

T2

T3

T4

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C QUAD4

111

203

31

74

75

32

Field

Contents

EID

Unique element identification number.

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PSHELL, PCOMP, PCOMPP or PHFSHL property entry. Default = EID (Integer > 0)

G1,G2,G3,G4

Grid point identification numbers of connection points. No default (Integers > 0, all unique)

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Field

Contents

Theta

Material orientation angle in degrees. Default = 0.0 (Real)

MCID

Material coordinate system identification number. The x-axis of this coordinate system is projected onto the element to define the x-axis of the material coordinate system. If MCID = 0, it specifies the basic coordinate system. MCID must be an integer > 0. If blank, Theta = 0.0 is used, unless the material referenced by the element is isotropic (MAT1) – then MCID = 0 is used. See comments 4, 5, and 6. Default is Theta = 0.0 (Integer > 0)

ZOFFS

Offset from the plane defined by element grid points to the shell reference plane. See comment 10. Overrides the ZOFFS specified on the PSHELL entry. Default = 0.0 (Real or blank)

Ti

Thickness of the element at the grid points. Overrides the thickness specified on the PSHELL entry. If Ti is specified, the average of all four thicknesses is used as the element thickness. For defaults: See comments 7 and 9. (Real > 0.0 or blank)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

Grid points G1 through G4 must be ordered consecutively around the perimeter of the element.

3.

All of the interior angles must be less than 180 degrees.

4.

The elemental coordinate system is a bisection definition as depicted in the following figure:

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Elemental coordinate system

5.

For H3D and OUTPUT2 output formats, stresses and strains are always output in the elemental system.

6.

For HM, PUNCH and OPTI output formats, stresses and strains are output by default in the material coordinate system. PARAM, OMID can be set to NO to output results in the elemental system. For elements with blank Theta/MCID, THETA = 0.0 is assumed, and the material coordinate system is aligned with side G1-G2 of the shell element. For elements with prescribed THETA, the material x-axis is rotated from side G1-G2 by angle THETA. For elements with prescribed MCID, the material system is constructed by projecting the prescribed MCID onto the plane of the element.

Orientation when Theta (real value) is entered in 8th field

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Orientation when MC ID (integer value) is entered in 8th field

7.

If any of the Ti fields are blank, the thickness specified on the PSHELL data will be used for that node’s thickness. If 0.0 is specified for Ti, then the thickness at that node is zero.

8.

If the property referenced by PID is selected as a region for free-size or size optimization, then any Ti values defined here are ignored. If you input Ti for elements in the design space for Topology or Free-Size optimization, the run will error out.

9.

If Ti is present, the PID cannot reference PCOMP or PCOMPP data.

10. The shell reference plane can be offset from the plane defined by element nodes by means of ZOFFS. In this case all other information, such as material matrices or fiber locations for the calculation of stresses, is given relative to the offset reference plane. Similarly, shell results, such as shell element forces, are output on the offset reference plane. ZOFFS can be input in two different formats: 1. Real: A positive or a negative value of ZOFFS is specified in this format. A positive value of ZOFFS implies that the reference plane of each shell element is offset a distance of ZOFFS along the positive z-axis of its element coordinate system. 2. Surface: This format allows you to select either “Top” or “Bottom” option to specify the offset value. Top: The top surface of the shell element and the plane defined by the element nodes are coincident. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL property entry referenced by this element. (The sign of the ZOFFS value would depend on the direction of the offset relative to the positive z-axis of the element coordinate

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system, as defined in the Real section). See Figure 1.

Figure 1: Top option in ZOFFS

Bottom: The bottom surface of the shell element and the plane defined by the element nodes are coincident. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL property entry referenced by this element. (The sign of the ZOFFS value would depend on the direction of the offset relative to the positive z-axis of the element coordinate system, as defined in the Real section). See Figure 2.

Figure 2: Bottom option in ZOFFS

Note that when ZOFFS is used, both MID1 and MID2 must be specified on the PSHELL entry referenced by this element (otherwise, singular matrices would result). Offset is applied to all element matrices (stiffness, mass, and geometric stiffness), and to respective element loads (such as gravity). Hence, ZOFFS can be used in all types of analysis and optimization. Note, however, that for first order shell elements (CQUAD4 and CTRIA3), the offset operation does not correct for secondary effects, such as change of shell area when offset is applied on curved surfaces. Hence, the value of ZOFFS should be kept within a reasonable percentage (10% - 15%) of the local radius of curvature. Automatic offset control is available in composite free-size and sizing optimization where the specified offset values are automatically updated based on thickness changes. Moreover, while offset is correctly applied in geometric stiffness matrix and hence can be used in linear buckling analysis, caution is advised in interpreting the results. Without offset, a typical simple structure will bifurcate and loose stability “instantly” at the critical

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load. With offset, though, the loss of stability is gradual and asymptotically reaches a limit load, as shown below in figure (b):

Hence, the structure with offset can reach excessive deformation before the limit load is reached. Note that the above illustrations apply to linear buckling – in a fully nonlinear limit load simulation, additional instability points may be present on the load path. 11. PHFSHL properties are only valid with an @HYPERFORM statement in the first line of the input file. 12. This card is represented as a quad4 element in HyperMesh.

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CQUAD8 Bulk Data Entry CQUAD8 – Curved Quadrilateral Shell Element Connection Description Defines a curved quadrilateral shell element with eight grid points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C QUAD8

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

T1

T2

T3

T4

Theta or MC ID

ZOFFS

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C QUAD8

111

203

20

21

50

51

26

94

95

23

0.125

0.025

0.030

.025

30.

.03

Field

Contents

EID

Unique element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PSHELL, PCOMP or PCOMPP property entry. Default = EID (Integer > 0)

G1,G2,G3,G4

Grid point identification numbers of connected corner points. Required data for all four grid points. No default (Integers > 0, all unique)

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Field

Contents

G5,G6,G7,G8

Grid point identification numbers of connected edge points. Cannot be omitted. No default (Integer > 0 or blank)

Ti

Thickness of the element at the corner grid points G1 through G4. The thickness of the element with Ti specified will be constant and equal to an average of T1, T2, T3 and T4. For defaults: see comment 5. (Real > 0.0 or blank)

THETA

Material orientation angle in degrees. See comment 4. Default = 0,0 (Real)

MCID

Material coordinate system identification number. The x-axis of this coordinate system is projected onto the element to define the x-axis of the material coordinate system. If MCID = 0, it specifies the basic coordinate system. If blank, Theta = 0.0 is used, (See comments 3 and 4). Default is THETA = 0.0 (Integer > 0)

ZOFFS

Offset from the surface of grid points to the element reference plane. See comment 7. Overrides the ZOFFS specified on the PSHELL entry. Default = 0.0 (Real or blank)

Comments 1.

Element identification numbers should be unique with respect to all other element IDs.

2.

Grid points G1 through G8 must be numbered as shown here:

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3.

The element coordinate system is a Cartesian system defined locally for each point ( ,

It is based on the following rules: - The plane containing and -

and

is tangent to the surface of the element.

are obtained by doubly bisecting the lines of constant

increases in the general direction of increasing

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).

and

of

and

.

.

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4.

The orientation of the material coordinate system is defined locally at each interior integration point by THETA, which is the angle from the line of constant (essentially the same as the -axis) to the material x-direction (Xmaterial). If MCID is used in place of THETA, then the local material x-direction (Xmaterial) is obtained at any point in the element by projection of the x-axis of the prescribed MCID coordinate system onto the surface of the element at this point. The local z-direction is aligned with the normal to the surface and the material y-direction (Y material) is constructed accordingly to produce right-handed local material system X-Y-Zmaterial.

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Note that since changes directions throughout the element based on element shape, the material coordinate system varies similarly. Because of this, an orthotropic or anisotropic material will cause the CQUAD8's stiffness to be biased by both its shape and grid ordering. Use the CQUAD4 element if a constant material coordinate system direction is desired with orthotropic and anisotropic materials. 5.

T1, T2, T3, and T4 are optional. If they are not supplied, then the element thickness will be set equal to the value of T on the PSHELL entry. If 0.0 is specified for Ti, then the thickness at that node is zero. If Ti’s are supplied, PID cannot reference PCOMP or PCOMPP data. If the property referenced by PID is selected as a region for Size optimization, then any Ti values defined here are ignored. If you input Ti for elements in the design space for Topology or Free-Size optimization, the run will error out.

6.

It is required that the midside grid points be located within the middle third of the edge; that is the interval (0.25, 0.75) excluding the quarter points 0.25 and 0.75. If the edge point is located at the quarter point, the program may fail with an error or the calculated stresses will be meaningless.

7.

The shell reference plane can be offset from the plane defined by element nodes by means of ZOFFS. In this case all other information, such as material matrices or fiber locations for the calculation of stresses, is given relative to the offset reference plane. Similarly, shell results, such as shell element forces, are output on the offset reference plane. ZOFFS can be input in two different formats: 1. Real: A positive or a negative value of ZOFFS is specified in this format. A positive value of ZOFFS implies that the reference plane of each shell element is offset a distance of ZOFFS along the positive z-axis of its element coordinate system.

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2. Surface: This format allows you to select either “Top” or “Bottom” option to specify the offset value. Top: The top surface of the shell element and the plane defined by the element nodes are coincident. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL property entry referenced by this element. (The sign of the ZOFFS value would depend on the direction of the offset relative to the positive z-axis of the element coordinate system, as defined in the Real section). See Figure 1.

Figure 1: Top option in ZOFFS

Bottom: The bottom surface of the shell element and the plane defined by the element nodes are coincident. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL property entry referenced by this element. (The sign of the ZOFFS value would depend on the direction of the offset relative to the positive z-axis of the element coordinate system, as defined in the Real section). See Figure 2.

Figure 2: Bottom option in ZOFFS

Note that when ZOFFS is used, both MID1 and MID2 must be specified on the PSHELL entry referenced by this element (otherwise, singular matrices would result).

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Offset is applied to all element matrices (stiffness, mass and geometric stiffness) and to respective element loads (such as gravity). Hence, ZOFFS can be used in all types of analysis and optimization in OptiStruct. Automatic offset control is available in composite free-size and sizing optimization where the specified offset values are automatically updated based on thickness changes. However, while offset is correctly applied in geometric stiffness matrix and hence can be used in linear buckling analysis, caution is advised in interpreting the results. Without offset, a typical simple structure will bifurcate and loose stability “instantly” at the critical load. With offset, though, the loss of stability is gradual and asymptotically reaches a limit load, as shown below in figure (b):

Hence, the structure with offset can reach excessive deformation before the limit load is reached. Note that the above illustrations apply to linear buckling – in a fully nonlinear limit load simulation, additional instability points may be present on the load path. 8.

Stresses and strains are output in the local coordinate system identified by above.

and

9.

Size optimization of the property referenced by PID is not possible if Ti values are defined here. If the property referenced by PID is selected as a region for free-size optimization, then any Ti values defined here are ignored.

10. These 2nd order shell elements do not have normal rotational degrees-of-freedom (often referred to as "drilling stiffness"). No mass is associated with these degrees-of-freedom. If unconstrained, massless mechanisms may occur. It is therefore advisable to use PARAM,AUTOSPC,YES when working with these elements. 11. This card is represented as a quad8 element in HyperMesh.

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CQUADR Bulk Data Entry CQUADR – Quadrilateral Element Connection Description CQUADR entry is equivalent to CQUAD4. Unlike other Nastran codes, a 6 degree-of-freedom per node formulation is used for all shell elements. Refer to the documentation for the CQUAD4 Bulk Data Entry.

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CROD Bulk Data Entry CROD – Rod Element Connection Description Defines a tension-compression-torsion element (ROD) of the structural model. Format (1)

(2)

(3)

(4)

(5)

C ROD

EID

PID

G1

G2

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C ROD

12

13

21

23

(6)

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

(Integer > 0) PID

Identification number of a PROD property entry. (Integer > 0; If blank defaults to EID)

G1,G2

Grid point identification numbers of connection points.

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

Only one ROD element may be defined on a single entry.

3.

This card is represented as a rod element in HyperMesh.

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CSEAM Bulk Data Entry CSEAM – Seam Weld Element Connection Description Define a seam weld connecting two shell surfaces. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C SEAM

EID

PID

SMLN

C TYPE

IDAS

IDBS

IDAE

IDBE

GS

GE

Examples

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C SEAM

22

3

SEAM1

PSHELL

1

2

7

8

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

C SEAM

22

3

ELEM

11

12

21

22

7

8

Alternate Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C SEAM

EID

PID

SMLN

C TYPE

IDAS

IDBS

IDAE

IDBE

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(10)

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XS

YS

ZS

XE

YE

ZE

Alternate Format Examples

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C SEAM

22

3

SEAM1

PSHELL

1

2

0.3

0.4

0.25

0.6

0.4

0.25

(1)

(2)

(3)

(4)

(5)

(6)

C SEAM

22

3

ELEM

0.3

0.4

0.6

0.25

Field

Contents

EID

Unique element identification number.

(8)

(9)

(10)

(7)

(8)

(9)

(10)

11

12

21

22

0.4

0.25

No default (Integer > 0) PID

Identification number of a PSEAM entry. No default (Integer > 0)

SMLN

Identification of a seam line (See comment 2). No default (Maximum eight characters)

CTYPE

Character string indicating how the connection is defined. Either format connects up to 3 x 3 quadrilateral shell elements per patch (possibly more for triangular elements). For PSHELL type, the connection of surface patch to surface patch is defined by specifying the property identification numbers. For ELEM type, the connection of surface patch to surface patch is defined by specifying element identification numbers.

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Field

Contents

IDAS, IDBS

Used to define the two connecting patches or the start parts of patch A and patch B. If CTYPE="PSHELL", then IDAS and IDBS refer to the property identification numbers of patch A and patch B. If CTYPE="ELEM", then IDAS and IDBS refer to the element identification numbers of patch A and B.

IDAE, IDBE

Used to define the end parts of patch A and patch B. If CTYPE="PSHELL", IDAE and IDBE could be zero. If they are not zero, then IDAE and IDBE refer to the property identification numbers of the end parts of patch A and patch B. They could be used to define a tailored blank model. If CTYPE="ELEM", IDAS and IDBS refer to the element identification numbers of the end parts of patch A and B. For PSHELL type, Integer >

GS

Identification number of a grid point which defines the start location of the connector. No default (Integer > 0)

GE

Identification number of a grid point which defines the end location of the connector. No default (Integer > 0)

XS, YS, ZS

Coordinates of point that defines the start location (GS) of the seam weld in the basic coordinate system. (Real)

XE, YE, ZE

Coordinates of point that defines the end location (GE) of the seam weld in the basic coordinate system. (Real)

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Comments 1.

CSEAM defines a flexible connection between two surface patches. With all of the information provided, a fictitious 8-node CHEXA will be generated internally for a CSEAM, and the eight corner nodes are all constrained by the grids of corresponding shell elements. Then the element stiffness of this fictitious CHEXA will be transferred to the corresponding shell grids. The CSEAM element itself does not hold any independent DOF. See the figure below:

A CSEAM element connects Shell A and Shell B. A fictitious hexa is generated for the CSEAM, and the corner nodes of the hexa are all constrained by corresponding shell grids. To have a clear view, only one of this kind of constraint relationship is shown with dotted lines. 2.

In the SMLN entry, a name can be given for the CSEAM element. If one CSEAM's GS or GE is common to the GS or GE of the other CSEAM and they have the same SMLN, the two CSEAM elements are regarded as neighbors. For two neighboring CSEAM elements, the faces of the internally generated CHEXAs will be adjusted to form a single common face. A seam line does not have a branch with the same SMLN,

3.

The distance between GS and GE is the length of the element. The width of the seam weld is defined in the PSEAM card as W. It is measured perpendicular to the length and lies in the plane of Shell A or B.

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4.

Building the connectivity for CSEAM. Since the geometry for finding the correct projection could be various and complicated, many geometry related checks will be implemented in the following procedure. The default projection algorithm and checking rules can be modified to some extent via changing the default value defined in the SWLDPRM card. To build the connectivity, at first, project GS on Shell A and B; the projection points are denoted as SA and SB respectively. This is also true for GE, and the projection points are denoted as EA and EB. SA, SB, EA and EB are also called piercing points. Meanwhile, the shell elements supporting these piercing points are denoted as EIDSA, EIDSB, EIDEA and EIDEB. Take SA as an example. For ELEM type, the program will try to project GS on the user specified element; if the piercing point falls inside the element, the program will accept it and move to find the next piercing point. If the piercing point falls outside the element but within the tolerance defined by PROJTOL in the SWLDPRM card, the program will still accept it. Otherwise, an error will be issued for this CSEAM element, and the program continues to process other CSEAM elements. For PSHELL type, the case could be much more complicated. First, a bunch of shell elements which are the closest ones to GS and have the user-specified shell property will be selected as candidates. Then project GS on each of the candidates. If the piercing point falls inside one of the candidates, the program will accept it and move to find the next one. After looping all the candidates, if there is no appropriate one to support the piercing point, the tolerance defined by PROJTOL will be used and all candidates will be searched again. At last, if still no element is found to support the piercing point, an error will be issued for this CSEAM, and the program continues to process other CSEAM elements. In this way, all the four piercing points and elements supporting them are found, or an error is issued. If GMCHK > 0 (be defined in the SWLDPRM card), various geometry checks will be implemented at specific steps. If GMCHK > 0 and GSPROJ > 0.0 (be defined in the SWLDPRM card), the program will check the angle between the normal vectors of EIDSA and EIDSB, and the angle between the normal vectors of EIDEA and EIDEB. If the angle is larger than GSPROJ, an error will be issued for this CSEAM. If GSTOL > 0.0 (be defined in the SWLDPRM card) and one of the lengths of GS-SA, GS-SB, GE-EA and GE-EB is larger than GSTOL, an error will be issued. Besides these basic checks, a group of cutout and span checks will be performed if GMCHK>0. After the four piercing points are found, the auxiliary points will then need to be located with the definition of the seam width. Take SA as an example, with the coordinates of the piercing point, the supporting element EIDSA and the seam weld width W, you can define the following vector n × GS-GE where n is the normal vector of EIDSA. Through SA, two points SA1 ' and SA2 ' can be defined along this vector and |SA1 '-SA2 '| = W. SA1 ' and SA2 ' are called the preliminary auxiliary points. For a curved or folded shell patch, the preliminary points may not lie on the shell surface. Therefore, a second projection is needed to find the final auxiliary points. Take SA1 ' as an example. First, a group of candidate elements needs to be collected. They are composed of shell elements surrounding EIDSA. SA1 ' will be projected on each of the candidates to find the best one to support the projection point. If no element with the user specified shell property is found with/without tolerance, elements with different shell property will be supplemented to the candidate list. After projecting all the eight preliminary auxiliary points on the shell

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surfaces, the number of good auxiliary points will be counted. If all of the eight auxiliary points and corresponding shell elements are successfully located, the building of the connectivity for this CSEAM succeeds. Otherwise, GSMOVE defined in the SWLDPRM card will be implemented to avoid the failure if GSMOVE > 0. When collecting candidate shell elements which will be used to support the auxiliary points, the angle between the normal vector of the shell element and the thickness direction of the fictitious CHEXA will be checked. If the angle is larger than GSPORJ, this shell element will not be considered as a candidate. If EIDSA, EIDSB, EIDEA or EIDEB fails the check, a warning message will be issued. For curved or folded shell surface, shell elements on it have more chances to be eliminated from the candidate list, thus may possibly induce the failure of locating all auxiliary points. One remedy to this problem is to increase the value of GSPORJ to include more shell elements into the candidate list.

Various projection points generated in building the connectivity for a CSEAM element. 5.

When building the connectivity for CSEAM, if not all eight auxiliary points can be found and GSMOVE > 0, GS or/and GE will be moved by W/2 and re-projected to avoid the failure. This often happens near the mesh boundary.

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Both GS and GE are moved by W/2 to find correct projection. 6.

For PSHELL type CSEAM, when the GS or GE is close to a folded or curved part of a shell surface, the program has more chances to fail in locating the correct element to support the piercing points because of multiple possible choices. In this case, using ELEM type to directly specify the elements for projection would be a wise alternative.

7.

Check whether the CSEAM spans a cutout or spans more than three shell elements on each shell surface when GMCHK > 0. Take EIDSA and EIDEA as an example. If EIDSA = EIDEA, the seam lies on the same element on this surface. This case is accepted. EIDEA and they share at least one common grid, it is necessary to do some checks. (In the following check, an element called EIDMA is used to assist the check. EIDMA is located on the same shell surface where EIDSA and EIDEA are located. It shares one of the common grids shared by EIDSA and EIDEA. EIDMA could be multiple.) a)If EIDSA and EIDEA share only one common grid but no EIDMA is found, then this case is rejected.

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This case is rejected. b)If EIDSA and EIDEA share only one common grid and at least one EIDMA is found, the number of free edges will be counted. The following cases are considered.

If there are three or more free edges (bold lines), this case is rejected.

Angle check.

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Projection check. M is the middle point of the two free edges' ends.

If there are two free edges, the angle (α) between the free edges will be calculated. If the angle is larger than CNRAGLI (be defined in the SWLDPRM card), this case is accepted. If the angle is smaller than CNRAGLI, then you project the mid-point M to EIDSA, EIDEA and EIDMA, if the projection point falls inside, this case is still accepted. Or it will be rejected.

If there is only one free edge, this case is accepted.

If there is no free edge, this case is accepted.

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c)If EIDSA and EIDEA share two common grids, that means EIDSA and EIDEA share a common edge. Before accepting this case, it is still necessary to check the angle or project the middle point M.

Angle check.

Projection check. M is the middle point of the two free edges' ends.

Compare the angle (α) with CNRAGLO even EIDSA and EIDEA share an edge. If the angle is larger than CNRAGLI, this case is accepted. If the angle is smaller than CNRAGLI, then you project the mid-point M to EIDSA and EIDEA, if the projection point falls inside, this case is still accepted. Or it will be rejected. elements around them and check how these elements are connected with EIDSA and EIDEA. (In the following check, EIDMA is re-defined as an element which shares at least one grid respectively with EIDSA and EIDEA) a) If there is no EIDMA, this means the CSEAM element spans more than three elements in the current shell surface, and this case is rejected.

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This case is rejected. b) If there are three EIDMA which share edges with both EIDSA and EIDEA, this case is accepted.

This case is accepted. c) If there are two EIDMA which share edges with both EIDSA and EIDEA, it is necessary to check whether the two EIDMA share a common edge or not. If the two EIDMA do not share a common edge, there is a cutout and this case is rejected.

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If the two EIDMA do not share a common If the two EIDMA share a common edge, this edge, there is a cutout and this case is case is accepted. rejected. Two different cases when there are two EIDMA who share edges with both EIDSA and EIDEA. d) If there is only one EIDMA which shares edges with both EIDSA and EIDEA. The check presented in the following figure needs to be implemented.

Point M is the average of the two piercing points, that is SA and EA. If the projection from point M on EIDMA falls inside this element, this case is accepted, or it will be rejected. e) If there is only one EIDMA which shares one edge with EIDSA and shares a corner with EIDEA (or shares one corner with EIDSA and shares one edge with EIDEA), the same check implemented for the last case will be adopted.

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f) If the projection from point M on EIDMA falls inside this element, this case is accepted, or it will be rejected. g) If there are two EIDMA and each of them shares an edge with EIDSA or EIDEA and shares a corner with EIDEA or EIDSA, this case is accepted.

This case is accepted. h) If there is only EIDMA which shares only corners but no edge with EIDSA or EIDEA, this case is rejected.

These two cases are rejected. For the one on the right, although there is no cutout on the surface, but EIDMA is not fully constrained (only two corners are constrained) by the CSEAM. Therefore, this case is still rejected. For EIDSB and EIDEB, the same cutout/span check applies. All the cutout/span checks introduced here still cannot cover 100% cases, but they can spot most of the bad cases that will lead to unreal modeling of the seam weld. Thus, it is recommended to turn on the cutout/span check (GMCHK > 0) to exam the seam weld model in the first round. After all possible problems are resolved, then start the final run. 8.

662

Check whether the CSEAM spans a corner on each shell surface when GMCHK > 0.

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Take EIDSA and EIDEA as an example. The angle between the normal vectors of the two elements should not larger than the value of CNRAGLO (be defined in the SWLDPRM card) as shown in the following figure. The same check applies to EIDSB and EIDEB. This prevents generating single CSEAM element across a very curved shell configuration.

If α > CNRAGLO, this CSEAM element is rejected. 9.

Diagnostic print outs, checkout runs and non-default setting of search and projection parameters are requested on the SWLDPRM bulk data entry.

10. It is possible to visualize the fictitious CHEXA via setting SHOWAUX = 1 in the SWLDPRM card. To have the fictitious CHEXA and corresponding results output into the H3D file, one also needs to set SHOWAUX = 1. 11. It is recommended to start with default settings and turn on the full geometry check by setting GMCHK=1 or 2. With the full geometry check, most of the unexpected cases which may possibly induce unreasonable projections can be spotted. If the switch for outputting diagnostic info, that is PRTSW, is turned on, the connectivity detail of each CSEAM element will be printed in the .out file. Also, a summary of various geometry data will be printed after all CSEAM elements are gone through by the program. They will be very useful for debugging the seam weld model. 12. Seam weld elements are ignored in heat transfer analysis.

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CSEC2 Bulk Data Entry CSEC2 – 1D Section Element Description Defines a two-noded element used in the definition of arbitrary beam cross-sections. Format (1)

(2)

(3)

(4)

(5)

C SEC 2

EID

PID

G1

G2

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C SEC 2

71

4

3

4

Field

Contents

EID

Element identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PSEC section property entry. Default = EID (Integer > 0)

G#

Identification number of GRIDS section grid points. No default (Integer > 0)

Comments 1.

Element identification numbers within a section definition must be unique with respect to all other element identification numbers within the same section definition.

2.

This entry is only valid when it appears between the BEGIN and END statements.

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CSEC3 Bulk Data Entry CSEC3 – Triangular Section Element Description Defines a 1st order three-noded element used in the definition of arbitrary beam crosssections. Format (1)

(2)

(3)

(4)

(5)

(6)

C SEC 3

EID

PID

G1

G2

G3

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

C SEC 3

10

100

3

4

5

Field

Contents

EID

Element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PSEC section property entry. Default = EID (Integer > 0)

G#

Identification number of GRIDS section grid points. No default (Integer > 0)

Comments 1.

Element identification numbers within a section definition must be unique with respect to all other element identification numbers within the same section definition.

2.

This entry is only valid when it appears between the BEGIN and END statements.

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CSEC4 Bulk Data Entry CSEC4 – Quadrilateral Section Element Description Defines a 1st order four-noded element used in the definition of arbitrary beam cross-sections. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

C SEC 4

EID

PID

G1

G2

G3

G4

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C SEC 4

10

100

3

4

5

6

Field

Contents

EID

Element identification number.

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PSEC section property entry. Default = EID (Integer > 0)

G#

Identification number of GRIDS section grid points. No default (Integer > 0)

Comments 1.

Element identification numbers within a section definition must be unique with respect to all other element identification numbers within the same section definition.

2.

This entry is only valid when it appears between the BEGIN and END statements.

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CSEC6 Bulk Data Entry CSEC6 – Curved Triangular Section Element Description Defines a planar, 2nd order, six-noded element used in the definition of arbitrary beam crosssections. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C SEC 6

EID

PID

G1

G2

G3

G4

G5

G6

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C SEC 6

10

100

3

4

5

6

7

8

Field

Contents

EID

Element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PSEC section property entry. Default = EID (Integer > 0)

G#

Identification number of GRIDS section grid points. No default (Integer > 0)

Comments 1.

Element identification numbers within a section definition must be unique with respect to all other element identification numbers within the same section definition.

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2.

Grid points G1 through G6 must be numbered as shown here:

3.

This entry is only valid when it appears between the BEGIN and END statements.

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CSEC8 Bulk Data Entry CSEC8 – Curved Quadrilateral Section Element Description Defines a planar 2nd order eight-noded element used in the definition of arbitrary beam crosssections. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C SEC 8

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C SEC 8

10

100

3

4

5

6

13

14

15

16

Field

Contents

EID

Element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PSEC section property entry. Default = EID (Integer > 0)

G#

Identification number of GRIDS section grid points. No default (Integer > 0)

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Comments 1.

Element identification numbers within a section definition must be unique with respect to all other element identification numbers within the same section definition.

2.

Grid points G1 through G8 must be numbered as shown here:

3.

This entry is only valid when it appears between the BEGIN and END statements.

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CSET Bulk Data Entry CSET – Boundary Degrees-of-Freedom of a Superelement Assembly Description CSET entry is equivalent to BNDFREE. Refer to the documentation for the BNDFREE Bulk Data Entry.

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CSET1 Bulk Data Entry CSET1 – Boundary Degrees-of-Freedom of a Superelement Assembly Description CSET1 entry is equivalent to BNDFRE1. Refer to the documentation for the BNDFRE1 Bulk Data Entry.

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CSHEAR Bulk Data Entry CSHEAR – Shear Panel Element Connection Description Defines a shear panel element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

C SHEAR

EID

PID

G1

G2

G3

G4

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C SHEAR

111

67

89

123

124

56

Field

Contents

EID

Unique element identification number.

(8)

(9)

(10)

(Integer > 0) PID

Identification number of a PSHEAR property entry. (Integer > 0; If blank, defaults to EID)

G1, G2, G3, G4 Grid point identification numbers of connection points. (Integer > 0; all unique) Comments 1.

Element identification numbers should be unique with respect to all other element identification numbers.

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2.

Grid points G1 through G4 must be ordered consecutively around the perimeter of the element.

3.

All interior angles must be less than 180 degrees.

C SHEAR definition

C SHEAR Element C orner Forces and Shear Flows

4.

Shear panel elements are ignored in heat transfer analysis.

5.

This card is represented as a quad4 element in HyperMesh.

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CTAXI Bulk Data Entry CTAXI – Axisymmetric Triangular Element Connection Description Defines an axisymmetric triangular cross-section ring element for use in linear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C TAXI

EID

PID

G1

G2

G3

G4

G5

G6

(10)

Theta

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C TAXI

111

2

31

74

75

32

51

52

(10)

15.0

Field

Contents

EID

Unique element identification number. No default (Integer > 0)

PID

Identification number of a PAXI entry. Default = EID (Integer > 0)

G1,G3,G5

Identification numbers of connected corner grid points. Cannot be omitted. No default (Integers > 0, all unique)

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Field

Contents

G2,G4,G6

Identification numbers of connected edge grid points. Cannot be omitted. No default (Integers > 0, all unique)

Theta

Material orientation angle in degrees. Default = 0.0 (Real)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

All the grid points must be located in the x-z plane of the basic coordinate system with x = r > 0, and ordered consecutively starting at a corner grid point and proceeding around the perimeter in either direction. Corner grid points G1, G3 and G5 must be present. The edge points G2, G4 and G6 are optional. If any of the edge points are present, they all must be used.

C TAXI definition

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3.

The continuation is optional.

4.

If the PAXI entry referenced in field 3 references a MAT3 entry, material properties and stresses are always given in the (xm, zm) coordinate system shown in the figure above.

5.

A concentrated load (for example, the load specified on a FORCE entry) at a grid Gi of this element denotes that applied onto the circumference with radius of Gi. For example, in order to apply a load of 200N/m on the circumference at Gi which is located at a radius of 0.4m, the magnitude of the load specified on the static load entry must be: (200 N/m) * 2

* (0.4m) = 502.655N

6.

CTAXI and CTRIAX6 elements cannot be used simultaneously in an input model.

7.

This card is represented as an element in HyperMesh.

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CTETRA Bulk Data Entry CTETRA – Four-sided Solid Element with four or ten grid points Description Defines the connections of the CTETRA element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C TETRA

EID

PID

G1

G2

G3

G4

G5

G6

G7

G8

G9

G10

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

C TETRA

112

2

3

15

14

4

Field

Contents

EID

Unique element identification number.

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PSOLID property entry. Default = EID (Integer > 0)

G#

Identification numbers of connected grid points. Default = blank (Integer > 0)

Comments 1.

678

Element ID numbers must be unique with respect to all other element ID numbers.

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2.

The grid points G1, G2, G3, and G4 must describe the vertices and the remaining grid points describe mid side nodes in the order shown here: The edge points G5 to G10 are optional. All or none of the edge points can be specified. It is recommended that the edge points be located within the middle third of the edge.

C TETRA definition

3.

If the user-prescribed node numbering on the bottom face is reversed as compared to the sequence shown above, then the nodes are renumbered to produce right-handed orientation of numbering. This is accomplished by swapping node G2 with G3. For 10noded CTETRA, appropriate changes to mid-side node numbering are also performed. In such cases, the element coordinate system will be built on the renumbered node sequence.

4.

Stresses are output in the material coordinate system. The material coordinate system is defined on the referenced PSOLID entry. It may be defined as the basic coordinate system (CORDM = 0), a defined system (CORDM = Integer > 0), or the element coordinate system (CORDM = -1).

5.

The element coordinate system for the CTETRA element is defined as follows: Three intermediate vectors R, S, and T are chosen by the following rules: R

Joins the midpoints of the edges from G1 to G2 and G3 to G4.

S

Joins the midpoints of the edges from G1 to G3 and G2 to G4.

T

Joins the midpoints of the edges from G1 to G4 and G2 to G3

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C TETRA element coordinate system

The origin of the element coordinate system is located at G1. The element z-axis corresponds to the T vector. The element y-axis is the cross product of the T and R vectors. The element x-axis is the cross product of the element y-axis and the element z-axis. 6.

680

This card is represented as a tetra4 or tetra10 element in HyperMesh.

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CTRIA3 Bulk Data Entry CTRIA3 – Triangular Element Connection Description Defines a triangular plate element (TRIA3) of the structural model. This element uses a 6 degree-of-freedom per node formulation. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C TRIA3

EID

PID

G1

G2

G3

Theta or MC ID

ZOFFS

T1

T2

T3

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

C TRIA3

111

203

31

74

75

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PSHELL, PCOMP, PCOMPP or PHFSHL property entry. Default = EID (Integer > 0)

G1,G2,G3

Grid point identification numbers of connection points. No default (Integers > 0, all unique)

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Field

Contents

Theta

Material orientation angle in degrees. Default = 0.0 (Real)

MCID

Material coordinate system identification number. The x-axis of this coordinate system is projected onto the element to define the x-axis of the material coordinate system. If MCID = 0, it specifies the basic coordinate system. MCID must be an integer > 0. If blank, Theta = 0.0 is used (See comments 2, 3, and 4). Default is Theta = 0.0 (Integer > 0)

ZOFFS

Offset from the plane defined by element grid points to the shell reference plane. See comment 8. Overrides the ZOFFS specified on the PSHELL entry. Default = 0.0 (Real or blank)

Ti

Thickness of the element at the grid points. Overrides the thickness specified on the PSHELL entry. If Ti is specified, the average of all three thicknesses is used as the element thickness. For defaults: see comments 5 and 7. (Real > 0.0 or blank)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

The x-axis of the element coordinate system is aligned with side 1-2 of the shell element.

3.

For H3D and OUTPUT2 output formats, stresses and strains are always output in the elemental system.

4.

For HM, PUNCH, and OPTI output formats, stresses and strains are output by default in the material coordinate system. PARAM,OMID can be set to NO to output results in the elemental system. For elements with blank Theta/MCID, the material coordinate system is aligned with elemental coordinate system. For elements with prescribed THETA, the material x-axis is rotated from side G1-G2 by angle THETA. For elements with prescribed MCID, the material system is constructed by projecting the prescribed MCID onto the plane of the element.

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Orientation when Theta (real value) is entered in 8th field

Orientation when MC ID (integer value) is entered in 8th field

5.

If any of the Ti fields are blank, the thickness specified on the PSHELL data will be used for that node’s thickness. If 0.0 is specified for Ti, then the thickness at that node is zero.

6.

If the property referenced by PID is selected as a region for free-size or size optimization, then any Ti values defined here are ignored. If you input Ti for elements in the design space for Topology or Free-Size optimization, the run will error out.

7.

If Ti is present, the PID cannot reference PCOMP or PCOMPP data.

8.

The shell reference plane can be offset from the plane defined by element nodes by means of ZOFFS. In this case all other information, such as material matrices or fiber locations for the calculation of stresses, is given relative to the offset reference plane. Similarly, shell results, such as shell element forces, are output on the offset reference plane. ZOFFS can be input in two different formats: 1. Real: A positive or a negative value of ZOFFS is specified in this format. A positive value of ZOFFS implies that the reference plane of each shell element is offset a distance of ZOFFS along the positive z-axis of its element coordinate system.

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2. Surface: This format allows you to select either “Top” or “Bottom” option to specify the offset value. Top: The top surface of the shell element and the plane defined by the element nodes are coincident. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL property entry referenced by this element. (The sign of the ZOFFS value would depend on the direction of the offset relative to the positive z-axis of the element coordinate system, as defined in the Real section). See Figure 1.

Figure 1: Top option in ZOFFS

Bottom: The bottom surface of the shell element and the plane defined by the element nodes are coincident. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL property entry referenced by this element. (The sign of the ZOFFS value would depend on the direction of the offset relative to the positive z-axis of the element coordinate system, as defined in the Real section). See Figure 2.

Figure 2: Bottom option in ZOFFS

Note that when ZOFFS is used, both MID1 and MID2 must be specified on the PSHELL entry referenced by this element (otherwise, singular matrices would result).

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Offset is applied to all element matrices (stiffness, mass, and geometric stiffness), and to respective element loads (such as gravity). Hence, ZOFFS can be used in all types of analysis and optimization. Note, however, that for first order shell elements (CQUAD4 and CTRIA3), the offset operation does not correct for secondary effects, such as change of shell area when offset is applied on curved surfaces. Hence, the value of ZOFFS should be kept within a reasonable percentage (10% - 15%) of the local radius of curvature. Automatic offset control is available in composite free-size and sizing optimization where the specified offset values are automatically updated based on thickness changes. Moreover, while offset is correctly applied in geometric stiffness matrix and hence can be used in linear buckling analysis, caution is advised in interpreting the results. Without offset, a typical simple structure will bifurcate and loose stability “instantly” at the critical load. With offset, though, the loss of stability is gradual and asymptotically reaches a limit load, as shown below in figure (b):

Hence, the structure with offset can reach excessive deformation before the limit load is reached. Note that the above illustrations apply to linear buckling – in a fully nonlinear limit load simulation, additional instability points may be present on the load path. 9.

PHFSHL properties are only valid with an @HYPERFORM statement in the first line of the input file.

10. This card is represented as a tria3 element in HyperMesh.

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CTRIA6 Bulk Data Entry CTRIA6 – Curved Triangular Shell Element Connection Description Defines a curved triangular shell element with six grid points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C TRIA6

EID

PID

G1

G2

G3

G4

G5

G6

THETA or MC ID

ZOFFS

T1

T2

T3

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C TRIA6

302

3

31

33

71

32

51

52

45

.03

.020

.025

.025

Field

Contents

EID

Unique element identification number.

(10)

No default (Integer > 0) PID

Identification number of a PSHELL, PCOMP or PCOMPP entry. Default = EID (Integer > 0)

G1,G2,G3

Grid point identification numbers of connected corner points. No default (Integers > 0, all unique)

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Field

Contents

G4,G5,G6

Grid point identification number of connected edge points. Cannot be omitted. No default (Integer > 0 or blank)

THETA

Material orientation angle in degrees. Default = 0.0 (Real)

MCID

Material coordinate system identification number. The x-axis of this material coordinate system is determined by projecting the x-axis of the MCID coordinate system (defined by the CORDij entry or zero for the basic coordinate system) onto the surface of the element. Default is THETA = 0.0 (Integer > 0)

ZOFFS

Offset from the surface of grid points to the element reference plane; see Comment 7. Overrides the ZOFFS specified on the PSHELL entry. Default = 0.0 (Real or blank)

Ti

Membrane thickness of element at grid points G1 through G3. The thickness of the element with Ti specified will be constant and equal to an average of T1, T2, and T3. For defaults: see comment 5. (Real > 0.0 or blank)

Comments 1.

Element identification numbers should be unique with respect to all other element IDs.

2.

Grid points G1 through G6 must be numbered as shown here:

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3.

The element coordinate system is a Cartesian system defined locally for each point ( , ).

It is based on the following rules: -

The plane containing

and

is tangent to the surface of the element.

-

is tangent to the line of constant

-

increases in the general direction of increasing

688

. and

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

of

.

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4.

The orientation of the material coordinate system is defined locally at each interior integration point by THETA, which is the angle from the line of constant (essentially the same as the -axis) to the material x-direction (Xmaterial). If MCID is used in place of THETA, then the local material x-direction (Xmaterial) is obtained at any point in the element by projection of the x-axis of the prescribed MCID coordinate system onto the surface of the element at this point. The local z-direction is aligned with the normal to the surface and the material y-direction (Y material) is constructed accordingly to produce right-handed local material system X-Y-Zmaterial.

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5.

T1, T2, and T3 are optional. If they are not supplied, then the element thickness will be set equal to the value of T on the PSHELL entry. If 0.0 is specified for Ti, then the thickness at that node is zero. If Ti is supplied, PID cannot reference PCOMP or PCOMPP data. If the property referenced by PID is selected as a region for Size optimization, then any Ti values defined here are ignored. If you input Ti for elements in the design space for Topology or Free-Size optimization, the run will error out.

6.

It is required that the midside grid points be located within the middle third of the edge. That is the interval (0.25, 0.75) excluding the quarter points 0.25 and 0.75. If the edge point is located at the quarter point, the program may fail with an error or the calculated stresses will be meaningless.

7.

The shell reference plane can be offset from the plane defined by element nodes by means of ZOFFS. In this case all other information, such as material matrices or fiber locations for the calculation of stresses, is given relative to the offset reference plane. Similarly, shell results, such as shell element forces, are output on the offset reference plane. ZOFFS can be input in two different formats: 1. Real: A positive or a negative value of ZOFFS is specified in this format. A positive value of ZOFFS implies that the reference plane of each shell element is offset a distance of ZOFFS along the positive z-axis of its element coordinate system. 2. Surface: This format allows you to select either “Top” or “Bottom” option to specify the offset value.

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Top: The top surface of the shell element and the plane defined by the element nodes are coincident. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL property entry referenced by this element. (The sign of the ZOFFS value would depend on the direction of the offset relative to the positive z-axis of the element coordinate system, as defined in the Real section). See Figure 1.

Figure 1: Top option in ZOFFS

Bottom: The bottom surface of the shell element and the plane defined by the element nodes are coincident. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL property entry referenced by this element. (The sign of the ZOFFS value would depend on the direction of the offset relative to the positive z-axis of the element coordinate system, as defined in the Real section). See Figure 2.

Figure 2: Bottom option in ZOFFS

Note that when ZOFFS is used, both MID1 and MID2 must be specified on the PSHELL entry referenced by this element (otherwise, singular matrices would result). Offset is applied to all element matrices (stiffness, mass and geometric stiffness) and to respective element loads (such as gravity). Hence, ZOFFS can be used in all types of analysis and optimization. Automatic offset control is available in composite free-size and sizing optimization where the specified offset values are automatically updated based on thickness changes.

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However, while offset is correctly applied in geometric stiffness matrix and hence can be used in linear buckling analysis, caution is advised in interpreting the results. Without offset, a typical simple structure will bifurcate and loose stability “instantly” at the critical load. With offset, though, the loss of stability is gradual and asymptotically reaches a limit load, as shown below in figure (b):

Hence, the structure with offset can reach excessive deformation before the limit load is reached. Note that the above illustrations apply to linear buckling – in a fully nonlinear limit load simulation, additional instability points may be present on the load path. 8.

Stresses and strains are output in the local coordinate system identified by above.

and

9.

Size optimization of the property referenced by PID is not possible if Ti values are defined here. If the property referenced by PID is selected as a region for free-size optimization, then any Ti values defined here are ignored.

10. These 2nd order shell elements do not have normal rotational degrees-of-freedom (often referred to as "drilling stiffness"). No mass is associated with these degrees-of-freedom. If unconstrained, massless mechanisms may occur. It is therefore advisable to use PARAM,AUTOSPC,YES when working with these elements. 11. This card is represented as a tria6 element in HyperMesh.

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CTRIAR Bulk Data Entry CTRIAR – Triangular Element Connection Description CTRIAR entry is equivalent to CTRIA3. Unlike other Nastran codes, a 6 degrees-of-freedom per node formulation is used for all shell elements. Refer to the documentation for the CTRIA3 Bulk Data Entry.

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CTRIAX6 Bulk Data Entry CTRIAX6 – Axisymmetric Triangular Element Connection Description Defines an axisymmetric triangular cross-section ring element for use in linear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C TRIAX6

EID

MID

G1

G2

G3

G4

G5

G6

(10)

Theta

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C TRIAX6

111

203

31

74

75

32

51

52

(10)

15.0

Field

Contents

EID

Unique element identification number. No default (Integer > 0)

MID

Identification number of a MAT1 or MAT3 entry. No default (Integer > 0)

G1,G3,G5

Identification numbers of connected corner grid points. Cannot be omitted. No default (Integers > 0, all unique)

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Field

Contents

G2,G4,G6

Identification numbers of connected edge grid points. Cannot be omitted. No default (Integers > 0, all unique)

Theta

Material orientation angle in degrees. Default = 0.0 (Real or blank)

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

All the grid points must be located in the x-z plane of the basic coordinate system with x = r > 0, and ordered consecutively starting at a corner grid point and proceeding around the perimeter in either direction. Corner grid points G1, G3 and G5 must be present. The edge points G2, G4 and G6 are optional. If any of the edge points are present, they all must be used.

C TRIAX6 definition

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3.

The continuation is optional.

4.

If MID is defined on a MAT3 entry, material properties and stresses are always given in the (xm, zm) coordinate system shown in the figure above.

5.

A concentrated load (for example, the load specified on a FORCE entry) at a grid Gi of this element denotes that applied onto the circumference with radius of Gi. For example, in order to apply a load of 200N/m on the circumference at Gi which is located at a radius of 0.4m, the magnitude of the load specified on the static load entry must be: (200 N/m) * 2

* (0.4m) = 502.655N

6.

CTRIAX6 and CTAXI elements cannot be used simultaneously in an input model.

7.

This card is represented as an element in HyperMesh.

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CTUBE Bulk Data Entry CTUBE – Tube Element Connection Description Defines a tension-compression-torsion element (TUBE) of the structural model. Format (1)

(2)

(3)

(4)

(5)

C TUBE

EID

PID

G1

G2

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C TUBE

12

13

21

23

Field

Contents

EID

Element identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) PID

Identification number of a PTUBE property entry. (Default = EID, Integer > 0)

G1,G2

Grid point identification numbers of connection points.

Comments 1.

Element identification numbers must be unique with respect to all other element identification numbers.

2.

Only one TUBE element may be defined on a single entry.

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3.

CTUBE data is converted to CROD data as it is read. PTUBE data is converted into PROD data.

4.

This card is represented as a rod element in HyperMesh.

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CVISC Bulk Data Entry CVISC – Viscous Damper Connection Description Defines a viscous damper element. Format (1)

(2)

(3)

(4)

(5)

C VISC

EID

PID

G1

G2

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

C VISC

2

64

12

63

(6)

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) PID

Identification number of a PVISC entry. Default = EID (Integer > 0)

G1, G2

Geometric grid point identification numbers of connection points. No default (Integer > 0)

Comments 1. 2.

Element identification numbers must be unique with respect to all other element identification numbers.

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3.

Only one viscous damper element may be defined on a single entry.

4.

Viscous damper elements are ignored in heat transfer analysis.

5.

This card is represented as a spring element in HyperMesh.

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CWELD Bulk Data Entry CWELD – Weld or Fastener Element Connection Description Defines a weld or fastener connecting two surface patches or points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C WELD

EWID

PWID

GS

TYP

GA

GB

SPTYP

GA1/SHIDA

GA2/ SHIDB

GA3

GA4

GA5

GA6

GA7

GA8

GB1

GB2

GB3

GB4

GB5

GB6

GB7

GB8

(7)

(8)

(10)

Example 1

(1)

(2)

(3)

(4)

(5)

C WELD

7

34

233

GRIDID

55

56

21

22

101

102

378

(1)

(2)

(3)

(4)

(5)

C WELD

7

34

233

ELEMID

15

16

(6)

(9)

(10)

(9)

(10)

QT

Example 2

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(6)

(7)

(8)

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Example 3

(1)

(2)

(3)

C WELD

7

34

(4)

(5)

(6)

(7)

ALIGN

103

259

(8)

(9)

(10)

Alternate Formats of CWELD Card – PARTPAT/ELPAT The alternative formats of CWELD listed below are useful in cases when the weld diameter extends beyond a single shell element. These options connect up to 3x3 shell elements per patch (possibly more for triangular elements) on each side of weld element. Format (Alternate) (1)

(2)

(3)

(4)

(5)

(6)

(7)

C WELD

EWID

PWID

GS

PATC HTYP

GA

GB

PIDA/ SHIDA

PIDB/ SHIDB

XS

YS

(8)

(9)

(10)

ZS

Example 1 (Alternate)

(1)

(2)

(3)

C WELD

10

20

33

34

5.0

5.0

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PARTPAT

0.0

Example 2 (Alternate)

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(1)

(2)

(3)

(4)

(5)

C WELD

10

20

345

ELPAT

1034

2035

(6)

Field

Contents

EWID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) PWID

Identification number of a PWELD entry. Default = EWID (Integer > 0)

GS

Identification number of a grid point which defines the location of the connector. Required when TYP is GRIDID or ELEMID and GA and GB are unspecified (See comments 2 and 4). No default (Integer > 0)

TYP

Character string indicating how the connection is defined. GRIDID indicates that the connection is defined with grid identification numbers GA# and GB#, respectively (See comment 3). ELEMID indicates that the connection is defined with shell element identification numbers SHIDA and SHIDB (See comment 7). ALIGN indicates that the connection is defined between two shell vertex grid points (See comment 8). No default (GRIDID, ELEMID or ALIGN)

GA, GB

When TYP is GRIDID or ELEMID, these represent grid identification numbers of piercing points on surface A and surface B respectively (See comment 4). When TYPE is ALIGN, these represent vertex grid identification numbers of the first and second shells respectively. No default (Integer > 0)

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Field

Contents

SPTYP

String indicating types of surface patches A and B. Q indicates quadrilateral surface patch, and T indicates triangular surface patch. Required when TYP is GRIDID (See comment 5). No default (QQ, TT, QT, TQ, Q or T)

GA#

Grid identification numbers of the first surface patch. GA1 to GA3 are required (See comment 6). No default (Integer > 0)

GB#

Grid identification numbers of the second surface patch (See comment 6).

PATCHTYP

The type of connection between the patches. Either format connects up to 3x3 elements per patch (possibly more for triangular elements). See comment 12. For PARTPAT, the connection of surface patch to surface patch is defined by specifying the property numbers of shells on side A and B, PIDA and PIDB, respectively. For ELPAT, the connection of surface patch to surface patch is defined by specifying IDs of shells SHIDA and SHIDB, respectively.

PIDA,PIDB

Property identification numbers of PSHELL entries defining surface A and B, respectively. Required for PARTPAT.

SHIDA, SHIDB

Element identification numbers of shells defining weld ends A and B, respectively. Required for ELPAT.

XS, YS, ZS

Coordinates of point that defines the location of the weld in the basic coordinate system. It is an alternate way of specifying the location of GS. Available with PARTPAT/ELPAT options only. Real

Comments 1.

704

CWELD defines a flexible connection between two surface patches, between a point and a surface patch, or between two shell vertex grid points. See figure below:

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C onnection between two surface patches

C onnection between a point and a surface patch

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705

C onnection between two shell vertex grid points

2.

GS is ignored if TYP is ALIGN.

3.

If TYP is GRIDID, either a point to patch (GS to GA#) or a patch to patch (GA# to GB#) connection is defined. For the patch to patch connection, GA# describes the first surface patch and GB# describes the second surface patch.

4.

The input of the piercing points GA and GB is optional when TYP is GRIDID and ELEMID. If GA or GB are not specified, they are generated from the normal projection of GS onto the surface patches. If GA and/or GB are specified, they take precedence over GS in defining the respective end points. Also, their locations will be corrected so that they lie on surface patch A and B, respectively. If GS is not specified, both GA and GB are required. The length of the connector is the distance from GA to GB.

5.

SPTYP defines the type of surface patches to be connected. SPTYP is required when TYP is GRIDID to identify quadrilateral or triangular patches. Allowable combinations are:

706

SPTYP

Description

QQ

Connects a quadrilateral surface patch A (QUAD4 or QUAD8) with a quadrilateral surface patch B (QUAD4 or QUAD8).

QT

Connects a quadrilateral surface patch A (QUAD4 or QUAD8) with a triangular surface patch B (TRIA3 or TRIA6).

TT

Connects a triangular surface patch A (TRIA3 or TRIA6) with a triangular surface patch B (TRIA3 or TRIA6).

TQ

Connects a triangular surface patch A (TRIA3 or TRIA6) with a quadrilateral surface patch B (QUAD4 or QUAD8).

Q

Connects a grid point GB (or GS if GB not provided) with a quadrilateral surface patch A (QUAD4 or QUAD8). Surface patch B should not be specified.

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6.

SPTYP

Description

T

Connects a grid point GB (or GS if GB not provided) with a triangular surface patch A (TRIA3 or TRIA6). Surface patch B should not be specified.

GA# are required when TYP is GRIDID. At least 3, and at most 8, grid IDs may be specified for GA#. Triangular and quadrilateral element definition sequences apply for the order of GA# and GB#, see below. Missing mid-side nodes are allowed.

Quadrilateral and Triangular Surface Patches as defined when TYP is GRIDID

7.

When TYP is ELEMID, a point to patch connection is defined, GS to SHIDA or a patch to patch connection, SHIDA to SHIDB. SHIDA and SHIDB must be valid shell element identification numbers.

8.

When TYP is ALIGN, a point to point connection is defined. GA and GB are required. GA and GB are not required when TYP is GRIDID or ELEMID.

9.

Forces and moments are output in the element coordinate system (shown in comment 10 below). The element x-axis points from GA to GB. The element y-axis lies on the plane created by the element x-axis and the smallest component of the element x-axis is the basic coordinate system, and is orthogonal to the element x-axis. The element z-axis is the cross-product of the element x-axis and the element y-axis.

10. The output format of the forces and moments, including the sign convention, is identical to the CBAR element.

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Element coordinate system and sign convention of element forces

11. Diagnostic print outs, checkout runs and non-default setting of search and projection parameters are requested on the SWLDPRM bulk data entry. It is recommended to start with default settings. 12. The formats PARTPAT and ELPAT connect shell element patches on side A and B. The patches are identified by specifying SHIDA and SHIDB (for ELPAT connection) and by specifying property IDs PIDA and PIDB for PARTPAT connection (wherein SHIDA and SHIDB are found by appropriate search of best projections of GS (or GA) onto the surfaces A and B, respectivel)y. The piercing points GA and GB are found by appropriate projections onto SHIDA and SHIDB. Then the axis GA-GB is used to define four pairs of auxiliary points GAHi, GBHi, i=1,4 that are located on patches A and B, respectively. The crosssection area of the resulting hexahedral is equivalent to the area of the weld. The weld stiffness matrix is first built using the auxiliary points and then constrained to supporting shell nodes using respective shape functions.

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13. Fastener elements are ignored in heat transfer analysis. 14. This card is represented as a rod element in HyperMesh.

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DAREA Bulk Data Entry DAREA – Dynamic Load Scale Factor Description Defines scale (area) factors for dynamic loads. DAREA is used in conjunction with RLOAD1, RLOAD2, TLOAD1, and TLOAD2 entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DAREA

SID

P1

C1

A1

P2

C2

A2

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DAREA

3

64

2

5.7

65

2

5.7

Field

Contents

SID

Identification number.

(9)

(10)

No default (Integer > 0) P1, P2#

Grid or scalar point identification number. No default (Integer > 0)

C1, C2#

Component number. No default (Integer 1 through 6, or 0 for scalar points)

A1, A2#

Scale (area) factor. No default (Real)

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Comments 1.

One or two scale factors may be defined on a single entry.

2.

Refer to RLOAD1, RLOAD2, TLOAD1, or TLOAD2 entries for the formula that define the scale factor A#.

3.

Component numbers refer to the displacement coordinate system.

4.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

5.

This card is represented as a constraint load in HyperMesh.

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DCOMP Bulk Data Entry DCOMP – Manufacturing Constraints for Composite Sizing Optimization Description Defines manufacturing constraints for composite sizing optimization. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DC OMP

ID

ETYPE

EID1

EID2

EID3

EID4

EID5

EID6

EID7

…

+ +

LAMTHK

LTMIN

LTMAX

LTSET

LTEXC

+

PLYTHK

PTGRP

PTMIN

PTMAX

PTOPT

PTSET

PTEXC

+

PLYPC T

PPGRP

PPMIN

PPMAX

PPOPT

PPSET

PPEXC

+

BALANC E

BGRP1

BGRP2

BOPT

+

C ONST

C GRP

C THIC K

C OPT

+

PLYDRP

PDGRIP

PDTYP

PDSET

PDEXC

PDMAX

Field

Contents

ID

Unique identification number.

PDOPT

(10)

No default (Integer > 0) ETYPE

Entity type for which this DCOMP card is defined. No default (PCOMP or STACK)

EID#

Entity identification numbers. List of entities of type ETYPE for which this DCOMP card is defined. No default (Integer > 0)

LAMTHK

712

LAMTHK flag indicating that laminate thickness constraints are applied.

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Field

Contents Multiple LAMTHK constraints are allowed.

LTMIN

Minimum laminate thickness for the LAMTHK constraint. Default = blank (Real > 0.0)

LTMAX

Maximum laminate thickness for the LAMTHK constraint. Default = blank (Real > 0.0 and > LTMIN)

LTSET

Set ID of elements to which the LAMTHK constraint is applied.

LTEXC

Exclusion flag indicates that certain plies are excluded from the LAMTHK constraint. The following options are supported: NONE: Plies are not excluded. CORE: The core is excluded. (Default) CONST: Plies defined in the CONST constraint are excluded. BOTH: CORE and CONST are considered.

PLYTHK

PLYTHK flag indicating that ply thickness constraints are applied. Multiple PLYTHK constraints are allowed.

PTGRP

Ply orientation in degrees, ply sets or ply IDs, to which the PLYTHK constraint is applied, depending on the PTOPT selection. No default (Real or Integer)

PTMIN

Minimum thickness for the PLYTHK constraint. Default = blank (Real > 0.0)

PTMAX

Maximum thickness for the PLYTHK constraint. Default = blank (Real > 0.0 and > PTMIN)

PTOPT

Ply selection options for the PLYTHK constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

PTSET

Set ID of elements to which the PLYTHK constraint is applied.

PTEXC

Exclusion flag indicates that certain plies are excluded from the PLYTHK constraint. The following options are supported: NONE: Plies are not excluded.

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Field

Contents CORE: The core is excluded. (Default) CONST: Plies defined in the CONST constraint are excluded. BOTH: CORE and CONST are considered.

PLYPCT

PLYPCT flag indicating that ply thickness percentage constraints are applied. Multiple PLYPCT constraints are allowed.

PPGRP

Ply orientation in degrees, ply sets or ply IDs, to which the PLYPCT constraint is applied, depending on the PPOPT selection. No default (Real or Integer)

PPMIN

Minimum percentage thickness for the PLYPCT constraint. Default = blank (Real > 0.0 and < 1.0)

PPMAX

Maximum percentage thickness for the PLYPCT constraint. Default = blank (Real > 0.0, < 1.0 and > PPMIN)

PPOPT

Ply selection options for the PLYPCT constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

PPSET

Set ID of elements to which the PLYPCT constraint is applied.

PPEXC

Exclusion flag indicates that certain plies are excluded from the PLYPCT constraint. The following options are supported: NONE: Plies are not excluded. CORE: The core is excluded. (Default) CONST: Plies defined in the CONST constraint are excluded. BOTH: CORE and CONST are considered.

BALANCE

BALANCE flag indicating that a balancing constraint is applied. Multiple BALANCE constraints are allowed.

BGRP1

First ply orientation in degrees, ply sets or ply IDs, to which the BALANCE constraint is applied, depending on the BOPT selection. No default (Real or Integer)

BGRP2

Second ply orientation in degrees, ply sets or ply IDs, to which the BALANCE constraint is applied, depending on the BOPT selection. No default (Real or Integer)

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Field

Contents

BOPT

Ply selection options for the BALANCE constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

CONST

CONST flag indicating that a constant thickness constraint is applied. Multiple CONST constraints are allowed.

CGRP

Ply orientation in degrees, ply sets or ply IDs, to which the CONST constraint is applied, depending on the COPT selection. No default (Real or Integer)

CTHICK

Constant ply thickness for the CONST constraint. No default (Real > 0.0)

COPT

Ply selection options for the CONST constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

PLYDRP

Indicates that ply drop-off constraints are applied. Multiple PLYDRP constraints are allowed.

PDGRIP

Ply orientation in degrees, ply sets or ply IDs, to which the PLYDRP constraint is applied, depending on the PDOPT selection. No default. (Real or Integer)

PDTYP

Specifies the type of the drop-off constraint as: TOTDRP (see comment 5).

PDMAX

Maximum allowed drop-off for the PLYDRP constraint. No default (Real > 0)

PDOPT

Ply selection options for the PLYDRP constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

PDSET

Set IDs of elements to which the PLYDRP constraint is applied.

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Field

Contents

PDEXC

Exclusion flag indicates certain plies are excluded from the PLYDRP constraint. The following options are supported: NONE: Plies are not excluded. CORE: The core is excluded. (Default). CONST: Plies defined in the CONST constraint are excluded. BOTH: CORE and CONST are considered.

Comments 1.

The following manufacturing constraints are available for ply-based composite sizing optimization: Lower and upper bounds on the total thickness of the laminate (LAMTHK) Lower and upper bounds on the thickness of a given orientation (PLYTHK) Lower and upper bounds on the thickness percentage of a given orientation (PLYPCT) Manufacturable ply thickness (PLYMAN) Linking between the thicknesses of two given orientations (BALANCE) Constant (non-designable) thickness of a given orientation (CONST) LAMTHK, PLYTHK and PLYPCT can be applied locally to sets of elements. There can be elements that do not belong to any set.

2.

These constraints are automatically created after performing free-sizing optimization when the OUTPUT,FSTOSZ control card is activated.

3.

For a more detailed description and an example, refer to the User’s Guide section, Optimization of Composite Structures.

4.

Older versions of the DCOMP card (OptiStruct version 11.0 and prior) are supported and handled appropriately.

5.

The option for selecting the type of drop-off constraints for PDTYP is defined for a set of plies, as shown in the figure below: The option for PDTYP in DCOMP is: TOTDRP.

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Assuming that the plies are stacked as shown above, you have the following definition:

6.

This card is represented as an optimization designvariable in HyperMesh.

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DCONADD Bulk Data Entry DCONADD – Design Constraint Addition Description Creates a combination of several DCONSTR sets that can be referenced by a subcase. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

DC ONADD

DC ID

DC 1

DC 2

DC 3

DC 4

DC 5

DC 6

DC 7

DC 8

etc.

Example

(1)

(2)

(3)

(4)

(5)

DC ONADD

101

10

20

30

Field

Contents

DCID

DCONADD identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) DCi

DCONSTR identification number. (Integer > 0)

Comments 1.

The DCONADD entry is selected by a DESSUB or DESGLB in the Subcase Information section.

2.

All DCi must be unique.

3.

All DCID must be unique with respect to all Dci (DCONSTR IDs).

4.

This card is represented as an optimizationconstraint in HyperMesh.

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DCONSTR Bulk Data Entry DCONSTR – Design Constraints Description Defines design constraint upper and lower bounds where response is defined by DRESP1, DRESP2, and DRESP3 cards. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DC ONSTR

DC ID

RID

LBOUND/ LTID

UBOUND/ UTID

LFREQ

UFREQ

PROB

(10)

Example

(1)

(2)

(3)

(4)

(5)

DC ONSTR

1

9

0.5

10.0

(6)

(7)

(8)

(9)

(10)

Associated Cards (1)

(2)

(3)

(4)

DRESP1

9

TOPN

DISP

(5)

(6)

(7)

(8)

3

Field

Contents

DCID

Design constraint identification number.

(9)

(10)

4668

(Integer > 0) RID

DRESP1, DRESP2, or DRESP3 identification number. (Integer > 0)

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Field

Contents

LBOUND/LTID

Lower bound on response or table identification number of a TABLEDi entry that specifies the lower bound as function of a loading frequency. (Real, Integer, or blank)

UBOUND/UTID

Upper bound on response or table identification number of a TABLEDi entry that specifies the upper bound as function of a loading frequency. (Real, Integer, or blank)

LFREQ

Lower bound on a loading frequency range. Default = 0.0 (Real > 0.0)

UFREQ

Upper bound on a loading frequency range. Default = 1.0E+20 (Real > LFREQ)

PROB

Probability value for Reliability based Design Optimization runs. (50.0 < Real < 100.0)

Comments 1.

The DCONSTR DCID is selected in the Subcase Information section by the DESSUB or DESGLB cards and/or referenced by the DCONADD card.

2.

For any DCID, the associated RID can be referenced only once.

3.

If LBOUND or UBOUND are blank, no constraint will be generated for the bound.

4.

Constraint bounds of zero should be avoided. Unnecessary bounds should be left blank. For example, lower bounds on von Mises stress should be blank, not zero. If a bound of zero is input, the bound will be changed to 1.0E-7 for lower bounds and –1.0E-7 for upper bounds. This will remove numerical difficulties and cause the constraints to be ignored unless the response is actually very near zero.

5.

LFREQ, UFREQ apply only to response types related to a frequency response subcase (DRESPi, RTYPE = FRDISP, FRVELO, FRACCL, FRSTRS, FRSTRN, FRFORC, and FRERP). The constraint bounds LBOUND and UBOUND are applied only if the loading frequency falls between LFREQ and UFREQ. If ATTB of DRESP1 specifies a frequency value, LFREQ and UFREQ are ignored.

6.

LTID, UTID identify a loading frequency dependent tabular input using TABLEDi. They are applied analogous to LFREQ, UFREQ detailed in comment 5.

7.

This card is represented as an optimizationconstraint in HyperMesh.

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DDVAL Bulk Data Entry DDVAL – Discrete Design Variable Values Description This bulk data entry can be used to define real, discrete design variable values for discrete variable optimization or to define relative rotor spin rates in rotor dynamics. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DDVAL

ID

DVAL1

DVAL2

DVAL3

DVAL4

DVAL5

DVAL6

DVAL7

(8)

(9)

(10)

Alternate Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

DDVAL

ID

DVAL1

"THRU"

DVAL

"BY"

INC

(10)

The continuation entry formats (shown below) may be used more than once, and in any order. They may also be used with either format above. Continuation Entry Format 1 (1)

(2)

(3)

(4)

(5)

(6)

DVAL8

DVAL9

DVAL10

DVAL11

-etc.-

(7)

(8)

(9)

(10)

(7)

(8)

(9)

(10)

Continuation Entry Format 2 (1)

(2)

(3)

(4)

(5)

(6)

DVAL8

"THRU"

DVAL9

"BY"

INC

Example

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(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DDVAL

110

0.1

0.2

0.3

0.5

0.6

0.4

.7

thru

1.0

by

0.05

1.5

20

Field

Contents

ID

Unique discrete value set identification number.

(9)

(10)

(Integer > 0) DVALi

Discrete values. (Real or "THRU" or "BY")

INC

Discrete value increment. (Real)

Comments 1.

DDVAL entries must be referenced by a) The DDVAL field of a DESVAR bulk data entry. b) The SPTID field of a RSPINR bulk data entry.

2.

Trailing fields on a DDVAL record can be left blank if the next record is of type DVALi "THRU" DVALj "BY" INC. Also, fields 7 though 9 must be blank when the type DVALi "THRU" DVALj "BY" INC is used in fields 2 through 6. Fields 8 through 9 must be blank when the type DVALi "THRU" DVALj "BY" INC is used in fields 3 through 7 for the first record. Embedded blanks are not permitted in other cases.

3.

The DVALi sequence can be random.

4.

The format DVALi "THRU" DVALj "BY" INC defines a list of discrete values, for example, DVALi, DVALi+INC, DVALi+2.0*INC, …, DVALj. The last discrete DVALj is always included, even if the range is not evenly divisible by INC.

5.

This card is represented as a discretedesignvariable in HyperMesh.

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DEFORM Bulk Data Entry DEFORM – Static Element Deformation Description Defines enforced axial deformation for one-dimensional elements for use in statics problems. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DEFORM

SID

EID1

D1

EID2

D2

EID3

D3

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

DEFORM

21

157

-0.2

111

1.4

(7)

Field

Contents

SID

Identification number of a deformation set.

(8)

(9)

(10)

No default (Integer > 0) EID#

Element Identification Number. See comment 1. No default (Integer > 0)

D#

Deformation. (Positive value represents elongation). No default (Real)

Comments 1.

Only CBAR, CBEAM, CROD, CONROD, and CTUBE elements are valid.

2.

To be used in an analysis, deformation sets must be referenced by a DEFORM Subcase Information entry.

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3.

DEFORM does not enforce an actual extension of the length of the element; it applies an internal strain within the element, which produces the specified extension if the element is free to expand (similar to the effect of thermal expansion). Since most elements in an FEA model are not free to expand, the specified extension value may not be achieved because elastic compression of the element will partially or completely offset the effect of the prescribed strain. To precisely enforce a prescribed increase in length, MPC equations are more appropriate. Alternatively, giving the DEFORM element a very high axial stiffness can approximate such conditions.

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DELAY Bulk Data Entry DELAY – Dynamic Load Time Delay Description Defines the time delay term in the equations of the dynamic loading function. DELAY is used in conjunction with RLOAD1, RLOAD2, TLOAD1, and TLOAD2 entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DELAY

SID

P1

C1

T1

P2

C2

T2

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DELAY

3

64

2

5.7

65

2

5.7

Field

Contents

SID

Identification number.

(9)

(10)

No default (Integer > 0) P1, P2

Grid or scalar point identification number. No default (Integer > 0)

C1, C2

Component number. No default (Integer 1 through 6, or 0 for scalar points)

T1, T2

time delay term, , for designated point and component. No default (Real)

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Comments 1.

One or two dynamic load time delays may be defined on a single entry.

2.

SID must also be specified on a RLOAD1, RLOAD2, TLOAD1, or TLOAD2 entry. See those entry descriptions for the formulae that define the manner in which the time delay term, , is used.

3.

A DAREA entry should be used to define a load at P# and C#.

4.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

5.

This card is represented as a constraint load in HyperMesh.

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DEQATN Bulk Data Entry DEQATN – Design Equation Definition Description Specifies one or more equations for use in optimization. Format (1)

(2)

(3)

DEQATN

EQUID

(4)

EQN1;

…;

(5)

(6)

(7)

(8)

EQN2;

…;

EQNn-1;

(9)

(10)

EQN3;

EQNn

Example 1

DEQATN

3

y(x1, x2) = x1 + x2**-3.0*(2-1)+5.0;

z = -y*1.3E-2

Example 2

DEQATN

104

z(x1, x2) = min(sin(x1), x2); y = max(0.3, -2.0, z) + 4.0

Field

Contents

EQUID

Unique equation identification number. (Integer > 0)

EQNi

i-th equation.

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(Character string) Comments 1.

All equation identification numbers must be unique.

2.

Each equation card is specified in a fixed format, without the limitation of data field boundaries. Equations are located in columns 17-72 on the first card, and in columns 972 on each continuation card. There is no limit on the total length of any equation.

3.

Large field format is not allowed.

4.

Free field format is allowed, but only the same number of characters as in the fixed format (56 on the first line and 64 on the continuation lines) and will be accepted. Characters after the 72nd column will not be accepted. Excess characters are silently disregarded, which may result in DEQATN error or in a valid expression different from that intended. On the continuation card in free format, the comma must be present within the first 8 columns; otherwise, the card will be interpreted in a fixed field format.

5.

Blank characters in the equation have no effect, even within a constant, variable or function name. Lower and upper case letters are equivalent.

6.

There must be only one variable at the left-hand side of each equation in any equation card. The variable of the first equation must be followed by an argument list in the following format: v1(x1,x2,…,xn) = expression(x1,x2,…,xn); v2 = expression(x1,x2,…,xn,v1); … vi

= expression(x1,x2,…,xn,v1,v2,…,vi-1);

… vn = expression(x1,x2,…,xn,v1,v2,…,vn-1); where, vi is the variable of equation i. (x1, x2, …, xn) is the argument list for variable v1. (v1,v2,…,vi-1) is the variable list which corresponds to the result of equation 1 through equation i-1. Only the value of the last expression is returned to the bulk data card referencing EQUID (DRESP2). 7.

Constants can be specified in a format of either integer or floating point. A floating point number can be in a format of either normal decimal-point format ("3.90") or scientific notation ("-2.0E-3"), which means -2x10-3. The list of supported mathematical functions is as follows:

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One-argument functions abs(x)

absolute value

acos(x)

arccosine

acosh(x)

hyperbolic arccosine

asin(x)

arcsine

asinh(x)

hyperbolic arcsine

atan(x)

arctangent

atanh(x)

hyperbolic arctangent

cos(x)

cosine

cosh(x)

hyperbolic cosine

exp(x)

exponential

log(x)

natural logarithm

log10(x)

common logarithm

pi(x)

multiples of

sin(x)

sine

sinh(x)

hyperbolic sine

int (x)

real to integer conversion

sqrt(x)

square root

Two-argument functions

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Multi-argument functions

8.

730

The supported operators are listed below: Symbol

Meaning

Example

+

binary +

x+y

-

binary -

x-y

*

multiplication,

x*y

/

division

x/y

**

power

x**y

+

unary +

+1.0

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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9.

Symbol

Meaning

Example

-

unary -

-1.0

The precedence of mathematical calculations follows the rules of Fortran language. Parenthesis has a higher priority in the order of precedence than the operators listed in 8. Two consecutive operators are allowed only if the second one is unary plus or minus. Examples of operator precedence: Expression

Result

2**-3

0.128

1 / 2 +3

3.5

2*3-4

2.0

-2**3**2

-512.0

2 + -5

-3.0

2 * -5

-10.0

2 - -5

7.0

2/3/4

0.16666666…

2/(3/4)

2.6666666…

10. Functions can be defined in a layered format, for example, min(sin(x1), x2). There is no limit on the number of layers. 11. The DEQATN entry is referenced by DRESP2 and/or DVPREL2 bulk data cards. DRESP2 card, the variable identified by DVIDi, LABj, NRk, Gr and DPIP correspond to variable arguments listed in the left-hand side of the first equation of a DEQATN card identified by EQUID. The variable arguments x1 through xN (where N = n + m + p + q + s) are assigned in the order DVID1, DVID2, …, DVIDn, LAB1, LAB2, …, LABm, NR1,NR2, …, NRp, G1, …, Gq, DPIP1,…,DPIPS. In a DVPREL2 card, the variables identified by DVIDi and LABj correspond to variable arguments listed in the left-hand side of the first equation of a DEQATN card identified by EQUID. The variable arguments x1 through xN (where N = n + m) are assigned in the order DVID1, DVID2, …, DVIDn, LAB1, LAB2, …, LABm. Only the computed value of the last expression (vn) is used by DRESP2 and/or DVPREL2 entry. 12. This card is represented as an optimizationfunction in HyperMesh.

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Restrictions Variable names longer than 8 characters are truncated, which may create an error in equation if two names are identical after such truncation. All trigonometric arguments are in radians. Only alphanumeric characters may be used in variable names (that is do not use underscores, monetary symbols, punctuation symbols, mathematical operators, letters from non-English alphabet, and so on). Mathematical function names (such as those listed in comment 7 above) should not be used as variable names. The following functions are not accepted: DB() DBA() INVDB() INVDBA() Possible Errors An informative error message with the DEQATN ID will be displayed if the parsing of the equation fails. However, in certain cases, the following generic message will be provided: Error 1690: This equation could not be parsed. See the DEQATN entry in the OptiStruct manual. This error message means that it was not possible to clearly identify the reason for the failure. If this happens, check for the following possible causes, and contact [email protected]: The length of the equation exceeds the 72 character per line limitation. The last character of the equation is an operator. There are two adjacent operators in the equation. There are non-alphanumeric characters (besides operators) in the equation.

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DESVAR Bulk Data Entry DESVAR – Design Variable Description Defines a design variable. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DESVAR

ID

LABEL

XINIT

XLB

XUB

DELXV

DDVAL

+

RAND

ITYPE

P1

P2

P3

+

RANP

ITYPE

P1

P2

P3

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

DESVAR

1

DV001

0.0

-1.0

1.0

Field

Contents

ID

Unique design variable identification number.

(7)

(8)

(9)

(10)

(Integer > 0) LABEL

User-defined name for the variable. (Character)

XINIT

Initial value for variable. (Real between XLB and XUB)

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Field

Contents

XLB

Design variable lower bound. (Real)

XUB

Design variable upper bound. (Real)

DELXV

Initial move limit for each design variable. (Real > 0.0 or blank) Size: fraction of the variable itself. (Default = value of DOPTPRM parameter DELSIZ) Shape: fraction of the range (XUB – XLB) of the variable. (Default = value of DOPTPRM parameter DELSHP)

DDVAL

ID of DDVAL entry that provides a set of discrete values. (Blank or Integer > 0; Default = blank for continuous design variables)

RAND

Random Design Variable RAND flag indicating that the random design variable distribution parameters for Reliability-based Design Optimization (RBDO).

ITYPE

Type of Random Distribution (see comment 5): (Character string) NORM – Normal distribution LOG – Logarithmic normal distribution UNIF – Uniform distribution TRIA – Triangular distribution EXPO – Exponential distribution WEIB – Weibull distribution GUMB – Gumbel distribution

P1

The first distribution parameter (see comment 5) (Real > 0.0)

P2

734

The second distribution parameter (see comment 5)

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Field

Contents (Real > 0.0)

P3

The third distribution parameter (see comment 5) (Real > 0.0) Set it to zero, if this parameter does not exist

RANP

Random Parameter RANP flag indicating that the random parameter distribution parameters for Reliability-based Design Optimization (RBDO).

Comments 1.

Only the initial value of the move limits can be set. Move limits are automatically adjusted to enhance iterative stability and convergence speed.

2.

LABEL must begin with an alphabetical character, and cannot have embedded blanks.

3.

If the design variable is discrete (Integer > 0 in DDVAL field), and if either XLB and/or XUB bounds are wider than those given by the discrete list of values on the corresponding DDVAL entry, XLB and/or XUB will be replaced by the minimum and maximum discrete values.

4.

Setting XINIT=XLB=XUB freezes the design variable.

5.

The various distribution types are as follows: Normal Distribution (NORM)

Log-normal Distribution (LOG)

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Uniform distribution (UNIF)

Triangular distribution (TRIA)

Exponential distribution (EXPO)

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Weibull distribution (WEIB)

Gumbel distribution (GUMB)

6.

This card is represented as an optimization designvariable in HyperMesh

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DESVARG Bulk Data Entry DESVARG – Design Variable Group Override Description Defines an override for design variable settings. Format (1)

(2)

(3)

(4)

(5)

(6)

DESVARG

ID

INIT

LB

UB

SET

Field

Contents

ID

Identification Number.

(7)

(8)

(9)

(10)

No default (Integer > 0) INIT

Overrides the initial value setting for affected design variables. See comment 1. Default = blank (UB, LB, blank, Real or ANALYSIS)

LB

Overrides the lower bound setting for affected design variables. Default = blank (blank or Real)

UB

Overrides the upper bound setting for affected design variables. Default = blank (blank or Real)

SET

Defines the design variables that are affected by this DESVARG entry. Can either be the keyword ALL or the SID of a SET of type DESVAR. Default = ALL (ALL or Integer)

Comments 1.

738

If any of INIT, LB or UB are left blank, then no override is applied to the corresponding field on affected DESVARs.

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2.

If INIT is defined as LB, then for all affected DESVAR entries the initial value is set to the lower bound setting. Likewise if INIT is defined as UB, then for all affected DESVAR entries the initial value is set to the upper bound setting. If, INIT is defined as ANALYSIS, then for all affected DESVAR entries the initialization is accomplished based on the corresponding analysis properties. Limitations for the ANALYSIS mode of initialization in the INIT field: When a Design Variable is associated with multiple properties that have different values. When a Design Variable is associated with a property through DVPREL2 When a Design Variable is associated with a property through DVPREL1 with multiple design variables. When one of the three limitations occurs, a warning is issued and the Design Variable is initialized based on the DESVAR card.

3.

Multiple DESVARGs are allowed (DESVARGs are processed in the order of input).

4.

If the bounds are invalid after DESVARG is applied, then an error will occur.

5.

This card is represented as a control card in HyperMesh.

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DGLOBAL Bulk Data Entry DGLOBAL – Input Data for Selecting the Global Search Option Description Defines input parameters required for the Global Search Option (GSO). Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

DGLOBA L

ID

NGROU P

NPOINT

SPMETH

NOUTDE S

DESTOL

MAXSP

MAXSUC C

MAXWAL L

MAXC PU

+

+

GROUP

SID1

NPOINT1

SPMETH1

+

GROUP

SID2

NPOINT2

SPMETH2

+

…

…

Field

Contents

ID

Each DGLOBAL card must have a unique ID.

(8)

(9)

(10)

No default (Integer > 0) NGROUP

Number of groups of design variables. See comment 1. Default = AUTO (Integer > 0, AUTO or blank)

NPOINT

Number of starting points for each group of design variables. See comment 1. Default = AUTO (Integer > 0, AUTO or blank)

SPMETH

740

Method used to generate the starting points. See comment 2.

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Field

Contents Default = OFFSET (EXTREME, OFFSET or blank)

NOUTDES

Number of unique designs to be saved. See comment 4. Default = ALL (Integer > 0, ALL or blank)

DESTOL

Unique design tolerance. See comment 4. Default = 1% (Real > 0.0 or blank)

MAXSP

Maximum number of starting points. See comment 5. Default = 20 (Integer > 0 or blank)

MAXSUCC

Maximum number of consecutive starting points without finding a unique design. See comment 5. Default = 10 (Integer > 0 or blank)

MAXWALL

Maximum amount of WALL time (in hours). See comment 5. Default = infinite (Real > 0.0 or blank)

MAXCPU

Maximum amount of CPU time (in hours). See comment 5. Default = infinite (Real > 0.0 or blank)

GROUP

GROUP flag indicating that design variables grouping information is to follow. See comment 3.

SID#

Design variables SET identification number. No default (Integer > 0)

NPOINT#

Number of starting points for the current group of design variables. Default = AUTO (Integer > 0, AUTO or blank)

SPMETH#

Method used to generate the starting points for the current group of design variables. Default = AUTO (EXTREME, OFFSET, AUTO or blank)

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Comments 1.

Design variables are automatically organized in groups, and design variables within a given group are assigned the same relative starting points, such as their lower or upper bound. With the AUTO option, OptiStruct determines NGROUP and NPOINT so as to generate a reasonable and manageable number of starting points. Note that for small optimization problems, each design variable might be assigned its own group. By default, the number of groups is equal to the number of independent design variables with an upper limit of 10. For larger optimization problems, design variables are grouped together in order to consolidate the potential starting points.

2.

With the EXTREME option, the lower and upper bounds are included in the list of starting points; whereas with the OFFSET option, the lower and upper bounds are not considered as starting points. In both cases, the starting points are distributed evenly.

3.

In situations where finer control is required, design variables can be grouped manually by creating DESVAR SETs. NPOINT# and SPMETH# can also be defined for individual groups. If those parameters are not defined for a specific group, they inherit their value from the generic NPOINT and SPMETH parameters.

4.

The unique design tolerance DESTOL provides the threshold under which two designs are considered identical. It is measured as the average of the relative differences between the design variables at the last iteration. If such identical designs are found, the best occurrence is preserved and other results are discarded. Up to NOUTDES unique designs are saved in subdirectories named , where #s is the starting point and #u is the rank of the unique design.

5.

The global search option stops searching for optimal designs when any of the following criteria has been met: the maximum number of starting points (MAXSP) has been reached the maximum number of consecutive starting points without finding a unique design (MAXSUCC) has been reached the maximum amount of WALL time (MAXWALL) has been reached or exceeded the maximum amount of CPU time (MAXCPU) has been reached or exceeded all possible starting points have been explored

6.

In general, it is recommended to run the global search option with the default parameters, except for the termination criteria.

7.

The DGLOBAL bulk data entry is referenced by the DGLOBAL command in the I/O section of the input data.

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DIM Bulk Data Entry DIM – Dimension Definition Description Defines a link between a DIM# field on a PBARL or PBEAML property and either the thickness on a PSEC definition or the y or z coordinate on a GRIDS definition; it is used in the definition of arbitrary beam cross-sections. Format (1)

(2)

(3)

(4)

DIM

DIMID

T

PID

(5)

(6)

(7)

(8)

(9)

(10)

(6)

(7)

(8)

(9)

(10)

Alternate Format (1)

(2)

(3)

(4)

(5)

DIM

DIMID

G

GID

C OORD

Example

(1)

(2)

(3)

(4)

DIM

1

T

10

(5)

(6)

(7)

(8)

(9)

(10)

Field

Contents

DIMID

Dimension identification number. The number of a cross-section dimension field on a PBARL, or PBEAML property definition. No default (Integer > 0)

T

Thickness flag. Indicates that the dimension definition is related to a PSEC thickness.

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Field

Contents

PID

Identification number of a PSEC definition. No default (Integer > 0)

G

Grid flag. Indicates that the dimension definition is related to a GRIDS coordinate.

GID

Identification number of a GRIDS definition. No default (Integer > 0)

COORD

Coordinate. No default (Y or Z)

Comments 1.

DIMID may be repeated in a section definition, but a PSEC thickness or a GRIDS coordinate must not be mentioned on more than one DIM entry within a section definition.

2.

This entry is only valid when it appears between the BEGIN and END statements.

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DLINK Bulk Data Entry DLINK – Design Variable Link Description The DLINK bulk data entry defines a link between one design variable and one or more other design variables. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DLINK

ID

DDVID

C0

C MULT

IDV1

C1

IDV2

C2

IDV3

C3

etc.

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DLINK

55

3

0.2

0.45

5

2.0

10

5.5

15

-3.0

Field

Contents

ID

Unique DLINK identification number.

(10)

(Integer > 0) DDVID

Identification number of the Dependent Design Variable. (Integer > 0)

C0

Constant. Default = 0.0 (Real)

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Field

Contents

CMULT

Constant multiplier. Default = 1.0 (Real)

IDVi

Identification number of the Independent Design Variable. (Integer > 0)

Ci

Coefficient multiplier for IDVi. (Real)

Comments 1.

DLINK defines the relationship.

This capability allows physical and non-physical design variables to be related such as shell thickness and interpolating functions. 2.

Independent IDVi’s can occur on the same DLINK entry only once.

3.

CMULT and Ci can be used together to provide a simple means of scaling.

4.

This card is represented as an optimization designvariablelink in HyperMesh.

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DLINK2 Bulk Data Entry DLINK2 – Design Variable Link Defined by User-supplied Equation Description Defines a link of one design variable to one or more other design variables defined by a DEQATN card. The equation inputs come from the referenced DESVAR values and the constants defined on the DTABLE card. Format (1)

(2)

(3)

(4)

DLINK2

ID

DDVID

EQUID or FUNC

DESVAR

DVID1

DTABLE

(5)

(6)

(7)

(8)

(9)

(10)

DVID2

DVID3

DVID4

DVID5

DVID6

DVID7

DVID8

DVID9

etc.

LABL1

LABL2

LABL3

LABL4

LABL5

LABL6

LABL7

LABL8

etc.

Example

(1)

(2)

(3)

(4)

DLINK2

201

7

101

DESVAR

5

6

Altair Engineering

(5)

(6)

(7)

(8)

(9)

(10)

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Associated Cards (1)

(2)

(3)

(4)

(5)

(6)

DESVAR

5

X

0.0

-1.0

1.0

DESVAR

6

Y

0.0

-1.0

1.0

DESVAR

7

R

0.0

-1.0

1.0

DEQATN

101

(7)

(8)

(9)

(10)

RADIUS(X,Y) = SQRT(X**2+Y**2)

Field

Contents

ID

Relationship identity. Each DVPREL2 card must have a unique ID. No default (Integer > 0)

DDVID

Identification number of Dependent Design Variable. (Integer > 0)

EQID

Equation ID of DEQATN data. No default (Integer > 0)

FUNC

Function to be applied to the arguments. See comment 2. (Character)

DESVAR

DESVAR flag indicating DESVAR ID numbers follow.

DVIDi

DESVAR ID. No default (Integer > 0)

DTABLE

DTABLE flag indicating DTABLE labels follow.

LABLi

Constant label on DTABLE card. No default (Character)

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Comments 1.

The main application for this entity is to link shape design variables with each other through equations. DVPREL2 should be used for linking sizing design variables with each other through equations.

2.

The following functions can be used instead of an EQUID. If FUNC is used, the DEQATN entry is no longer needed. The functions are applied to all arguments on the DLINK2 regardless of their type.

3.

Function

Description

Formula

SUM

Sum of arguments

AVG

Average of arguments

SSQ

Sum of square of arguments

RSS

Square root of sum of squares of arguments

MAX

Maximum of arguments

MIN

Minimum of arguments

SUMABS

Sum of absolute value of arguments

AVGABS

Average of absolute value of arguments

MAXABS

Maximum of absolute arguments

MINABS

Minimum of absolute value of arguments

This card is represented as an optimization designvariablelink in HyperMesh.

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DLOAD Bulk Data Entry DLOAD – Dynamic Load Combination or Superposition Description Defines a dynamic loading condition for frequency response problems as a linear combination of load sets defined via RLOAD1 and RLOAD2 entries, or for transient problems as a linear combination of load sets defined via TLOAD1 and TLOAD2 entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DLOAD

SID

S

S1

L1

S2

L2

S3

L3

S4

L4

…

…

…

…

…

…

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DLOAD

5

1.0

2.0

101

2.0

102

2.0

103

-2.0

201

Field

Contents

SID

Load set identification number.

(10)

No default (Integer > 0) S

Scale factor. No default (Real)

S#

Scale factors. No default (Real)

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Field

Contents

L#

Load set identification numbers of RLOAD1 and RLOAD2 or TLOAD1 and TLOAD2 entries. No default (Integer > 0)

Comments 1.

Dynamic load sets must be selected in the I/O Options or Subcase Information sections with DLOAD=SID. (See I/O Options and Subcase Information DLOAD entry).

2.

The load vector being defined by this entry is given by:

3.

Each L# must be unique from any other L# on the same entry.

4.

SID must be unique from all RLOAD1 and RLOAD2 or TLOAD1 and TLOAD2 entries.

5.

A DLOAD entry may not reference a set identification number defined by another DLOAD entry.

6.

RLOAD1 and RLOAD2 loads and TLOAD1 and TLOAD2 loads may be combined only through the use of the DLOAD entry.

7.

This card is represented as a loadcollector in HyperMesh.

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DMIG Bulk Data Entry DMIG – Direct Matrix Input at Points Description Defines direct input matrices related to grid points. The matrix is defined by a single header entry and one or more column entries. A column entry is required for each column with nonzero elements. Header Entry Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DMIG

NAME

"0"

IFO

TIN

TOUT

(5)

(6)

(7)

(8)

C1

A1

(9)

(10)

NC OL

Column Entry Format (1)

(2)

(3)

(4)

DMIG

NAME

GJ

CJ

G1

G2

C2

A2

G3

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

DMIG

STIF

0

9

1

0

DMIG

STIF

27

1

120

4

2.5+10

STIF

28

1

123

4

4.1+8

DMIG

752

(7)

(8)

(9)

(10)

2

120

3

3.+5

123

3

6.+7

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Field

Contents

NAME

Name of the matrix -- See comment 1. No default (One to eight alphanumeric characters, the first must be alphabetic)

IFO

Form of matrix input. No default (6 = Symmetric, 9 = rectangular)

TIN

Type of matrix being input. (Ignored) All data is read in as double precision. The number of significant digits is equal to the number of digits in the input. The input can be free, short fixed field, or long fixed field data.

TOUT

Type of matrix that will be created. (Ignored) All data is stored internally as double precision.

NCOL

Number of columns in a rectangular matrix. Must be used when IFO = 9. Not used when IFO = 6. Default = blank (Integer > 0, or blank)

GJ

Grid point identification number for column index. No default (Integer > 0)

CJ

Component number for grid point GJ. No default (0 < Integer < 6)

Gi

Grid point identification number for row index. No default (Integer > 0)

Ci

Component number for Gi for a grid point. No default (0 < CJ < 6)

Ai

Real value of a matrix element. No default (Real)

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Comments 1.

Matrices may be selected for all solution sequences by the structural matrices before constraints are applied.

2.

The header entry containing IFO is required. Each no-null column is started with a GJ, CJ pair. The entries for each row of that column follow. Only non-zero terms need be entered. The terms may be input in arbitrary order. A GJ, CJ pair may be entered more than once, but input of an element of the matrix more than once will produce a fatal message.

3.

Field 3 of the header entry must contain an integer 0.

4.

A given off-diagonal element may be input either below or above the diagonal. While upper and lower triangle terms may be mixed, a fatal message will be issued if an element is input both below and above the diagonal.

5.

The matrix names must be unique among all DMIGs.

6.

The recommended format for rectangular matrices requires the use of NCOL and IFO = 9. The number of columns in the matrix is NCOL. (The number of rows in all DMIG matrices is always g-set size). The GJ term is used for the column index. The CJ term is ignored.

7.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

8.

The DMIG matrices can be multiplied by real numbers and combined when referenced by the K2GG, M2GG, K42GG, K2PP, B2GG, and A2GG data.

9.

The DMIG matrices can be multiplied by real numbers as they are assembled into the global matrices using the PARAM data C2K, CP2, CB2, and CM2 for K2GG, K2PP, B2GG, and M2GG data respectively.

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DMIGMOD Bulk Data Entry DMIGMOD – H3DDMIG Modification Description Defines changes in the contents of a super element from H3DDMIG input. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DMIGMO D

MTXNAM E

SHFGID

SHFSPI D

SHFSPID_ F

SHFC ID

SHFEID

SHFRID

HYBDAM P

METHOD

SDAMP

KDAMP

METHOD_ F

SDAMP_ F

KDAMP_ F

ORIGIN

A1

A2

A3

GIDMAP

GID1

GID1A

GID2

GID2A

GID3

GID3A

C IDMAP

C ID1

C ID1A

C ID2

C ID2A

C ID3

C ID3A

RELOC

PA1

PA2

PA3

PB1

PB2

PB3

Field

Contents

MTXNAME

Matrix name defined on ASSIGN,H3DDMIG.

(9)

(10)

No default (1 to 6 characters) SHFGID

All Grid identification numbers in the superelement are shifted by the specified value. If this field is left blank, then a shift does not occur (see comment 2). Default = blank (Integer, or blank)

SHFSPID

All SPOINT identification numbers in the superelement are shifted by the specified value. If this field is left blank, then a shift does not occur (see

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Field

Contents comment 2). Default = blank (Integer, or blank)

SHFSPID_F

All Fluid SPOINT identification numbers in the superelement are shifted by the specified value. If this field is left blank, then a shift does not occur (see comment 2). Default = blank (Integer, or blank)

SHFCID

All Coordinate System identification numbers in the superelement are shifted by the specified value. If this field is left blank, then a shift does not occur (see comment 2). Default = blank (Integer, or blank)

SHFEID

All Element identification numbers in the superelement are shifted by the specified value. If this field is left blank, then a shift does not occur (see comment 2). Default = blank (Integer, or blank)

SHFRID

All Rigid Element identification numbers in the superelement are shifted by the specified value. If this field is left blank, then a shift does not occur (see comment 2). Default = blank (Integer, or blank)

HYBDAMP

Keyword for the remaining data for superelement damping.

METHOD

Identification number of EIGRL card. Hybrid damping would be applied on the superelements for the modes referred by EIGRL card. If blank, then applied damping on all the modes. Default = blank (Integer > 0, or blank)

SDAMP

Identification number of TABDMP1 entry for modal damping. No default (Integer > 0)

KDAMP

If KDAMP is set to -1, viscous modal damping is entered into the complex stiffness matrix as structural damping instead of viscous damping. Default = 1 (Integer)

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Field

Contents

METHOD_F

Identification number of EIGRL card. Hybrid damping would be applied on the fluid part of superelement for the modes referred by the EIGRL card. If blank, then modal damping is applied damping to all the fluid modes.

SDAMP_F

Identification number of TABDMP1 entry for fluid modal damping of the superelement. No default (Integer > 0)

KDAMP_F

If KDAMP_F is set to -1, viscous modal damping is entered into the complex stiffness matrix as structural damping instead of viscous damping. Default = 1 (Integer)

ORIGIN

Keyword for defining the new ORIGIN for DMIG.

A1,A2,A3

Defines the new location of the origin of the DMIG. Default = 0.0 (Real)

GIDMAP

Keyword for defining mapped grid ID pairs.

GIDn,GIDnA

Mapped grid ID pairs.

CIDMAP

Keyword for defining mapped coordinate system ID pairs.

CIDn,CIDnA

Mapped coordinate system ID pairs.

RELOC

Keyword indicating that matching grid point ID pairs in the residual structure and superelement are to follow (see comment 1).

PA1, PA2, PA3

ID’s of three non-collinear grid points in the residual structure.

PB1, PB2, PB3

ID’s of three non-collinear grid points in the superelement that will be matched to corresponding grid points in the residual structure (defined by PA1, PA2 and PA3).

Comments 1.

The RELOC entry and its related fields define three matching grid point pairs on the residual structure and the superelement. The superelement defined using ASSIGN, H3DDMIG is relocated (translated and rotated, as required) such that the three non-

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collinear grids PB1, PB2, and PB3 coincide with PA1, PA2, and PA3, respectively on the residual structure.

Figure 1: Matching three grids on the superelement with grids on the residual structure

2.

758

Identification numbers of certain entities in a superelement can be modified during H3DDMIG input. Negative integers can be input in the shift fields on this entry (see fields beginning with ‘SHF’ above), however, care should be taken to ensure that the identification numbers are not shifted to negative values. The values of identification numbers after shifting should always be greater than zero, otherwise, the run will error out.

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DOBJREF Bulk Data Entry DOBJREF – Design Objective for Minmax Problems Description Defines a response and its reference values for a minmax (maxmin) optimization problem. Format (1)

(2)

(3)

(4)

(5)

DOBJREF

DOID

RID

SID

(6)

NEGREF POSREF / LID / UID

(7)

(8)

(9)

LOWFQ

HIGHFQ

(10)

Example 1

(1)

(2)

(3)

(4)

(5)

(6)

DOBJREF

22

3

ALL

-1.0

1.0

DOBJREF

22

5

ALL

-1.0

1.0

(5)

(6)

(7)

(8)

(9)

(10)

(7)

(8)

(9)

(10)

Associated Cards (1)

(2)

(3)

(4)

DRESP1

3

TOP

DISP

3

488

DRESP1

5

BOTTOM

DISP

3

601

Example 2

(1)

(2)

(3)

(4)

(5)

(6)

DOBJREF

23

14

ALL

-1.0

1.0

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(8)

(9)

(10)

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Associated Cards (1)

(2)

(3)

(4)

(5)

(6)

DRESP1

3

TOP

DISP

3

488

DRESP1

5

BOTTOM

DISP

3

601

Field

Contents

DOID

Design objective identification number.

(7)

(8)

(9)

(10)

(Integer > 0) RID

DRESP1 or DRESP2 identification number. (Integer > 0)

SID

Subcase identification number - use ALL if it applies to all subcases. Default = ALL (Integer > 0, blank or ALL)

NEGREF/ LID

NEGREF (Real < 0.0) Default = -1 LID No default

POSREF/ UID

POSREF (Real > 0.0) Default = 1.0 UID No default

760

Reference value for a negative response (should always be a negative real number or blank). See comments 2, 3 and 5. Table identification number of a TABLEDi entry that specifies the negative reference as a function of loading frequency. See comments 2, 3 and 5. Reference value for a positive response (should always be a positive real number or blank). See comments 2, 3 and 5. Table identification number of a TABLEDi entry that specifies the positive reference as a function of loading frequency. See comments 2, 3 and 5.

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Field

Contents

LOWFQ

Lower bound on a loading frequency range. Default = 0.0 (Real > 0.0)

HIGHFQ

Upper bound on a loading frequency range. Default = 1.0E+20 (Real > LOWFQ)

Comments 1.

The same DOID can be used for multiple DOBJREF entries. If only one DOID is used, only one MINMAX=DOID entry is needed in the Subcase Information section.

2.

The use of reference values allows users to set up general minmax problems involving different responses with different magnitudes. For these problems, the objective can be defined as:

Minimize max(W1 ( x)/r1, W2 (x)/r 2 , ... Wk ( x)/ rk ) Or, alternatively:

Maximimze max(W1 ( x)/r 1, W2 ( x)/ r2 ,...Wk ( x)/ rk ) where, Wk are response values, and rk are corresponding reference values, which can take different values depending on whether the response is positive or negative. 3.

Typically, the target value or constraint value of a response can be used as its reference value. So, instead of the traditional optimization problem where there is a single objective and multiple constraints, the problem may be formulated as a minmax (maxmin) optimization, where all the responses which were previously constrained are defined as objectives and their bounds are used as reference values. This works toward pushing the maximum ratio of response versus bound value as low as possible, thus increasing the safety of the structure.

4.

LOWFQ and HIGHFQ apply only to response types related to a frequency response subcase (DRESPi, RTYPE = FRDISP, FRVELO, FRACCL, FRSTRS, FRSTRN, FRFORC, FRPRES and FRERP). The reference values NEGREF and POSREF are applied only if the loading frequency falls between LOWFQ and HIGHFQ. If ATTB of DRESP1 specifies a frequency value, LOWFQ and HIGHFQ are ignored.

5.

LID and UID identify a loading frequency dependent tabular input using TABLEDi. They are applied analogous to LOWFQ, HIGHFQ detailed in comment 4.

6.

This card is represented as a designobjectivereference in HyperMesh.

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DOPTPRM Bulk Data Entry DOPTPRM – Design Optimization Parameters Description Defines design optimization parameters by overriding the defaults. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

DOPTPRM

PARAM1

VAL1

PARAM2

VAL2

PARAM3

VAL3

PARAM4

VAL4

PARM5

VAL5

Etc …

Example

(1)

(2)

(3)

(4)

(5)

DOPTPRM

MINDIM

10.0

OBJTOL

0.01

(6)

(7)

Field

Contents

PARAMi

Parameter name. See below for allowable names.

VALi

Parameter value.

(8)

(9)

(10)

(Real or Integer) The available parameters and their values are listed below (click the parameter name for detailed parameter descriptions).

Parameter

Brief Description

Value

APPROX

Switch to select the approximation type for stress/strain responses of shells, composites and 1-D elements.

FULL or REDUCED Default = FULL

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Parameter

Brief Description

Value

CHECKER

This option controls the checkerboard-like element wise density distribution.

0 or 1 Default = 0

DDVOPT

Control options for discrete design optimization.

1, 2, or 3 Default = 1

DELSHP

The initial fractional move limit for topography/shape design variables (fractional difference between the upper and lower bounds).

Real > 0.0 Default = 0.2

DELSIZ

The initial fractional move limit for size design variables.

Real > 0 Default = 0.5

DELTOP

The initial fractional move limit for topology and free-size design variables.

Real > 0 Default = 0.5

DESMAX or MAXITER

Defines the maximum number of design iterations.

Integer > 0 Default = 30, or if MINDIM is defined, default = 80

DISCRETE

Discreteness parameter. Influences the tendency for elements in a topology optimization to converge to a material density of 0 or 1.

Real > 0.0 Defaults 1.0 – general default. 2.0 - for solid dominant structures with member size control and no manufacturing constraints.

DISCRT1D

Discreteness parameter for 1-D elements.

Real > 0.0 Default = DISCRETE

ESLMAX

Maximum number of outer design loops in the design of Multi-body dynamic systems and for nonlinear optimization using ESLM.

Integer > 0 Default = 30

ESLSOPT

Controls the time step screen strategy in the design of multi-body dynamic systems.

Default = 1

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Parameter

Brief Description

Value

ESLSTOL

Controls the tolerance for screening out time steps in the design of multibody dynamic systems.

0.0 < Real < 1.0 Default = 0.3

GBUCK

Controls the global buckling constraint.

YES, NO, 1 or 0 Default = 0

MATINIT

Defines the initial material fraction.

Real between 0.0 and 1.0

MAX_BUCK

Controls the maximum number of Integer > 0 buckling eigenvalues to be considered Default = 15 for each buckling subcase in an optimization problem.

MINDENS

Sets the minimum element material density.

Real > 0.0 Default = 0.01

MINDIM

Specifies the minimum diameter of members formed in a topology optimization.

Real > 0.0 Default = no minimum member size control

MMCHECK

Parameter to ensure a checkerboard- Integer = 0,1 free solution. Default = 0

NESLEXPD

Specifies the number of time steps retained for optimization from each EXPDYN subcase. At each time step, one ESL is generated.

Integer > 0 Default = 20

NESLIMPD

Specifies the number of time steps retained for optimization from each IMPDYN subcase. At each time step, one ESL is generated.

Integer > 0 Default = 20

NESLNLGM

Specifies the number of time steps retained for optimization from each NLGEOM subcase. At each time step, one ESL is generated.

Integer > 0 Default = 1

OBJTOL

Relative convergence criterion.

Real > 0.0 Default = 0.005

OPTMETH

Options to choose the optimization

MFD, SQP, DUAL, BIGOPT

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Parameter

Brief Description

Value

algorithm.

Default = See descriptions

REMESH

Parameter to activate the remeshing process.

Integer = 0,1 Default = 0

SHAPEOPT

Optional parameter to select an alternative shape optimization algorithm.

Default = 1

TMINPLY

Defines the minimum ply thickness allowed for all plies of PCOMP’s selected by DSIZE or DTPL design variable definitions.

0.0 < Real < min(Ti)

Comments 1.

Some of the parameters may also be defined as separate entities in the I/O section of the deck, using the previous (OS3.5) input format. Only one definition is allowed.

2.

This card is represented as an opticontrols in HyperMesh.

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DOPTPRM, APPROX Parameter

Values

Description

APPROX

< FULL or REDUCED > Default = FULL

Approximation type switch for stress/strain responses for shells, composites and 1D elements.

766

When REDUCED is chosen, some stress/strain responses will use the constant force approximation. This method has the benefit of reducing the memory requirement for large optimization problems (many stress/strain responses for many size design variables). Another benefit is the reduction in runtime if the bottleneck occurs due to sensitivity analysis. You are encouraged to try the REDUCED option for the large size optimization model, and, if the FULL option results in the error 832 (Optimization problem is too big to be solved by OptiStruct).

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DOPTPRM, CHECKER Parameter

Values

Description

CHECKER

< 0 or 1 > Default = 0

Checkerboard control option. Use 0 for no checkerboard control. Use 1 for global checkerboard control. This option controls checkerboard-like element wise density distribution. The undesired side effect is that a layer of semi-dense elements will remain at the transition from solid (fully dense domain) to void. To reduce this side effect, you can activate minimum member size control (MEMBSIZ on DTPL) which has built-in checkerboard control. MINDIM can be smaller than the mesh size if a large member size is not desired. Minimum member size control has a 3phase iterative process in which the final phase targets the removal of the semi-dense element layer. If manufacturing constraints are applied, minimum member size control is always activated. However, the final iterative phase will not target the removal of semi-dense elements, as this may have an adverse effect on manufacturing constraint preservation.

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DOPTPRM, DDVOPT Parameter

Values

Description

DDVOPT

< 1, 2, 3 > Default = 1

Discrete Design Variable Option. Use 1 for full discrete design optimization. Use 2 for two-phased approach, a continuous optimization phase followed by a discrete optimization phase (starting from the continuous optimum). Use 3 for a continuous optimization regardless of DDVAL definitions. The bounds will be affected by DDVAL if DDVAL bounds are more restrictive than those defined on DESVAR.

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DOPTPRM, DELSHP Parameter

Values

Description

DELSHP

Real > 0.0 Default = 0.2

Initial fractional move limit for topography/shape design variables. Defined as the fractional difference between the upper and lower bounds. Only the initial value of the move limits can be set. Move limits are automatically adjusted to enhance iterative stability and convergence speed. The move limits for subsequent iterations may not be greater than this initial move limit.

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DOPTPRM, DELSIZ Parameter

Values

Description

DELSIZ

Real > 0 Default = 0.5

Initial fractional move limit for size design variables. Only the initial value of the move limits can be set. Move limits are automatically adjusted to enhance iterative stability and convergence speed. The move limits for subsequent iterations may not be greater than this initial move limit.

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DOPTPRM, DELTOP Parameter

Values

Description

DELTOP

Real > 0 Default = 0.5

Initial fractional move limit for topology and free-size design variables. Only the initial value of the move limits can be set. Move limits are automatically adjusted to enhance iterative stability and convergence speed. The move limits for subsequent iterations may not be greater than this initial move limit.

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DOPTPRM, DESMAX or MAXITER Parameter

Values

Description

DESMAX or

Integer > 0 Default = 30 or if MINDIM is defined, Default = 80

Maximum number of design iterations.

MAXITER

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DOPTPRM, DISCRETE Parameter DISCRETE

Values

Description

Real > 0.0 Defaults 1.0 – general default. 2.0 - for solid dominant structures with member size control and no manufacturing constraints.

Altair Engineering

Discreteness parameter. Influences the tendency for elements in a topology optimization to converge to a material density of 0 or 1. Higher values decrease the number of elements that remain between 0 and 1. Note: Recommended bounds are 0.0 and 2.0 for shells, or 3.0 for solids.

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DOPTPRM, DISCRT1D Parameter

Values

Description

DISCRT1D

Real > 0.0 Default = DISCRETE

Discreteness parameter for 1D elements. Same effect as DISCRETE, but applies only to 1D elements. It is often desirable to have a higher discreteness for 1D elements than for 2D or 3D elements.

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DOPTPRM, ESLMAX Parameter

Values

Description

ESLMAX

Integer > 0 Default = 30

Maximum number of outer design loops in the design of multi-body dynamics systems, and for nonlinear optimization using the equivalent static load method. If 0, then the optimization process is not activated.

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DOPTPRM, ESLSOPT Parameter

Values

Description

ESLSOPT

< 0, 1 > Default = 1

Controls the time step screen strategy in the design of multi-body dynamics systems. 1 – Screens out time steps that do not play an important role in the design of multi-body dynamics systems. 0 – Does not screen out time steps. All of the steps in the multi-body dynamics analysis are involved in the design process. Refer to Equivalent Static Load Method (ESLM) for more information.

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DOPTPRM, ESLSTOL Parameter

Values

Description

ESLSTOL

0.0 < Real < 1.0 Default = 0.3

Controls the tolerance for screening out time steps in the design of multi-body dynamic systems. Valid only when DOPTPRM, ESLSOPT is 1. The smaller value it has, the smaller number of time steps the design process handles, which makes the design process even faster. Too small a value may cause the design process to diverge though. Therefore, if the number of time steps retained by ESLSTOL is less than 10, the 10 most dominant time steps will be involved in the optimization process. If the value is 1.0, this is equivalent to DOPTPRM, ESLSOPT, 0. That is, all of the steps in the multibody dynamic analysis are involved in the design process, which causes more CPU time to be used.

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DOPTPRM, GBUCK Parameter

Values

Description

GBUCK

YES, NO, 1 or 0 Controls global buckling constraint. Default = 0 Use 0, NO, or omit this parameter for no global buckling constraint. Use 1 or YES to activate global buckling constraint. When activated, the global buckling constraint affects those subcases in which buckling eigenvalues (LAMA) are constrained. For these subcases, when this parameter is activated, only a single buckling mode needs to be constrained with a lower bound. The GBUCK parameter will then ensure that all buckling eigenvalues that are less than or equal to the lower bound defined in this constraint will be considered within the optimization problem. More than one buckling eigenvalue constraint (or if the single constraint is not a lower bound) in any buckling subcase will cause termination with an error. The MAX_BUCK parameter on the DOPTPRM card controls the maximum number of buckling modes for each subcase that are considered in the optimization. The EIGRL card referenced in the buckling subcase controls the number of modes calculated at each iteration.

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DOPTPRM, MATINIT Parameter

Values

Description

MATINIT

Real between 0.0 and 1.0

This parameter declares the initial material fraction. For topology optimization runs with mass as the objective, default is 0.9. For runs with constrained mass, the default is reset to the constraint value. If mass is not the objective function and is not constrained, the default is 0.6.

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DOPTPRM, MAX_BUCK Parameter

Values

Description

MAX_BUCK

Integer > 0 Default = 15

Controls maximum number of buckling eigenvalues to be considered for each buckling subcase in the optimization problem. Can only exist if GBUCK exists. Only up to MAX_BUCK eigenvalues are considered for each buckling subcase. If the user-defined MAX_BUCK is less than 15 when auto screening is turned on, MAX_BUCK will be reset to 15. If more buckling modes need to be involved for a problem, explicitly specify MAX_BUCK (MAX_BUCK>15). To reduce the computational cost, OptiStruct automatically and dynamically adjusts the upper bound of the eigenvalue range on the EIGRL card for each buckling subcase at each iteration and only the eigenvalues that are possibly retained in the optimization would be calculated.

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DOPTPRM, MINDENS Parameter

Values

Description

MINDENS

Real > 0.0 Default = 0.01

Minimum element material density. Sets a lower limit on the amount of material that can be assigned to any design element. Extremely low values for this parameter can result in an ill-conditioned stiffness matrix.

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DOPTPRM, MINDIM Parameter

Values

Description

MINDIM

Real > 0.0 Default = no minimum member size control

Specifies the minimum diameter of members formed in a topology optimization. This command is used to eliminate small members.

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DOPTPRM, MMCHECK Parameter

Values

Description

MMCHECK

Integer = 0,1 Default = 0

The use of this parameter, in conjunction with MINDIM, will ensure a checkerboard-free solution, although with the undesired side effect of achieving a solution that involves a large number of semi-dense elements, similar to the result of using CHECKER=1. Therefore, use this parameter only when it is necessary.

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DOPTPRM, NESLEXPD Parameter

Values

Description

NESLEXPD

Integer > 0 Default = 20

This parameter specifies the number of time steps retained for optimization from each EXPDYN subcase. At each time step, one ESL (equivalent static load) is generated. The termination time (TTERM) of the subcase is always retained. If 0, all of the time steps are retained. The total number of time steps is determined by the duration of the subcase (difference in TTERM between current and previous subcases) and animation output control (TA0 and DTA on XSTEP card). While retaining fewer time steps will result in less computational time in the inner loop of the ESL method, very low number of retained time steps could result in many outer loops required or even divergence of the solution in the outer loop.

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DOPTPRM, NESLIMPD Parameter

Values

Description

NESLIMPD

Integer > 0 Default = 20

This parameter specifies the number of time steps retained for optimization from each IMPDYN subcase. At each time step, one ESL (equivalent static load) is generated. The termination time (TTERM) of the subcase is always retained. If 0, all of the time steps are retained. The total number of time steps is determined by the duration of the subcase (difference in TTERM between current and previous subcases) and animation output control (TA0 and DTA on TSTEPNX card). While retaining fewer time steps will result in less computational time in the inner loop of the ESL method, a very low number of retained time steps could result in many outer loops required or even divergence of the solution in the outer loop.

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DOPTPRM, NESLNLGM Parameter

Values

Description

NESLNLGM

Integer > 0 Default = 1

This parameter specifies the number of time steps retained for optimization from each NLGEOM subcase. At each time step, one ESL (equivalent static load) is generated. The termination time (TTERM) of the subcase is always retained. If 0, all of the time steps are retained. The total number of time steps is determined by the duration of the subcase (difference in TTERM between current and previous subcases) and animation output control (TA0 and DTA on NLPARMX card). While retaining fewer time steps will result in less computational time in the inner loop of the ESL method, a very low number of retained time steps could result in many outer loops required or even divergence of the solution in the outer loop.

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DOPTPRM, OBJTOL Parameter

Values

Description

OBJTOL

Real > 0.0 Default = 0.005

Relative convergence criterion. If relative change in the objective function between two design iterations is less than OBJTOL, then optimization stops. A relative change in the objective function of 0.005 is the same as a 0.5% change in the objective function.

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DOPTPRM, OPTMETH Parameter

Values

Description

OPTMETH

< MFD, SQP, DUAL, BIGOPT > Default = See description and Note

Options to choose the optimization algorithm: MFD = Method of feasible directions SQP = Sequential Quadratic Programming DUAL = Dual Optimizer based on separable convex approximation. BIGOPT = Large scale optimization algorithm. The DUAL algorithm should be used for concept level optimization (Topology, free-size and Topography) since such problems typically involve a very large number of design variables. For size and shape optimization, primal methods (MFD and SQP) and BIGOPT are more suitable since the approximate problem typically involves coupled terms due to advanced approximation formulation utilizing intermediate variables and responses. MFD has been and remains the default optimizer. Note: During a run, the corresponding optimization algorithms are automatically selected by OptiStruct based on the optimization type. The use of this parameter will override the defaults.

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DOPTPRM, REMESH Parameter

Values

Description

REMESH

Integer = 0, 1 Default = 0

This parameter specifies if the remeshing process will be activated when the optimization runs into element quality error. 1 – Yes. When optimization runs into element quality error, the remeshing process will be activated to improve element quality. After remeshing is completed, the optimization process will then continue based on the remeshed model. 0 – No. The remeshing process will not be activated regardless of whether element quality error occurs. Note: 1.

When an optimization run results in element quality error (usually during Shape, Free-shape or Topography optimization), OptiStruct calls HyperMesh in batch mode. The model from the latest optimization iteration is automatically loaded into HyperMesh and remeshing is performed to improve element quality. HyperMesh, then automatically exports a new input deck named *_rmsh###.fem (### = 001, 002, 003, represents the remeshing round number) that is loaded into OptiStruct to continue the optimization run with the remeshed model.

2.

When an element quality error occurs, OptiStruct 12.0.210 will automatically check the HyperMesh version. If HyperMesh version 12.0.110 or later is installed, the new function *remesh_optistruct will be called to accomplish the remeshing process. For all other versions (HyperMesh 12.0 or earlier) an old function, previously used in 12.0, is called.

3.

Altair Engineering

Installing the latest version of HyperMesh (12.0.110 or later) is recommended to access all the latest improvements in the *remesh_optistruct function.

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DOPTPRM, SHAPEOPT Parameter

Values

Description

SHAPEOPT

Integer = 1, 2 Default = 1

Defines an optional parameter to select an alternative shape optimization algorithm. This algorithm can be selected when non-moving shapes are encountered in the optimization. 1 – Default algorithm for shape optimization. 2 – Selects the alternate algorithm for shape optimization. If discrete design variables are present, it is recommended to use this parameter along with design optimization parameter, DDVOPT=2.

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DOPTPRM, TMINPLY Parameter

Values

Description

TMINPLY

0.0 < Real < min(Ti)

Defines the minimum ply thickness allowed for all plies of PCOMPs selected by DSIZE or DTPL design variable definitions. Should be smaller than the minimum of all relevant Ti on the selected PCOMPs. Check its compatibility with volume constraint if applied. Note also that for volume fraction calculation, TMINPLY is not treated as none design volume in the same way as T0 for regular PSHELLs. Buckling responses for composite structures may be considered for free-size and topology optimization when this parameter is non-zero.

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DPHASE Bulk Data Entry DPHASE – Dynamic Load Phase Lead Description Defines the phase lead term in the equation of the dynamic loading function. DPHASE is used in conjunction with RLOAD1 and RLOAD2 entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DPHASE

SID

P1

C1

TH1

P2

C2

TH2

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DPHASE

5

33

1

3.4

34

1

3.4

Field

Contents

SID

Identification number.

(9)

(10)

No default (Integer > 0) P1, P2

Grid or scalar point identification number. No default (Integer > 0)

C1, C2

Component number. No default (Integers 1 through 6, or 0 for scalar points)

TH1, TH2

Phase lead

in degrees.

No default (Real)

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Comments 1.

One or two dynamic load phase lead terms may be defined on a single entry.

2.

SID must be referenced on a RLOAD1 or RLOAD2 entry for the formulae that define how the phase lead is used.

3.

A DAREA entry should be used to define a load at P# and C#.

4.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

5.

This card is represented as a constraint load in HyperMesh.

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DRAPE Bulk Data Entry DRAPE – Draping Information for Ply-based Composite Definition Description Defines the draping data for plies used in ply-based composite definition. Format (1)

(2)

(3)

(4)

(5)

DRAPE

ID

DTYPE1

DID1

T1

THETA1

DTYPE2

DID2

T2

THETA2

(6)

(7)

(8)

(9)

(10)

...

Field

Contents

ID

Unique draping identification number. No default (Integer > 0)

DTYPE#

Entity type. No default (ELEM, SET, or ALL)

DID#

Entity number. Must refer to an element (for ELEM) or SET (for SET) bulk data entry. Must be blank for ALL. No default (Integer > 0 or blank)

T#

Thinning factor. Default = 1.0 (Real or blank)

THETA#

Angle variation. Default = 0.0 (Real or blank)

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DREPADD Bulk Data Entry DREPADD – Addition of Response Selection to be Reported without being Constrained Description Creates a combination of several DREPORT sets that can be referenced by a subcase. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DREPAD D

DRID

DR1

DR2

DR3

Dr4

DR5

DR6

DR7

DR8

etc.

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

DREPAD D

101

10

20

30

Field

Contents

DRID

DREPADD identification number.

(6)

(10)

(Integer > 0) DRi

DREPORT ID number. (Integer > 0)

Comments 1.

The DREPADD entry is selected by a REPSUB or REPGLB in the Subcase Information section.

2.

All DRi must be unique.

3.

All DRID must be unique with respect to all DRi (DREPORT IDs).

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DREPORT Bulk Data Entry DREPORT – Report Unconstrained Responses Description The DREPORT card is used in the bulk data section to report responses, defined by DRESP1, DRESP2 and DRESP3 cards, to the output file, which are not constrained or used as the objective function, as defined by the optimization problem. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

DREPOR T

DRID

RID

LALLOW

UALLOW

NL

NU

(8)

(9)

(10)

(9)

(10)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

DREPOR T

1

1

1.0

5.0

2

5

(8)

Associated Cards (1)

(2)

(3)

(4)

DRESP1

1

TOPN

DISP

(5)

Field

Contents

DRID

Report identification number.

(6)

(7)

(8)

3

4668

(Integer > 0) RID

DRESP1, DRESP2, or DRESP3 identification number. (Integer > 0)

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Field

Contents

LALLOW

Optional lower bound on response for reporting purposes. (Real or blank)

UALLOW

Optional upper bound on response for reporting purposes. (Real or blank)

NL

Optional number of lowest responses to report. See comment 3. (Integer or blank)

NU

Optional number of highest response to report. See comment 3. (Integer or blank)

Comments 1.

The DREPORT DRID is selected in the Subcase Information section by the REPSUB or REPGLB cards and/or referenced by the DREPADD card.

2.

For any DRID, the associated RID can be referenced only once.

3.

If NL=1, only the lowest response in the range [LALLOW, UALLOW] (if specified) is reported. If NU=1, only the highest response in the range [LALLOW, UALLOW] (if specified) is reported.

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DRESP1 Bulk Data Entry DRESP1 – Optimization Design Response Description A response, or set of responses, that are the result of a design analysis iteration. These responses can be used as a design objective or as design constraints. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DRESP1

ID

LABEL

RTYPE

PTYPE

REGION

ATTA

ATTB

ATT1

ATT2

…

…

…

…

…

…

…

EXC L

EID1

EID2

EID3

EID4

EID5

EID6

EID7

EID8

…

…

…

EXTN

(10)

RANDID

Examples

The maximum principal stress in PSHELL PID 1 (1)

(2)

(3)

(4)

(5)

DRESP1

99

SS11

STRESS

PSHELL

(1)

(2)

(3)

(4)

(5)

DRESP1

99

SS11

STRESS

PSHELL

(6)

(7)

(8)

7

(9)

(10)

1

or

798

(6)

(7)

(8)

SMP1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(9)

(10)

1

Altair Engineering

The maximum principal stress in elements 2001-2004 (1)

(2)

(3)

(4)

(5)

DRESP1

88

SS11

STRESS

ELEM

2002

2003

2004

(6)

(7)

(8)

7

(9)

(10)

2001

The combined mass of PSHELL PID 2, 4, 7 (1)

(2)

(3)

(4)

(5)

DRESP1

77

TMASS

MASS

PSHELL

4

7

(6)

(7)

(8)

(9)

SUM

2

(10)

Field

Contents

ID

Response identification number. Each DRESP1 card must have a unique ID. No default (Integer > 0)

LABEL

User-defined name for the response. No default (Character)

RTYPE

Type of response that is defined – mass, volume, freq, disp, stress, etc. No default (See Responses and attributes for DRESP1 card for full list of response types)

PTYPE

If a property response, then PTYPE is the property type, for example, PSHELL. It is used in conjunction with ATT1 to identify the unique property. If an element response, then PTYPE = ELEM. It is used in conjunction with ATTi to identify the element IDs. For material responses, PTYPE is MAT and ATTi are material IDs. For grid responses, PTYPE is blank and ATTi are grid IDs. (See Responses and attributes for DRESP1 card for further information). No default (ELEM, MAT, PSHELL, PCOMP, PCOMPG, PLY, PROD, PSOLID, PELAS, PBAR, PBARL, PBEAM, PBEAML, PFBODY, MBREQM, MBREQE, or blank)

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Field

Contents

REGION

Region identifier. Default = blank (Integer > 0 or blank, See comment 2)

ATTA, ATTB

The attributes of a response where further definition is required. No default (See Responses and attributes for DRESP1 card for further information)

ATTi

PID, MID, EID, MBREQM ID, MBREQE ID, PFBODY ID or Grid ID as referenced by PTYPE and RTYPE. (See Responses and attributes for DRESP1 card for further information). No default (Integer > 0)

EXCL

EXCL flag indicating that IDs of elements excluded from the response follow.

EIDi

Element ID. For these elements, no response will be generated. No default (Integer > 0)

EXTN

EXTN flag indicating that extended attribute definition follows. RANDID is currently supported as an extended attribute definition and is the RANDPS ID to which the response applies. See comments 30 and 31.

Responses and Attributes Center of Gravity and Moment of Inertia Item Codes Static Stress/Strain Item Codes Static Stress Item Codes for Bar Elements using PBARL, PBEAML Properties Static Stress/Strain Item Codes for Composites Static Failure Item Codes for Composites Static Force Item Codes Frequency Response Displacement, Velocity, and Acceleration Item Codes Frequency Response Pressure Item Codes Frequency Response Stress/Strain Item Codes Frequency Response Force Item Codes PSD/RMS Displacement, Velocity, and Acceleration Item Codes PSD/RMS Pressure Item Codes PSD/RMS Stress/Strain Item Codes MBD Displacement Item Codes

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MBD Velocity/Acceleration Item Codes MBD Force Item Codes Comments 1.

VOLFRAC is equivalent to MATFRAC in previous versions of OptiStruct. MATFRAC is still supported.

2.

Responses of the same RTYPE with the same region identifier are grouped together into the same region. If the region identifier is blank, elements identified by an ATTi field (when PTYPE = ELEM) are grouped together into the same region, but for properties or materials, each property or material identified by an ATTi field will form its own region. Refer to the User's Guide section Constraint Screening for a more detailed explanation. For composite responses (RTYPE = CSTRESS, CSTRAIN, CFAILURE; PTYPE = PCOMP, PCOMPG), each ply is given its own region. However, if a region identifier is defined explicitly for the entire lay-up (ATTB=ALL), this region identifier applies to all plies. It is not recommended to do this.

3.

DRESP1 entries must have unique identification numbers with respect to DRESP2 and DRESP3 entries.

4.

In normal modes analysis, the frequencies are in Hz (cycles/time).

5.

The total displacement can be requested using ATTA=7; the total rotation using ATTA=8.

6.

PTYPE = PCOMP, PCOMPG can be selected for RTYPE = STRESS or RTYPE = STRAIN, in which case homogenized stresses or strains are used. RTYPE = CSTRESS or RTYPE = CSTRAIN should be used instead for composite responses.

7.

Stresses are element stresses. For CBAR, CBEAM, stresses are normal (axial) stresses for the element.

8.

VOLFRAC and MASSFRAC can only be applied to topology design domains. OptiStruct will terminate with an error if this is not the case.

9.

MASS, MASSFRAC, COG and INERTIA responses are not available for PBUSH, PDAMP, PELAS, PGAP, PVISC, and PWELD.

10. VOLUME and VOLFRAC responses are not available for CONM2, PDAMP, PELAS, PGAP, PMASS, and PVISC. 11. The VOLUME of a single CWELD element is 1.0. The response then is the number of welds. 12. WCOMP, WFREQ, COMB require the definition of WEIGHT and/or MODEWEIGHT subcase commands. If WEIGHT or MODEWEIGHT are not defined, the following defaults apply: RTYPE

Applicable subcase commands Default

WCOMP

WEIGHT in static subcases

WEIGHT = 1.0 for all static subcases.

WFREQ

MODEWEIGHT in normal modes subcase

MODEWEIGHT (1) = 1.0 in most cases for topology optimization.

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RTYPE

Applicable subcase commands Default MODEWEIGHT (7) = 1.0 if no SPC is defined for the subcase, EIGRL does not define a V1 > 0.0, and it is solving for more than 6 modes or all modes below an upper bound.

COMB

WEIGHT in static subcases

WEIGHT = 1.0 for all static subcases.

MODEWEIGHT in normal modes subcase 13. CSTRESS, CSTRAIN, and CFAILURE are only available for PCOMP, PCOMPG. ATTB = # refers to a ply on a PCOMP. Example: DRESP1, 12, PLY23, CSTRESS, PCOMP, SMAP, 23, 43. ATTB = G# refers to a global ply on a PCOMPG. Example: DRESP1, 12, GLOBAL11, CFAILURE, PCOMPG, HILL, G11, 17. ATTB must be blank for PLY response type. 14. STRAIN responses not applicable for CELAS. 15. Composite Stress/Strain item codes S1Z and S2Z for Shear-1Z and Shear-2Z are for CSTRESS only, these are not available for CSTRAIN. 16. Lower bound constraints are not allowed on von Mises stress. 17. LABEL must begin with an alphabetical character. 18. Responses that do not exist are ignored, and a warning is issued. 19. EXCL only applies to RTYPE = STRESS, STRAIN, FORCE, CSTRESS, CSTRAIN, CFAILURE, FRSTRS, FRSTRN, and FRFORC response types. 20. For RTYPE = MASS, MASSFRAC, VOLUME, VOLFRAC, COG, INERTIA, BEADFRAC, and COMP; ATTi can only be blank if PTYPE is also blank. ATTi blank means that all relevant entities are included. They all belong to the same region for constraint screening. 21. For RTYPE=STRESS, STRAIN, FORCE, FRSTRS, FRSTRN, FRFORC, CSTRESS, CSTRAIN, and CFAILURE; ATTi can only be blank if PTYPE is a property type (not allowed when PTYPE is "ELEM"). ATTi blank means that all entities of the defined PTYPE are selected. 22. For RTYPE = MASS, MASSFRAC, MBMASS, VOLUME, VOLFRAC, COG, MBCOG, INERTIA, MBINER, COMP, and BEADFRAC; ATTB = COMB results in the creation of a single response for the combination of all ATTi entities. 23. For RTYPE=MASS, MBMASS, VOLUME, MBCOG, MBINER, COMP, MASSFRAC, and VOLFRAC; ATTB=SUM is the same as ATTB=COMB. 24. For RTYPE = FRDISP, FRVELO, FRACCL, FRSTRS, FRSTRN, FRFORC, FRERP, PSDDISP, PSDVELO, PSDACCL, and PSDPRES the following functions can be applied through the character input on ATTB. The formulas are applied across all loading frequencies. The use of MAX can be very inefficient computationally and it is better to leave ATTB blank and let constraint screening take care of it.

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Function

Description

SUM

Sum of arguments

AVG

Average of arguments

SSQ

Sum of square of arguments

RSS

Square root of sum of squares of arguments

MAX

Maximum of arguments

MIN

Minimum of arguments

SUMABS

Sum of absolute value of arguments

AVGABS

Average of absolute value of arguments

MAXABS

Maximum of absolute arguments

MINABS

Minimum of absolute value of arguments

Formula

25. For RTYPE = INERTIA, the Moment of Inertia is with reference to the center of gravity. The Moment of Inertia of the whole model is referred to the center of gravity of the whole model. The Moment of Inertia of each property or material is referred to the center of gravity of that property or material. 26. For acoustic optimization, pressure responses are defined using RTYPE=FRPRES; however, it is acceptable to define a pressure response on a fluid grid as RTYPE=FRDISP with ATTA as one of M-TX, R-TX or I-TX, internally it will be converted to FRPRES (with M-TX/R-TX/ I-TX interpreted as M-PRES/R-PRES/I-PRES). Likewise, RTYPE=PSDDISP or RMSDISP are accepted in place of PSDPRES or RMSPRES, respectively. 27. For RTYPE = MBDIS, MBVEL, MBACC, or MBFRC, the PTYPE must be MBREQM. These four response types must be defined using MARKERs, and requested by MBREQM. For RTYPE = MBEXPR, the PTYPE must be MBREQE. The response must be requested by MBREQE. For

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RTYPE = MBMASS, MBCOG, or MBINER, the PTYPE must be PFBODY. 28. MBREQE referenced in DRESP1 must have single expression although MBREQE allows up to 6 expressions for analysis output. 29. MBD system level responses must be scalar quantities. Thus, THE ATTB field must have one of the following - MAX, MIN, MAXABS, or MINABS so that time dependent vectors can be converted to scalar quantities. 30. Legacy data with RANDPS ID defined on the PTYPE or ATTB entry is also supported. 31. A blank field for RANDID on the EXTN extended attributes entry indicates that all RANDPS cards in the input file will be used. 32. “Cluster Size” represents the number of elements around the specified element whose stress contributions are included in the calculation of the individual element’s stress contribution. The contributions of the elements in the cluster are weighted based on their distance to the center of the cluster (Available for Shell and Solid elements). Weighting element stress contributions using “Cluster Size” is generally useful in models with stress gradients or stress concentrations in the design space. If the stress distribution within the selected element cluster is uniform, there may not be any significant difference in the stress response. A separate result type “Element Stress Cluster” is available in the _s#.h3d file and stress results based on element cluster response(s) can be viewed in HyperView by selecting Element Stresses Cluster in the Result type: drop-down menu. 33. This card is represented as an optimization response in HyperMesh.

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DRESP1 - Responses and Attributes Response s

RTYPE

PTYPE

ATTA

ATTB

ATTi

EXTN

MASS

PTYPE, "MAT", or blank

-

COMB**, SUM or blank

PID, MID or blank*

-

Fraction of MASSFR PTYPE, mass AC "MAT", or blank

-

COMB**, SUM, or blank

PID, MID or blank*

-

Volume

Mass

VOLUME

PTYPE, "MAT", or blank

-

COMB**, SUM or blank

PID, MID or blank*

-

Fraction of VOLFRA design C volume

PTYPE, "MAT", or blank

-

COMB**, SUM, or blank

PID, MID or blank*

-

Center of Gravity

PTYPE, "MAT", or blank

Center of Gravity item code

COMB** or blank

PID, MID or blank*

-

Moment of INERTIA PTYPE, Inertia "MAT", or blank

Moment of Inertia item code

COMB** or blank

PID, MID or blank*

-

COG

Complianc e of a static subcase

COMP

PTYPE, "MAT", or blank

-

COMB**, SUM or blank

PID, MID or blank*

-

Static displaceme nt

DISP

-

Static displacement Component

-

Grid ID

-

Mode shape

DISP

-

Component

Mode #

Grid ID

-

Frequency of a normal mode

FREQ

-

Normal mode #

-

-

-

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Response s

RTYPE

PTYPE

ATTA

ATTB

ATTi

EXTN

LAMA

-

Buckling mode #

-

-

-

Static STRESS stress of homogeno us material

PTYPE or "ELEM"

Static stress item code

Cluster Size ****** or blank

PID, EID or blank***

-

Static STRAIN strain of homogeno us material

PTYPE or "ELEM"

Static strain item code

-

PID, EID or blank***

-

Static stress in a composite lay-up

CSTRES "PCOMP", S "PCOMPG" , "PLY", or "ELEM"

Composite Stress item code

ALL, Ply No. or ‘G#**** (Default = 1) or blank*****

PID, EID, Ply ID, or blank***

-

Static strain in a composite lay-up

CSTRAI "PCOMP", N "PCOMPG" , "PLY", or "ELEM"

Composite Strain item code

ALL, Ply No. or ‘G#**** (Default = 1) or blank*****

PID, EID, Ply ID, or blank***

-

Static failure in a composite lay-up

CFAILU RE

"PCOMP", "PCOMPG" , "PLY", or "ELEM"

Composite Failure item code

ALL, Ply No. or ‘G#**** (Default = 1) or blank*****

PID, EID, Ply ID, or blank***

-

Static force

FORCE

PTYPE or "ELEM"

Static force item code

-

PID, EID or blank***

-

Frequency response displaceme nt

FRDISP

-

Frequency Response displacement component

Frequency Value. (Blank, Real > 0.0 or Character)

Grid ID

-

Frequency response velocity

FRVELO

-

Frequency Response velocity component

Frequency Value (Blank, Real > 0.0 or Character)

Grid ID

-

Eigenvalue of a buckling mode

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Response s

RTYPE

Frequency FRACCL response acceleratio n

PTYPE

ATTA

ATTB

ATTi

EXTN

-

Frequency Response acceleration component

Frequency Value (Blank, Real > 0.0 or Character)

Grid ID

-

Frequency response stress

FRSTRS

PTYPE or "ELEM"

Frequency Response Stress item code

Frequency Value (Blank, Real > 0.0 or Character)

PID, EID or blank***

-

Frequency response strain

FRSTRN

PTYPE or "ELEM"

Frequency Response Strain item code

Frequency Value (Blank, Real > 0.0 or Character)

PID, EID or blank***

-

Frequency response force

FRFORC

PTYPE or "ELEM"

Frequency Response Force item code

Frequency Value (Blank, Real > 0.0 or Character)

PID, EID or blank***

-

Frequency response equivalent radiated power

FRERP

-

-

Frequency Value (Blank, Real > 0.0 or Character)

Panel ID

FRPRES

-

M-PRES, RPRES or IPRES

Frequency Value. (Blank, Real > 0.0 or Character)

Grid ID

-

PSD PSDDIS displaceme P nt

-

PSD/RMS item Frequency Value. (Blank, Real > code

GRID ID

RANDPS ID

PSD velocity

PSDVEL O

-

PSD/RMS item (Blank, Real > code 0.0 or Character)

GRID ID

RANDPS ID

PSD PSDACC acceleratio L n

-

PSD/RMS item Frequency Value. (Blank, Real > code

GRID ID

RANDPS ID

PSD stress PSDSTR S

PTYPE or

PID, EID or blank***

RANDPS ID

Acoustic pressure

Altair Engineering

0.0 or Character) Frequency Value.

0.0 or Character)

PSD/RMS item code

Frequency Value

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

807

Response s

RTYPE

PTYPE

ATTA

"ELEM"

ATTB

ATTi

EXTN

(Blank, Real > 0.0 or Character)

PSD strain

PSDSTR N

PTYPE or "ELEM"

PSD/RMS item code

Frequency Value (Blank, Real > 0.0 or Character)

PID, EID or blank***

RANDPS ID

PSD pressure

PSDPRE S

-

PRES

Frequency Value. (Blank, Real > 0.0 or Character)

GRID ID

RANDPS ID

RMS RMSDIS displaceme P nt

-

PSD/RMS item code

-

GRID ID

RANDPS ID

RMS velocity

RMSVEL O

-

PSD/RMS item code

-

GRID ID

RANDPS ID

RMS acceleratio n

RMSAC CL

-

PSD/RMS item code

-

GRID ID

RANDPS ID

RMS stress RMSSTR S

PTYPE or "ELEM"

PSD/RMS item code

-

PID, EID or blank***

RANDPS ID

RMS strain RMSSTR N

PTYPE or "ELEM"

PSD/RMS item code

-

PID, EID or blank***

RANDPS ID

RMSPRE S

-

PRES

-

GRID ID

RANDPS ID

Static WCOMP compliance weighted across all

-

-

-

-

-

RMS pressure

808

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Response s

RTYPE

PTYPE

ATTA

ATTB

ATTi

EXTN

Frequency weighted across reciprocal eigenvalue s

WFREQ

-

-

-

-

-

Combined static compliance and frequency index (Combined Complianc e Index)

COMB

-

-

-

-

-

Bead discretene ss fraction for topograph y design space (0.0 < BEADFRAC < 1.0)

BEADFR AC

-

-

COMB** or blank

DTPGID or blank*

-

MBD displaceme nt

MBDIS

MBREQM

MBD Displacement item code

MAX, MIN, MAXABS, MINABS

MBREQM ID

-

MBD velocity

MBVEL

MBREQM

MBD Velocity item code

MAX, MIN, MAXABS, MINABS

MBREQM ID

-

MBD acceleratio n

MBACC

MBREQM

MBD Acceleration item code

MAX, MIN, MAXABS, MINABS

MBREQM ID

-

MBD force

MBFRC

MBREQM

MBD Force

MAX, MIN,

MBREQM ID

-

subcases

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

809

Response s

RTYPE

PTYPE

ATTA

ATTB

item code

MAXABS, MINABS

ATTi

EXTN

MBD expression

MBEXPR

MBREQE

-

-

MBREQE ID

-

Mass of flexible body

MBMAS S

PFBODY

-

COMB, SUM or blank

PFBODY ID

-

Center of gravity of flexible body

MBCOG

PFBODY

Center of Gravity item code

COMB, SUM or blank

PFBODY ID

-

Moment of inertia of flexible body

MBINER

PFBODY

Moment of Inertia item code

COMB, SUM or blank

PFBODY ID

-

Fatigue results

FATIGU E

PTYPE or "ELEM"

LIFE, DAMAGE or FOS

-

PID, EID or blank***

-

TEMP

-

-

-

Grid ID

-

SPCFOR CE

-

-

Grid ID

-

GPFORC E

Grid ID

-

EID

-

Temperatu re SPC Forces (Reaction forces/ moments) Grid point force balance results

Component ID (1-6) – Degrees of Freedom

Component ID (1-6) – Degrees of Freedom

*

ATTi can only be blank when PTYPE is also blank, and means that all relevant entities will be included. See comment 20 on the DRESP1 page.

**

ATTB = COMB – Response represents a single response for the combination of all

810

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Response s

RTYPE

PTYPE

ATTA

ATTB

ATTi

EXTN

ATTi entities. See comment 22 on the DRESP1 page. ***

ATTi can only be blank when a property type is defined in the PTYPE field (not allowed for "ELEM"), and means that all entities of the defined property type will be selected. See comment 21 on the DRESP1 page.

****

ATTB = G# – # is the number of the global ply defined on a PCOMPG. See comment 13 on the DRESP1 page.

*****

ATTB must be Blank for PLY response type. See comment 13 on the DRESP1 page.

******

ATTB = Cluster Size represents the number of elements in a cluster for which Stress Constraints need to be defined. See comment 32 on the DRESP1 page.

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

811

DRESP1 - Static Stress/Strain Item Codes Element

Stress/Strain Item

ASCII Code

Number Code *

CELAS

Stress/Strain

S

2

CROD

Both ends

SAB

-

End A

SA

2

End B

SB

2

All stresses/strains

SALL

-

End A pt. C

SAC

2

End A pt. D

SAD

3

End A pt. E

SAE

4

End A pt. F

SAF

5

End B pt. C

SBC

10

End B pt. D

SBD

11

End B pt. E

SBE

12

End B pt. F

SBF

13

Max end A

SAMAX

7

Max end B

SBMAX

14

CBAR**

812

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CBEAM**

All stresses/strains

SALL

-

End A pt. C

SAC

4

End A pt. D

SAD

5

End A pt. E

SAE

6

End A pt. F

SAF

7

End B pt. C

SBC

104

End B pt. D

SBD

105

End B pt. E

SBE

106

End B pt. F

SBF

107

Max end A

SAMAX

8

Max end B

SBMAX

108

CSHEAR

All Solid elements

Maximum Shear

SHMAX

2

Average Shear

SHAVG

3

Safety Margin

SHMRG

4

von Mises

SVM

Max Principal Stress

SMP

Major Principal

SMAP

8

Mid Principal

SMDP

16

Altair Engineering

13

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

813

All Shell elements

814

Minor Principal

SMIP

22

Normal X

SXX

6

Normal Y

SYY

14

Normal Z

SZZ

20

Shear XY

SXY

7

Shear YZ

SYZ

15

Shear XZ

SXZ

21

Equivalent Plastic Strain

PLAS

-

von Mises both surfaces

SVMB

-

Major Principal both surfaces

SMPB

-

von Mises 1

SVM1

9

von Mises 2

SVM2

17

Major Principal 1

SMP1

7

Major Principal 2

SMP2

15

Minor Principal both surfaces

SMIPB

-

Minor Principal 1

SMIP1

8

Minor Principal 2

SMIP2

16

Normal X both surfaces

SXB

-

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Normal X 1

SX1

3

Normal X 2

SX2

11

Normal Y both surfaces

SYB

-

Normal Y 1

SY1

4

Normal Y 2

SY2

12

Shear XY both surfaces

SXYB

-

Shear XY 1

SXY1

5

Shear XY 2

SXY2

13

Equivalent Plastic Strain both surfaces

PLASB

-

Equivalent Plastic Strain 1

PLAS1

-

Equivalent Plastic Strain 2

PLAS2

-

*OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended that the OptiStruct ASCII item codes be used. **For Bar elements that reference PBARL, PBEAML, it is recommended that the special stress item codes listed under Stress Item Codes for Bar Elements using PBARL, PBEAML Properties be used. Stress/strain items listed here for CBAR, CBEAM elements using PBAR, PBEAM, PBARL, or PBEAML properties include only normal stress/strain.

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

815

DRESP1 - Static Stress Item Codes for Bar Elements using PBARL, PBEAML Properties The evaluation stresses (normal, shear, and von Mises) for each bar element are listed in the links provided below. The shear stress includes torsion and shear. Bar Element Types BAR element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

S1N S2N S3N S4N

816

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SNMAX

S8S

S8V

SSMAX

SVMAX

BOX element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S1N

S1S

S1V

S2N

S2S

S2V

S3N

S3S

S3V

S4N

S4S

S4V

S5S

S5V

S6S

S6V

S7S

S7V

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

817

Normal Stress

SNMAX

Shear Stress

von Mises Stress

S8S

S8V

S9S

S9V

S10S

S10V

S11S

S11V

S12S

S12V

SSMAX

SVMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. BOX1 element type

C ross-sectional dimensions and stress constraint evaluation points

818

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S1N

S1S

S1V

S2N

S2S

S2V

S3N

S3S

S3V

S4N

S4S

S4V

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S9S

S9V

S10S

S10V

S11S

S11V

S12S

S12V

SSMAX

SVMAX

SNMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. CHAN element type

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

819

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S9S

S9V

SSMAX

SVMAX

S1N S2N S3N S4N

SNMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number

820

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

refers to stress recovered in the xz plane. CHAN1 element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress Shear Stress

von Mises Stress

S1N S2N S3N S4N

SNMAX

Altair Engineering

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S9S

S9V

SSMAX

SVMAX

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

821

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. CHAN2 element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S9S

S9V

S1N S2N S3N S4N

822

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SNMAX

SSMAX

SVMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. CROSS element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S1N

S1V

S2N

S2V

S3N

S3V

S4N

S4V

Altair Engineering

S5S

S5V

S6S

S6V

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

823

SNMAX

S7S

S7V

S8S

S8V

SSMAX

SVMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. H element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S1N S2N S3N S4N

824

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SNMAX

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S9S

S9V

SSMAX

SVMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. HAT element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S1N S2N S3N S4N

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

825

SNMAX

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S9S

S9V

S10S

S10V

S11S

S11V

S12S

S12V

S13S

S13V

S14S

S14V

S15S

S15V

SSMAX

SVMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. I element type

826

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S9S

S9V

SSMAX

SVMAX

S1N S2N S3N S4N

SNMAX

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

827

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. I1 element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S9S

S9V

S1N S2N S3N S4N

828

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SNMAX

SSMAX

SVMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. L element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S1N S2N S3N S4N

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

829

SNMAX

SSMAX

SVMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. ROD element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

S1N

S1S

S2N

S2S

S3N

S3S

S4N

S4S

von Mises Stress

S5V The location of point 5 will be determined by varying the the maximum von Mises stress.

830

from 0 to 360 degrees to find

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

T element type

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

SSMAX

SVMAX

S1N S2N S3N S4N

SNMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. T1 element type

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

831

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

SSMAX

SVMAX

S1N S2N S3N S4N

SNMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. T2 element type

832

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

SSMAX

SVMAX

S1N S2N S3N S4N

SNMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane. TUBE element type

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

833

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

S1N

S1S

S2N

S2S

S3N

S3S

S4N

S4S

von Mises Stress

S5V The location of point 5 will be determined by varying the the maximum von Mises stress.

from 0 to 360 degrees to find

Z element type

834

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

C ross-sectional dimensions and stress constraint evaluation points

Evaluation Stresses Normal Stress

Shear Stress

von Mises Stress

S5S

S5V

S6S

S6V

S7S

S7V

S8S

S8V

S9S

S9V

SSMAX

SVMAX

S1N S2N S3N S4N

SNMAX

Several stress recovery points are coincident (for example, 1 and 5, 2 and 6). In these

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

835

cases, the lower number refers to stress recovered in the xy plane and the higher number refers to stress recovered in the xz plane.

836

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DRESP1 - Frequency Response Force Item Codes Element

Response

Component ASCII code Number code*

CELAS

Force

Real

R-F

2

Imaginary

I-F

3

Magnitude

M-F

2

Phase

P-F

3

Real

R-FA

2

Imaginary

I-FA

3

Magnitude

M-FA

2

Phase

P-FA

3

Real

R-FA

2

Imaginary

I-FA

3

Magnitude

M-FA

2

Phase

P-FA

3

Real

R-FB

4

Imaginary

I-FB

5

Magnitude

M-FB

4

Phase

P-FB

5

Real

R-FA

2

Imaginary

I-FA

3

CDAMP

CVISC

Force

Axial force

Torque

CROD

Force at end A

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

837

Force at end B

CBAR/ CBEAM

Bending at end A plane 1

Bending at end A plane 2

Bending at end B plane 1

Bending at end B plane 2

838

Magnitude

M-FA

2

Phase

P-FA

3

Real

R-FB

Imaginary

I-FB

Magnitude

M-FB

Phase

P-FB

Real

R-MA1

2

Imaginary

I-MA1

10

Magnitude

M-MA1

2

Phase

P-MA1

10

Real

R-MA2

3

Imaginary

I-MA2

11

Magnitude

M-MA2

3

Phase

P-MA2

11

Real

R-MB1

4

Imaginary

I-MB1

12

Magnitude

M-MB1

4

Phase

P-MB1

12

Real

R-MB2

5

Imaginary

I-MB2

13

Magnitude

M-MB2

5

Phase

P-MB2

13

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Shear at end A plane 1

Shear at end A plane 2

Real

R-SA1

6

Imaginary

I-SA1

14

Magnitude

M-SA1

6

Phase

P-SA1

14

Real

R-SA2

7

Imaginary

I-SA2

15

Magnitude

M-SA2

7

Phase

P-SA2

15

R-FA

8

Imaginary

I-FA

16

Magnitude

M-FA

8

Phase

P-FA

16

Real

R-TA

9

Imaginary

I-TA

17

Magnitude

M-TA

9

Phase

P-TA

17

Real

R-SB1

Imaginary

I-SB1

Magnitude

M-SB1

Phase

P-SB1

Real

R-SB2

Imaginary

I-SB2

Axial force at end A Real

Torque at end A

Shear at end B plane 1

Shear at end B plane 2

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

839

Magnitude

M-SB2

Phase

P-SB2

Axial force at end B Real

Torque at end B

CBUSH

Force X

Force Y

Force Z

840

R-FB

Imaginary

I-FB

Magnitude

M-FB

Phase

P-FB

Real

R-TB

Imaginary

I-TB

Magnitude

M-TB

Phase

P-TB

Real

R-FX

2

Imaginary

I-FX

8

Magnitude

M-FX

2

Phase

P-FX

8

Real

R-FY

3

Imaginary

I-FY

9

Magnitude

M-FY

3

Phase

P-FY

9

Real

R-FZ

4

Imaginary

I-FZ

10

Magnitude

M-FZ

4

Phase

P-FZ

10

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Moment X

Moment Y

Moment Z

CSHEAR

Force 4 to 1

Force 2 to 1

Force 1 to 2

Altair Engineering

Real

R-MX

5

Imaginary

I-MX

11

Magnitude

M-MX

5

Phase

P-MX

11

Real

R-MY

6

Imaginary

I-MY

12

Magnitude

M-MY

6

Phase

P-MY

12

Real

R-MZ

7

Imaginary

I-MZ

13

Magnitude

M-MZ

7

Phase

P-MZ

13

Real

R-F41

2

Imaginary

I-F41

10

Magnitude

M-F41

2

Phase

P-F41

10

Real

R-F21

3

Imaginary

I-F21

11

Magnitude

M-F21

3

Phase

R-F21

11

Real

R-F12

4

Imaginary

I-F12

12

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

841

Force 3 to 2

Force 2 to 3

Force 4 to 3

Force 3 to 4

Force 1 to 4

Kick Force on 1

842

Magnitude

M-F12

4

Phase

P-F12

12

Real

I-F32

5

Imaginary

I-F32

13

Magnitude

M-F32

5

Phase

P-F32

13

Real

R-F23

6

Imaginary

I-F23

14

Magnitude

M-F23

6

Phase

P-F23

14

Real

R-F43

7

Imaginary

I-F43

15

Magnitude

M-F43

7

Phase

P-F43

15

Real

R-F34

8

Imaginary

I-F34

16

Magnitude

M-F34

8

Phase

P-F34

16

Real

R-F14

9

Imaginary

I-F14

17

Magnitude

M-F14

9

Phase

P-F14

17

Real

R-KF1

18

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Shear Flow 12

Kick Force on 2

All Shell Elements

Membrane force X

Membrane force Y

Membrane shear force XY

Altair Engineering

Imaginary

I-KF1

26

Magnitude

M-KF1

18

Phase

P-KF1

26

Real

R-SH12

19

Imaginary

I-SH12

27

Magnitude

M-SH12

19

Phase

P-SH12

27

Real

R-KF2

20

Imaginary

I-KF2

28

Magnitude

M-KF2

20

Phase

P-KF2

28

Real

R-NX

2

Imaginary

I-NX

10

Magnitude

M-NX

2

Phase

P-NX

10

Real

R-NY

3

Imaginary

I-NY

11

Magnitude

M-NY

3

Phase

P-NY

11

Real

R-NXY

4

Imaginary

I-NXY

12

Magnitude

M-NXY

4

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

843

Phase

P-NXY

12

R-MX

5

Imaginary

I-MX

13

Magnitude

M-MX

5

Phase

P-MX

13

R-MY

6

Imaginary

I-MY

14

Magnitude

M-MY

6

Phase

P-MY

14

Real

R-MXY

7

Imaginary

I-MXY

15

Magnitude

M-MXY

7

Phase

P-MXY

15

Real

R-SXZ

8

Imaginary

I-SXZ

16

Magnitude

M-SXZ

8

Phase

P-SXZ

16

Real

R-SYZ

9

Imaginary

I-SYZ

17

Magnitude

M-SYZ

9

Phase

P-SYZ

17

Bending Moment X Real

Bending Moment Y Real

Twisting moment XY

Transverse shear XZ

Transverse shear YZ

*OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended that the OptiStruct ASCII item codes be used.

844

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DRESP1 - Frequency Response Stress/Strain Item Codes Element

Stress/Strain Item

Component

ASCII code Number code*

CELAS

Stress/Strain

Real

R-S

2

Imaginary

I-S

3

Magnitude

M-S

2

Phase

P-S

3

Real

R-SAB

Imaginary

I-SAB

Magnitude

M-SAB

Phase

P-SAB

Real

R-SA

2

Imaginary

I-SA

3

Magnitude

M-SA

2

Phase

P-SA

3

Real

R-SB

Imaginary

I-SB

Magnitude

M-SB

Phase

P-SB

Real

R-SALL

Imaginary

I-SALL

Magnitude

M-SALL

Phase

P-SALL

CROD

Both ends

End A

End B

CBAR

All Stresses/ Strains

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

845

Element

Stress/Strain Item

Component

ASCII code Number code*

End A point C

Real

R-SAC

2

Imaginary

I-SAC

7

Magnitude

M-SAC

2

Phase

P-SAC

7

Real

R-SAD

3

Imaginary

I-SAD

8

Magnitude

M-SAD

3

Phase

P-SAD

8

Real

R-SAE

4

Imaginary

I-SAE

9

Magnitude

M-SAE

4

Phase

P-SAE

9

Real

R-SAF

5

Imaginary

I-SAF

10

Magnitude

M-SAF

5

Phase

P-SAF

10

Real

R-SBC

12

Imaginary

I-SBC

16

Magnitude

M-SBC

12

Phase

P-SBC

16

Real

R-SBD

13

End A point D

End A point E

End A point F

End B point C

End B point D

846

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Element

Stress/Strain Item

End B point E

End B point F

Maximum at end A

Maximum at end B

CBEAM

All Stresses/ Strains

Altair Engineering

Component

ASCII code Number code*

Imaginary

I-SBD

17

Magnitude

M-SBD

13

Phase

P-SBD

17

Real

R-SBE

14

Imaginary

I-SBE

18

Magnitude

M-SBE

14

Phase

P-SBE

18

Real

R-SBF

15

Imaginary

I-SBF

19

Magnitude

M-SBF

15

Phase

P-SBF

19

Real

R-SAMAX

Imaginary

I-SAMAX

Magnitude

M-SAMAX

Phase

P-SAMAX

Real

R-SBMAX

Imaginary

I-SBMAS

Magnitude

M-SBMAX

Phase

P-SBMAX

Real

R-SALL

Imaginary

I-SALL

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

847

Element

Stress/Strain Item

End A point C

End A point D

End A point E

End A point F

End B point C

848

Component

ASCII code Number code*

Magnitude

M-SALL

Phase

P-SALL

Real

R-SAC

4

Imaginary

I-SAC

8

Magnitude

M-SAC

4

Phase

P-SAC

8

Real

R-SAD

5

Imaginary

I-SAD

9

Magnitude

M-SAD

5

Phase

P-SAD

9

Real

R-SAE

6

Imaginary

I-SAE

10

Magnitude

M-SAE

6

Phase

P-SAE

10

Real

R-SAF

7

Imaginary

I-SAF

11

Magnitude

M-SAF

7

Phase

P-SAF

11

Real

R-SBC

104

Imaginary

I-SBC

108

Magnitude

M-SBC

104

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Element

Stress/Strain Item

End B point D

End B point E

End B point F

Maximum at end A

Maximum at end B

Altair Engineering

Component

ASCII code Number code*

Phase

P-SBC

108

Real

R-SBD

105

Imaginary

I-SBD

109

Magnitude

M-SBD

105

Phase

P-SBD

109

Real

R-SBE

106

Imaginary

I-SBE

110

Magnitude

M-SBE

106

Phase

P-SBE

110

Real

R-SBF

107

Imaginary

I-SBF

111

Magnitude

M-SBF

107

Phase

P-SBF

111

Real

R-SAMAX

Imaginary

I-SAMAX

Magnitude

M-SAMAX

Phase

P-SAMAX

Real

R-SBMAX

Imaginary

I-SBMAX

Magnitude

M-SBMAX

Phase

P-SBMAX

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

849

Element

Stress/Strain Item

Component

ASCII code Number code*

CSHEAR

Maximum Shear

Real

R-SHMAX

2

Imaginary

I-SHMAX

3

Magnitude

M-SHMAX

2

Phase

P-SHMAX

3

Real

R-SHAVG

4

Imaginary

I-SHAVG

5

Magnitude

M-SHAVG

4

Phase

P-SHAVG

5

Real

R-SXX

6

Imaginary

I-SXX

12

Magnitude

M-SXX

6

Phase

P-SXX

12

Real

R-SYY

7

Imaginary

I-SYY

13

Magnitude

M-SYY

7

Phase

P-SYY

13

Real

R-SZZ

8

Imaginary

I-SZZ

14

Magnitude

M-SZZ

8

Phase

P-SZZ

14

Average Shear

All Solid Elements

Normal X

Normal Y

Normal Z

850

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Element

Stress/Strain Item

Component

ASCII code Number code*

Shear XY

Real

R-SXY

9

Imaginary

I-SXY

15

Magnitude

M-SXY

9

Phase

P-SXY

15

Real

R-SYZ

10

Imaginary

I-SYZ

16

Magnitude

M-SYZ

10

Phase

P-SYZ

16

Real

R-SXZ

11

Imaginary

I-SXZ

17

Magnitude

M-SXZ

11

Phase

P-SXZ

17

-

SVM

-

Shear YZ

Shear XZ

von Mises All Shell Elements

Normal X at both Real surfaces Imaginary

Normal X at Z1

Altair Engineering

R-SXB I-SXB

Magnitude

M-SXB

Phase

P-SXB

Real

R-SX1

3

Imaginary

I-SX1

4

Magnitude

M-SX1

3

Phase

P-SX1

4

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

851

Element

Stress/Strain Item

Component

ASCII code Number code*

Normal X at Z2

Real

R-SX2

10

Imaginary

I-SX2

11

Magnitude

M-SX2

10

Phase

P-SX2

11

Normal Y at both Real surfaces Imaginary

Normal Y at Z1

Normal Y at Z2

852

I-SYB

Magnitude

M-SYB

Phase

P-SYB

Real

R-SY1

5

Imaginary

I-SY1

6

Magnitude

M-SY1

5

Phase

P-SY1

6

Real

R-SY2

12

Imaginary

I-SY2

13

Magnitude

M-SY2

12

Phase

P-SY2

13

Shear XY at both Real surfaces Imaginary

Shear XY at Z1

R-SYB

R-SXYB I-SXYB

Magnitude

M-SXYB

Phase

P-SXYB

Real

R-SXY1

7

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Element

Stress/Strain Item

Component

ASCII code Number code*

Imaginary

I-SXY1

8

Magnitude

M-SXY1

7

Phase

P-SXY1

8

Real

R-SXY2

14

Imaginary

I-SXY2

15

Magnitude

M-SXY2

14

Phase

P-SXY2

15

von Mises at Z1

-

SVM1

-

von Mises at Z2

-

SVM2

-

von Mises

-

SVMB

-

Shear XY at Z2

* OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended that the OptiStruct ASCII item codes be used.

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

853

DRESP1 - Frequency Response Displacement, Velocity, and Acceleration Item Codes Response

Component

ASCII code Number code*

Translation X

Real

R-TX

1

Imaginary

I-TX

7

Magnitude

M-TX

1

Phase

P-TX

7

Real

R-TY

2

Imaginary

I-TY

8

Magnitude

M-TY

2

Phase

P-TY

8

Real

R-TZ

3

Imaginary

I-TZ

9

Magnitude

M-TZ

3

Phase

P-TZ

9

Real

R-RX

4

Imaginary

I-RX

10

Magnitude

M-RX

4

Phase

P-RX

10

Real

R-RY

5

Imaginary

I-RY

11

Magnitude

M-RY

5

Phase

P-RY

11

Translation Y

Translation Z

Rotation X

Rotation Y

854

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Response

Component

ASCII code Number code*

Rotation Z

Real

R-RZ

6

Imaginary

I-RZ

12

Magnitude

M-RZ

6

Phase

P-RZ

12

Real

R-NORM

-

Imaginary

I-NORM

-

Magnitude

M-NORM

-

Phase

P-NORM

-

Normal

*OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended that the OptiStruct ASCII item codes be used.

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

855

DRESP1 - Frequency Response Pressure Item Codes Response

Component

ASCII code Number code*

Pressure

Real

R-PRES

1

Imaginary

I-PRES

7

Magnitude

M-PRES

1

Phase

P-PRES

7

*OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended that the OptiStruct ASCII item codes be used.

856

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DRESP1 - Center of Gravity and Moments of Inertia Item Codes Center of Gravity Component

ASCII Code

x-coordinate

X

y-coordinate

Y

z-coordinate

Z

Moments of Inertia Component

ASCII Code

lxx

XX

lyy

YY

lzz

ZZ

lxy

XY

lxz

XZ

lyz

YZ

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

857

DRESP1 - Static Force Item Codes Element

Force Item

ASCII Code

Number Code *

CELAS

Force

F

2

CROD

Force End A

FA

2

Force End B

FB

-

Bending End A Plane 1

MA1

2

Bending End A Plane 2

MA2

3

Bending End B Plane 1

MB1

4

Bending End B Plane 2

MB2

5

Shear End A Plane 1

SA1

6

Shear End A Plane 2

SA2

7

Axial Force End A

FA

8

Torque End A

TA

9

Shear End B Plane 1

SB1

-

Shear End B Plane 2

SB2

-

Axial Force End B

FB

-

Torque End B

TB

-

Bending End A Plane 1

MA1

4

Bending End A Plane 2

MA2

5

Bending End B Plane 1

MB1

94

Bending End B Plane 2

MB2

95

CBAR

CBEAM

858

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Element

CBUSH

All Shell Elements

Altair Engineering

Force Item

ASCII Code

Number Code *

Shear End A Plane 1

SA1

6

Shear End A Plane 2

SA2

7

Axial Force End A

FA

8

Torque End A

TA

9

Shear End B Plane 1

SB1

96

Shear End B Plane 2

SB2

97

Axial Force End B

FB

98

Torque End B

TB

99

Force-X

FX

2

Force-Y

FY

3

Force-Z

FZ

4

Moment-X

MX

5

Moment-Y

MY

6

Moment-Z

MZ

7

Membrane Force X

NX

2

Membrane Force Y

NY

3

Membrane Shear Force XY

NXY

4

Bending Moment X

MX

5

Bending Moment Y

MY

6

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

859

Element

CSHEAR

Force Item

ASCII Code

Number Code *

Twisting Moment XY

MXY

7

Transverse Shear XZ

SXZ

8

Transverse Shear YZ

SYZ

9

Force 4 to 1

F41

2

Force 2 to 1

F21

3

Force 1 to 2

F12

4

Force 3 to 2

F32

5

Force 2 to 3

F23

6

Force 4 to 3

F43

7

Force 3 to 4

F34

8

Force 1 to 4

F14

9

Kick Force on 1

KF1

10

Shear Flow 12

SH12

11

Kick Force on 2

KF2

12

Shear Flow 23

SH23

13

Kick Force on 3

KF3

14

Shear Flow 34

SH34

15

Kick Force on 4

KF4

16

Shear Flow 41

SH41

17

*OptiStruct provides partial support for Nastran item codes. Since Nastran response items

860

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

are not fully compatible with those used in OptiStruct, it is recommended that the OptiStruct ASCII item codes be used.

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

861

DRESP1 - Static Failure Item Codes for Composites Theory

ASCII code

Hill

HILL

Hoffman

HOFF

Tsai-Wu

TSAI

Maximum Strain

STRN

862

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DRESP1 - Static Stress/Strain Item Codes for Composites

*

*

Stress Item

ASCII Code

Number code*

Normal - 1

S1

3

Normal - 2

S2

4

Shear - 12

S12

5

Shear - 1Z

S1Z

6

Shear - 2Z

S2Z

7

Maj. Principal

SMAP

9

Min. Principal

SMIP

10

OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended to use the OptiStruct ASCII item codes.

Strain Item

ASCII Code

Number Code*

Normal - 1

S1

3

Normal - 2

S2

4

Shear - 12

S12

5

Maj. Principal

SMAP

9

Min. Principal

SMIP

10

OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended to use the OptiStruct ASCII item codes.

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

863

*

Thermal Strain Item

ASCII Code

Number Code*

Normal - 1

TS1

-

Normal - 2

TS2

-

Shear - 12

TS12

-

Maj. Principal

TSMAP

-

Min. Principal

TSMIP

-

OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended to use the OptiStruct ASCII item codes.

Mechanical Strain Item

ASCII Code

Number Code*

Normal - 1

MS1

-

Normal - 2

MS2

-

Shear - 12

MS12

-

Maj. Principal

MSMAP

-

Min. Principal

MSMIP

-

*

864

OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended to use the OptiStruct ASCII item codes.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DRESP1 - MBD Displacement Item Codes Displacement

ASCII code

Translational X

TX

Translational Y

TY

Translational Z

TZ

Rotational X

RX

Rotational Y

RY

Rotational Z

RZ

Translational resultant

TXYZ

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

865

DRESP1 - MBD Velocity/Acceleration Item Codes Vel/Acc

ASCII code

Translational X

TX

Translational Y

TY

Translational Z

TZ

Rotational X

RX

Rotational Y

RY

Rotational Z

RZ

Translational resultant

TXYZ

Rotational resultant

RXYZ

866

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DRESP1 - MBD Force Item Codes Force

ASCII code

Translational X

FX

Translational Y

FY

Translational Z

FZ

Rotational X

MX

Rotational Y

MY

Rotational Z

MZ

Translational resultant

FXYZ

Rotational resultant

MXYZ

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

867

DRESP1 – PSD/RMS Displacement, Velocity, and Acceleration Item Codes Response

ASCII code Number code*

Translation X

TX

1

Translation Y

TY

2

Translation Z

TZ

3

Rotation X

RX

4

Rotation Y

RY

5

Rotation Z

RZ

6

*OptiStruct provides partial support for Nastran item codes. Since Nastran response items are not fully compatible with those used in OptiStruct, it is recommended that the OptiStruct ASCII item codes be used.

868

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DRESP1 – PSD/RMS Pressure Item Codes Response

ASCII code

Pressure

PRES

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

869

DRESP1 - PSD/RMS Stress/Strain Item Codes All Solid elements

All Shell elements

870

Stress/Strain Item

ASCII code

Normal X

SXX

Normal Y

SYY

Normal Z

SZZ

Shear XY

SXY

Shear YZ

SYZ

Shear XZ

SXZ

Stress/Strain Item

ASCII code

Normal X both surfaces

SXB

Normal X 1

SX1

Normal X 2

SX2

Normal Y both surfaces

SYB

Normal Y 1

SY1

Normal Y 2

SY2

Shear XY both surfaces

SXYB

Shear XY 1

SXY1

Shear XY 2

SXY2

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DRESP2 Bulk Data Entry DRESP2 – Design Response via Equations for Design Optimization Description When a desired response is not directly available from OptiStruct, it may be calculated using DRESP2. This response can be a functional combination of any set of responses resulting from the design analysis iteration. Responses defined in this manner can be used as design objectives or constraints. The DRESP2 card identifies the equation to use for the response relationship and the input values to evaluate the response function. Format (1)

(2)

(3)

(4)

(5)

DRESP2

ID

LABEL

EQID or FUNC

REGION

DRESPM

RID1

MODEL NAME1

VARTYPE1

ID1

VARTYPE2

...

(6)

(7)

(8)

(9)

RID2

MODEL NAME2

...

...

ID2

ID3

ID4

ID5

ID6

ID7

ID8

...

...

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

...

...

...

...

...

...

...

...

...

(10)

Example 1

Define a response labeled FUNC1 that references equation #999, where DESVAR #11 is the first variable, the DTABLE entry PI is the second variable, DRESP1 #1 is the third variable, the Y location of grid #11 is the forth variable and the DVPREL1 #22 is the fifth variable.

(1)

(2)

Altair Engineering

(3)

(4)

(5)

(6)

(7)

(8)

(9)

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(10)

871

DRESP2

10

FUNC 1

DESVAR

11

DTABLE

PI

DRESP1

1

DGRID

11

DVPREL1

22

999

2

Example 2

Define a response that is the weighted average of 2 displacements (1)

(2)

(3)

(4)

(5)

DRESP2

3

AVDIS

7

2

DRESP1

9

2

(6)

(7)

(8)

(9)

(10)

Associated Cards (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DRESP1

9

TOPN

DISP

1

3

4668

DRESP1

2

BOTN

DISP

1

3

5432

(10)

DEQATN

7

Field

Contents

ID

Response identification number. Each DRESP2 card must have a unique

872

y(x1, x2) = (x1*1.5+ x2*4.0)/2

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents ID with respect to all other DRESP# cards. No default (Integer > 0)

LABEL

User defined name for the response. No default (Character)

EQID

DEQATN identifier that defines the response relationship. No default (Integer > 0)

FUNC

Function to be applied to the arguments (see comment 14). No default (Character)

REGION

Region identifier (see comment 4). Default = blank (Integer > 0 or blank)

DRESPM

Indicates the beginning of a continuation line, which defines modelspecific response ID and Model Name pairs to be used in a Multi-Model Optimization run.

RID#

Identification numbers of model-specific responses (see comment 15).

MODEL NAME#

User-defined model names defined on the ASSIGN, MMO entry (see comment 15).

VARTYPE# Indicates the type of variables to follow. Can be one of: DESVAR, DTABLE, DGRID, DGRIDB, DRESP1, DRESP1L, DRESP2, DRESP2L, DVPREL1, DVPREL2, DVCREL1, DVCREL2, DVMREL1, DVMREL2, DVMBRL1, or DVMBRL2 (see comments 5, 13 and 16). No default (Character) ID#

When VARTYPE is DESVAR, DTABLE, DRESP1, DRESP2, DVPREL1, DVPREL2, DVCREL1, DVCREL2, DVMREL1, DVMREL2, DVMBRL1, or DVMBRL2 this list of IDs reference entities of the defined VARTYPE. When VARTYPE is DGRID or DGRIDB, the list is a list of GRID/ID Component pairs, where every second value is a component (1, 2, or 3). For example, DGRID, 11, 2 indicates the Y component of grid 11 (see

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Field

Contents comment 13). When VARTYPE is DRESP1L or DRESP2L, the list is a list of response/ subcase pairs, where every second value is a subcase ID, for example, DRESP1L, 9, 1, 9, 3 indicates response 9 calculated for subcase 1 and response 9 calculated for subcase 3. No default (Integer > 0)

Comments 1.

DRESP2 entries are referenced from the subcase through one of DESOBJ, DESSUB, or DESGBL.

2.

DRESP2 entries must have unique identification numbers with respect to DRESP1 and DRESP3 entries.

3.

DRESP1L, DRESP2L define a response defined with a DRESP1 or DRESP2, respectively, and a SUBCASE. The SUBCASE number 0 should be used for global responses.

4.

Responses with the same region identifier are grouped together into the same region. If the region identifier is blank, then a separate region is formed for each DRESP2 definition. The RTYPE EQUA on the DSCREEN definition refers to DRESP2 responses. It is important to ensure that responses with the same region identifier reference similar equations. For further information, refer to Constraint Screening in the User's Guide.

5.

Any number of VARTYPE# continuation lines can be defined. The order in which the VARTYPE# continuation lines are listed on the DRESP2 card is not prescribed. The same VARTYPE# can be repeated any number of times, in any position, on the card. However, the order in which the VARTYPE# continuation lines are listed will affect the solution as the values are passed to the equation (or function) in the listed sequence.

6.

The entries on the DRESP2 cards are assigned to the variable on the DEQATN card in the order that they occur. For example 2 above x1 is the displacement response defined by the DRESP1 card with ID=9 and x2 is the displacement response defined by the DRESP1 card with ID=2.

7.

DRESPi and DRESPiL cards cannot be mixed on the same DRESP2 definition.

8.

If DRESP1L, DRESP2L are used for a constrained DRESP2, DESGLB must be used to identify the DRESP2.

9.

If DRESP1L, DRESP2L are used in a DRESP2 objective function, then the DESOBJ that references the DRESP2 must be defined before the first Subcase.

10. If the DRESP2 data is referenced by DESOBJ data, the DESOBJ data must be above the first SUBCASE if: The DRESP2 contains DRESP1L, DRESP2L data. The DRESP2 contains no DRESP1DRESP2, DRESP1L, or DRESP2L data.

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The DRESP2 contains DRESP1, DRESP2 global responses. The DESOBJ data must be in the correct SUBCASE if the DRESP2 contains subcase dependent DRESP1 responses. 11. LABEL must begin with an alphabetical character. 12. DRESP2 cannot reference itself directly or recursively, but multiple levels of referencing are allowed. 13. The DGRID and DGRIDB VARTYPE’s can be used to select grid point locations as variables to be passed to the specified equation or function. The grid point locations are specified as a list of Grid point ID/Component pairs where every second value is a component. The Grid point ID’s are unique grid point identification numbers (ID) and Components are the grid point locations X1, X2, and X3 fields on the GRID bulk data entry. Examples:

DGRIDB: The VARTYPE DGRIDB can be used to select grid point locations in the basic coordinate system. The basic coordinate system is the default rectangular coordinate system in OptiStruct. DGRID: The VARTYPE DGRID can be used to select the grid point locations in the local coordinate system of each grid point. This local coordinate system may be specified by the CP field of the GRID bulk data entry for a particular grid point of interest. All local (or user defined) coordinate systems are directly or indirectly based on the default basic coordinate system. 14. The following functions can be used instead of an EQID. If FUNC is used, the DEQATN entry is no longer needed. The functions are applied to all arguments on the DRESP2 regardless of their type. Function

Description

SUM

Sum of arguments

AVG

Average of arguments

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Function

Description

Formula

SSQ

Sum of square of arguments

RSS

Square root of sum of squares of arguments

MAX

Maximum of arguments

MIN

Minimum of arguments

SUMABS

Sum of absolute value of arguments

AVGABS

Average of absolute value of arguments

MAXABS

Maximum of absolute arguments

MINABS

Minimum of absolute value of arguments

15. Multiple RID-Model Name pairs can be specified on a single DRESPM continuation line. These responses can be used similar to responses defined via the VARTYPE# -ID# entries. ASSIGN, MMO can be used to identify the filename of the model and the user-defined Model Name that contains the referenced response definition. 16. An inconsistent number of responses can be referenced via multiple DRESP#L VARTYPE’s. The following requirements should be met for such entries: 1. A minimum of one DRESP# entry listed on a corresponding DRESP#L VARTYPE should reference only a single response value, (and) 2. DRESP# entries listed on other DRESP#L VARTYPE’s should reference the same number of responses. 3. If requirement (1) above is not met, then the number of responses referenced by all the DRESP# entries (listed on all the DRESP#L VARTYPE’s) should be equal. Example Allowed DRESP1 2 DRESP1

876

1

R1

STRESS

ELEM

SVM3

1

2

R2

STRESS

PSHELL

SVM4

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DRESP2 + + DRESP1 DEQATN

3 MA 1 DRESP1L 4 0 DRESP1L 2 2 4 vol VOLUME 1 f(a,b)=a+b

Not Allowed DRESP1 2 DRESP1 DRESP2 + + + DRESP1 DEQATN

1

R1

STRESS

ELEM

2 R2 STRESS PSHELL 3 MNA 1 DRESP1L 4 0 DRESP1L 1 2 DRESP1L 2 2 4 vol VOLUME 1 f(a,b,c)=a+b+c

SVM1

1

SVM2

1

In the above example (Allowed), the number of responses referenced by DRESP1L=4 is one. Also, DRESP1L=2 references multiple responses, this is allowed as there are no other DRESP#L that reference more than one response. However, in the “Not Allowed” example, DRESP1L=1 references two responses and DRESP1L=2 references multiple responses (this violates requirement 2 above). 17. This card is represented as optimization responses in HyperMesh.

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DRESP3 Bulk Data Entry DRESP3 – Design Response via External User-supplied Functions Description When a desired response is not available from OptiStruct, either directly or via equations, it may be calculated through external user-supplied functions implemented in shared/dynamic libraries or external files (see External Reponses). The DRESP3 card identifies the external function to be called and defines the parameters to be transferred to that function. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DRESP3

ID

LABEL

GROUP

FUNC

REGION

RESP

MAXRESP

DRESPM

RID1

MODEL NAME1

RID2

MODEL NAME2

...

...

VARTYPE1

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

...

...

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

...

...

ID1

ID2

ID3

ID4

ID5

ID6

ID7

C I2

C I3

...

C In

VARTYPE2

(9)

(10)

...

VARTYPEn

ID8

878

C ELLIN

C I1

C ELLOUT

CO

SENSOPT

METHOD

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Alternate format for CELLIN (cell input) specifications C ELLIN

C I1

thru

C In

Alternate format when VARTYPE is DEIGV DEIGV

EIGV1

LID1

G1

C1

EIGV2

LID2

G2

C2

...

...

...

...

Alternate format when VARTYPE is USRDATA USRDATA

STRNG

...

Field

Contents

ID

Response identification number. Each DRESP3 must have a unique ID with respect to all other DRESP# cards. No default (Integer > 0)

LABEL

User-defined name for the response. No default (Character)

GROUP

GROUP identifier that defines the shared/dynamic library or external Microsoft Excel workbook to be used (see comment 19). It references an existing LOADLIB entry in the input deck. No default (Character)

FUNC

FUNC identifier that defines the external function to be used. No default (Character)

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Field

Contents

REGION

Region identifier (see comment 4). Default = blank (Integer > 0 or blank)

DRESPM

Indicates the beginning of a continuation line, which defines modelspecific response ID and Model Name pairs to be used in a Multi-Model Optimization run.

RID#

Identification numbers of model-specific responses (see comment 21)

MODEL NAME#

User-defined model names defined on the ASSIGN, MMO entry (see comment 21).

RESP

RESP identifier that defines the response to be returned by the external function. No default (Integer > 0)

MAXRESP

MAXRESP identifier that defines the number of responses available in the external function. No default (Integer > 0)

VARTYPE#

Indicates the type of variables to follow. Can be one of: DESVAR, DTABLE, DGRID, DGRIDB, DEIGV, DRESP1, DRESP1L, DRESP2, DRESP2L, DVPREL1, DVPREL2, DVCREL1, DVCREL2, DVMREL1, DVMREL2, DVMBRL1, DVMBRL2, USRDATA or SLAVE (see comment 18). No default (Character)

ID#

When VARTYPE is DESVAR, DTABLE, DRESP1, DRESP2, DVPREL1, DVPREL2, DVCREL1, DVCREL2, DVMREL1, DVMREL2, DVMBRL1, or DVMBRL2 this list of IDs reference entities of the defined VARTYPE. When VARTYPE is DGRID or DGRIDB, the list is a list of GRID/Component pairs, where every second value is a component (1, 2, or 3). For example, DGRID, 11, 2 indicates the Y component of grid 11. When VARTYPE is DEIGV, the ID# list is replaced by a list of eigenvectors, with each line defining an eigenvector ID, a subcase ID, and a grid/ component pair (where the component is one of 1, 2, 3, 4, 5 or 6). When VARTYPE is DRESP1L or DRESP2L, the list is a list of response/ subcase pairs, where every second value is a subcase ID, for example,

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Field

Contents DRESP1L, 9, 1, 9, 3 indicates response 9 calculated for subcase 1 and response 9 calculated for subcase 3. When VARTYPE is USRDATA, the list is replaced by a user-defined character string, which is passed to the external function. This character string must be less than 32000 characters. When VARTYPE is SLAVE, only a single ID should follow. This is the ID of another DRESP3 entry from which data should be copied. No default (Integer > 0, or Character)

CELLIN

CELLIN flag indicates that a list of Microsoft Excel worksheet cell references are to follow, that define response input values (see comments 19 and 20).

CI#

A list of Microsoft Excel worksheet cell references that define response input values (see comments 19 and 20). No default (Alphanumeric)

CELLOUT

CELLIN flag indicates that a Microsoft Excel Worksheet cell reference is to follow that defines the response output value (see comments 19 and 20).

CO

A Microsoft Excel worksheet cell reference that defines the response output value (see comments 19 and 20). No default (Alphanumeric)

SENSOPT

Indicates that the sensitivities evaluation method follows.

METHOD

Method to be used for sensitivities evaluation (see comment 17). NONE (or blank): Sensitivities are not provided. Full evaluations are performed at every step of the approximation process. AUTO: Sensitivities are automatically evaluated by finite differences at the beginning of the iteration, and subsequently used in the approximation process. USER: Sensitivities are provided by the external function at the beginning of the iteration, and subsequently used in the approximation process. Default = NONE (or blank)

EIGVi

Eigenvector numbers.

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Field

Contents No default (Integer > 0)

LIDi

Subcase IDs. No default (Integer > 0)

Gi

Grid IDs. No default (Integer > 0)

Ci

Component IDs. No default (1, 2, 3, 4, 5, or 6)

STRNG

User-defined string to be passed to the external function. No default (Character string < 32000 characters)

Comments 1.

DRESP3 entries are referenced from the subcases through one of DESOBJ, DESSUB, or DESGBL.

2.

DRESP3 entries must have unique identification numbers with respect to DRESP2 and DRESP1 entries.

3.

DRESP1L, DRESP2L define a response defined with a DRESP1 or DRESP2, respectively, and a SUBCASE. The SUBCASE number 0 should be used for global responses.

4.

Responses with the same region identifier are grouped together into the same region. If the region identifier is blank, then a separate region is formed for each DRESP3 definition. The RTYPE EXTERNAL on the DSCREEN definition refers to DRESP3 responses. It is important to ensure that responses with the same region identifier reference similar external responses. For further information, refer to Constraint Screening in the User's Guide.

5.

Any number of VARTYPE# continuation lines can be defined. The order in which the VARTYPE# continuation lines are listed on the DRESP2 card is not prescribed. The same VARTYPE# can be repeated any number of times, in any position, on the card.

6.

The entries on the DRESP3 card are assigned to the parameters passed to the external function in the order that they occur.

7.

DRESPi and DRESPiL cards cannot be mixed on one DRESP3 definition.

8.

If DRESP1L, DRESP2L is used for a constrained DRESP3, DESGLB must be used to identify the DRESP3.

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9.

If DRESP1L, DRESP2L is used in a DRESP3 objective function, then the DESOBJ that references the DRESP3 must be defined before the first subcase.

10. If the DRESP3 data is referenced by DESOBJ data, the DESOBJ data must be above the first SUBCASE if: DRESP3 contains DRESP1L, DRESP2L data. DRESP3 contains no DRESP1, DRESP2 or DRESP1L, DRESP2L data. DRESP3 contains DRESP1, DRESP2 global responses. The DESOBJ data must be in the correct static or eigenvalue SUBCASE if the DRESP3 contains static or eigenvalue DRESP1 responses. 11. DRESP1 of RTYPE = WCOMB, WFREQ, and COMP cannot be referenced by DRESP3 data. 12. LABEL must begin with an alphabetical character. 13. The RESP field may be used to request a specific response from the external function, while MAXRESP defines the maximum number of responses available in that function. External functions can be implemented to compute any number of responses and to return any subset of these responses. This approach has two main benefits: There is no need to write a specific external function for each response that you want computed. One general function may be written instead. In many cases, this allows for easier code maintenance and better code reusability. OptiStruct will automatically group responses which point to the same external function, and which use the same set of input data. The external function will only be called once for that group of responses, which may save computational time in the library. 14. The SLAVE continuation line indicates that the input data (DESVAR, and so on) for the current DRESP3 card is identical to the input data of the master DRESP3 card. There cannot be any other continuation line when SLAVE is used. This simplifies the DRESP3 definition and reduces potential errors when modifying input decks, either via the HyperMesh interface or manually. Also, as explained above, OptiStruct will group responses that share the same input data. 15. The data in the STRNG field is character string based. It provides a convenient way to pass constants to the external response server routines. The maximum number of characters allowed in 32000. 16. The eigenvector values provided on the DEIGV continuation are normalized against the mass matrix. No sensitivities are calculated for these values. 17. Performance of the sensitivity evaluation method is problem dependent, and selection of a method depends on the number of arguments and the cost of each evaluation. The default method works best for most problems. However, if the approximation module is observed to be very slow with the default, AUTO or USER can be tried. USER: This setup is more complex as it requires user-calculated gradients. However, since finite differences are not used, it can improve the quality of those gradients and may also increase the speed at which those gradients are calculated. 18. The DGRID and DGRIDB VARTYPE’s can be used to select grid point locations as variables

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to be passed to the specified equation or function. The grid point locations are specified as a list of Grid point ID/Component pairs where every second value is a component. The Grid point ID’s are unique grid point identification numbers (ID) and Components are the grid point locations X1, X2, and X3 fields on the GRID Bulk Data Entries. Examples:

DGRIDB: The VARTYPE DGRIDB can be used to select grid point locations in the basic coordinate system. The basic coordinate system is the default rectangular coordinate system in OptiStruct. DGRID: The VARTYPE DGRID can be used to select the grid point locations in the local coordinate system of each grid point. This local coordinate system may be specified by the CP field of the GRID Bulk Data Entry for a particular grid point of interest. All local (or user defined) coordinate systems are directly or indirectly based on the default basic coordinate system. 19. An external Microsoft Excel workbook can be referenced on the GROUP field via the LOADLIB I/O Options Entry. 20. Multiple CELLIN continuation lines can be specified; each CI# entry on the CELLIN continuation lines corresponds to responses (ID#) defined on the VARTYPE# continuation lines. See External Responses in the User’s Guide for further information. 21. Multiple RID-Model Name pairs can be specified on a single DRESPM continuation line. These responses can be used similar to responses defined via the VARTYPE# -ID# entries. ASSIGN, MMO can be used to identify the filename of the model and the user-defined Model Name that contains the referenced response definition.

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DSCREEN Bulk Data Entry DSCREEN – Design Constraint Screening Description Defines design constraint screening data. Refer to Constraint Screening in the User's Guide section. Format (1)

(2)

(3)

(4)

DSC REEN

RTYPE

THOLD

MAXC

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(5)

(6)

(7)

(8)

(9)

(10)

Alternate Format (1)

(2)

(3)

DSC REEN

AUTO

LEVEL

Example

(1)

(2)

(3)

(4)

DSC REEN

STRESS

-0.6

4

(5)

(6)

(7)

(8)

(9)

(10)

Associated Cards (1)

(2)

(3)

(4)

(5)

(6)

(7)

DRESP1

98

SS11

STRESS

PSHELL

1

7

1

DRESP1

99

SS11

STRESS

PSHELL

2

7

3

DRESP1

100

SS11

STRESS

PSHELL

2

7

5

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(8)

(9)

(10)

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Field

Contents

RTYPE

Response type affected by the constraint screening settings on this definition. No default (Character; See comment 1)

THOLD

Normalized threshold value – constraint will not be retained during the current iteration if its normalized value is below THOLD. Default = -0.5 (Real < 0.0)

MAXC

Maximum number of constraints to be retained for each region definition and each load case. Default = 20 (Integer > 0)

AUTO

Automatic adjustment of screening criteria. When this is activated, the screening algorithm will seek to retain the least number of responses that are necessary for stable convergence. Automatic constraint screening is active by default. It is disabled by the presence of any DSCREEN definition in the input data.

LEVEL

The automatic constraint screening has levels 1 through 5, with 1 being the least aggressive (more responses retained) and 5 being the most aggressive (less responses retained). Level 3 is the default. The automatic constraint screening can also be disabled by setting it to OFF. Default = 3 (1, 2, 3, 4, 5 or OFF)

Comments 1.

RTYPE may be any of the RTYPEs allowed on the DRESP1 entry, or EQUA or EXTERNAL or AUTO.

2.

RTYPE EQUA refers to DRESP2 definitions. If DRESP2 definitions are given the same region identifier, they should reference similar equations.

3.

RTYPE EXTERNAL refers to DRESP3 definitions. If DRESP3 definitions are given the same region identifier, they should reference similar equations.

4.

F is the normalized constraint. If F> THOLD, then the constraint will be retained. F is calculated with respect to the upper and lower bounds of the constraint as follows:

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5.

The THOLD and MAXC defaults do not apply for MASS, MASSFRAC, VOLUME, VOLUMEFRAC, or FREQ. Constraint screening is not active for these responses by default.

6.

When no DSCREEN definitions are present in the input data, automatic constraint screening is active for all responses. The presence of any DSCREEN definition disables the automatic screening for all response types.

7.

With automatic screening, the upper bound on the EIGRL card for buckling analysis will be adjusted in order to calculate only the necessary buckling eigenvalues (responses) that are potentially retained in the optimization.

8.

This card is represented as an optidscreens in HyperMesh.

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DSHAPE Bulk Data Entry DSHAPE – Design Variable for Free-Shape Optimization Description Defines parameters for the generation of free-shape design variables. Format (1)

(2)

DSHAPE

ID

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MXSHRK

MXGROW

SMETHO D

NTRANS

GID4

GID5

GID6

PERT

DTYPE

MVFAC TO NSMOOT R H

GRID

GMETH

GSETID / GID1

GID2

GID3

GID7

GID8

…

…

PATRN

PATYP

AID/XA

YA

ZA

FID/VXF

VYF

VZF

DRAW

DTYP

DAID/ XDA

YDA

ZDA

DFID/ XDF

YDF

ZDF

(10)

DRAFT EXTR

EC ID

XE

YE

ZE

GRIDC O N

GC METH

GC SETID 1/ GDID1

C TYPE1

C ID1

X1

Y1

Z1

GC METH

GC SETID 2/ GDID2

C TYPE2

C ID2

X2

Y2

Z2

…

…

SDC ID1

XL1

XU1

YL1

YU1

ZL1

ZU1

SDC ID2

XL2

XU2

YL2

YU2

ZL2

ZU2

…

…

SDC ON

BMESH

888

BMID

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Field

Contents

ID

Each DSHAPE card must have a unique ID. No default (Integer > 0)

PERT

PERT flag indicating perturbation information is to follow.

DTYPE

Specifies the direction type for the free-shape variation (Comment 1). Default = BOTH (GROW, SHRINK, or BOTH)

MVFACTOR

Initial limit on the movement factor of the design grids. The unit of MVFACTOR is the average mesh size of meshes adjacent to grids defined after GRID. Only the initial value of this limit can be set. The values in subsequent optimization iterations are automatically adjusted to enhance to enhance iterative stability and convergence speed; however, they will never be greater than the initial limit. Default = 0.5 (Real > 0.0)

NSMOOTH

Number of grids layers NSMOOTH. Default = 10 (Integer)

MXSHRK

Maximum shrinking distance. No default

MXGROW

Maximum growing distance. No default

SMETHOD

Mesh smoothing method. Default = 1 (1 or 2) Method 1 is faster than method 2, but method 2 is more robust in avoiding mesh distortion.

NTRANS

Number of design grid layers in the transition zone to non-design area, where additional treatment will be applied to produce smooth transition (Comment 4). Default = 0 (Integer > 0)

GRID

GRID flag indicating that a list of grid IDs is to follow. These grids are design variables for the free-shape optimization.

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Field

Contents

GMETH

Flag indicating that a list of grids is to be defined by a list of grid IDs or a single SET reference. Default = ID (SET or ID)

GID#

Grid identification numbers. List of grids for which this DSHAPE card is defined. No default (Integer > 0)

GSETID

Grid SET identification number. A grid set containing design grids for freeshape optimization. No default (Integer > 0)

PATRN

PATRN flag indicating that variable pattern grouping is active. Indicates that information about the pattern group will follow.

PATYP

Type of variable pattern grouping. Required if any symmetry or variable pattern grouping is desired. Only 1-plane symmetry (TYP=10) is currently supported. Default = 0 (0 or 10)

AID/XA, YA, ZA

Variable pattern grouping anchor point. These fields define a point that determines how grids are grouped into variables (See comment 3). The X, Y, and Z values are in the global coordinate system. You may put a grid ID in the AID/XA field to define the anchor point. Default = origin (Real in all three fields or Integer in AID/XA field)

FID/VXF, VYF, VZF

Direction of first vector for variable pattern grouping. These fields define an xyz vector which determines how grids are grouped into variables (Comment 3). The X, Y, and Z values are in the global coordinate system. If FID is defined, it defines a vector pointing from grid AID or point (XA, YA, and ZA) to grid FID. If VXF, VYF, VZF are defined, it defines a vector pointing from point (XA, YA, and ZA) to point (XA+VXF,YA+VYF,ZA+VZF). (XA, YA, and ZA) are coordinates of the anchor point defined by AID or XA, YA, and ZA. If all fields are blank and the PATYP field is not blank or zero, OptiStruct gives an error. No default

DRAW

890

DRAW flag indicating that casting constraints are being applied. Indicates that draw direction information is to follow. Only valid for design grids on solid elements.

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Field

Contents

DTYP

Type of draw direction constraint to be used. SINGLE indicates that a single die will be used, the die being withdrawn in the given draw direction. Only SINGLE is available in 9.0.

DAID/XDA, YDA, ZDA

Draw direction anchor point. These fields define the anchor point for draw direction of the casting. The point may be defined by entering a grid ID in the DAID field or by entering X, Y, and Z coordinates in the XDA, YDA, and ZDA fields, these coordinates will be in the basic coordinate system. Default = origin (Real in all three fields or Integer in first field)

DFID/XDF, YDF, ZDF

Direction of vector for draw direction definition. These fields define a point. The vector goes from the anchor point to this point. The point may be defined by entering a grid ID in the DFID field or by entering X, Y, and Z coordinates in the XDF, YDF, and ZDF fields, these coordinates will be in the basic coordinate system. No default (Real in all three fields or Integer in first field)

DRAFT

Draft angle in degrees. See comment 5. Default = 0.0 (0.0 < Real < 90.0)

SDCON#

SDCON# flag indicating that side constraints are being applied.

SDCID#

The ID of a coordinate system which the following XL#, XU#, YL#, YU#, ZL#, or ZU# components are resolved in.

XL#, XU#, YL#, YU#, ZL#, ZU#

Side constraints defined by lower and upper bounds of coordinates, which restrict the moving space of the design grids. Any of the six fields could be blank, which means the corresponding coordinate is not constrained.

EXTR

EXTR flag indicating that extrusion constraints are being applied. Indicates that extrusion information is to follow. Only valid for design grids on solid elements.

ECID

The ID of a coordinate system which the following X, Y, and Z components are resolved in. Default = 0 (Integer > 0) For Free-Shape 9.0, only consider two simple extrusion paths: Line and Circle. Line - ECID is a rectangular system. Circle - ECID is a cylindrical system.

XE, YE, ZE

When ECID is a rectangular system ID, X, Y, and Z are components of a vector under system EID, which define the extrusion path.

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Field

Contents

GRIDCON

GRIDCON flag indicating that a list of grids with associated constraints are to follow. Note: Grids within the smoothing zone (defined by NSMOOTH) will move during Free-shape optimization to avoid mesh distortion without changing the shape of the model. Users can also constrain the movement of these grids by GRIDCON even if they are not defined after GRID.

GCMETH

Flag indicating that a list of grids is to be defined by a list of grid IDs or a single SET reference. Default = ID (SET or ID)

GCSETID#

Grid SET identification numbers. IDs of certain grid SETs which are constrained to move in a predefined manner. No default (Integer > 0)

GDID#

IDs of certain grids which are constrained to move in a predefined manner. No default (Integer > 0, ID must also be present in the list following the GRID flag)

CTYPE#

Specifies the type of constraint applied to the grid GDID# (Comment 2). No default (FIXED, DIR, or NORM)

CID#

The ID of a coordinate system which the following X, Y, and Z components are resolved in. Default = 0 (Integer > 0)

X#, Y#, Z#

X, Y, and Z components of a vector, which either defines the direction in which the grid GDID# is constrained to move, or the normal of a plane on which the grid GDID# is constrained to remain. Default = 0.0 (Real)

BMESH

BMESH flag indicating that a BMFACE ID is to follow.

BMID

The BMFACE ID which defines a list of QUADs and/or TRIAs which define a barrier that the design surface will not penetrate during shape optimization.

Comments 1.

DTYPE has three distinct options: a) GROW – grids cannot move inside of the initial part boundary.

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b) SHRINK – grids cannot move outside of the initial part boundary. c) BOTH – grids are unconstrained. For a more detailed description, refer to Free-shape Optimization in the User’s Guide. 2.

CTYPE has three distinct options: a) FIXED – grid cannot move due to free-shape optimization. b) DIR – grid is forced to move along the vector defined by the following fields. c) NORM – grid is forced to remain on a plane for which the following fields define the normal direction. For a more detailed description, refer to Free-shape Optimization in the User’s Guide.

3.

For a single plane of symmetry (TYP = 10), the plane is defined normal to the first vector and is located at the anchor node.

4.

The NTRANS option allows you to achieve a smooth transition between design and nondesign regions. This additional smoothness, however, comes with an inherent cost of a reduction in design flexibility. NTRANS improves design smoothness across the transition zone between design and non-design regions at the expense of design flexibility. For detailed information illustrating the working mechanism of NTRANS, refer to Defining Free-shape Design Regions in the User’s Guide.

5.

The draft angle can be specified in degrees via the DRAFT field, as illustrated in the figure below. Geometric constraints (GRIDCON and SDCON) may not be satisfied when the draft angle is activated:

6.

This card is represented as an optimization design variable in HyperMesh.

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DSHUFFLE Bulk Data Entry DSHUFFLE – Design Variable for Composite Shuffling Optimization Description Defines parameters for the generation of composite shuffling design variables. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DSHUFFL E

ID

ETYPE

EID1

EID2

EID3

EID4

EID5

EID6

EID7

…

MAXSUC C

MANGLE

MSUC C

VSUC C

+

PAIR

PANGLE 1

PANGLE2

POPT

+

C ORE

C REP

C ANG1

C ANG2

C ANG3

C ANG4

C ANG5

C ANG6

C ANG7

…

VANG1

VANG2

VANG3

VANG4

VANG5

VANG6

VANG7

…

+ +

(10)

+

+ +

C OVER

VREP

+ +

RANGE

PIDSTA

PIDEND

Field

Contents

ID

Unique identification number. No default (Integer > 0)

ETYPE

Entity type for which this DSHUFFLE card is defined. No default (STACK, PCOMP, or PCOMPG)

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Field

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EID#

Entity identification numbers. List of entities of type ETYPE for which this DSHUFFLE card is defined. No default (Integer > 0)

MAXSUCC

MAXSUCC flag indicating that the "maximum number of successive plies" constraint is applied. Multiple MAXSUCC constraints are allowed (see Comment 1).

MANGLE

Ply orientation, in degrees, to which the MAXSUCC constraint is applied. No default (Real or ALL)

MSUCC

Maximum number of successive plies for the MAXSUCC constraint. No default (Integer > 0)

VSUCC

Allowable percentage violation for the MAXSUCC constraint. 0.0 indicates that this constraint cannot be violated. Default = 0.0 (Real)

PAIR

PAIR flag indicating that a pairing constraint is applied (see Comment 2).

PANGLE1

First ply orientation, in degrees, to which the PAIR constraint is applied. No default (Real, only 45.0 allowed at this time)

PANGLE2

Second ply orientation, in degrees, to which the PAIR constraint is applied. No default (Real, only -45.0 allowed at this time)

POPT

Pairing option. SAME indicates that the stacking sequence should remain the same for consecutive pairs. REVERSE indicates that the stacking sequence should be reversed for alternate pairs. Default = blank (SAME, REVERSE or BLANK)

CORE

CORE flag indicating that a ply sequence for the core layer is defined. Only one CORE sequence is allowed (see Comment 3).

CREP

Number of times the core ply sequence should be repeated. Default = 1 (Integer > 0)

CANG#

Ply orientations, in degrees, defining the core. No default (Real)

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COVER

COVER flag indicating that a ply sequence for the cover layer is defined. Only one COVER sequence is allowed (see Comment 3).

VREP

Number of times the cover ply sequence should be repeated. Default = 1 (Integer > 0)

VANG#

Ply orientations, in degrees, defining the cover. No default (Real)

RANGE

Indicates that starting and ending ply identification numbers are defined in the following fields to specify the range of plies to be shuffled. OptiStruct will only shuffle plies between PIDSTA and PIDEND. Multiple DSHUFFLE entries can be created to define different ply ranges.

PIDSTA

The ply identification number (starting ply) that defines the first ply in the range to be shuffled. No default (Integer > 0)

PIDEND

The ply identification number (ending ply) that defines the last ply in the range to be shuffled. No default (Integer > 0)

Comments 1.

896

The MAXSUCC constraint indicates that the stacking sequence should contain no sections with more than a given number of successive plies with the same orientation. In the case of symmetrical laminates, this constraint accounts for the mirrored successive plies on both sides of the symmetry plane. In the image below, (a) shows invalid and valid sequences for a non-symmetrical stack, and (b) shows invalid and valid sequences for a symmetrical stack, both for MAXSUCC=3.

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2.

The PAIR constraint indicates that 45° and -45° plies should be paired together. The POPT option specifies how the pairing should be accomplished, as illustrated on the figure below.

3.

The CORE and COVER constraints specify stacking sequences for the core and cover layers respectively. Plies are listed from the bottom surface upward, in respect to the element’s normal direction. In the example below, the sequence for the core is (0°, 0°, 90°, 90°) while the sequence for the cover is defined as (90°, 90°, 0°, 0°).

Note that, for non-symmetrical laminates, COVER actually corresponds to the bottom cover, whereas CORE corresponds to the upper cover. At this point, it is not possible to create an actual core for non-symmetrical stacks. 4.

For a more detailed description and an example, refer to Optimization of Composite Structures in the User’s Guide.

5.

This card is represented as an optimization design variable in HyperMesh.

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DSIZE Bulk Data Entry DSIZE – Design Variable for Free-Size Optimization Description DSIZE defines parameters for the generation of free-size design variables. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

DSIZE

ID

PTYPE

PID1

PID2

PID3

PID4

PID5

PID6

PID7

…

…

…

…

…

…

(7)

(8)

(9)

(10)

(7)

(8)

(9)

(10)

(8)

(9)

(10)

Optional continuation lines for thickness definition: (1)

(2)

(3)

(4)

THIC K

T0

T1

(5)

(6)

Optional continuation lines for stress constraint definition: (1)

(2)

(3)

(4)

STRESS

UBOUND

(5)

(6)

Optional continuation lines for member size constraint definition: (1)

(2)

(3)

(4)

MEMBSIZ

MINDIM

(5)

(6)

(7)

Optional continuation lines for composite manufacturing constraints definition: (1)

(2)

(3)

(4)

(5)

(6)

(7)

+

C OMP

LAMTHK

LTMIN

LTMAX

LTSET

LTEXC

898

(8)

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(9)

(10)

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(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

+

C OMP

PLYTHK

PTGRP

PTMIN

PTMAX

PTOPT

PTSET

PTEXC

+

C OMP

PLYPC T

PPGRP

PPMIN

PPMAX

PPOPT

PPSET

PPEXC

+

C OMP

PLYMAN

PMGRP

PMMAN

PMOPT

PMSET

PMEXC

+

C OMP

BALANC E

BGRP1

BGRP2

BOPT

+

C OMP

C ONST

C GRP

C THIC K

C OPT

+

C OMP

PLYDRP

PDGRIP

PDTYP

PDMAX

PDOPT

PDSET

PDEXC

PDDEF

PDX

PDY

PDZ

+

(10)

Optional continuation lines for pattern grouping constraint definition: (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PATRN

TYP

AID/XA

YA

ZA

FID/XF

YF

ZF

UC YC

SID/XS

YS

ZS

(10)

Optional continuation lines for "Master" definition for pattern repetition constraint: (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ID

C AID/ XC A

YC A

ZC A

C FID/XC F

YC F

ZC F

C SID/ XC S

YC S

ZC S

C TID/XC T

YC T

ZC T

(10)

MASTER

C OORD

Optional continuation lines for "Slave" definition for pattern repetition constraint: (1)

(2)

(3)

(4)

(5)

(6)

SLAVE

DSIZE_ID

SX

SY

SZ

C OORD

C ID

C AID/

YC A

ZC A

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(7)

(8)

(9)

C FID/XC F

YC F

ZC F

(10)

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XC A C SID/ XC S

YC S

ZC S

C TID/XC T

YC T

ZC T

(8)

(9)

(10)

(10)

Optional continuation lines for fatigue constraint definition: (1)

(2)

(3)

(4)

FATIGUE

FTYPE

FBOUND

(5)

(6)

(7)

Optional continuation lines for zone based free-sizing definition: (1)

(2)

(3)

GROUP

EG7

(4)

(5)

(6)

(7)

(8)

(9)

EG1

EG2

EG3

EG4

EG5

EG6

EG8

EG9

…

…

…

…

Alternate continuation line for zone based free-sizing definition (Alternate Format): (1)

(2)

GROUP

(3)

(4)

(5)

(6)

EG1

THRU

EG2

(7)

Field

Contents

ID

Each DSIZE card must have a unique ID.

(8)

(9)

(10)

No default (Integer > 0) PTYPE

Property type for which DSIZE card is defined. No default (PCOMP, PCOMPG, PSHELL, or STACK)

PID#

Property identification numbers. List of properties of type PTYPE for which this DSIZE card is defined. Use ALL in PID1 field if it applies to all properties of type PTYPE in the model. No default (Integer > 0, or ALL)

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Field

Contents

THICK

THICK flag indicating that minimum and possibly maximum thickness value are to follow.

T0

Minimum thickness. For PTYPE = PSHELL, this refers to the minimum thickness of the shell. If no value is entered for T0, the T0 value on the PSHELL card is used. If T0 is not defined on the PSHELL card, then T0=0.0 is assumed. This option does not apply for PTYPE = PCOMP, PCOMPG, or STACK. Default = blank (Real > 0.0)

T1

Maximum thickness. For PTYPE = PSHELL, this refers to the maximum thickness of the shell. If no value is entered for T1, the T value on the PSHELL card is used. This option does not apply for PTYPE = PCOMP, PCOMPG, or STACK. Default = blank (Real > T0)

STRESS

STRESS flag indicating that von Mises stress constraints are active and that an upper bound value for the stress is to follow. See comment 4.

UBOUND

Upper bound constraint on von Mises stress. No default (Real > 0.0)

MEMBSIZ

MEMBSIZ flag indicating that member size control is active for the properties listed. Indicates that MINDIM is to follow.

MINDIM

Specifies the minimum diameter of members formed. This command is used to eliminate small members. It also eliminates checkerboard results. See comment 3. Default = No minimum member size control (Real > 0.0)

COMP

Altair Engineering

COMP flag indicating that composite manufacturing constraints are applied. Indicates that information about manufacturing constraints is to follow. See comment 5.

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Field

Contents

LAMTHK

LAMTHK flag indicating that laminate thickness constraints are applied. Multiple LAMTHK constraints are allowed. See comment 5.

LTMIN

Minimum laminate thickness for the LAMTHK constraint. Default = blank (Real > 0.0)

LTMAX

Maximum laminate thickness for the LAMTHK constraint. Default = blank (Real > 0.0 and > LTMIN)

LTSET

Set ID of elements to which the LAMTHK constraint is applied.

LTEXC

Exclusion flag indicating that certain plies are excluded from the LAMTHK constraint. The following options are supported: NONE: Plies are not excluded. CORE: The core is excluded. (Default) CONST: Plies defined in the CONST constraint are excluded. BOTH: CORE and CONST are considered.

PLYTHK

PLYTHK flag indicating that ply thickness constraints are applied. Multiple PLYTHK constraints are allowed.

PTGRP

Ply orientation in degrees, ply sets or ply IDs, to which the PLYTHK constraint is applied, depending on the PTOPT selection. No default (Real or Integer)

PTMIN

Minimum thickness for the PLYTHK constraint. Default = blank (Real > 0.0)

PTMAX

Maximum thickness for the PLYTHK constraint. Default = blank (Real > 0.0 and > PTMIN)

PTOPT

Ply selection options for the PLYTHK constraint. Plies can be selected based on the following: BYANG: Orientation (Default)

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Field

Contents BYSET: Ply sets BYPLY: Ply IDs

PTSET

Set ID of elements to which the PLYTHK constraint is applied.

PTEXC

Exclusion flag indicating that certain plies are excluded from the PLYTHK constraint. The following options are supported: NONE: Plies are not excluded. CORE: The core is excluded. (Default) CONST: Plies defined in the CONST constraint are excluded. BOTH: CORE and CONST are considered.

PLYPCT

PLYPCT flag indicating that ply thickness percentage constraints are applied. Multiple PLYPCT constraints are allowed.

PPGRP

Ply orientation in degrees, ply sets or ply IDs, to which the PLYPCT constraint is applied, depending on the PPOPT selection. No default (Real or Integer)

PPMIN

Minimum percentage thickness for the PLYPCT constraint. Default = blank (Real > 0.0 and < 1.0)

PPMAX

Maximum percentage thickness for the PLYPCT constraint. Default = blank (Real > 0.0, < 1.0 and > PPMIN)

PPOPT

Ply selection options for the PLYPCT constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

PPSET

Set ID of elements to which the PLYPCT constraint is applied.

PPEXC

Exclusion flag indicating that certain plies are excluded from the PLYPCT constraint. The following options are supported: NONE: Plies are not excluded. CORE: The core is excluded. (Default)

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Field

Contents CONST: Plies defined in the CONST constraint are excluded. BOTH: CORE and CONST are considered.

PLYMAN

PLYMAN flag indicating that manufacturable ply thickness constraints are applied. Multiple PLYMAN constraints are allowed.

PMGRP

Ply orientation in degrees, ply sets or ply IDs, to which the PLYMAN constraint is applied, depending on the PMOPT selection. No default (Real or Integer)

PMMAN

Manufacturable ply thickness. See comment 6. Default = blank (Real > 0.0)

PMOPT

Ply selection options for the PLYMAN constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

PMSET

Set ID of elements to which the PLYMAN constraint is applied.

PMEXC

Exclusion flag indicating that certain plies are excluded from the PLYMAN constraint. The following options are supported: NONE: Plies are not excluded. CORE: The core is excluded. (Default) CONST: Plies defined in the CONST constraint are excluded. BOTH: CORE and CONST are considered.

BALANCE

BALANCE flag indicating that a balancing constraint is applied. Multiple BALANCE constraints are allowed.

BGRP1

First ply orientation in degrees, ply sets or ply IDs, to which the BALANCE constraint is applied, depending on the BOPT selection. No default (Real or Integer)

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Field

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BGRP2

Second ply orientation in degrees, ply sets or ply IDs, to which the BALANCE constraint is applied, depending on the BOPT selection. No default (Real or Integer)

BOPT

Ply selection options for the BALANCE constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

CONST

CONST flag indicating that a constant thickness constraint is applied. Multiple CONST constraints are allowed.

CGRP

Ply orientation in degrees, ply sets or ply IDs, to which the CONST constraint is applied, depending on the COPT selection. No default (Real or Integer)

CTHICK

Constant ply thickness for the CONST constraint. No default (Real > 0.0)

COPT

Ply selection options for the CONST constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

PLYDRP

Indicates that ply drop-off constraints are applied. Multiple PLYDRP constraints are allowed.

PDGRP

Ply orientation in degrees, ply sets or ply IDs, to which the PLYDRP constraint is applied, depending on the PDOPT selection. No default. (Real or Integer)

PDTYP

PDTYP specifies the type of the drop-off constraint as: PLYSLP (Default) PLYDRP TOTSLP

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Field

Contents TOTDRP (see Comment 11)

PDMAX

Maximum allowed drop-off for the PLYDRP constraint. No default (Real > 0)

PDOPT

Ply selection options for the PLYDRP constraint. Plies can be selected based on the following: BYANG: Orientation (Default) BYSET: Ply sets BYPLY: Ply IDs

PDSET

Set IDs of elements to which the PLYDRP constraint is applied.

PDEXC

Exclusion flag indicates that certain plies are excluded from the PLYDRP constraint. The following options are supported: NONE: Plies are not excluded. CORE: The core is excluded. (Default). CONST: Plies defined in the CONST constraint are excluded. BOTH: CORE and CONST are considered.

PDDEF

Optional definition to fine-tune the drop-off constraint. Currently only DIRECT is available to request directional dropoff, in which case PDX, PDY and PDZ specify the drop-off direction. See comment 12.

PDX, PDY, PDZ

Used to specify the drop-off direction when DIRECT is input in the PDDEF field. See comment 12.

PATRN

PATRN flag indicating that pattern grouping is active for the properties listed. Indicates that information for pattern grouping is to follow.

TYP

Indicates the type of pattern grouping requested. See comment 1. Default = No pattern grouping (1, 2, 3, 9, or 10)

AID/XA, YA, ZA

906

Anchor point for pattern grouping. The point may be defined by entering a grid ID in the AID field or by entering X, Y, and Z coordinates in the XA, YA, and ZA fields. These coordinates will be in the basic coordinate system. See comment 1.

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Field

Contents Default = origin (Real in all three fields or Integer in first field)

FID/XF, YF, ZF

First point for pattern grouping. The point may be defined by entering a grid ID in the FID field or by entering X, Y, and Z coordinates in the XF, YF, and ZF fields. These coordinates will be in the basic coordinate system. See comment 1. No default (Real in all three fields or Integer in the first field)

UCYC

Number of cyclical repetitions for cyclical symmetry. This field defines the number of radial "wedges" for cyclical symmetry. The angle of each wedge is computed as 360.0/UCYC. See comment 1. Default = blank (Integer > 0 or blank)

SID/XS, YS, ZS

Second point for pattern grouping. The point may be defined by entering a grid ID in the SID field or by entering X, Y, and Z coordinates in the XS, YS, and ZS fields. These coordinates will be in the basic coordinate system. See comment 1. No default (Real in all three fields or Integer in first field)

MASTER

MASTER flag indicating that this design variable may be used as a master pattern for pattern repetition. See comment 2.

SLAVE

SLAVE flag indicating that this design variable is slave to the master pattern definition referenced by the following DSIZE_ID entry. See comment 2.

DSIZE_ID

DSIZE identification number for a master pattern definition. No default (Integer > 0)

SX, SY, SZ

Scale factors for pattern repetition, in X, Y, and Z directions respectively. See comment 2. Default = 1.0 (Real > 0.0)

COORD

COORD flag indicating information regarding the coordinate system for pattern repetition is to follow. This is required if either MASTER or SLAVE flags are present.

CID

Coordinate system ID for a rectangular coordinate system that may be used as the pattern repetition coordinate system. See comment 2.

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Field

Contents Default = 0 (Integer > 0)

CAID/XCA, YCA, ZCA Anchor point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CAID field or by entering X, Y, and Z coordinates in the XCA, YCA, and ZCA fields. These coordinates will be in the basic coordinate system. See comment 2. No default (Real in all three fields or Integer in the first field) CFID/XCF, YCF, ZCF

First point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CFID field or by entering X, Y, and Z coordinates in the XCF, YCF, and ZCF fields. These coordinates will be in the basic coordinate system. See comment 2. No default (Real in all three fields or Integer in the first field)

CSID/XCS, YCS, ZCS Second point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CSID field or by entering X, Y, and Z coordinates in the XCS, YCS, and ZCS fields. These coordinates will be in the basic coordinate system. See comment 2. No default (Real in all three fields or Integer in the first field) CTID/XCT, YCT, ZCT Third point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CTID field or by entering X, Y, and Z coordinates in the XCT, YCT, and ZCT fields. These coordinates will be in the basic coordinate system. See comment 2. No default (Real in all three fields or Integer in the first field) FATIGUE

FATIGUE flag indicating that fatigue constraints are active and their definition is to follow.

FTYPE

Specifies the type of fatigue constraint; it can be DAMAGE, LIFE or FOS.

FBOUND

Specifies the bound value. If FTYPE is DAMAGE, FBOUND will be the upper bound of fatigue damage. If FTYPE is LIFE or FOS, FBOUND will be the lower bound of fatigue life (LIFE) or Factor of Safety (FOS), respectively. No default (Real)

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Field

Contents

GROUP

Specifies the definition of zone based free-sizing optimization. Indicates that element group IDs will follow.

EG#

Element group numbers. Element groups are created through element sets. See comment 7. No default (Integer > 0)

THRU

This keyword can be used in the optional alternate format to define zone based free-sizing optimization. This keyword is used for ID range definition to indicate that all ID’s between the preceding ID (EG1) and the following ID (EG2) are to be included in the set.

Comments 1.

There are currently five pattern grouping options for free-size optimization: 1-plane symmetry (TYP = 1) This type of pattern grouping requires that the anchor point and the first point be defined. A vector from the anchor point to the first point is normal to the plane of symmetry. 2-plane symmetry (TYP = 2) This type of pattern grouping requires that the anchor point, first point, and second point be defined. A vector from the anchor point to the first point is normal to the first plane of symmetry. The second point is projected normally onto the first plane of symmetry. A vector from the anchor point to this projected point is normal to the second plane of symmetry. 3-plane symmetry (TYP = 3) This type of pattern grouping requires that the anchor point, first point, and second point be defined. A vector from the anchor point to the first point is normal to the first plane of symmetry. The second point is projected normally onto the first plane of symmetry. A vector from the anchor point to this projected point is normal to the second plane of symmetry. The third plane of symmetry is orthogonal to both the first and second planes of symmetry, passing through the anchor point. Cyclic (TYP = 10) This type of pattern grouping requires that the anchor point, first point, and number of cyclical repetitions be defined. A vector from the anchor point to the first point defines the axis of symmetry. Cyclic with symmetry (TYP = 11) This type of pattern grouping requires that the anchor point, first point, second point, and number of cyclical repetitions be defined. A vector from the anchor point to the first

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point defines the axis of symmetry. The anchor point, first point, and second point all lay on a plane of symmetry. A plane of symmetry lies at the center of each cyclical repetition. For a more detailed description, refer to the Pattern Grouping for Free-Size Optimization page contained within the User’s Guide section Manufacturability for Free-Size Optimization. 2.

Pattern repetition allows similar regions of the design domain to be linked together so as to produce similar topological layouts. This is facilitated through the definition of "Master" and "Slave" regions. A DSIZE card may only contain one MASTER or SLAVE flag. For both "Master" and "Slave" regions, a pattern repetition coordinate system is required and is described following the COORD flag. In order to facilitate reflection, the coordinate system may be a left-handed or right-handed Cartesian system. The coordinate system may be defined in one of two ways, listed here in order of precedence: Four points are defined and these are utilized as follows to define the coordinate system (this is the only way to define a left-handed system): -

A vector from the anchor point to the first point defines the x-axis.

-

The second point lies on the x-y plane, indicating the positive sense of the y-axis.

-

The third point indicates the positive sense of the z-axis.

A rectangular coordinate system and an anchor point are defined. If only an anchor point is defined, it is assumed that the basic coordinate system is to be used. Multiple "Slaves" may reference the same "Master." Scale factors may be defined for "Slave" regions, allowing the "Master" layout to be adjusted. For a more detailed description, refer to the Pattern Repetition for Free-Size Optimization contained within the User’s Guide section Manufacturability for Free-Size Optimization. 3.

It is recommended that a MINDIM value be chosen which allows for the formation of members that are at least three elements thick. When pattern grouping constraints are active, a MINDIM value of three times the average element edge length is enforced, and user-defined values (which are smaller than this value) will be replaced by this value.

4.

Von Mises stress constraints may be defined for topology and free-size optimization through the STRESS optional continuation line on the DTPL or the DSIZE card. There are a number of restrictions with this constraint: The definition of stress constraints is limited to a single von Mises permissible stress. The phenomenon of singular topology is pronounced when different materials with different permissible stresses exist in a structure. Singular topology refers to the problem associated with the conditional nature of stress constraints that is the stress constraint of an element disappears when the element vanishes. This creates another problem in that a huge number of reduced problems exist with solutions that cannot usually be found by a gradient-based optimizer in the full design space. Stress constraints for a partial domain of the structure are not allowed because they often create an ill-posed optimization problem since elimination of the partial domain would remove all stress constraints. Consequently, the stress constraint applies to the

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entire model when active, including both design and non-design regions, and stress constraint settings must be identical for all DSIZE and DTPL cards. The capability has built-in intelligence to filter out artificial stress concentrations around point loads and point boundary conditions. Stress concentrations due to boundary geometry are also filtered to some extent as they can be improved more effectively with local shape optimization. Due to the large number of elements with active stress constraints, no element stress report is given in the table of retained constraints in the .out file. The iterative history of the stress state of the model can be viewed in HyperView or HyperMesh. Stress constraints do not apply to 1D elements. Stress constraints may not be used when enforced displacements are present in the model. 5.

The following manufacturing constraints are available for composite free-sizing optimization: Lower and upper bounds on the total thickness of the laminate (LAMTHK). Lower and upper bounds on the thickness of a given orientation (PLYTHK). Lower and upper bounds on the thickness percentage of a given orientation (PLYPCT). Linking between the thicknesses of two given orientations (BALANCE). Constant (non-designable) thickness of a given orientation (CONST). LAMTHK, PLYTHK, PLYPCT, and PLYMAN can be applied locally to sets of elements. There can be elements that do not belong to any set. For a more detailed description and an example, refer to Optimization of Composite Structures in the User’s Guide.

6.

PLYMAN has no influence on the free-size phase, but this information will be translated into the TMANUF entry on the PLY card for the sizing phase.

7.

Elements within each group will have uniform ply thicknesses.

8.

The core is designable by default. It can be made non-designable through the CONST manufacturing constraint. To facilitate this, the keyword CORE can be used instead of a ply ID when BYPLY is activated.

9.

The core is excluded from the LAMTHK, PLYTHK, PLYPCT and PLYMAN manufacturing constraints by default.

10. Legacy data field PTMAN (for manufacturable ply thickness) defined on the PLYTHK and PLYPCT entries is supported. However, it is now recommended to define the manufacturable ply thickness in the PMMAN field through the PLYMAN continuation line as this offers more control. 11. The options for selecting the type of drop-off constraints for PDTYP are defined for a set of plies, as shown in the figures below: The options for PDTYP are: PLYSLP

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PLYDRP TOTSLP TOTDRP

Assuming that the plies are stacked as shown above, you have the following definitions:

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12. The optional PDDEF definition is used to fine-tune the drop-off constraint. Currently, only the DIRECT option is available for the PDDEF field. Field

Value

PDDEF

DIRECT – This option allows you to fine-tune the drop-off constraint by requesting directional drop-off. The direction of drop-off can be specified by defining a directional vector with respect to the basic coordinate system. The directional vector is defined using the PDX, PDY and PDZ values.

PDX, PDY, PDZ

PDX, PDY and PDZ are real numbers. These values are used to specify the drop-off direction when DIRECT is input in the PDDEF field. They specify the three components of a directional vector defined with respect to the basic coordinate system. Example: If drop-off control is required in the X-direction, then 1,0,0 can be defined in the PDX, PDY, PDZ fields respectively. 0,1,0 can be defined for Y-direction drop-off control.

13. This card is represented as an optimization design variable in HyperMesh.

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DSYSID Bulk Data Entry DSYSID – Design Objective for System Identification Description Defines responses and their target values for a system identification problem. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

DSYSID

DOID

LABEL

RID1

SID1

T1

W1

+

RID2

SID2

T2

W2

+

...

+

RIDn

SIDn

Tn

Wn

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

DSYSID

22

SYS

3

4

0.002

5

5

0.05

+

(7)

(8)

(9)

(10)

Associated Cards (1)

(2)

(3)

(4)

DRESP1

3

TZ488

DISP

3

488

DRESP1

5

TZ601

DISP

3

601

Altair Engineering

(5)

(6)

(7)

(8)

(9)

(10)

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915

Field

Contents

DOID

Design objective identification number. (Integer > 0)

LABEL

User-defined name for the response. No default (Character)

RIDi

DRESP1, DRESP2, or DRESP3 identification number. (Integer > 0)

SIDi

Subcase identification number; use ALL if it applies to all subcases. Default = ALL (Integer > 0, blank or ALL)

Ti

Target value. No default (Real)

Wi

Weighting factor. Default = 1.0 (Real or blank)

Comments 1.

If the DSYSID entry is referenced by a DESOBJ subcase entry, a least squares objective function is used in the optimization. The objective function is the sum of the squared, weighted, normalized differences between the target responses and those calculated by the finite element analysis:

If the DSYSID entry is referenced by a MINMAX or MAXMIN subcase entry, the beta method is applied in the optimization as follows:

2.

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DSYSID entries must have unique identification numbers with respect to DRESP1, DRESP2, and DRESP3 entries.

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3.

DRESP1, DRESP2, and DRESP3 entries referenced by the DSYSID entry can define only a single response per subcase when the DESOBJ formulation is used. There is no such limitation with the MINMAX or MAXMIN formulations.

4.

In order to use DSCREEN to control the number of retained responses when performing a system identification, RTYPE=EQUA needs to be used on the DSCREEN entry.

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DTABLE Bulk Data Entry DTABLE – Table of Constants Description List of constants to be used in functions defined by DEQATN. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

DTABLE

LABL1

VAL1

LABL2

VAL2

LABL3

VAL3

LABL4

VAL4

LABL5

VAL5

Etc…

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DTABLE

W

123.00

H

321.00

B

55.55

AGE

21

C

36.0

WST

24.0

HPS

35.0

Field

Contents

LABLi

Constant Label.

(10)

(Character) VALi

Constant value. (Real)

Comments 1.

If a DTABLE entry has a pair of blank fields, they are ignored. If there are other constants after the blank fields, they are read in.

2.

If fields are full of zeros, the constant label is "0", and the value is 0.0.

3.

This card is represented as an optimization table entry in HyperMesh.

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DTI,SPECSEL Bulk Data Entry DTI,SPECSEL – Response Spectra Input Correlation Table Description Correlates spectra lines specified on TABLED1 entries with damping values. Format (1)

(2)

(3)

(4)

DTI

SPEC SEL

ID

TID3

DAMP3

…

…

…

(5)

(6)

(7)

(8)

(9)

TYPE

TID1

DAMP1

TID2

DAMP2

…

…

…

…

…

(10)

Example

(1)

(2)

(3)

DTI

SPEC SEL

99

4

0.04

(4)

(5)

(6)

(7)

(8)

(9)

A

2

0.0

3

0.02

Field

Contents

ID

DTI,SPECSEL identification number.

(10)

No default (Integer > 0) TYPE

Type of spectrum. Can be either acceleration (A), velocity (V) or displacement (D). No default (A, V, D)

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Field

Contents

TID#

Identification number of a TABLED1 entry that defines a line of the spectrum. No default (Integer > 0)

DAMP#

Damping value assigned to TID#. No default (Real)

Comments 1.

All DTI,SPECSEL cards must have unique ID numbers.

2.

The TID#, DAMP# pairs list the TABLED1 entry, which defines a line of the spectrum and the damping value assigned to it. The damping value is in the units of fraction of critical damping.

3.

Refer to Response Spectrum Analysis in the User’s Guide for more details.

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DTI,UNITS Bulk Data Entry DTI,UNITS – Units Definition Description Defines units for multi-body, component mode synthesis (flexible-body preparation), and geometric nonlinear solution sequences. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DTI

UNITS

1

MASS

FORC E

LENGTH

TIME

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

DTI

UNITS

1

KG

N

M

S

Field

Contents

MASS

Units of mass. See comment 1.

(8)

(9)

(10)

Default = KG (KG, LBM, SLUG, GRAM, OZM, KLBM, MGG, SLINCH, UG, NG, USTON, or MG) FORCE

Units of force. See comment 2. Default = N (N, LBF, KGF, OZF, DYNE, KN, KLBF, MN, UN, or NN)

LENGTH

Units of length. See comment 3. Default = MM (MM, KM, M, CM, MI, FT, IN, UM, NM, ANG, YD, MIL, or UIN)

TIME

Units of time. See comment 4. Default = S (S, H, MIN, MS, US, NANOSEC, or D)

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Comments 1.

2.

922

The following options are available for input for MASS: kg

kilogram

lbm

pound-mass

slug

slug

gram

gram

ozm

ounce-mass

klbm

kilo pound-mass (1000.lbm)

mgg

megagram

slinch

12 slugs

ug

Microgram

ng

Nanogram

uston

US ton

mg

Milligram

The following options are available for input for FORCE: n

newton

lbf

pounds-force

kgf

kilograms-force

ozf

ounce-force

dyne

dyne

kn

kilonewton

klbf

kilo pound-force (1000.lbf)

mn

Millinewton

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3.

4.

un

Micronewton

nn

Nanonewton

The following options are available for input for LENGTH: km

kilometer

m

meter

cm

centimeter

mm

millimeter

mi

mile

ft

foot

in

inch

um

Micrometer

nm

Nanometer

ang

Angstrom

yd

Yard

mil

Milli-inch

uin

Micro-inch

The following options are available for input for TIME: s

seconds

h

hours

min

minutes

ms

milliseconds

us

Microsecond

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nanosec Nanosecond d

day

5.

PARAM, WTMASS is ignored for the multi-body and component mode synthesis (flexiblebody preparation) solution sequences. Unit data for these solution sequences is supplied on the DTI,UNITS bulk data entry.

6.

This DTI, UNITS data entry is the same as the UNITS entry.

7.

This card is represented as a control card in HyperMesh.

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DTPG Bulk Data Entry DTPG – Design Variable for Topography Optimization Description Defines parameters for the generation of topography design variables. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DTPG

ID

TYPE

PID1/DVID

PID2

PID3

PID4

PID5

PID6

PID7

…

…

…

…

…

…

MW

ANG

BF

HGT

Norm/XD

YD

ZD

SKIP

PATRN

TYP

AID/XA

YA

ZA

FID/XF

YF

ZF

PATRN2

UC YC

SID/XS

YS

ZS

BOUNDS

LB

UB

INIT

(10)

Optional continuation lines for "Master" definition for pattern repetition constraint: (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ID

C AID/ XC A

YC A

ZC A

C FID/XC F

YC F

ZC F

C SID/ XC S

YC S

ZC S

C TID/ XC T

YC T

ZC T

(10)

MASTER

C OORD

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Optional continuation lines for "Slave" definition for pattern repetition constraint: (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SLAVE

DTPL_ID

SX

SY

SZ

C OORD

C ID

C AID/ XC A

YC A

C SID/ XC S

YC S

(10)

ZC A

C FID/XC F

YC F

ZC F

ZC S

C TID/ XC T

YC T

ZC T

Example 1 This example defines a topography design variable which allows for swages to be created in components referencing the PSHELL properties 1, 9, and 23. The swages will have a minimum width of 3 units, a draw angle of 600, and a maximum height of 5 units. The draw direction will be in the element’s normal direction, but the swages may grow in either the positive or negative direction. The swages should be grouped such that they form a cyclical pattern of 1200 intervals about the z-axis, through the point (0,25,0), and they also should be symmetrical about the xy plane. (1)

(2)

(3)

(4)

(5)

(6)

DTPG

1

PSHELL

1

9

23

3.0

60.0

Yes

5.0

Norm

PATRN

50

0.0

25.0

0.0

PATRN2

3

1.0

0.0

0.0

BOUNDS

-1.0

1.0

(7)

(8)

(9)

(10)

both

0.0

1.0

0.0

Example 2 This example defines a topography design variable that references the shape variables defined by the DVGRIDs with ID 1. The swages will have a minimum width of 5 units and a draw angle of 750. The height and draw direction of the swages is defined by the DVGRID cards. Also ensure that the swages can only grow in the positive direction as defined by the DVGRID cards.

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(1)

(2)

(3)

(4)

DTPG

1

DVGRID

1

5.0

75.0

YES

BOUNDS

0.0

1.0

(5)

(6)

Field

Contents

ID

Each DTPG card must have a unique ID.

(7)

(8)

(9)

(10)

No default (Integer > 0) TYPE

Indicate whether DTPG card is defined for PSHELL, PCOMP, or DVGRID. No default (PSHELL, PCOMP, or DVGRID)

PID/DVID

If TYPE is PSHELL or PCOMP, then this entry is a Property identification number. Use ALL if it applies to all properties of type PTYPE in the model. Numerous PIDs may be given. If TYPE is DVGRID, then this entry is the Design Variable Number for a set of DVGRIDs. Only one DVID may be given. Default = ALL (Integer > 0, blank or ALL)

MW

Bead minimum width. This parameter controls the width of the beads in the model [recommended value between 1.5 and 2.5 times the average element width]. See comment 1. No default (Real > 0.0)

ANG

Draw angle in degrees. This parameter controls the angle of the sides of the beads (recommended value between 60 and 75 degrees). See comment 1. No default (1.0 < Real < 89.0)

BF

Buffer zone. This parameter will establish a buffer zone between elements in the design domain and elements outside the design domain. See comment 2.

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Field

Contents Default = YES (YES, or NO)

HGT

Draw height. This parameter sets the maximum height of the beads to be drawn. This field is only valid if TYPE is PSHELL or PCOMP. No default (Real > 0.0)

norm/XD,YD,ZD Draw direction. If norm/XD field is ‘norm’, the shape variables will be created in the normal directions of the elements. If all the fields are real, the shape variable will be created in the direction specified by the xyz vector defined by the three fields. The X, Y, and Z values are in the global coordinate system. This field is only valid if TYPE is PSHELL or PCOMP. Default = NORM (NORM in norm/XD field or Real in all three fields) SKIP

Boundary skip. This parameter tells OptiStruct to leave certain nodes out of the design domain. If ‘none’, all nodes attached to elements whose PIDs are specified will be a part of the shape variables. If ‘bc’ or ‘spc’, any nodes which have SPC or SPC1 declarations are omitted from the design domain. If ‘load’, any nodes which have FORCE, FORCE1, MOMENT, MOMENT1, or SPCD declarations are omitted from the design domain. If ‘both’, nodes with either ‘spc’ or ‘load’ declarations are omitted from the design domain. This field is only valid if TYPE is PSHELL or PCOMP. Default = BOTH (BOTH, BC, SPC, LOAD, or NONE)

PATRN

PATRN flag indicating that variable pattern grouping is active. Indicates that information about the pattern group will follow.

TYP

Type of variable grouping pattern. Required if any symmetry or variable pattern grouping is desired. If zero or blank, anchor node, first vector, and second vector definitions are ignored. If less than 20, second vector definition is ignored. See comment 4. Default = 0 (Integer > 0)

AID/XA,YA,ZA

Variable grouping pattern anchor point. These fields define a point that determines how grids are grouped into variables. See comment 3. The X, Y, and Z values are in the global coordinate system. You may put a grid ID in the AID/XA field to define the anchor point. Default = origin (Real in all three fields or Integer in AID/XA field)

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Field

Contents

FID/XF,YF,ZF

Direction of first vector for variable pattern grouping. These fields define an xyz vector which determines how grids are grouped into variables (See comment 3). The X, Y, and Z values are in the global coordinate system. You may put a grid ID in the FID/XF field to define the first vector. This vector goes from the anchor point to this grid. If all fields are blank and the TYP field is not blank or zero, OptiStruct gives an error. No default

PATRN2

PATRN2 flag indicating variable pattern grouping continuation card. This card is only required when a second vector is needed to define the pattern grouping.

UCYC

Number of cyclical repetitions for cyclical symmetry. This field defines the number of radial "wedges" for cyclical symmetry. The angle of each wedge is computed as 360.0 / UCYC. See comment 4. Default = 0 (Integer > 0 or blank)

SID/XS,YS,ZS

Direction used to determine second vector for variable pattern grouping. These fields define an xyz vector which, when combined with the first vector, form a plane. The second vector is calculated to lie in that plane and is perpendicular to the first vector. The second vector is sometimes required to determine how grids are grouped into variables (See comment 3). The X, Y, and Z values are in the global coordinate system. You may put a grid ID in the SID/XS field to define the second vector. This vector goes from the anchor point to this grid. If all fields are blank and the TYP field contains a value of 20 or higher, OptiStruct gives an error. No default

BOUNDS

BOUNDS flag indicating that information on upper and lower limits and the initial value for grid movement are to follow.

LB

Lower bound on variables controlling grid movement. This sets the lower bound on grid movement equal to LB*HGT. Default = 0.0 (Real < UB)

UB

Upper bound on variables controlling grid movement. This sets the upper bound on grid movement equal to UB*HGT. Default = 1.0 (Real > LB)

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Field

Contents

INIT

The initial value of the variables controlling grid movement. This sets the initial value on grid movement equal to INIT*HGT. Default = LB + factor*(UB-LB), if LB > 0.0 and UB > 0.0 Default = UB - factor*(UB-LB), if LB < 0.0 and UB < 0.0 Default = factor*max(abs(LB),UB), if LB < 0.0 and UB > 0.0 where: factor = 0.0 if this DTPG is not used in a BEADFRAC response or is used in a BEADFRAC response that is neither chosen as the objective nor constrained. factor = 0.9 if this DTPG is used in a BEADFRAC response that is chosen as the objective. factor = constraint_value if this DTPG is used in a BEADFRAC response that is constrained. (LB < Real < UB)

MASTER

MASTER flag indicating that this design variable may be used as a master pattern for pattern repetition.

COORD

COORD flag indicating information regarding the coordinate system for pattern repetition is to follow. This is required if either MASTER or SLAVE flags are present.

CID

Coordinate system ID for a rectangular coordinate system that may be used as the pattern repetition coordinate system. See comment 6. Default = 0 (Integer > 0)

CAID/XCA, YCA, ZCA

Anchor point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CAID field or by entering X, Y, and Z coordinates in the XCA, YCA, and ZCA fields. These coordinates will be in the basic coordinate system. See comment 6. No default (Real in all three fields or Integer in the first field)

CFID/XCF, YCF, First point for pattern repetition coordinate system. The point may ZCF be defined by entering a grid ID in the CFID field or by entering X, Y,

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Field

Contents and Z coordinates in the XCF, YCF, and ZCF fields. These coordinates will be in the basic coordinate system. See comment 6. No default (Real in all three fields or Integer in the first field)

CSID/XCS, YCS, ZCS

Second point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CSID field or by entering X, Y, and Z coordinates in the XCS, YCS, and ZCS fields. These coordinates will be in the basic coordinate system. See comment 6. No default (Real in all three fields or Integer in the first field)

CTID/XCT, YCT, ZCT

Third point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CTID field or by entering X, Y, and Z coordinates in the XCT, YCT, and ZCT fields. These coordinates will be in the basic coordinate system. See comment 6. No default (Real in all three fields or Integer in the first field)

SLAVE

SLAVE flag indicating that this design variable is slaved to the master pattern definition referenced by the following DTPL_ID entry. See comment 6.

DTPL_ID

DTPL identification number for a master pattern definition. No default (Integer > 0)

SX, SY, SZ

Scale factors for pattern repetition in X, Y, and Z directions respectively. See comment 6. Default = 1.0 (Real > 0.0)

Comments 1.

The bead minimum width and draw angles are used to determine the geometry of the shape variables. The figure below shows a cross-section of a single shape variable fully extended normal to the plane of the design elements. The top of the bead is flat across the circular area with a diameter equal to the minimum bead width parameter. The sides of the bead taper down at an angle equal to the draw angle parameter.

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Bead width and draw angle definitions

2.

The buffer zone is a parameter that controls how the interfaces between design and nondesign elements are treated. If active, OptiStruct will place the shape variables far enough away from the non-design elements so that the proper bead widths and draw angles are maintained. If inactive, the boundary between the beads and non-design elements will have an abrupt transition. Any nodes that were skipped due to the boundary skip parameter (field 10) will also have a buffer zone created around them.

Transitions between design and non-design elements with and without buffer zone

3.

Symmetry of topography optimization can be enforced across one, two, or three planes. Defining symmetry planes for symmetric model and loading conditions is recommended because automatic variable generation may not be symmetric if it is not enforced. A symmetric mesh is not necessary, OptiStruct will create variables that are very close to identical across the plane(s) of symmetry. If the mesh is larger on one side of the plane(s) of symmetry than the other, OptiStruct will reflect variables created on the ‘positive’ side of the plane(s) of symmetry to the other side(s) but will not create variables on the ‘negative’ side(s) of the plane(s) of symmetry that do not overlap with the positive side. The positive side of the plane(s) of symmetry is the one in which the first vector, second vector, and cross product thereof are pointing toward.

4.

Variable pattern grouping may be defined for a DTPG card. OptiStruct will generate shape variables based on the type of pattern selected in field 20. For variable grouping pattern types 1 through 14, only the first vector and anchor node need to be defined. For variable pattern grouping types 20 or higher, the first and second vectors need to be defined as well as the anchor node. If a grid is used to define the first vector, the normal vector will begin at the anchor point and extend towards the given grid (see below). Grids or xyz data may be used for either the first vector, second vector, or anchor point and can be a mixture, (that is the anchor point may be determined by a grid and the first vector determined by xyz data or vice-versa). One very useful feature for topography optimization in OptiStruct is the automatic generation of shape variables in simple patterns. In many cases, due to manufacturing constraints or the risk of elements being collapsed upon them during shape optimization, it

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is required to create shape variables in patterns that conform to the desired shape of the part. In basic topography optimization (TYP = 0), OptiStruct creates shape variables that are circular. OptiStruct contains a library of different shape variable patterns which can be accessed using the TYP parameter on the DTPG card.

Defining the first vector using a grid point

The second vector is calculated by taking the grid point or vector defined in fields 22, 23, and 24 and projecting it onto plane 1. If a grid point was used to define the second vector, the second vector is a vector running from the anchor node to the projected grid point. If a vector was used to define the second vector, the base of the projected vector is placed at the anchor point. The second vector is normal to plane 2 (see below).

Plane 3 is determined to be normal to both plane 1 and plane 2 (see below).

5.

For a list of patterns supported by OptiStruct, refer to Pattern Grouping Options.

6.

Pattern repetition allows similar regions of the design domain to be linked together so as

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to produce similar topographical layouts. This is facilitated through the definition of "Master" and "Slave" regions. A DTPG card may only contain one MASTER or SLAVE flag. Bead parameters will not be exported for any DTPG cards containing the SLAVE flag. For both "Master" and "Slave" regions, a pattern repetition coordinate system is required and is described following the COORD flag. In order to facilitate reflection, the coordinate system may be a left-handed or right-handed Cartesian system. The coordinate system may be defined in one of two ways, listed here in order of precedence: Four points are defined and these are utilized as follows to the define the coordinate system (this is the only way to define a left-handed system): - A vector from the anchor point to the first point defines the x-axis. - The second point lies on the x-y plane, indicating the positive sense of the y-axis. - The third point indicates the positive sense of the z-axis. A rectangular coordinate system and an anchor point are defined. If only an anchor point is defined, it is assumed that the basic coordinate system is to be used. Multiple "Slaves" may reference the same "Master." Scale factors may be defined for "Slave" regions, allowing the "Master" layout to be adjusted. For a more detailed description, refer to the Pattern Repetition page contained within the User's Guide section Manufacturability for Topography Optimization. 7.

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This card is represented as an optimization design variable in HyperMesh.

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DTPL Bulk Data Entry DTPL – Design Variable for Topology Optimization Description Defines parameters for the generation of topology design variables. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

DTPL

ID

PTYPE

PID1

PID2

PID3

PID4

PID5

PID6

PID7

…

…

…

…

…

…

…

…

(8)

(9)

(10)

(8)

(9)

(10)

Optional continuation lines for minimum thickness definition: (1)

(2)

(3)

TMIN

T0

(4)

(5)

(6)

(7)

Optional continuation lines for stress constraint definition: (1)

(2)

(3)

(4)

STRESS

UBOUND

(5)

(6)

(7)

Optional continuation lines for member size constraint definition: (1)

(2)

(3)

(4)

MEMBSIZ MINDIM MAXDIM

Altair Engineering

(5)

(6)

(7)

(8)

(9)

(10)

MINGAP

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Optional continuation lines for mesh type definition: (1)

(2)

(3)

MESH

MTYP

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(10)

Optional continuation lines for draw direction constraint definition: (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

DRAW

DTYP

DAID/ XDA

YDA

ZDA

DFID/ XDF

YDF

ZDF

OBST

OPID1

OPID2

OPID3

OPID4

OPID5

OPID6

OPID7

OPID8

…

…

…

…

…

…

(8)

(9)

NOHOLE

STAMP

TSTAMP

Optional continuation lines for extrusion constraint definition: (1)

(2)

(3)

EXTR

ETYP

EPATH1

EPATH2

(4)

(5)

(6)

(7)

(10)

EP1_ID1 EP1_ID2 EP1_ID3 EP1_ID4 EP1_ID5 EP1_ID6 EP1_ID7

EP1_ID8

…

…

…

…

…

…

…

…

EP2_ID1 EP2_ID2 EP2_ID3 EP2_ID4 EP2_ID5 EP2_ID6 EP2_ID7

EP2_ID8

…

…

…

…

…

…

…

…

Optional continuation lines for "Master" definition for pattern repetition constraint:

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(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

C ID

C AID/ XC A

YC A

ZC A

C FID/ XC F

YC F

ZC F

C SID/ XC S

YC S

ZC S

C TID/ XC T

YC T

ZC T

(10)

MASTER

C OORD

Optional continuation lines for "Slave" definition for pattern repetition constraint: (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SLAVE

DTPL_ID

SX

SY

SZ

C OORD

C ID

C AID/ XC A

YC A

ZC A

C FID/ XC F

YC F

ZC F

C SID/ XC S

YC S

ZC S

C TID/ XC T

YC T

ZC T

(10)

Optional continuation lines for pattern grouping constraint definition: (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PATRN

TYP

AID/XA

YA

ZA

FID/XF

YF

ZF

UC YC

SID/XS

YS

ZS

(8)

(9)

(10)

(8)

(9)

(10)

Optional continuation lines for material definition if PTYPE=COMP: (1)

(2)

(3)

MAT

MATOPT

(4)

(5)

(6)

(7)

Optional continuation lines for fatigue constraint definition: (1)

(2)

(3)

(4)

FATIGUE

FTYPE

FBOUND

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(5)

(6)

(7)

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Optional continuation lines for Level Set Method (Topology Optimization) activation: (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

LEVELSE T

HOLEIN ST

HOLERA D

NHOLES X

NHOLES Y

NHOLES Z

(9)

(10)

Example 1

Define a topology design variable that allows the thickness of components referencing the PSHELL properties 7, 8, and 17 to vary between 1.0 and 5.0 (the thickness defined on PSHELL definitions with PID 7, 8, and 17 is 5.0). The optimized design should contain members whose width is no less than 60.0 units. (1)

(2)

(3)

(4)

(5)

(6)

DTPL

1

PSHELL

7

8

17

MEMBSIZ

60.0

TMIN

1.0

(7)

(8)

(9)

(10)

Example 2

Define a topology design variable for components referencing the PSOLID properties 4, 5, and 6. The optimized design should contain members whose diameter is no less than 60.0 units. The final design will be manufactured using a casting process, where the draw direction lies along the x-axis. The components referencing PSOLID properties 10, 11, and 12 are non-designable, but will form part of the same casting as the designable components.

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(1)

(2)

(3)

(4)

(5)

(6)

DTPL

1

PSOLID

4

5

6

MEMBSIZ

60.0

DRAW

SPLIT

0.0

0.0

0.0

(7)

(8)

(9)

1.0

0.0

0.0

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(10)

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OBST

10

11

12

Field

Contents

ID

Each DTPL card must have a unique ID. No default (Integer > 0)

PTYPE

Property type for which DTPL card is defined, PBAR, PBARL, PBEAM, PBEAML, PBUSH, PROD, PWELD, PSHELL, PCOMP, or PSOLID. No default (PBAR, PBARL, PBEAM, PBEAML, PBUSH, PROD, PWELD, PSHELL, PCOMP, or PSOLID)

PID#

Property identification numbers. List of properties of type PTYPE for which this DTPL card is defined. Use ALL in PID1 field, if it applies to all properties of type PTYPE in the model. If no PIDs are listed, OptiStruct will check all properties of type PTYPE to see if they are to be included in the design space (see help section for PCOMP, PSHELL, and PSOLID). If any properties satisfy this search, then they will be affected by entries on this card. In this situation (where no PIDs are defined), only one DTPL card can be defined for the given PTYPE. Default = blank (Integer > 0, blank or ALL)

TMIN

TMIN flag indicating that minimum thickness value will follow. Only valid when PTYPE = PSHELL. If not present when PTYPE = PSHELL, then minimum thickness will default to the T0 value defined on the PSHELL card. If no T0 value is defined on the PSHELL card, the minimum thickness will default to 0.0.

T0

Minimum thickness for PSHELL properties when the referenced material is of type MAT1. If PSHELL references a material which is not of type MAT1, this value is ignored and T0 = 0.0 is used. If no value is entered for T0, the T0 value on the PSHELL card is used. If T0 is not defined on the PSHELL card, then T0=0.0 is assumed. Default = blank (Real > 0.0)

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Field

Contents

STRESS

STRESS flag indicating that stress constraints are active and that an upper bound value for stress is to follow. See comment 1.

UBOUND

Upper bound constraint on stress. No default (Real > 0.0)

MEMBSIZ

MEMBSIZ flag indicating that member size control is active for the properties listed. Indicates that MINDIM and possibly MAXDIM are to follow.

MINDIM

Specifies the minimum diameter of members formed. This command is used to eliminate small members. It also eliminates checkerboard results. See comment 2. Default = No Minimum Member Size Control (Real > 0.0)

MAXDIM

Specifies the maximum diameter of members formed. This command is used to prevent the formation of large members. It can only be used in combination with MINDIM. See comment 3. Default = No Maximum Member Size Control (Real > 0.0)

MINGAP

Defines the minimum spacing between structural members formed. This command can only be used in conjunction with MAXDIM. See comment 3. Default = blank (Real > MAXDIM)

MESH

MESH flag indicating that mesh type information is to follow.

MTYP

Indicates that the mesh conforms to certain rules for which the optimizer is tuned. Currently, only the ALIGN option is available. ALIGN indicates that when manufacturing constraints are active, the mesh is aligned with the draw direction or extrusion path. See comment 4. Default = blank (ALIGN or blank)

DRAW

DRAW flag indicating that casting constraints are being applied. Indicates that draw direction information is to follow. Only valid for PTYPE = PSOLID. OptiStruct will terminate with an error if present for other PTYPEs.

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Field

Contents

DTYP

Type of draw direction constraint to be used. Can choose between SINGLE, SPLIT, SPLIT2, or SPLIT3. SINGLE indicates that a single die will be used, the die being withdrawn in the given draw direction. SPLIT allows the optimization of the splitting surface of two dies, with both dies moving apart in the given draw direction. SPLIT2 and SPLIT3 provide alternative methods to optimize the splitting surface. These should only be used in the case where SPLIT creates non-castable cavities. Default = SPLIT (SINGLE, SPLIT, SPLIT2, or SPLIT3)

DAID/XDA, YDA, ZDA

Draw direction anchor point. These fields define the anchor point for draw direction of the casting. The point may be defined by entering a grid ID in the DAID field or by entering X, Y, and Z coordinates in the XDA, YDA, and ZDA fields, these coordinates will be in the basic coordinate system. Default = origin (Real in all three fields or Integer in first field)

DFID/XDF, YDF, ZDF

Direction of vector for draw direction definition. These fields define a point. The vector goes from the anchor point to this point. The point may be defined by entering a grid ID in the DFID field or by entering X, Y, and Z coordinates in the XDF, YDF, and ZDF fields, these coordinates will be in the basic coordinate system. No default (Real in all three fields or Integer in first field)

OBST

OBST flag indicating that a list of PIDs will follow which are non-designable, but their interaction with designable parts needs to be considered with regard to the defined draw direction. OBST stands for obstacle. Only recognized if DRAW flag is also present on same DTPL card. OptiStruct will terminate with an error if OBST flag is present without DRAW flag.

OPID#

Obstacle property identification number. List of nondesignable properties that are to be considered with regard to the defined draw direction. These must be PSOLID. No default (Integer > 0, blank or ALL)

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Field

Contents

NOHOLE

Prevents the formation of through-holes in the draw direction. Note that it does not prevent holes perpendicular to the draw direction. The assumed minimum thickness in the draw direction is twice the average mesh size.

STAMP

STAMP flag forcing the design to evolve into a 3D shell structure. Indicates that thickness, TSTAMP, is to follow. See comment 5.

TSTAMP

Defines the thickness of the 3D shell structure that is evolved with the STAMP option. The recommended minimum thickness is three times the average mesh size. See comment 5. No default (Real > 0.0)

EXTR

EXTR flag indicating that extrusion constraints are being applied. Indicates that extrusion information is to follow. Only valid for PTYPE = PSOLID. OptiStruct will terminate with an error if present for other PTYPEs.

ETYP

Type of extrusion constraint to be used. Can choose between NOTWIST or TWIST. NOTWIST indicates that the cross-section cannot twist about the neutral axis, in which case only one path needs to be defined. TWIST indicates that the cross-section can twist about the neutral axis, in which case two paths need to be defined. Default = NOTWIST (NOTWIST or TWIST)

EPATH1

EPATH1 flag indicating that a list of grid IDs will follow to define the primary extrusion path. Only recognized if EXTR flag is also present on same DTPL card. OptiStruct will terminate with an error if EPATH1 flag is present without EXTR flag.

EP1_ID#

Primary extrusion path identification numbers. List of grid IDs that define the primary extrusion path. No default (Integer > 0 or blank)

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Field

Contents

EPATH2

EPATH2 flag indicating that a list of grid IDs will follow to define the secondary extrusion path. This is only required when ETYP has been set to TWIST. Only recognized if EXTR flag is also present on same DTPL card. OptiStruct will terminate with an error if EPATH2 flag is present without EXTR flag.

EP2_ID#

Secondary extrusion path identification numbers. List of grid IDs that define the secondary extrusion path. No default (Integer > 0 or blank)

MASTER

MASTER flag indicating that this design variable may be used as a master pattern for pattern repetition. See comment 7.

COORD

COORD flag indicating information regarding the coordinate system for pattern repetition is to follow. This is required if either MASTER or SLAVE flags are present.

CID

Coordinate system ID for a rectangular coordinate system that may be used as the pattern repetition coordinate system. See comment 7. Default = 0 (Integer > 0)

CAID/XCA, YCA, ZCA

Anchor point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CAID field or by entering X, Y, and Z coordinates in the XCA, YCA, and ZCA fields. These coordinates will be in the basic coordinate system. See comment 7. No default (Real in all three fields or Integer in first field)

CFID/XCF, YCF, ZCF

First point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CFID field or by entering X, Y, and Z coordinates in the XCF, YCF, and ZCF fields. These coordinates will be in the basic coordinate system. See comment 7. No default (Real in all three fields or Integer in first field)

CSID/XCS, YCS, ZCS

Altair Engineering

Second point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CSID field

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Field

Contents or by entering X, Y, and Z coordinates in the XCS, YCS, and ZCS fields. These coordinates will be in the basic coordinate system. See comment 7. No default (Real in all three fields or Integer in first field)

CTID/XCT, YCT, ZCT

Third point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CTID field or by entering X, Y, and Z coordinates in the XCT, YCT, and ZCT fields. These coordinates will be in the basic coordinate system. See comment 7. No default (Real in all three fields or Integer in first field)

SLAVE

SLAVE flag indicating that this design variable is slaved to the master pattern definition referenced by the following DTPL_ID entry. See comment 7.

DTPL_ID

DTPL identification number for a master pattern definition. No default (Integer > 0)

SX, SY, SZ

Scale factors for pattern repetition in X, Y, and Z directions respectively. See comment 7. Default = 1.0 (Real > 0.0)

COORD

COORD flag indicating information regarding the coordinate system for pattern repetition is to follow. This is required if either MASTER or SLAVE flags are present.

CID

Coordinate system ID for a rectangular coordinate system that may be used as the pattern repetition coordinate system. See comment 7. Default = 0 (Integer > 0)

CAID/XCA, YCA, ZCA

Anchor point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CAID field or by entering X, Y, and Z coordinates in the XCA, YCA, and ZCA fields. These coordinates will be in the basic coordinate system. See comment 7. No default (Real in all three fields or Integer in first field)

CFID/XCF, YCF, ZCF

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First point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CFID field or by entering X, Y, and Z coordinates in the XCF, YCF, and

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Field

Contents ZCF fields. These coordinates will be in the basic coordinate system. See comment 7. No default (Real in all three fields or Integer in first field)

CSID/XCS, YCS, ZCS

Second point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CSID field or by entering X, Y, and Z coordinates in the XCS, YCS, and ZCS fields. These coordinates will be in the basic coordinate system. See comment 7. No default (Real in all three fields or Integer in first field)

CTID/XCT, YCT, ZCT

Third point for pattern repetition coordinate system. The point may be defined by entering a grid ID in the CTID field or by entering X, Y, and Z coordinates in the XCT, YCT, and ZCT fields. These coordinates will be in the basic coordinate system. See comment 7. No default (Real in all three fields or Integer in first field)

PATRN

PATRN flag indicating that pattern grouping is active for the properties listed. Indicates that information for pattern grouping is to follow. Only valid for PTYPE = PCOMP, PSHELL, and PSOLID. OptiStruct will terminate with an error if present for other PTYPEs.

TYP

Indicates the type of pattern grouping requested. See comment 10. Default = No Pattern Grouping (1, 2, 3, 9, 10, or 11)

AID/XA, YA, ZA

Anchor point for pattern grouping. The point may be defined by entering a grid ID in the AID field or by entering X, Y, and Z coordinates in the XA, YA, and ZA fields. These coordinates will be in the basic coordinate system. See comment 10. Default = origin (Real in all three fields or Integer in first field)

FID/XF, YF, ZF

Altair Engineering

First point for pattern grouping. The point may be defined by entering a grid ID in the FID field or by entering X, Y, and Z coordinates in the XF, YF, and ZF fields. These coordinates will be in the basic coordinate system. See comment 10.

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Field

Contents No default (Real in all three fields or Integer in first field)

UCYC

Number of cyclical repetitions for cyclical symmetry. This field defines the number of radial "wedges" for cyclical symmetry. The angle of each wedge is computed as 360.0 / UCYC. See comment 10. Default = blank (Integer > 0 or blank)

SID/XS, YS, ZS

Second point for pattern grouping. The point may be defined by entering a grid ID in the SID field or by entering X, Y, and Z coordinates in the XS, YS, and ZS fields. These coordinates will be in the basic coordinate system. See comment 10. No default (Real in all three fields or Integer in first field)

MAT

Indicates the type of composite topology optimization. Only considered for PTYPE=PCOMP.

MATOPT

PLY: Indicates that the optimization should be performed at the ply level. Topology design variables are applied to each ply individually. This method allows the optimization process to determine which orientation is preferred for each element. HOMO: Indicates that the optimization should be performed on the homogenized shell. This is the method which was used in previous versions of OptiStruct. Default = PLY

FATIGUE

FATIGUE flag indicating that fatigue constraints are active and their definitions are to follow.

FTYPE

Specifies the type of fatigue constraint; it can be DAMAGE, LIFE or FOS.

FBOUND

Specifies the bound value. If FTYPE is DAMAGE, FBOUND will be the upper bound of fatigue damage. If FTYPE is LIFE or FOS, FBOUND will be the lower bound of fatigue life (LIFE) or Factor of Safety (FOS), respectively. No default (Real)

LEVELSET

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LEVELSET flag indicating that the Level Set method (for topology optimization) is activated and the definitions of the required parameters follow.

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Field

Contents

HOLEINST

Defines the method used to insert holes into the design. NONE/ADAPT/ALIGN/TOPDER DEFAULT = ADAPT NONE: Indicates that there are no holes in the initial design, and it will work similar to shape optimization. ADAPT: Indicates that the optimization will start with a cheese-like initial design, where the holes are adaptively inserted into the design domain, as illustrated in Figure 2. This works well with irregular design domains. ALIGN: Indicates that the optimization will start with evenly distributed holes aligned with axes X and Y (and Z for 3D) of the basic coordinate system, as illustrated in Figure 3. This option is specially developed for regular design domains. TOPDER: Indicates that OptiStruct will automatically identify locations for the insertion of holes during the optimization process. If the HOLEINST Field is blank, it is set to ADAPT by default

HOLERAD

DEFAULT = 4 times the average mesh size A real number that specifies the initial radius of the holes. If the field HOLERAD is blank, the radius will be set to 4 times the average mesh size.

NHOLESX / NHOLESY / NHOLESZ

A positive integer that specifies the number of holes in X direction (when HOLEINST= ALIGN). If the field NHOLESX is blank, OptiStruct will automatically assign a number based on HOLERAD and the dimensions of the domain. NHOLESY and NHOLESZ can be inferred by analogy.

Comments 1.

Von Mises stress constraints may be defined for topology and free-size optimization through the STRESS optional continuation line on the DTPL or the DSIZE card. There are a number of restrictions with this constraint: The definition of stress constraints is limited to a single von Mises permissible stress. The phenomenon of singular topology is pronounced when different materials with

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different permissible stresses exist in a structure. Singular topology refers to the problem associated with the conditional nature of stress constraints, that is, the stress constraint of an element disappears when the element vanishes. This creates another problem in that a huge number of reduced problems exist with solutions that cannot usually be found by a gradient-based optimizer in the full design space. Stress constraints for a partial domain of the structure are not allowed because they often create an ill-posed optimization problem since elimination of the partial domain would remove all stress constraints. Consequently, the stress constraint applies to the entire model when active, including both design and non-design regions, and stress constraint settings must be identical for all DSIZE and DTPL cards. The capability has built-in intelligence to filter out artificial stress concentrations around point loads and point boundary conditions. Stress concentrations due to boundary geometry are also filtered to some extent as they can be improved more effectively with local shape optimization. Due to the large number of elements with active stress constraints, no element stress report is given in the table of retained constraints in the .out file. The iterative history of the stress state of the model can be viewed in HyperView or HyperMesh. Stress constraints do not apply to 1D elements. Stress constraints may not be used when enforced displacements are present in the model. 2.

It is recommended that a MINDIM value be chosen such that it is at least 3 times, and no greater than 12 times, the average element size. When pattern grouping, draw direction, or extrusion constraints are active, a MINDIM value of 3 times the average element size is enforced, and user-defined values (which are smaller than this value) will be replaced by this value. However, in cases where a MINDIM greater than 12 times the average element size is defined, irrespective of whether or not other manufacturing constraints are defined, the value is reset to be equal to 12 times the average element size. If MINDIM is defined, but no other manufacturing constraint exists, MINDIM will not be reset to the recommended lower bound value for PTYPE = PSHELL or PSOLID, if the defined value is less than the recommended value. For PTYPE = PCOMP, MINDIM will be reset in the absence of manufacturing constraints.

3.

MAXDIM should at least be twice the value of MINDIM. If the input value of MAXDIM is too small, OptiStruct automatically resets the value and an INFORMATION message is printed. The MAXDIM constraint introduces significant restriction to the design problem. Therefore, it should only be used when it is a necessary design requirement. A study without MAXDIM should always be carried out in order to compare the impact of this additional constraint. MAXDIM implies the application of a MINGAP constraint of the same value as MAXDIM, as well. Therefore, for MINGAP to be effective, it should be greater than MAXDIM. It is important to pay attention to volume fraction as the achievable volume is below 50% when MAXDIM is defined, and further decreases as MINGAP increases.

4.

948

MTYP "ALIGN" may be used in conjunction with draw direction or extrusion manufacturing constraints to indicate that a mesh is aligned with a draw direction or extrusion path.

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Figure 1: Draw direction

Mesh 1 is "aligned" for draw direction 1 in the example shown, but not for draw direction 2. MTYP "ALIGN" may also be used in conjunction with manufacturing constraints (minimum member, maximum member, pattern grouping, and pattern repetition) other than draw direction and extrusion, and Mesh 1 is considered "aligned" for those manufacturing constraints, too. In both cases, this will enable OptiStruct to use a smaller minimum member size and smaller maximum member sizes. The default minimum member size is three times the average element edge length; with an "aligned" mesh, the default size can be two times the average element edge length. Mesh 2 in the example shown is not "aligned" in any case. 5.

The stamping constraint is available for only one sheet, which is defined by the combination of STAMP and DTYP as SINGLE. It is recommended that the stamping thickness, TSTAMP, be chosen such that it is at least 3 times the average element size. If TSTAMP is defined less than the minimum recommended value, TSTAMP will be reset to the minimum recommended value. STAMP and NOHOLE can be a good combination as this helps to produce a continuous/ spread shell structure. Note that attention should be paid to the compatibility between thickness and target volume.

6.

Extrusion constraints cannot be combined with draw direction constraints.

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7.

Pattern repetition allows similar regions of the design domain to be linked together so as to produce similar topological layouts. This is facilitated through the definition of "Master" and "Slave" regions. A DTPL card may only contain one MASTER or SLAVE flag. Parameters will not be exported for any DTPL cards containing the SLAVE flag. For both "Master" and "Slave" regions, a pattern repetition coordinate system is required and is described following the COORD flag. In order to facilitate reflection, the coordinate system may be a left-handed or right-handed Cartesian system. The coordinate system may be defined in one of two ways, listed here in order of precedence: Four points are defined and these are utilized as follows to define the coordinate system (this is the only way to define a left-handed system): - A vector from the anchor point to the first point defines the x-axis. - The second point lies on the x-y plane, indicating the positive sense of the y-axis. - The third point indicates the positive sense of the z-axis. A rectangular coordinate system and an anchor point are defined. If only an anchor point is defined, it is assumed that the basic coordinate system is to be used. Multiple "Slaves" may reference the same "Master." Scale factors may be defined for "Slave" regions, allowing the "Master" layout to be adjusted. For a more detailed description, refer to the Pattern Repetition page contained within the User's Guide section Manufacturability for Topology Optimization.

8.

Pattern grouping is applicable for PCOMP, PSHELL, and PSOLID components only.

9.

For historic reasons, the SYMM flag may be used in place of the PATRN flag.

10. Currently there are six pattern grouping options: 1-plane symmetry (TYP = 1) This type of pattern grouping requires the anchor point and first point to be defined. A vector from the anchor point to the first point is normal to the plane of symmetry. 2-plane symmetry (TYP = 2) This type of pattern grouping requires the anchor point, first point, and second point to be defined. A vector from the anchor point to the first point is normal to the first plane of symmetry. The second point is projected normally onto the first plane of symmetry. A vector from the anchor point to this projected point is normal to the second plane of symmetry. 3-plane symmetry (TYP = 3) This type of pattern grouping requires the anchor point, first point, and second point to be defined. A vector from the anchor point to the first point is normal to the first plane of symmetry. The second point is projected normally onto the first plane of symmetry. A vector from the anchor point to this projected point is normal to the second plane of symmetry. The third plane of symmetry is orthogonal to both the first and second planes of symmetry, passing through the anchor point. Uniform (TYP = 9) This type of pattern grouping does not require any additional input.

950

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Altair Engineering

Cyclic (TYP = 10) This type of pattern grouping requires the anchor point, first point, and number of cyclical repetitions to be defined. A vector from the anchor point to the first point defines the axis of symmetry. Cyclic with symmetry (TYP = 11) This type of pattern grouping requires the anchor point, first point, second point, and number of cyclical repetitions to be defined. A vector from the anchor point to the first point defines the axis of symmetry. The anchor point, first point, and second point all lay on a plane of symmetry. A plane of symmetry lies at the center of each cyclical repetition. For a more detailed description, refer to the Pattern Grouping page contained within the User's Guide section Manufacturability for Topology Optimization. 11. The level set method can merge existing holes but cannot nucleate new holes in the design domain. Therefore, creating an initial design with holes is necessary, especially for 2D design problems (For 3D design problems, new holes can be “tunneled” when two surfaces merged). 12. By default, OptiStruct will automatically create a Cheese-Like initial design with holes adaptively distributed over the design domain, as shown in Figure 2. The default hole radius is 4.0 times the average mesh size.

Figure 2: A C heese-Like Initial design generated with (left) the default setting, and (right) double hole radius.

13. Changing the value of HOLERAD can result in different initial designs. Figure 2 (Right) shows an initial design filled with holes possessing a doubled hole radius when compared to Figure 2 (Left). If the you wish to create an initial design with evenly distributed and well aligned holes (this may be preferable for regular design domains), HOLEINST can be set to ALIGN. The number of holes in each direction can be further specified by using NHOLESX, NHOLESY and NHOLESZ as shown in Figure 3.

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Figure 3: A C heese-Like initial design with 3-by-5 evenly distributed holes generated using the following settings: HOLEINST=ALIGN, NHOLESX=5 and NHOLESY=3.

14. Currently, level set supports both SINGLE and SPLIT draw direction constraints. When multiple DTPL cards are involved, the draw directions need to be the same. The information needed for draw direction constraint is read from the DTPL cards and thus no extra settings are required. 15. This card is represented as an optimization design variable in HyperMesh.

952

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Altair Engineering

DVCREL1 Bulk Data Entry DVCREL1 – Relates Design Variables to Analysis Model Element Properties Description Linearly relates a design variable to an analysis model element property using the equation:

Format (1)

(2)

(3)

(4)

(5)

DVC REL1

ID

TYPE

EID

EPNAME/FID

DVID1

C OEF1

DVID2

C OEF2

(6)

(7)

(8)

(9)

(10)

C0

etc.

Field

Contents

ID

Relationship identification number. ID must be unique with respect to other DVCREL1 cards. No default (Integer > 0)

TYPE

Element type to be related (See DVCREL - Types) No default (Character)

EID

Element Identification Number. No default (Integer > 0)

EPNAME/FID Element property name, such as "K" or “ZOFFS" (as in the documentation of the element bulk data entries), or field number on an element bulk data entry. No default (Character or Integer > 0) C0

Constant in relationship equation.

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Field

Contents Default = 0.0 (Real)

DVIDi

DESVAR ID. No default (Integer > 0)

COEFi

Coefficient in relationship equation. Default = 1.0 (Real)

Comments 1.

954

This card is represented as an optimization design variable property relationship in HyperMesh.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DVCREL2 Bulk Data Entry DVCREL2 – Relates Design Variables to Analysis Model Element Properties via Relationship Defined by User-supplied Equation Description Relates design variables to an analysis model element property using a relationship defined by a DEQATN card. The equation inputs come from the referenced DESVAR values and constants defined on a DTABLE card. Format (1)

(2)

(3)

(4)

(5)

DVC REL2

ID

TYPE

EID

EPNAME/ FID

DESVAR

DVID1

DVID2

DVID3

DVID8

DVID9

etc.

LABL1

LABL2

LABL3

LABL8

etc.

DTABLE

(6)

(7)

(8)

(9)

(10)

EQID

DVID4

DVID5

DVID6

DVID7

LABL4

LABL5

LABL6

LABL7

Field

Contents

ID

Relationship identification number. ID must be unique with respect to other DVCREL2 cards. No default (Integer > 0)

TYPE

Element type to be related (See DVCREL - Types) No default (Character)

EID

Element Identification Number. No default (Integer > 0)

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Field

Contents

EPNAME/FID Element property name, such as "K" or “ZOFFS" (as in the documentation of the element bulk data entries), or field number on an element bulk data entry. No default (Character or Integer > 0) EQID

Equation ID of DEQATN data. No default (Integer > 0)

DESVAR

DESVAR flag indicating DESVAR ID numbers follow.

DVID#

DESVAR ID. No default (Integer > 0)

DTABLE

DTABLE flag indicating DTABLE labels follow.

LABL#

Constant label. Must match with a constant label of a DTABLE entry. No default (Character)

Comments 1.

956

This card is represented as an optimization design variable property relationship in HyperMesh.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DVCREL - Types Types Depending on the TYPE entry, the FID of the appropriate design parameter can be determined from the table below. Type

Field 1

Field 2

Field 3

Field 4

CONM1

Field 5

Field 6

Field 7

Field 8

Field 9

M11

M21

M22

M31

M32

Field 10

FID 11-20

M33

M41

M42

M43

M44

M51

M52

M53

FID 21-30

M54

M55

M61

M62

M63

M64

M65

M66

Field 2

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

M

X1

X2

X3

Type

Field 1

CONM2

FID 1120

Type

Field 1

I11

I21

I22

I31

I32

I33

Field 2

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

CMASS2

Type

M

Field 1

Field 2

CMASS4

Type

Field 3 M

Field 1

CDAMP2

Altair Engineering

Field 2

Field 3 B

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Type

Field 1

Type

Field 1

Field 2 Field 2

CDAMP4

Type

Field 3 Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

X1

X2

X3

B

Field 1

Field 2

Field 3

CBAR

FID 1120

Type

Field 1

Field 2

Field 3

W1A

W2A

W3A

W1B

W2B

W3B

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

X1

X2

X3

CBEAM

FID 1120

Type

Field 1

Field 2

Field 3

W1A

W2A

W3A

W1B

W2B

W3B

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

A

J

C

NSM

Field 6

Field 7

Field 8

Field 9

GE

S

Field 8

Field 9

GE

S

CONROD

Type

Field 1

Field 2

CELAS2

Type

CELAS4

958

Field 3

Field 4

Field 5

K

Field 1

Field 2

Field 3

Field 4

Field 5

Field 6

Field 7

K

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Field 10

Field 10

Field 10

Field 10

Altair Engineering

Type

Field 1

Type

Field 1

Field 2

Field 2

Field 3

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

CTRIA3

Type

ZOFFS

Field 1

Field 2

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

CTRIA6

FID 11-20

Type

ZOFFS

Field 1

Field 2

Field 3

CQUAD4

Type

ZOFFS

Field 1

Field 2

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

CQUAD8 FID 11-20

Altair Engineering

ZOFFS

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DVGRID Bulk Data Entry DVGRID – Relationship between Design Variable and Grid Point Location Description Defines the relationship between a design variable and a grid point location. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DVGRID

DVID

GID

C ID

C OEFF

X

Y

Z

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

DVGRID

1

1032

0

1.0

1.0

0.0

0.0

Field

Contents

DVID

DESVAR identification number.

(9)

(10)

(Integer > 0) GID

GRID identification number. (Integer > 0)

CID

Coordinate system identification number. Default = 0 (Integer > 0)

COEFF

Multiplier to the vector defined in fields 6, 7, and 8.

X, Y, Z

Components of the vector defining the perturbation of the grid in the coordinate system defined by CID.

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Comments 1.

A CID of zero or blank references the basic coordinate system.

2.

Multiple references to the same grid ID will yield a summation of perturbation vectors for the given grid.

3.

The DVGRID data defines perturbations in the locations of the grids. The updated location of the grid is:

where, DVj is the value of design variable j and [N]T is the coordinate transformation matrix based on the CID and the GRID location. 4.

This card is represented as an optimization design variable in HyperMesh.

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DVMBRL1 Bulk Data Entry DVMBRL1 – Relates Design Variables to Properties of MBD Entities Description Linearly relates a design variable to properties of an MBD entity using the equation:

Format (1)

(2)

(3)

(4)

(5)

(6)

DVMBRL1

ID

TYPE

BID/EID

PNAME

DVID1

C OEF1

DVID2

C OEF2

(7)

(8)

(9)

(10)

C0

etc.

Example 1

To relate the translational x component of stiffness value (K1) on a CMBUSH whose ID is 22 to Design Variable 5. (1)

(2)

(3)

(4)

(5)

DVMBRL1

88

C MBUSH

22

K1

5

1.

5

5.00

1.50

9.90

DESVAR

(6)

(7)

(8)

(9)

(10)

(9)

(10)

0.0

Example 2

To relate the mass of a rigid boy whose ID is 3 to design variable 5. (1)

962

(2)

(3)

(4)

(5)

(6)

(7)

(8)

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DVMBRL1

DESVAR

88

PRBODY

5

1.

5

5.00

3

M

1.50

9.90

0.0

Field

Contents

ID

Response identity. ID must be unique with respect to other DVMBRL1 and DVMBRL2 cards. No default (Integer > 0)

TYPE

MBD entity type to be related (see table below). No default (Character)

BID/EID

Body ID or Element ID number. When TYPE is PRBODY, this field is the ID number of a rigid body. When TYPE is CMBUSH(M), CMBEAM(M), or CMSPDP(m), this field is the ID number of a corresponding element. No default (Integer > 0)

PNAME

Property name, such as "A" or "L" (as in the documentation of the PRBODY, CMBEAM(M), CMBUSH(M), and CMSPDP(M) cards). No default (Character or Integer > 0)

C0

Constant in relationship equation. Default = 0.0 (Real)

DVIDi

DESVAR ID. No default (Integer > 0)

COEFi

Coefficient in relationship equation. Default = 1.0 (Real)

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Comments 1.

Available TYPEs are PRBODY, CMBUSH, CMBUSHM, CMBEAM, CMBEAMM, CMSPDP, and CMSPDPM.

2.

MBD entity type information: TYPE

Available PNAME

PRBODY

IXX IYY IZZ IXY IXZ IYZ

CMBEAM/CMBEAMM

CMBUSH/CMBUSHM

964

X

X component of center of gravity.

Y

Y component of center of gravity.

Z

Z component of center of gravity.

L

Undeformed length along the X–axis of the beam.

A

Area of the beam cross-section.

I1

Area moment of inertia in plane 1 about the neutral axis.

I2

Area moment of inertia in plane 1 about the neutral axis.

J

Torsional constant.

K1 ~ K2

Area factor for shear.

K1 ~ K3

Translational stiffness.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

TYPE

CMSPDP/CMSPDPM

3.

Available PNAME K4 ~ K6

Rotational stiffness.

B1 ~ B3

Translational damping.

B4 ~ B6

Rotational damping.

P1 ~ P3

Translational preload.

P4 ~ P6

Rotational preload.

K

Stiffness

B

Damping

L

Unstretched length of spring damper.

PF

Preload force.

This card is represented as an optimization design variable property relationship in HyperMesh.

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DVMBRL2 Bulk Data Entry DVMBREL2 – Relates Design Variables to Properties of MBD Entities via Relationship Defined by User-supplied Equation Description Relates a design variable to properties of MBD entities using a relationship defined by a DEQATN card. The equation inputs come from the referenced DESVAR values and the constants defined on the DTABLE card. Format (1)

(2)

(3)

(4)

(5)

DVMBRL2

ID

PTYPE

BID/EID

PNAME

DESVAR

DVID1

DVID2

DVID3

DVID8

DVID9

etc.

LABL1

LABL2

LABL3

LABL8

etc.

DTABLE

(6)

(7)

(8)

(9)

(10)

EQID

DVID4

DVID5

DVID6

DVID7

LABL4

LABL5

LABL6

LABL7

Field

Contents

ID

Relationship identity. ID must be unique with respect to other DVMBRL1 and DVMBRL2 cards. No default (Integer > 0)

TYPE

Property type to be related (see table below). No default (Character)

BID/EID

Body ID or Element ID number. When TYPE is PRBODY, this field is ID number of a rigid body. When TYPE is CMBUSH(M), CMBEAM(M), or CMSPDP(m), this field is ID number of a corresponding element. No default (Integer > 0)

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Field

Contents

PNAME

Property name, such as "A" or "L" (as in the documentation of the PRBODY, CMBEAM(M), CMBUSH(M), and CMSPDP(M) cards). No default (Character or Integer > 0)

EQID

Equation ID of DEQATN data. No default (Integer > 0)

DESVAR

DESVAR flag indicating DESVAR ID numbers follow.

DVIDi

DESVAR ID. No default (Integer > 0)

DTABLE

DTABLE flag indicating DTABLE labels follow.

LABLi

Constant label on DTABLE card. No default (Character)

Comments 1.

Available TYPE are PRBODY, CMBUSH, CMBUSHM, CMBEAM, CMBEAMM, CMSPDP, and CMSPDPM.

2.

Property type table: TYPE

Available PNAME

PRBODY

IXX IYY IZZ IXY IXZ IYZ

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TYPE

CMBEAM/CMBEAMM

CMBUSH/CMBUSHM

CMSPDP/CMSPDPM

968

Available PNAME X

X component of center of gravity.

Y

Y component of center of gravity.

Z

Z component of center of gravity.

L

Undeformed length along the X–axis of the beam.

A

Area of the beam cross-section.

I1

Area moment of inertia in plane 1 about the neutral axis.

I2

Area moment of inertia in plane 1 about the neutral axis.

J

Torsional constant.

K1 ~ K2

Area factor for shear.

K1 ~ K3

Translational stiffness.

K4 ~ K6

Rotational stiffness.

B1 ~ B3

Translational damping.

B4 ~ B6

Rotational damping.

P1 ~ P3

Translational preload.

P4 ~ P6

Rotational preload.

K

Stiffness

B

Damping

L

Unstretched length of spring damper.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

TYPE

Available PNAME PF

3.

Preload force

This card is represented as an optimization design variable property relationship in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

969

DVMREL1 Bulk Data Entry DVMREL1 – Relates Design Variables to Analysis Model Material Properties Description Linearly relates a design variable to an analysis model material property using the equation:

Format (1)

(2)

(3)

(4)

(5)

DVMREL1

ID

TYPE

MID

MPNAME/ FID

DVID1

C OEF1

DVID2

C OEF2

(6)

(7)

(8)

(9)

(10)

C0

etc.

Example 1

To relate the Damping Coefficient value on a MAT1 card (field 9) to Design Variable 5. (1)

(2)

(3)

(4)

(5)

DVMREL 1

17

MAT1

22

9

5

1.0

(6)

(7)

(8)

(9)

(10)

0.0

Example 2

This example is the same as example 1 (above), except that it defines MPNAME in place of FID. (1)

(2)

(3)

(4)

(5)

DVMREL

17

MAT1

22

GE

970

(6)

(7)

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(8)

(9)

(10)

0.0

Altair Engineering

(1)

(2)

(3)

5

1.0

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(9)

(10)

1

Associated Cards (1)

(2)

(3)

(4)

(5)

(6)

DESVAR

5

GE

1.0

2.0

0.5

MAT1

22

2.1e5

0.3

7.85e-9

(7)

(8)

1.0

Field

Contents

ID

Relationship identification number. ID must be unique with respect to other DVMREL1 cards. No default (Integer > 0)

TYPE

Material type to be related (MAT1, MAT2, MAT4, MAT5, MAT8, and MAT9). No default (Character)

MID

Material identification number. No default (Integer > 0)

MPNAME/FID

Material property name, such as "E" or “RHO" (as in the documentation of the material bulk data entries), or field number on a material bulk data entry. No default (Character or Integer > 0)

C0

Constant in relationship equation. Default = 0.0 (Real)

DVIDi

DESVAR ID. No default (Integer > 0)

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COEFi

Coefficient in relationship equation. Default = 1.0 (Real)

Comments 1.

972

See the DVMREL - Types section for details on the supported material fields and the MPNAME/FID entries.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DVMREL2 Bulk Data Entry DVMREL2 – Relates Design Variables to Analysis Model Material Property Description Relates design variables to an analysis model material property using a relationship defined by a DEQATN card. The equation inputs come from the referenced DESVAR values and constants defined on a DTABLE card. Format (1)

(2)

(3)

(4)

(5)

DVMREL2

ID

TYPE

MID

MPNAME/ FID

DESVAR

DVID1

DVID2

DVID3

DVID8

DVID9

etc.

LABL1

LABL2

LABL3

LABL8

etc.

DTABLE

(6)

(7)

(8)

(9)

(10)

EQID

DVID4

DVID5

DVID6

DVID7

LABL4

LABL5

LABL6

LABL7

Example 1 To relate the Damping Coefficient value on a MAT1 card (field 9) to some user-defined relationship of design variables 5 and 6 and the table entry GE0. (1)

(2)

(3)

(4)

(5)

DVMREL 2

17

MAT1

22

9

DESVAR

5

6

DTABLE

GE0

(6)

(7)

(8)

(9)

(10)

1

Example 2

Altair Engineering

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973

This example is the same as example 1 (above), except that it defines MPNAME in place of FID. (1)

(2)

(3)

(4)

(5)

DVMREL 2

17

MAT1

22

GE

DESVAR

5

6

DTABLE

GE0

(6)

(7)

(8)

(9)

(10)

(9)

(10)

1

Associated Cards (1)

(2)

(3)

(4)

(5)

(6)

DESVAR

5

GE1

1.0

2.0

0.5

DESVAR

6

GE2

1.0

1.0

0.01

DTABLE

GE0

0.01

DEQATN

1

MAT1

22

(7)

(8)

GE(GE1, GE2, GE0) = GE0+(GE1*GE2) 2.1e5

0.3

7.85e-9

1.0

Field

Contents

ID

Relationship identification number. ID must be unique with respect to other DVMREL2 cards. No default (Integer > 0)

TYPE

Material type to be related (MAT1, MAT2, MAT4, MAT5, MAT8, and MAT9). No default (Character)

MID

Material identification number. No default (Integer > 0)

974

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Field

Contents

MPNAME/FID

Material property name, such as "E" or “RHO" (as in the documentation of the material bulk data entries), or field number on a material bulk data entry. No default (Character or Integer > 0)

EQID

Equation ID of DEQATN data. No default (Integer > 0)

DESVAR

DESVAR flag indicating DESVAR ID numbers follow.

DVID#

DESVAR ID. No default (Integer > 0)

DTABLE

DTABLE flag indicating DTABLE labels follow.

LABL#

Constant label. Must match with a constant label of a DTABLE entry. No default (Character)

Comments 1.

See the DVMREL - Types section for details on the supported material fields and the MPNAME/FID entries.

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DVMREL - Types Types Depending on the TYPE entry, the FID of the appropriate design parameter can be determined from the table below. Type

Field 1

Field 2

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

E

G

NU

RHO

A

TREF

GE

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

G11

G12

G13

G22

G23

G33

RHO

A1

A2

A12

TREF

GE

Field 2

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

Field 10

RHO

H

Field 9

Field 10

Field 10

MAT1

Type

Field 1

Field 2

MAT2

FID 1120

Type

Field 1

MAT4

Type

K

Field 1

Field 2

MAT5 FID 11-20

Type

Field 1

Field 4

Field 5

Field 6

Field 7

Field 8

KXX

KXY

KXZ

KYY

KYZ

KZZ

Field 2

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

E1

E2

NU12

G12

G1,Z

G2,Z

RHO

A2

TREF

A1

FID 21-

GE

976

Field 3

HGEN

FID 1120

Field 10

HGEN

RHO

MAT8

Field 10

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

30

Type

Field 1

Field 2

MAT9

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

G11

G12

G13

G14

G15

G16

G22

FID 11-20

G23

G24

G25

G26

G33

G34

G35

G36

FID 21-30

G44

G45

G46

G55

G56

G66

RHO

A1

FID 31-40

A2

A3

A4

A5

A6

TREF

GE

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Field 10

977

DVPREL1 Bulk Data Entry DVPREL1 – Relates Design Variables to Analysis Model Properties Description Linearly relates a design variable to an analysis model property using the equation:

Format (1)

(2)

(3)

(4)

(5)

(6)

DVPREL1

ID

TYPE

PID

PNAME/ FID

DVID1

C OEF1

DVID2

C OEF2

(7)

(8)

(9)

(10)

C0

etc.

Example 1 To relate the thickness value on a PSHELL card (field 4) to Design Variable 5. (1)

(2)

(3)

(4)

(5)

DVPREL1

88

PSHELL

1

4

5

1.

5

5.00

1.50

9.90

DESVAR

(6)

(7)

(8)

(9)

(10)

0.0

Example 2 This example is the same as example 1 (above), except that it defines PNAME.

978

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Altair Engineering

(1)

(2)

(3)

(4)

(5)

DVPREL1

88

PSHELL

1

T

5

1.

5

5.00

1.50

9.90

DESVAR

(6)

(7)

(8)

(9)

(10)

0.0

Field

Contents

ID

Relationship identification number. ID must be unique with respect to other DVPREL1 cards. No default (Integer > 0)

TYPE

Property type to be related (see DVPREL - Types). No default (Character)

PID

Property identification number. When PTYPE is PCOMPG, G# may be used where # is the GPLYID. When PTYPE is PCOMPP, P# may be used where # is the PLY ID. See comment 2. No default (Integer > 0)

PNAME/FID

Property name, such as "A" or "T" (as in the documentation of the property cards), or field number in property card (see table below). For the PSHELL property 12I/T3, only the filed number (6) is allowed. For PBARL and PBEAML only property names are allowed, as different sections use different fields. No default (Character or Integer > 0)

C0

Constant in relationship equation. Default = 0.0 (Real)

DVIDi

DESVAR ID. No default (Integer > 0)

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Field

Contents

COEFi

Coefficient in relationship equation. Default = 1.0 (Real)

Comments 1.

TYPE cannot be PSOLID. a) The DDVAL field of a DESVAR bulk data entry. b) The SPTID field of a RSPINR bulk data entry.

2.

When TYPE is PCOMPG, either global plies or property specific plies may be selected. To select property specific plies, the format is similar to that used for other property types where the property identification number of the PCOMPG is entered in the PID field and then either PNAME or FID is used to identify the value to be related. In this scenario, only the property with an ID given in the PID field is affected. To select global plies, G# is entered in the PID field where, # is the GPLYID of a global ply. In this instance, FID is not applicable so T or THETA is used in the PNAME field to relate either the thickness or orientation respectively. In this scenario, all plies that use the given GPLYID are affected. When TYPE is PCOMPP, P# is entered in the PID field where # is the ID of a PLY entity. In this instance, FID is not applicable so T or THETA is used in the PNAME field to relate either the thickness or orientation respectively.

3.

PBEAML definitions with more than one section definition may not be referenced by a DVPREL1.

4.

Properties of PBARL/PBEAML have to be controlled through DIMs (cannot be controlled directly), with the exception of NSM.

5.

When TYPE is PBARL or PBEAML, users should pay close attention to the variable ranges to avoid invalid dimensions. For example, the inner radius of a tube cross-section cannot exceed the outer radius. It is necessary to prevent combinations of dimensions from taking on values that are physically meaningless. Some constraints are applied automatically on section dimensions. The table below summarizes these constraints. Constraints are satisfied when they are < 0.0. Section Type Constraint TUBE

DIM2 – DIM1

I

DIM4 – DIM2 DIM4 – DIM3

980

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Section Type Constraint DIM5 + DIM6 – DIM1 CHAN

2 * DIM4 – DIM2 DIM3 – DIM1

T

DIM3 – DIM2 DIM4 – DIM1

BOX

DIM4 – DIM1 DIM3 – DIM2

CROSS

DIM4 – DIM3

H

DIM4 – DIM3

T1

DIM4 – DIM1

I1

DIM3 – DIM4

CHAN1

DIM3 – DIM4

Z

DIM3 – DIM4

CHAN2

DIM2 – DIM3 2 • DIM1 – DIM4

T2

DIM4 – DIM1 DIM3 – DIM2

BOX1

DIM4 + DIM3 – DIM2 DIM5 + DIM6 – DIM1

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Section Type Constraint HEXA

2 * DIM1 – DIM2

HAT

2 * DIM2 – DIM1 2 * DIM2 – DIM3

L

DIM3 – DIM2 DIM4 – DIM1

HAT1

DIM3 – DIM1 2 * DIM4 – DIM2 2 * DIM4 + DIM5 – DIM2

6.

982

This card is represented as an optimization design variable in HyperMesh.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DVPREL2 Bulk Data Entry DVPREL2 – Relates Design Variables to Analysis Model Properties via Relationship Defined by User-supplied Equation Description Relates a design variable to an analysis model property using a relationship defined by a DEQATN card. The equation inputs come from the referenced DESVAR values and the constants defined on the DTABLE card. Format (1)

(2)

(3)

(4)

(5)

DVPREL2

ID

TYPE

PID

PNAME/ FID

DESVAR

DVID1

DVID2

DVID3

DVID8

DVID9

etc.

LABL1

LABL2

LABL3

LABL8

etc.

DTABLE

(6)

(7)

(8)

(9)

(10)

EQID

DVID4

DVID5

DVID6

DVID7

LABL4

LABL5

LABL6

LABL7

Example 1

A rectangular bar of width W and depth D is defined using the PBAR card. The required fields on the PBAR for Area, I1 and I2 are all related to the width and depth, which are the design variables, by the referenced equations. (1)

(2)

(3)

(4)

(5)

DVPREL2

201

PBAR

1

4

101

DESVAR

5

6

203

PBAR

1

5

102

DVPREL2

Altair Engineering

(6)

(7)

(8)

(9)

(10)

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

983

(1)

(2)

(3)

(4)

DESVAR

5

6

204

PBAR

1

DESVAR

5

6

DVPREL2

(5)

(6)

(7)

(8)

6

(9)

(10)

103

Example 2

This example is the same as example 1 (above), except that it defines PNAME. (1)

(2)

(3)

(4)

(5)

DVPREL2

201

PBAR

1

A

101

DESVAR

5

6

203

PBAR

1

I1

102

DESVAR

5

6

204

PBAR

1

I2

103

DESVAR

5

6

DVPREL2

DVPREL2

(6)

(7)

(8)

(9)

(10)

Associated Cards (1)

(2)

(3)

(4)

(5)

(6)

DESVAR

5

W

6.0

1.0

10.0

DESVAR

6

D

5.0

1.0

20.0

DEQATN

101

AREA(W,D) = W*D

DEQATN

102

I1(W,D) = (W*D**3)/12

984

(7)

(8)

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(9)

(10)

Altair Engineering

(1)

(2)

DEQATN

103

PBAR

1

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

I2(W,D) = (D*W**3)/12 222

0.1

19e-4

1e-3

Field

Contents

ID

Relationship identification number. ID must be unique with respect to other DVPREL1 cards. No default (Integer > 0)

TYPE

Property type to be related (see DVPREL - Types). No default (Character)

PID

Property identification number. When PTYPE is PCOMPG, G# may be used where # is the GPLYID. When PTYPE is PCOMPP, P# may be used where # is the PLY ID. See comment 5. No default (Integer > 0)

PNAME/ FID

Property name, such as "A" or "T" (as in the documentation of the property cards), or field number in property card (see table below). For the PSHELL property 12I/T3, only the filed number (6) is allowed. For PBARL and PBEAML only property names are allowed, as different sections use different fields. No default (Character or Integer > 0)

EQID

Equation ID of DEQATN data. No default (Integer > 0)

DESVAR

DESVAR flag indicating DESVAR ID numbers follow.

DVIDi

DESVAR ID. No default (Integer > 0)

DTABLE

DTABLE flag indicating DTABLE labels follow.

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985

Field

Contents

LABLi

Constant label on DTABLE card. No default (Character)

Comments 1.

Type cannot be PSOLID.

2.

When Type is PBARL or PBEAML, users should pay close attention to the variable ranges to avoid invalid dimensions.

3.

PBEAML definitions with more than one section definition may not be referenced by a DVPREL1.

4.

Properties of PBARL/PBEAML have to be controlled through DIMs (cannot be controlled directly), with the exception of NSM.

5.

When TYPE is PCOMPG, either global plies or property specific plies may be selected. To select property specific plies, the format is similar to that used for other property types where the property identification number of the PCOMPG is entered in the PID field and then either PNAME or FID is used to identify the value to be related. In this scenario, only the property with an ID given in the PID field is affected. To select global plies, G# is entered in the PID field where # is the GPLYID of a global ply. In this instance, FID is not applicable so T or THETA is used in the PNAME field to relate either the thickness or orientation respectively. In this scenario, all plies that use the given GPLYID are affected. When TYPE is PCOMPP, P# is entered in the PID field where # is the ID of a PLY entity. In this instance, FID is not applicable so T or THETA is used in the PNAME field to relate either the thickness or orientation respectively.

6.

986

This card is represented as an optimization design variable in HyperMesh.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

DVPREL - Types Types Depending on the TYPE entry, the FID of the appropriate design parameter can be determined from the table below. Type

Field 1

Field 2

Field 3

Field 4

CONM2

FID 11-20

Type

Field 1

Field 8

M

X1

X2

X3

Field 9

Field 10

Field 9

Field 10

I22

I13

I23

I33

Field 2

Field 3

Field 4

Field 5

Field 6

Field 7

Field 8

A

I1

I2

J

NSM

D2

E1

E2

F1

F2

C1

C2

D1

FID 21-30

K1

K2

I12

Type

Field 7

I12

FID 11-20

PBARL

Field 6

I11

PBAR

Type

Field 5

Field numbers are not allowed for PBARL. DIMi

NSM

Field 1

Field 2

Field 3

PBEAM

FID 11-20

C 1(A)

C 2(A)

K1(A)

K2(A)

Field 4

Field 5

Field 6

Field 7

Field 8

Field 9

A(A)

I1(A)

I2(A)

I12(A)

J(A)

NSM(A)

D1(A)

D2(A)

E1(A)

E2(A)

F1(A)

F2(A)

NSI(A)

NSI(B)

Field 10

FID 21-30

FID 31-40

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

987

FID 41-50

Type

M1(A)

M2(A)

M1(B)

M2(B)

N1(A)

N2(A)

N1(B)

N2(B)

Field numbers are not allowed for PBEAML.

PBEAML

Type

DIMi

NSM

Field 1

Field 2

Field 3

Field 4

Field 5

Fiel d 6

Field 7

Field 8

Field 9

K1

K2

K3

K4

K5

K6

B1

B2

B3

B4

B5

B6

GE1

GE2

GE3

GE4

GE5

GE6

Field 3

Field 4

Field 5

Fiel d 6

Field 7

Field 8

Field 9

Field 10

PCOMP

Z0

NSM

FID 11-20

T1

THETA1

T2

THETA4

FID 21-30

T3

THETA3

…

…

…

…

…

…

…

Field 3

Field 4

Field 7

Field 8

Field 9

Field 10

Z0

NSM

PBUSH

Type

Field 1

Type

Field 1

PCOMPG

FID 11-20

988

Field 2

Field 2

T1

Field 5

Fiel d 6

Field 10

THETA1

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

FID 21-20

T2

THETA2

…

…

…

Type

PCOMPG

Type

Field numbers do not apply for PCOMPG when referencing global plies. See comment 2 (DVPREL1). T

THETA

Field 1

Field 2

PCOMPP

Type

Field 1

Field 2

PDAMP

Type

Field 1

Field 2

Z0

NSM

Field 3

Field 4

Field 3

Field 1

Field 2

Field 3

Field 4

Altair Engineering

Field 2

Field 3

Fiel d 6

Field 7

Field 8

Field 9

Field 10

Field 5

Fiel d 6

Field 7

Field 8

Field 9

Field 10

Field 5

B

Fiel d 6

S

Field 4

M

Field 1

Field 5

B

K

PMASS

Type

Field 4

B

PELAS

Type

Field 3

Field 5

Field 5

Field 8

K

Fiel d 6

M

Field 4

Field 7

B

Field 7

Field 7

Field 8

Field 9

Field 10

M

Field 8

Field 9

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Field 10

S

M

Fiel d

Field 9

Field 10

989

6 PROD

A

Type

Field 1

Field 2

Field 3

PSHELL

Field 1

Z1

Z2

Field 2

Field 3

Field 1

PVISC

990

Field 2

Fiel d 6

Field 7

12* I/T3

Field 8

Field 9

TS/T

NSM

Field 10

Field 8

Field 9

Field 10

Field 9

Field 10

ZOF FS

Field 4

Field 5

Fiel d 6

Field 7

T

NSM

F1

F2

Field 3

Field 4

Field 5

Fiel d 6

Field 7

Field 8

CE

CR

CE

CR

PSHEAR

Type

Field 5

T

FID 11-20

Type

Field 4

NSM

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

EDGEBH Bulk Data Entry EDGEBH – Edge Blank Holder Definition for One-Step Stamping Simulation Description Defines geometry and restraining force per unit length for an edge blank holder in a one-step stamping simulation. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

EDGEBH

EID

S1

T2

S2

T2

BFORC E

BSID

(9)

(10)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

EDGEBH

6

-1.0

1.0

1.0

1.0

100.0

5

Field

Contents

EID

Element identification number. No default (Integer > 0)

S1, T1

Parametric entry points for the line. No default (Real; | S1, T1 | < 1.0)

S2, T2

Parametric exit points for the line. No default (Real; | S2, T2 | < 1.0)

BFORCE

Blank holder restraining force. No default (Real)

BSID

Blank holder set identifier for retrieving the input file back to HyperForm. Not used by the solver. No default (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

991

Comments 1.

992

This entry is only valid with an @HyperForm statement in the first line of the input file.

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

EDRAWB Bulk Data Entry EDRAWB – Draw Bead Definition for One-Step Stamping Simulation Description Defines location and restraining force per unit length for a draw bead in a one-step stamping simulation. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

EDRAWB

EID

S1

T2

S2

T2

DFORC E

DSID

(9)

(10)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

EDRAW B

13

-1.0

1.0

1.0

-1.0

100.0

2

Field

Contents

EID

Element identification number. No default (Integer > 0)

S1, T1

Parametric entry points for the line. No default (Real; | S1, T1 | < 1.0)

S2, T2

Parametric exit points for the line. No default (Real; | S2, T2 | < 1.0)

DFORCE

Draw bead restraining force per unit length. No default (Real)

DSID

Draw bead set identifier for retrieving the input file back to HyperForm. Not used by the solver. No default (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

993

Comments 1. This entry is only valid with an @HyperForm statement in the first line of the input file.

994

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

EIGC Bulk Data Entry EIGC – Complex Eigenvalue Extraction Data Description Defines data required to perform complex eigenvalue analysis. Format (1)

(2)

(3)

EIGC

SID

(4)

(5)

(6)

NORM

G

C

(7)

(8)

(9)

(10)

ND0

Continuation for EIGC ALPHAAJ OMEGAAJ

ND1

Example 1

(1)

(2)

EIC G

4

(3)

(4)

(5)

(6)

(7)

MAX

(8)

(9)

(10)

(9)

(10)

15

Example 2

(1)

(2)

EIGC

4

(3)

(4)

(5)

(6)

(7)

(8)

MAX

15

Example 3

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

995

(1)

(2)

EIGC

4

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MAX

1000.0

1000.0

Field

Contents

SID

Unique set identification number.

15

No default (Integer > 0) NORM

Indicates the option for normalizing eigenvectors. MAX - Normalize the component having the largest magnitude to a unit value for the real part and a zero value for the imaginary part. POINT - Normalize the component defined in fields 5 and 6 to a unit value for the real part and a zero value for the imaginary part. The value for NORM defaults to MAX if the magnitude of the defined component is zero. Default = MAX

G

Grid or scalar point identification number. Required if and only if NORM = POINT. No default (Integer > 0)

C

Component number. Required if and only if NORM = POINT and G is a geometric grid point. No default (0 < Integer < 6)

ND0

Desired number of roots and eigenvectors to be extracted. No default (Integer > 0)

ND1

Desired number of roots and eigenvectors to be extracted. No default (Integer > 0)

ALPHAAJ

Real part of the shift point. Default = 0.0 (Real)

996

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

OMEGAAJ

Imaginary part of the shift point. Default = 0.0 (Real)

Comments 1.

ND0 is required if there is no continuation, and it must be empty if there is a continuation line.

2.

ALPHAAJ and OMEGAAJ are only useful for direct complex eigenvalue analysis. If there is no METHOD command present in the subcase control area, the direct method is considered for the complex eigenvalue analysis. Otherwise, modal method is used.

3.

The 3rd field is reserved for a numerical complex eigensolution (METHOD). Currently, this field should be left blank;however, certain method types (INV, HESS and CLAN) will be accepted, but there will be no effect on the analysis.

Altair Engineering

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

997

EIGRA Bulk Data Entry EIGRA – Real Eigenvalue Extraction Data using Automated Multi-Level Sub-structuring Description Defines the data required to perform real eigenvalue analysis with the Automated Multi-Level Sub-structuring technique. Format (1)

(2)

(3)

(4)

(5)

EIGRA

SID

V1

V2

ND

(6)

(7)

(8)

(9)

AMPFFAC T

(10)

NORM

Example

(1) EIGRA

(2)

(3)

(4)

(5)

0.1

3.2

10

Field

Contents

SID

Unique set identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) V1,V2

Frequency range of interest in cycles per unit time. V2 must be present. Default = 0.0 for V1 (V1 < V2, Real, or blank for V1)

ND

Number of roots desired. See comment 3. No default (Integer > 0 or blank)

AMPFFACT

998

Amplification Factor. The substructure modes are solved up to the frequency of AMPFFACT*V2. Higher values of AMPFFACT will lead to

OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents more accurate results and longer running times. See comments 6 and 9. Default = 5.0 (Real or blank)

NORM

Method used for eigenvector normalization. If MASS, then eigenvectors are normalized to the unit value of the generalized mass. If MAX, then eigenvectors are normalized to the unit value of the largest displacement in the analysis set. Default = MASS for normal modes analysis.

Comments 1.

The units of V1 and V2 are cycles per unit time.

2.

The eigenvectors are normalized with respect to the mass matrix by default.

3.

The roots are found in order of increasing magnitude; those closest to zero are found first. The number and type of roots to be found can be determined from the following table. V1

V2

ND

Number and Type of Roots Found

V1

V2

ND

Lowest ND or all in range, whichever is smaller.

V1

V2

blank

All in range.

blank

V2

ND

Lowest ND roots below V2.

blank

V2

blank

All below V2.

4.

Eigenvalues are sorted in the order of magnitude for output.

5.

In vibration analysis, small negative roots are usually computational zeros, indicating rigid body modes. Finite negative roots are an indication of modeling problems. If V1 is set to zero explicitly, V1 is ignored.

6.

AMPFFACT is used to increase the accuracy of the eigenvalue and eigenvectors at the expense of slightly longer run times. It is recommended to use higher values of AMPFFACT, between [5.0, 15.0], for solid structures like engine blocks and suspension components.

7.

EIGRA data can be referenced by multiple normal modes subcases with different MPC set SID’s in each subcase. However, only one can be used for modal frequency response or modal transient analysis.

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8.

EIGRA data can be referenced by multiple modal dynamic subcases, if the MPC set SID is the same in each SUBCASE and the set of SPCD DOF is the same in each SUBCASE. Additionally, multiple eigenvalue analysis subcases can be used with AMSES, however, only one can be used for modal frequency response or modal transient analysis.

9.

If AMPFFACT is not specified by you and the model contains a large number of solid elements, then the value of AMPFFACT is automatically reset to 10.

10. This card is represented as a loadcollector in HyperMesh.

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EIGRL Bulk Data Entry EIGRL – Real Eigenvalue Extraction Data, Lanczos Method Description Defines data required to perform real eigenvalue analysis (vibration or buckling) with the Lanczos Method. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

EIGRL

SID

V1

V2

ND

MSGLVL

MAXSET

SHFSC L

NORM

Example

(1)

(2)

EIGRL

(3)

(4)

(5)

0.1

3.2

10

Field

Contents

SID

Unique set identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) V1,V2

For vibration analysis: Frequency range of interest For buckling analysis: Eigenvalue range of interest. See comments 3, 4, and 10. Default = blank (V1 < V2, Real, or blank)

ND

Number of roots desired. See comments 3 and 4. No default (Integer > 0 or blank)

MSGLVL

Diagnostic level.

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Field

Contents Default = 0 (Integer 0 through 4 or blank)

MAXSET

Number of vectors in block or set. Default = 8 (Integer 1 through 16 or blank)

SHFSCL

For vibration analysis: Estimate of the frequency of the first flexible mode. For buckling analysis: Estimate of the first eigenvalue. See comment 9. Default = blank (Real or blank)

NORM

Method used for eigenvector normalization. If MASS, then eigenvectors are normalized to the unit value of the generalized mass (this is not a valid option for linear buckling analysis). If MAX, then eigenvectors are normalized to the unit value of the largest displacement in the analysis set. Default = MASS for normal modes analysis; Default = MAX for linear buckling analysis (MASS or MAX)

Comments 1.

In vibration analysis, the units of V1 and V2 are cycles per unit time. In buckling analysis, V1 and V2 are eigenvalues. Each buckling eigenvalue is the factor by which the prebuckling state of stress is multiplied to produce buckling in the shape defined by the corresponding eigenvector.

2.

In vibration analysis, eigenvectors are normalized with respect to the mass matrix by default. In buckling analysis, eigenvectors are normalized to have unit value. NORM = MASS is not a valid option for linear buckling analysis.

3.

The roots are found in order of increasing magnitude: that is, those closest to zero are found first. The number and type of roots to be found can be determined from the following table. In vibration analysis, blank V1 defaults to -10. V1

V2

ND

Number and Type of Roots Found

V1

V2

ND

Lowest ND or all in range, whichever is smaller.

V1

V2

blank

All in range

V1

blank

ND

Lowest ND in range [V1, + ¥]

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V1

V2

ND

Number and Type of Roots Found

V1

blank

blank

Lowest root in range [V1, + ¥]

blank

blank

ND

Lowest ND roots in [-¥,+¥]

blank

blank

blank

Lowest root.

blank

V2

ND

Lowest ND roots below V2

blank

V2

blank

All below V2

4.

The Lanczos eigensolver provides two different ways of solving the problem. If the eigenvalue range is defined with no upper bound (V2 blank) and less than 50 modes (ND < 50), the faster method is applied.

5.

Eigenvalues are sorted in the order of magnitude for output. An eigenvector is found for each eigenvalue.

6.

In vibration analysis, small negative roots are usually computational zeros, indicating rigid body modes. Finite negative roots are an indication of modeling problems. If V1 is set to zero explicitly, V1 is ignored. It is recommended that V1 not be set to zero when extracting rigid body modes.

7.

MSGLVL controls the amount of diagnostic output during the eigenvalue extraction. The default value of zero suppresses all diagnostic output. A value of one prints eigenvalues accepted at each shift. Higher values result in increasing levels of diagnostic output.

8.

MAXSET is used to limit the maximum block size in the Lanczos solver. It may be reduced if there is insufficient memory available. The default value is recommended.

9.

A specification of SHFSCL may improve the performance of a vibration analysis. It may also be used to improve the performance of a buckling analysis, especially when the applied load differs from the first buckling load by orders of magnitude.

10. AMLS and AMSES eigensolvers require that V2 be specified. 11. This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1003 Proprietary Information of Altair Engineering

ELEMQUAL Bulk Data Entry ELEMQUAL – Resets the Default Bound Values for Element Quality Check Description Resets the default values of the warning and error bound limits for element quality check. Format (1)

(2)

(3)

(4)

(5)

(6)

ELEMQUAL

ETYPE

PTYPE

LTYPE

V1

V2

(7)

(8)

(9)

(10)

Example 1

For CTRIA3 elements, change the upper limit of aspect ratio for error message to 300.0 (default is 500). (1)

(2)

(3)

(4)

ELEMQUAL

TRIA3

ARATIO

ERROR

(5)

(6)

(7)

(8)

(9)

(10)

300.0

Example 2

For CTETRA elements, change the bound limits of collapse for warning message to 0.01 and 10.0 (default lower and upper limits are 0.001 and 100.0). (1)

(2)

(3)

(4)

(5)

(6)

ELEMQUAL

TETRA

C OLLAPSE

WARNING

0.01

10.

(7)

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(8)

(9)

(10)

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Field

Contents

ETYPE

Element type. Allowable entries are: TRIA3 (CTRIA3), QUAD4 (CQUAD4), TETRA (1st-order CTETRA), TET10 (2nd-order CTETRA), PENTA (1st-order CPENTA), PENT15 (2nd-order CPENTA), HEXA (1st-order CHEXA), HEX20 (2nd-order CHEXA), PYRA (1st-order CPYRA), PYRA13 (2nd-order CPYRA), TAXI3 (1st-order CTAXI or CTRIAX6), TAXI6 (2nd-order CTAXI or CTRIAX6), GASK8 (CGASK8), GASK16 (CGASK16), GASK6 (CGASK6), and GASK12 (CGASK12). No default (TRIA3, QUAD4, TETRA, TET10, PENTA, PENT15, HEXA, HEX20, PYRA, PYRA13, TAXI3, TAXI6, GASK8, GASK16, GASK6, or GASK12).

PTYPE

Geometric property type. Allowable entries are: ARATIO (Aspect Ratio), SKEW (Skew Angle), TAPER (Face Taper), WARP (Warp Angle), TWIST (Twist Angle), EDGE (Edge Angle), COLLAPSE, ANGLE (Vertex Angle), HOENOR (Hoe Normal Offset), HOETAN (Hoe Tangent Offset). No default (ARATIO, SKEW, TAPER, WARP, TWIST, EDGE, COLLAPSE, ANGLE, HOENOR, or HOETAN).

LTYPE

Type of bound limits. No default (WARNING or ERROR)

V1

Lower bound value. No default (Real)

V2

Upper bound value. No default (Real)

Comments 1.

Element quality checks and their default settings are described in the Element Quality Check section.

2.

All specified values (V1 and V2) are checked against the corresponding limits used for validity check. Data outside the validity range is ignored.

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OptiStruct 13.0 Reference Guide 1005 Proprietary Information of Altair Engineering

ELIST Bulk Data Entry ELIST – Damp Shell Elements for a Fluid Volume Description Specifies damp shell elements for a fluid volume. ELIST entries are referenced by the MFLUID entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

ELIST

LID

EID1

EID2

EID3

EID4

EID5

EID6

EID7

EID8

EID9

EID10

- etc -

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

ELIST

25

47

22

THRU

35

-56

-57

Field

Contents

LID

List of identification number.

(9)

(10)

No default (Integer > 0) EID

Element identification number of CQUAD4, CTRIA3, CQUADR, and CTRIAR elements that are damp in the fluid volume.

Comments 1.

By default, for elements only damp on one side (see WSURF1 on MFLUID entry), the damp side of an element is on the same side of the element’s normal. But a negative EIDi indicates that the fluid is opposite to the normal. If there are negative EIDi’s specified in a "THRU" range, then both EIDi’s in the range must be negative.

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2.

Alternatively, the SURF and SET entries may be used to define damp elements but the SURF and SET entries may not be combined in the single with ELIST entries to define damp elements. For example, if any MFLUID references a missing ELIST,25, then the program will not search for a SET,25 if a ELIST card exists in the deck.

3.

ELIST entries are internally converted to SET entries. The continuation is optional.

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OptiStruct 13.0 Reference Guide 1007 Proprietary Information of Altair Engineering

ENDMETADATA Bulk Data Entry ENDMETADATA – Indicates the end of metadata that is to be passed to the metadata output file. Description ENDMETADATA indicates the end of metadata that is to be passed to the metadata output file. Metadata between the METADATA and ENDMETADATA commands is passed to the _metadata.xml file.

Example

METADATA This line will be passed to the filename_metadata.xml file. So will this information: Color=blue ENDMETADATA Comments 1.

There can be two sections of metadata; one in the Solution Control section and one in the Bulk Data section.

2.

Metadata can be used to pass information from the pre-processor seamlessly through the solver to a post-processing program.

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END Bulk Data Entry END – Indicates the end of data input for a specific entity Description The END bulk data entry indicates the end of data that is used to describe a specific entity (or entities) for inclusion in a model. The END entry is used in conjunction with the BEGIN entry to define the data required for a specific entity. Format (1)

(2)

(3)

(4)

END

TYPE

NAME

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

END

FEMODE L

Bumper

(1)

(2)

(3)

END

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

HYPRBEAM Square

Field

Contents

TYPE

Specifies the entity type that will be defined by the END data entry (see comment 2). (HYPRBEAM or FEMODEL)

NAME

This field specifies the name of the entity that is defined by the END entry (see comment 2). (Character String)

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OptiStruct 13.0 Reference Guide 1009 Proprietary Information of Altair Engineering

Comments 1.

The BEGIN and END bulk data entries can be used in conjunction to define a part within the full model (for TYPE = FEMODEL).

2.

TYPE = HYPRBEAM: Data required for the definition of an arbitrary beam section will be specified between the BEGIN and END data entries. TYPE = FEMODEL: In a model containing multiple parts, the parts are included within the full model specifying part data between the BEGIN and END bulk data entries (the INCLUDE entry can also be used for part data referencing). The name of the included part should be specified in the NAME field.

3.

The INCLUDE entry, similar to almost any other bulk data entry, is allowed between BEGIN and END entries. However, BEGIN and END should exist in the same file.

4.

Models are often defined in separate files, and the block (BEGIN – END) contains only INCLUDE entries. It is possible to duplicate a single part by including the same file(s) in different BEGIN-END blocks.

5.

There can be multiple sections of arbitrary beam data; one for each beam section.

6.

An example set of data for the definition of an arbitrary beam section is as follows: BEGIN,HYPRBEAM,SQUARE $ GRIDS,1,0.0,0.0 GRIDS,2,1.0,0.0 GRIDS,3,1.0,1.0 GRIDS,4,0.0,1.0 $ CSEC2,10,100,1,2 CSEC2,20,100,2,3 CSEC2,30,100,3,4 CSEC2,40,100,4,1 $ PSEC,100,1000,0.1 $ END,HYPRBEAM

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ERPPNL Bulk Data Entry ERPPNL – Panel Definition for Equivalent Radiated Power Output Description Defines one or more sets of elements as panels for equivalent radiated power output for a frequency response analysis of a coupled fluid-structural model. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

ERPPNL

NAME1

SID1

NAME2

SID2

NAME3

SID3

NAME4

SID4

NAME5

SID5

…

Field

Contents

NAME#

Panel label.

(10)

No default (Character string) SID#

Set identification number for a set of elements. No default (Integer > 0)

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OptiStruct 13.0 Reference Guide 1011 Proprietary Information of Altair Engineering

ESLTADD Bulk Data Entry ESLTADD – Combination of selected time steps for Geometric Nonlinear ESLM Optimization or a Multi-body Dynamics ESLM Optimization Description Defines a combined time step selection set as a union of selected time steps defined via ESLTIME entries for Geometric Nonlinear ESLM optimization or a Multi-body Dynamics ESLM optimization. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

ESLTADD

SID

S1

S2

S3

S4

S5

S6

S7

S8

S9

etc.

(10)

Example

(1)

(2)

(3)

(4)

(5)

ESLTADD

101

9

11

13

Field

Contents

SID

Set identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) Si

Set identification numbers of time step selections defined via ESLTIME bulk data entries. (Integer > 0)

Comments 1.

ESLTADD can be selected within the subcase information section using the command ESLTIME=SID.

2.

Si should be unique and may not be the identification number of a set defined by another ESLTADD entry.

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3.

ESLTADD entries take precedence over ESLTIME entries. If both entries have the same SID, only the ESLTADD entry will be used.

4.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1013 Proprietary Information of Altair Engineering

ESLTIME Bulk Data Entry ESLTIME – Time Step selection control for Geometric Nonlinear Response ESLM Optimization and Multi-body Dynamics ESLM Optimization Description Defines time step selection control for geometric nonlinear response ESL Optimization and Multi-body dynamics ESLM optimization. Format (1)

(2)

(3)

(4)

(5)

(6)

ESLTIME

SID

TLB

TUB

RID1

LB1

UB1

TYPE1

RID2

LB2

UB2

TYPE2

RID3

LB3

UB3

TYPE3

(7)

(8)

(9)

(10)

...

Example

(1)

(2)

ESLTIME

100

11

(3)

(4)

-19.9

99.9

12

(5)

(6)

(7)

(8)

(9)

(10)

1

13

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Field

Contents

SID

Set identification number. (Integer > 0)

RID

Identification number of a DRESP1, DRESP2, or DRESP3 bulk data entry. (Integer > 0)

TLB

Lower bound of time. No default (Real > 0.0, or blank)

TUB

Upper bound of time. No default (Real > 0.0, or blank)

LB#

Lower bound on response. (Real, or blank)

UB#

Upper bound on response. (Real, or blank)

TYPE#

Flag to select the time steps at which the highest or lowest response values or peaks or troughs of the response, occur. = 1, select the highest response value = -1, select the lowest response value = 2, select the response peaks = -2, select the response troughs (Integer = -2, -1, 1, 2, or blank)

Comments 1.

ESLTIME should be selected by the Subcase Information command ESLTIME = SID or in the bulk data section by the ESLTADD entry. It can only be selected in geometric nonlinear analysis subcases which are defined by an ANALYSIS = NLGEOM, IMPDYN or EXPDYN subcase entry, and for geometric nonlinear response ESL Optimization.

2.

The SID and RID fields cannot be left blank. Other fields, if blank, will be ignored.

3.

Lower bounds TLB and LB must be smaller than upper bounds TUB and UB respectively.

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OptiStruct 13.0 Reference Guide 1015 Proprietary Information of Altair Engineering

4.

The TLB and TUB fields can be used to define the range of time. OptiStruct will then select the most critical time steps in the time range with higher priority for ESL generation (Figure 1). If more time steps are required, then the critical time steps outside the time range will be taken into account.

5.

Using fields LB and UB, the user can define the range of a specific response. OptiStruct will then select the time steps with response values in this range for ESL generation (Figure 1).

Figure 1: Time step selection based on time and response range.

6.

If TYPE = 1, time steps which have the highest response values will be selected. If TYPE = -1, time steps which have the lowest response values will be selected.

Figure 2: Example illustration depicting TYPE=1 and TYPE=-1 response selection

7.

If TYPE = 2, time steps at which response peaks occur will be selected. If TYPE = -2, time steps at which response troughs occur will be selected.

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Figure 3: Example illustration depicting TYPE=2 and TYPE=-2 response selection.

8.

If a NLGEOM, IMPDYN or EXPDYN subcase is referenced by a DRESP2 entry with DRESP1L or DRESP2L definition, the generated ESL subcase at the most critical time step will be used for this DRESP2(DRESP1L/DRESP2L) entry.

9.

All continuation lines on the ESLTIME entry are ignored in Multi-body dynamics ESLM optimization. Only the first line (ESLTIME, SID, TLB, TUB) is considered.

10. DOPTPRM, ESLSTOL is ignored, if ESLTIME is defined in the model.

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OptiStruct 13.0 Reference Guide 1017 Proprietary Information of Altair Engineering

FATDEF Bulk Data Entry FATDEF – Elements for Fatigue Analysis Description Defines elements, and associated fatigue properties, for consideration in a fatigue analysis. Format (1)

(2)

(3)

FATDEF

ID

TOPSTR

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Optional continuation lines for selecting elements, and associated fatigue properties, using element sets (ELSET) ELSET

ELSID1

PFATID1

ELSID2

PFATID2

ELSID3

PFATID3

ELSID4

PFATID4

…

…

…

…

…

…

Optional continuation lines for selecting elements and associated fatigue properties through referenced properties (PSHELL) PSHELL

PID1

PFATID1

PID2

PFATID2

PID3

PFATID3

PID4

PFATID4

…

…

…

…

…

…

Optional continuation lines for selecting elements and associated fatigue properties through referenced properties (PSOLID) PSOLID

PID1

PFATID1

PID2

PFATID2

PID3

PFATID3

PID4

PFATID4

…

…

…

…

…

…

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Optional continuation lines for excluding elements using element sets (ELSET) XELSET

XELSID1 XELSID2 XELSID3 XELSID4 XELSID5 XELSID6 XELSID7 XELSID8

…

…

…

…

…

…

…

…

Optional continuation lines for excluding individual elements XELEM

XEID1

XEID2

XEID3

XEID4

XEID5

XEID6

XEID7

XEID8

…

…

…

…

…

…

…

…

Field

Contents

ID

Each FATDEF card must have a unique ID. FATDEF Subcase Information entry may reference this ID. No default (Integer > 0)

TOPSTR

Top stress fraction. Elements with combined stress not in this top fraction of each MATFAT group will be screened out and have no results. This field is ignored in fatigue analysis on a transient subcase. Default = blank (100% will be used internally), (0.0 < Real < 1.0)

ELSET

ELSET flag indicating that a list of pairs of ELSET and PFAT IDs will follow, defining elements, and their associated fatigue properties, for consideration in fatigue analyses where this FATDEF is selected.

ELSID#

Element Set ID. Elements in this set will be considered in fatigue analyses where this FATDEF is selected. No default (Integer > 0)

PFATID#

Fatigue property ID. This is identification number of a PFAT entry, which indicates the fatigue property used by the preceding elements defined by ELSID# or PID#.

PSHELL

PSHELL flag indicating that a list of pairs of PSHELL property IDs and PFAT IDs will follow; defining elements and their associated fatigue properties for consideration in fatigue analyses where this FATDEF is selected.

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OptiStruct 13.0 Reference Guide 1019 Proprietary Information of Altair Engineering

Field

Contents

PSOLID

PSOLID flag indicating that a list of pairs of PSOLID property IDs and PFAT IDs will follow; defining elements and their associated fatigue properties for consideration in fatigue analyses where this FATDEF is selected.

PID#

Property ID. This is identification number of a PSHELL or PSOLID entry. Elements referencing any property with this ID will be considered in fatigue analyses where this FATDEF is selected. No default (Integer > 0)

XELSET

XELSET flag indicating that IDs of elements sets excluded from fatigue analysis follow.

XELSID#

Element set ID. Elements in these sets will be excluded from fatigue analyses where this FATDEF is selected. No default (Integer > 0)

XELEM

XELEM flag indicating that IDs of elements excluded from fatigue analysis follow.

XEID#

Element ID. These elements will be excluded from fatigue analyses where this FATDEF is selected. No default (Integer > 0)

Comments 1.

At least one of the optional continuation lines ELSET or PROP must be present.

2.

This card is represented as a loadcollector in HyperMesh.

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FATEVNT Bulk Data Entry FATEVNT – Loading Event Definition for Fatigue Analysis Description Defines loading events for fatigue analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

FATEVNT

ID

FLOAD1

FLOAD2

FLOAD3

FLOAD4

FLOAD5

FLOAD6

FLOAD7

FLOAD8

...

...

(10)

Field

Contents

ID

Each FATEVNT card must have a unique ID. This identifier may be referenced by a FATSEQ definition. No default (Integer > 0)

FLOAD#

Identification number of a FATLOAD entry (see comments 1, 3 and 4). No default (Integer > 0)

Comments 1.

FATLOAD entries referenced on this bulk data entry may reference different subcases.

2.

Identification numbers of FATSEQ and FATEVNT share the same ID pool.

3.

These FATLOAD entries should reference the subcase types. For example, either static subcases or transient subcases can be referenced, but not both. Referencing a combination of subcase types via FATLOAD entries on the same FATEVNT entry is not allowed.

4.

If a specified FATLOAD entry references a transient subcase, only one FATLOAD entry is allowed.

5.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1021 Proprietary Information of Altair Engineering

FATLOAD Bulk Data Entry FATLOAD - Fatigue Load Description Defines fatigue loading parameters. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

FATLOAD

ID

TID

LC ID

LDM

Scale

Offset

(8)

(9)

Field

Contents

ID

Each FATLOAD card must have a unique ID. This identifier may be referenced by a FATEVNT definition.

(10)

No default (Integer > 0) TID

Identification number of TABFAT entry. (Integer > 0 or blank) If LCID references a linear-static subcase, TID should be a positive integer (Integer > 0). If LCID references transient subcase, TID should be blank.

LCID

Subcase identification number of a linear-static or transient analysis subcase. No default (Integer > 0)

LDM

The magnitude of the FEA load in the same units as those for the time history. It is ignored in fatigue analyses based on a transient analysis subcase (see comment 2). Default = 1.0 (Real)

Scale

Scale factor applied to the load or time history. It is ignored in fatigue analyses based on a transient analysis subcase. Default = 1.0 (Real)

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Field

Contents

Offset

Offset applied to the load or time history. It is ignored in fatigue analyses based on a transient analysis subcase. Default = 0.0 (Real)

Comments 1.

This magnitude is used as a scale factor to normalize the finite element stresses/strains to obtain the stress/strain distribution due to a unit loading.

2.

The sequence below depicts how LDM, Scale and Offset values work together to scale the FEA stress tensor at time t:

ij

(t )

Where,

ij . FEA

LDM

( P (t ) Scale Offset )

is the result stress tensor at time t.

is the stress tensor from static analysis.

P(t) is the y point value of load-time history at time t. 3.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1023 Proprietary Information of Altair Engineering

FATPARM Bulk Data Entry FATPARM - Fatigue Analysis Parameters Description This bulk data entry can be used to define parameters required for a Fatigue Analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

FATPARM

ID

Type

STRESS

C ombinatio n

C orrectio n

StressUni t

Plasticit y

RAINFLO W

RType

GateRel

C ERTNTY

SurvC ert

FOS

FOSType

(7)

(8)

(9)

(10)

Field

Contents

ID

Each FATPARM card must have a unique ID. The FATPARM Subcase Information entry may reference this identifier. No default (Integer > 0)

Type

Type of fatigue analysis that is defined. Default = SN (SN = Stress Life, EN = Strain Life, FOS = Factor of Safety Analysis - see comment 9) (NSTRESS is also supported for Stress Life for compatibility)

STRESS

STRESS flag indicating that parameters are to follow which define how the stress is used in fatigue calculation. This flag and following parameters will be used only when the "Type" field is set to SN or EN.

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Field

Contents

Combinatio n

Default = ABSMAXPR (ABSMAXPR = Abs Max Principal MINPRINC = Min Principal SGVON = Signed von Mises SGTRESCA = Signed Tresca XNORMAL = X Normal ZNORMAL = Z Normal YZSHEAR = Y-Z Shear

MAXPRINC = Max Principal VONMISES = von Mises TRESCA = Tresca SGMAXSHR = Signed Max Shear YNORMAL = Y Normal XYSHEAR = X-Y Shear ZXSHEAR = Z-X Shear)

The sign on the Signed von Mises, Signed Tresca, Signed Max. Shear is taken from the sign of the Abs. Max. Principal value. For Stress Life, combined stress value is used; For Strain Life, combined strain value is used. For Strain Life, shear strain components are engineering shear strain (two times tensor shear strain). For brittle materials, "Absolute maximum principle" is recommended. For ductile materials, "Signed von Mises" is recommended. Correction

Mean stress correction method. See comments 5, 6, 7 and 8. For Type = SN, valid options are: Default = GOODMAN (NONE, GOODMAN, GERBER, GERBER2, SODERBE) For Type = EN, valid options are: Default = SWT (NONE, MORROW, MORROW2, SWT = Smith-Watson-Topper)

StressUnit

FE analysis Stress Tensor Unit. The Unit is necessary because the S-N/E-N curve (MATFAT card) might be defined in different unit, and FEA stress needs to be converted before looking up the fatigue life for a given stress level on the S-N curve. See comment 10. Default = MPA (MPA, PA, PSI, KSI)

Plasticity

This parameter is only applicable for Type = EN. For Type = SN, it is not used. For Type = EN, valid options are: Default = NEUBER (NONE, NEUBER)

RAINFLOW

The RAINFLOW flag indicates that parameters required for Rainflow counting are to follow. This flag and its related parameters will be used only when the “Type” field is set to SN or EN.

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OptiStruct 13.0 Reference Guide 1025 Proprietary Information of Altair Engineering

Field

Contents

RType

Rainflow data type. See comment 1. Default = LOAD (LOAD - Load-time history STRESS - Stress-time history)

GateRel

Relative fraction of maximum gate range. The reference value is the maximum range multiplied by GateRel, and used for gating out small disturbances or "noise" in the time series.

CERTNTY

The CERTNTY flag indicates that parameters that define certainties in fatigue analysis are to follow. This flag and the following parameter will be used only when the “Type” field is set to SN or EN.

SurvCert

Certainty of survival based on the scatter of the S-N curve. See comment 4. Default = 0.5 (0.0 < Real < 1.0)

FOS

The FOS flag indicates that the following parameters are for Factor of Safety analysis (Type = FOS). This flag and following parameter will be used only when the “Type” field is set to FOS.

FOSType

This field can be used to select the Factor of safety analysis type. Default = DANGVAN

Comments 1.

RType = Load is valid when there is only one static load case defined in an event. If the event contains multiple static load cases, then RType will automatically be set to STRESS because there will be stress super-positioning among different load cases; doing rainflow counting on load-time history could not deal with it.

2.

When RType = Load, load-time history will be cycle counted using the rainflow cycle counting method. The cycle counting results (load Ranges and Means) will be scaled by combined FEA stress. Doing rainflow counting on load-time is much faster than doing it on stress-time (RType=Stress), especially when the load-time history is complex and contains a large number of time points, but it is less accurate.

3.

When RType = Stress, stress-time history will be cycle counted using the rainflow cycle counting method. The stress-time history has the same length as load-time, while each point of the stress time is the combined stress value where the stress tensor is FEA stress scaled by y point value of the corresponding load-time history.

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4.

Certainty of Survival is based on the scatter of the S-N / E-N curve. It is used to modify the S-N / E-N curve according to the standard error parameter (SE) defined in fatigue property of material card (MATFAT card). A higher reliability level requires a larger certainty of survival.

5.

When fatigue optimization is performed, EN method with SWT mean stress correction is changed to EN method with Morrow mean stress correction automatically.

6.

Correction=GERBER2 improves the GERBER method by ignoring the effect of negative mean stress.

7.

Correction=MORROW2 improves the MORROW method by ignoring the effect of negative mean stress.

8.

Correction=SODERBE is slightly different from GOODMAN, the mean stress is normalized by yield stress instead of ultimate tensile stress. Se = Sa / (1 - Sm / Sy ) Where, Se is equivalent stress amplitude, Sa is stress amplitude, Sm is mean stress, and Sy is yield stress.

9.

The “STRESS”, “RAINFLOW” and “CERTNTY” continuation lines are ignored in a factor of safety analysis (Type=FOS).

10. If UNITS=# or DTI UNITS is present, the default value of StressUnit should be determined by UNITS=# or DTI UNITS. If UNITS=# and DTI UNITS are absent, the default value of StressUnit is MPA. If UNITS=# or DTI UNITS is present, and StressUnit is also specified, but they are not consistent, an error will be issued. 11. This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1027 Proprietary Information of Altair Engineering

FATSEQ Bulk Data Entry FATSEQ – Load Sequence Definition for Fatigue Analysis Description This bulk data entry can be used to define a loading sequence for a Fatigue Analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

FATSEQ

ID

FID1

N1

FID2

N2

FID3

N3

FID4

N4

FID5

N5

(10)

Field

Contents

ID

Each FATSEQ card must have a unique ID. FATSEQ Subcase Information entry may reference this identifier. Alternatively this ID may be referenced by other FATSEQ definitions. No default (Integer > 0)

FID#

Identification number of FATSEQ or FATEVNT entry (see Comment 3) No default (Integer > 0)

N#

Number of times this loading sequence or event is repeated (see Comment 4). Default = 1 (Integer > 0)

Comments 1.

Identification numbers of FATSEQ and FATEVNT entries share the same ID pool.

2.

Repeat number (N#) has no effect on the results of a Factor of Safety (FOS) analysis.

3.

A fatigue subcase should reference the same subcase types through FATSEQ and FATEVNT entries (for example, either static subcases or transient subcases can be referenced, but not both). Referencing a combination of subcase types is not allowed.

4.

This card is represented as a loadcollector in HyperMesh.

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FLDATA Bulk Data Entry FLDATA – User-defined Forming Limit Curve for One-Step Stamping Simulation Description Defines a forming limit curve as a table of minor and major strain values in a one-step stamping simulation. Format (1)

(2)

(3)

(4)

FLDATA

FLDID

Ei1

Ei2

(5)

(6)

(7)

(8)

(9)

(10)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

FLDATA

2

-.194

.284

FLDATA

2

-.0.89

.269

FLDATA

2

…

…

FLDATA

2

.319

.319

Field FLDID

(5)

(6)

(7)

Contents Blank holder identification number. No default (Integer > 0)

Ei1

Minor strain value. No default (Real)

Ei2

Major strain value No default (Real)

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OptiStruct 13.0 Reference Guide 1029 Proprietary Information of Altair Engineering

Comments 1.

This entry is only valid with an @HyperForm statement in the first line of the input file.

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FORCE Bulk Data Entry FORCE – Point Force Description Defines a static force at a grid point by specifying a vector. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

FORC E

SID

G

C ID

F

N1

N2

N3

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

FORC E

2

5

6

2.9

0.0

1.0

0.0

Field

Contents

SID

Load set identification number.

(9)

(10)

(Integer > 0) G

Grid point identification number. (Integer > 0 or ) See comment 3.

CID

Coordinate system identification number. Default = 0 (Integer > 0, or blank)

F

Scale factor.

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Field

Contents (Real)

N1,N2,N3

Components of vector measured in coordinate system defined by CID. (Real; must have at least one non-zero component)

Comments 1.

The static force applied to grid point G is given by

where,

is the vector defined in fields 6, 7, and 8.

2.

A CID of zero or blank references the basic coordinate system.

3.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on FORCE entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

4.

This card is represented as a force load in HyperMesh.

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FORCE1 Bulk Data Entry FORCE1 – Static Force, Alternate Form 1 Description Used to define a static force by specification of a value and two grid points that determine the direction. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

FORC E1

SID

G

F

G1

G2

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

FORC E1

6

13

-2.93

16

13

Field

Contents

SID

Load set identification number.

(7)

(8)

(9)

(10)

(Integer > 0) G

Grid point identification number. (Integer > 0)

F

Value of force. (Real)

G1,G2

Grid point identification numbers.

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OptiStruct 13.0 Reference Guide 1033 Proprietary Information of Altair Engineering

Comments 1.

The static force applied to grid point G is

where, 2.

is a unit vector parallel to a vector from G1 to G2.

This card is represented as a force load in HyperMesh

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FORCE2 Bulk Data Entry FORCE2 – Static Force, Alternate Form 2 Description Used to define a static force by specification of a value and four grid points that determine the direction. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

FORC E2

SID

G

F

G1

G2

G3

G4

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

FORC E2

6

13

-2.93

16

13

18

19

Field

Contents

SID

Load set identification number.

(9)

(10)

(Integer > 0) G

Loaded Grid point identification number. (Integer > 0)

F

Value of force. (Real)

Gi

Grid point identification numbers. (Integer > 0; G1 and G2 may not be coincident; G3 and G4 cannot be coincident.)

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OptiStruct 13.0 Reference Guide 1035 Proprietary Information of Altair Engineering

Comments 1.

The static force applied to grid point G is

where, is a unit vector parallel to a vector calculated by the cross product of vectors from G1 to G2 and G3 to G4. 2.

This card is represented as a force load in HyperMesh

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FREQ Bulk Data Entry FREQ – Frequency List Description Defines a set of frequencies to be used in the solution of frequency response problems. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

FREQ

SID

F1

F2

F3

F4

F5

F6

F7

F8

…

…

…

…

…

…

…

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

FREQ

3

7.0

12.56

13.99

23.4

23.34

Field

Contents

SID

Identification number.

(8)

(9)

(10)

No default (Integer > 0) F#

Frequency value. No default (Real > 0.0)

Comments 1.

FREQ entries must be selected with the I/O Options or Subcase Information command FREQUENCY = SID.

2.

The units for F# are cycles per unit time.

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OptiStruct 13.0 Reference Guide 1037 Proprietary Information of Altair Engineering

3.

All FREQi entries with the same set identification numbers will be used. Duplicate frequencies will be ignored.

and

are considered duplicated if:

where, DFREQ is a user parameter with a default of 10 -5 * fMAX , and fMIN are the maximum and minimum excitation frequencies of the combined FREQi entries. 4.

This card is represented as a loadcollector in HyperMesh.

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FREQ1 Bulk Data Entry FREQ1 – Frequency List, Alternate Form 1 Description Defines a set of frequencies to be used in the solution of frequency response problems by specification of a starting frequency, frequency increment, and the number of increments desired. Format (1)

(2)

(3)

(4)

(5)

(6)

FREQ1

SID

F1

DF

NDF

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

FREQ1

6

2.9

0.5

13

Field

Contents

SID

Identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) F1

First frequency in set. No default (Real > 0)

DF

Frequency increment. No default (Real > 0.0)

NDF

Number of frequency increments. Default = 1 (Integer > 0)

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OptiStruct 13.0 Reference Guide 1039 Proprietary Information of Altair Engineering

Comments 1.

FREQ1 entries must be selected with the I/O Options or Subcase Information command FREQUENCY = SID.

2.

The units for F1 and DF are cycles per unit time.

3.

The frequencies defined by this entry are given by where i = 1 to (NDF + 1).

4.

All FREQi entries with the same set identification numbers will be used. Duplicate frequencies will be ignored.

and

are considered duplicated if:

where, DFREQ is a user parameter with a default of 10 -5 * fMAX , and

are the maximum

and minimum excitation frequencies of the combined FREQi entries. 5.

This card is represented as a loadcollector in HyperMesh.

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FREQ2 Bulk Data Entry FREQ2 – Frequency List, Alternate Form 2 Description Defines a set of frequencies to be used in the solution of frequency response problems by specification of a starting frequency, final frequency, and the number of logarithmic increments desired. Format (1)

(2)

(3)

(4)

(5)

FREQ2

SID

F1

F2

NF

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

FREQ2

6

1.0

8.0

6

Field

Contents

SID

Identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) F1

First frequency in set. No default (Real > 0.0)

F2

Last frequency in set. No default (Real > 0.0, F2 > F1)

NF

Number of logarithmic intervals. Default = 1 (Integer > 0)

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OptiStruct 13.0 Reference Guide 1041 Proprietary Information of Altair Engineering

Comments 1.

FREQ2 entries must be selected with the I/O Options or Subcase Information command FREQUENCY = SID.

2.

The units for F1 and F2 are cycles per unit time.

3.

The frequencies defined by this entry are given by

where, 4.

and i = 1, 2, …, (NF + 1).

All FREQi entries with the same set identification numbers will be used. Duplicate frequencies will be ignored.

and

are considered duplicated if:

where, DFREQ is a user parameter with a default of 10 -5 * fMAX , and

are the maximum

and minimum excitation frequencies of the combined FREQi entries. 5.

This card is represented as a loadcollector in HyperMesh.

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FREQ3 Bulk Data Entry FREQ3 – Frequency List, Alternate Form 3 Description Defines a set of frequencies for the modal method of frequency response analysis by specifying the number of frequencies between modal frequencies. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

FREQ3

SID

F1

F2

TYPE

NEF

C LUSTER

(9)

(10)

Example

Define a set of frequencies such that there will be 10 frequencies between each mode, within the frequency range 20 to 200, plus 10 frequencies between 20 and the lowest mode in the range, plus 10 frequencies between the highest mode in the range and 200. (1)

(2)

(3)

(4)

(5)

(6)

(7)

FREQ3

6

20.0

200.0

LINEAR

10

2.0

Field

Contents

SID

Set identification number.

(8)

(9)

(10)

No default (Integer > 0) F1

Lower bound of modal frequency range in cycles per unit time. No default (Real > 0.0 for TYPE = LINEAR ; Real > 0.0 for TYPE = LOG)

F2

Upper bound of modal frequency range in cycles per unit time. Default = F1 (Real > 0.0, F2 > F1)

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OptiStruct 13.0 Reference Guide 1043 Proprietary Information of Altair Engineering

Field

Contents

TYPE

Specifies linear or logarithmic interpolation between frequencies. Default = "LINEAR" (LINEAR or LOG)

NEF

Number of excitation frequencies within each sub range including the end points. The first sub range is between F1 and the first modal frequency within the bounds. Intermediate sub ranges exist between each mode calculated within the bounds. The last sub range is between the last modal frequency within the bounds and F2. Default = 10 (Integer > 1)

CLUSTER

Specifies cluster of the excitation frequency near the end points of the range. See comment 5. Default = 1.0 (Real > 0.0)

Comments 1.

FREQ3 applies only to the modal method of frequency response analysis.

2.

FREQ3 entries must be selected in the Subcase Information section with FREQUENCY = SID.

3.

Since the forcing frequencies are near structural resonances, it is important that some amount of damping be specified.

4.

All FREQi entries with the same set identification numbers will be used. Duplicate frequencies will be ignored.

and

are considered duplicated if:

where, DFREQ is a user parameter, with a default of 10 -5 * fMAX and

are the maximum

and minimum excitation frequencies of the combined FREQi entries. 5.

CLUSTER is used to obtain better resolution near the modal frequencies where the response variation is highest, in accordance with:

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where,

k

=

-1 + 2(k - 1)/(NEF - 1) is a parametric coordinate between -1 and 1.

=

excitation frequency number in the subrange (1,2,3,…,NEF)

=

frequency at the lower limit of the sub range. (If TYPE is LOG, then this is the logarithm of the frequency.)

=

frequency at the upper limit of the sub range. (If TYPE is LOG, then this is the logarithm of the frequency.)

=

the k-th excitation frequency. (If TYPE is LOG, then this is the logarithm of the frequency.)

CLUSTER > 1.0 provides closer spacing of excitation frequency towards the ends of the frequency range, while values of less than 1.0 provide closer spacing towards the center of the frequency range. For example, if the frequency range is between 10 and 20, NEF = 11, TYPE = "LINEAR"; then, the excitation frequencies for various values of CLUSTER would be as shown in the table below. CLUSTER Excitation Frequency Number

0.25

0.50

1.0

2.0

4.0

Excitation Frequencies in Hertz 1

-1.0

10.00

10.0

10.0

10.0

10.0

2

-0.8

12.95

11.8

11.0

10.53

10.27

3

-0.6

14.35

13.2

12.0

11.13

10.60

4

-0.4

14.87

14.2

13.0

11.84

11.02

5

-0.2

14.99

14.8

14.0

12.76

11.66

6

0.0

15.00

15.0

15.0

15.00

15.00

7

0.2

15.01

15.2

16.0

17.24

18.34

8

0.4

15.13

15.8

17.0

18.16

18.98

9

0.6

15.65

16.8

18.0

18.87

19.40

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OptiStruct 13.0 Reference Guide 1045 Proprietary Information of Altair Engineering

10

0.8

17.05

18.2

19.0

19.47

19.73

11

1.0

20.00

20.0

20.0

20.00

20.00

6.

In design optimization, the excitation frequencies are derived from the modal frequencies computed at each design iteration.

7.

In modal analysis, solutions for modal degrees-of-freedom from rigid body modes at zero excitation frequencies may be discarded. Solutions for non-zero modes are retained.

8.

This card is represented as a loadcollector in HyperMesh.

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FREQ4 Bulk Data Entry FREQ4 – Frequency List, Alternate Form 4 Description Defines a set of frequencies for the modal method of frequency response analysis by specifying the amount of "spread" around each modal frequency and the number of equally spaced frequencies within the spread. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

FREQ4

SID

F1

F2

FSPD

NFM

(8)

(9)

(10)

Example

Define a set of frequencies such that there will be 21 equally spaced frequencies across a frequency band of and 200.

to

for each modal frequency that occurs between 20

(1)

(2)

(3)

(4)

(5)

(6)

FREQ4

6

20.0

200.0

0.30

21

Field

Contents

SID

Set identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) F1

Lower bound of modal frequency range in cycles per unit time. Default = 0.0 (Real > 0.0)

F2

Upper bound of frequency range in cycles per unit time. Default = 1.0E20 (Real > 0.0, F2 > F1)

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OptiStruct 13.0 Reference Guide 1047 Proprietary Information of Altair Engineering

Field

Contents

FSPD

Frequency spread, +/- the fractional amount specified for each mode which occurs in the frequency range F1 to F2. Default = 0.10 (1.0 > Real > 0.0)

NFM

Number of evenly spaced frequencies per "spread" mode. Default = 3 (Integer > 0; If NFM is even, NFM + 1 will be used)

Comments 1.

FREQ4 applies only to the modal method of frequency response analysis.

2.

FREQ4 entries must be selected in the Subcase Information section with FREQUENCY = SID.

3.

There will be NFM excitation frequencies between and , for each modal frequency in the range F1 to F2. If this computation results in excitation frequencies less than F1 and greater than F2, those computed excitation frequencies are ignored.

4.

Excitation frequencies may be based on modal frequencies that are not within the range (F1 and F2) as long as the calculated excitation frequencies are within the range. Similarly, an excitation frequency calculated based on natural frequencies within the range (F1 through F2) may be excluded if it falls outside the range.

5.

The frequency spread can be used also to define the half-power bandwidth. The halfpower bandwidth is given by , where, is the damping ratio. Therefore, if FSPD is specified equal to the damping ratio for the mode, NFM specifies the number of excitation frequencies within the half-power bandwidth.

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6.

Since the forcing frequencies are near structural resonances, it is important that some amount of damping be specified.

7.

All FREQi entries with the same set identification numbers will be used. Duplicate frequencies will be ignored.

and

are considered duplicated if:

where, DFREQ is a user parameter, with a default of 10-5. The values and the maximum and minimum excitation frequencies of the combined FREQi entries.

are

8.

In design optimization, the excitation frequencies are derived from the modal frequencies computed at each design iteration.

9.

In modal analysis, solutions for modal degrees-of-freedom from rigid body modes at zero excitation frequencies may be discarded. Solutions for non-zero modes are retained.

10. This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1049 Proprietary Information of Altair Engineering

FREQ5 Bulk Data Entry FREQ5 – Frequency List, Alternate Form 5 Description Defines a set of frequencies for the modal method of frequency response analysis by specification of a frequency range and fractions of the natural frequencies within that range. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

FREQ5

SID

F1

F2

FR1

FR2

FR3

FR4

FR5

FR6

FR7

etc.

(10)

Example

Define a set of frequencies such that the list of frequencies will be 0.6, 0.8, 0.9, 0.95, 1.0, 1.05, 1.1, and 1.2 times each modal frequency between 20 and 200. (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

FREQ5

6

20.0

200.0

1.0

0.6

0.8

0.9

0.95

1.05

1.1

1.2

Field

Contents

SID

Set identification number.

(10)

No default (Integer > 0) F1

Lower bound of modal frequency range in cycles per unit time. Default = 0.0 (Real > 0.0)

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Field

Contents

F2

Upper bound of frequency range in cycles per unit time. Default = 1.0E20 (Real > 0.0, F2 > F1)

FRi

Fractions of the natural frequencies in the range F1 to F2. No default (Real > 0.0)

Comments 1.

FREQ5 applies only to the modal method frequency response analysis.

2.

FREQ5 entries must be selected in the Subcase Information section with FREQUENCY = SID.

3.

The frequencies defined by this entry are given by where,

are the modal frequencies in the range F1 through F2.

If this computation results in excitation frequencies less than F1 and greater than F2, those computed excitation frequencies are ignored. 4.

Excitation frequencies may be based on natural frequencies that are not within the range (F1 and F2) as long as the calculated excitation frequencies are within the range.

5.

Since the forcing frequencies are near structural resonances, it is important that some amount of damping be specified.

6.

All FREQi entries with the same set identification numbers will be used. Duplicate frequencies will be ignored.

and

are considered duplicated if:

where, DFREQ is a user parameter, with a default of 10-5. The values and the maximum and minimum excitation frequencies of the combined FREQi entries.

are

7.

In design optimization, the excitation frequencies are derived from the modal frequencies computed at each design iteration.

8.

In modal analysis, solutions for modal degrees-of-freedom from rigid body modes at zero excitation frequencies may be discarded. Solutions for non-zero modes are retained.

9.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1051 Proprietary Information of Altair Engineering

GAPPRM Bulk Data Entry GAPPRM – Parameters for Gap Element Connectivity and Configuration Checks Description Defines parameters that control connectivity and configuration checks for gap elements (CGAP and CGAPG). Most of these parameters also affect contact elements that are automatically created on CONTACT interfaces – see individual descriptions for details. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

GAPPRM

PARAM1

VAL1

PARAM2

VAL2

PARAM3

VAL3

PARAM4

VAL4

PARAM5

VAL5

etc.

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

GAPPRM

C KGPDIR

-1

PRTSW

1

C HKRUN

1

Field

Contents

PARAM#

Name of parameter.

VAL#

Value of parameter.

(8)

(9)

(10)

While textual values are recommended for clarity, their integer equivalents will also be read. The available parameters and their values are listed below (click the parameter name for parameter descriptions).

Parameter

Value

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CHKRN

NO, 0, YES, or 1 Default = NO

CKGPDIR

ERR, 2, WARN, 1, NO, 0, REV, or 3 Default = ERR

ERRMSG

SHORT, 1, FULL, or 2 Default = SHORT

GAPCMPL

NO, 0, YES, 1 Default = YES

GAPGPRJ

NORM, 1, SHORT, or 2 Default = SHORT

GAPOFFS

GPCOINC

YES, NO Default = YES Defaults For GAP elements: 1.0e-04 For CONTACT elements: Calculated automatically based on element size on the master face.

HMGAPST

NO, 0 YES, 1 Default = NO

PRTSW

NO, 0, YES, 1 Default = NO

Comments 1.

The GAPPRM entry changes the default settings of control parameters for the gap elements connectivity and checks for configuration errors. None of the parameters of this entry are required.

2.

The gap alignment check controlled by the default value of CKGPDIR = ERR applies correctly to the most typical situations wherein there is an initial opening between bodies A and B, and the gap element is used to enforce non-penetration condition. For cases of overlapping meshes (combined with a prescribed coordinate system), the REV value is appropriate – it allows both aligned and reversed gap directions (respective to the gap axis defined by the prescribed system).

3.

This card is represented as a control card in HyperMesh.

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OptiStruct 13.0 Reference Guide 1053 Proprietary Information of Altair Engineering

GAPPRM, CHKRN Parameter CHKRN

Values

Description

NO, 0, YES, or 1 Default = NO

Stop the run after the gap element checks are completed. If NO or 0, OptiStruct will run to completion unless other errors are present. If YES or 1, OptiStruct will stop after gap and contact elements have been checked.

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GAPPRM, CKGPDIR Parameter CKGPDIR

Values

Description

ERR, 2, WARN, 1, NO, 0, REV, or 3

Controls the checking of gap element alignment in case of prescribed coordinate system CID.

Default = ERR

If ERR or 2, then all non-zero length gap elements that have a prescribed coordinate system are checked for misalignment of the gap prescribed axis (x-axis of the prescribed coordinate system) with the vector GA->B. Angles larger than 30 degrees produce warnings, angles larger than 60 degrees produce errors. If WARN or 1, same as ERR or 2 with the exception that only warnings are issued. If NO or 0, then no gap CID direction checks are performed. If REV or 3, then orientations of the vector GA->B that are generally opposite to the prescribed axis are also accepted. The tolerance levels are the same as for the default case, except that they are measured from either 0 or 180 degrees reference angle.

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GAPPRM, ERRMSG Parameter ERRMSG

Values

Description

SHORT, 1, FULL, or 2

Defines the maximum number of error messages printed for gap and contact elements.

Default = SHORT

If SHORT or 1, then up to 10 error messages are printed along with a summary of the total number of errors. If FULL or 2, then all gap and contact element error messages are printed. Additional diagnostic information for elements with errors is also printed to the .out file.

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GAPPRM, GAPCMPL Parameter GAPCMPL

Values

Description

NO, 0, YES, or 1 Default = YES

This parameter can be used to allow/disallow the inclusion of gap and contact compliance in the calculation of global compliance. If YES or 1, then gap/contact compliances will be included in the calculation of global compliance. If NO or 0, then gap/contact compliances will not be included in the calculation of global compliance. Note: An example situation where the GAPCMPL parameter may be used is described as follows: In some cases, gap/contact elements may exist with initial penetration (U0 0)

GIi/CIi

Grid (or scalar point) and component identification numbers ordered according to stiffness or flexibility values specified after KZmn. For scalar points, CIi is zero. No default (GIi is integer > 0 and CIi is integer > 0).

UD

Flag indicating that the subsequent fields and continuation entries contain values for GDj/CDj until “K”, “Z”, or “S” is specified in field 2 or it is the end of the entry. No default (Character)

GDj/CDj

Grid (or scalar point) and component identification numbers ordered according to the columns in the “S” matrix. No default (GDj is integer > 0 and CDj is integer > 0).

K or Z

Flag indicating that the next fields and continuation entries contain stiffness values until “UD” or “S” is specified in field 2 or it is the end of the entry. No default (Character)

KZmn

Stiffness or flexibility matrix for degrees-of-freedom in GIi/CIi where “m” is

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Field

Contents the row number and “n” is the column number. Only the lower triangular terms in the matrix need to be specified. Zero values must be specified as blank or 0.0. Default = 0.0 (Real)

S

Flag indicating that the subsequent fields and continuation entries contain values for the S matrix. No default (Character)

Sij

“S” matrix values where “i” corresponds to GIi/CIi list and “j” corresponds to GDj/CDj list until “K”, “Z”, or “UD” is specified in field 2 or it is the end of the entry. All the terms in the matrix must be specified and zero values must be specified as blank or 0.0. Default = 0.0 (Real)

Comments 1.

GIi/CIi and KZmn are required inputs. Either “K” or “Z” must be specified, but not both.

2.

“UD”, “K”, “Z”, and “S”, may be specified in any order as demonstrated in the third example.

3.

“UD” and “S” are optional inputs. “S” defines the motion between the GIi/CIi and GDj/CDj degrees-of-freedom according to:

But if “S” is specified then GDj/CDj must also be specified. If “S” is not specified then GDj/CDj may contain six and only six degrees of freedom and they cannot refer to SPOINTs. 4.

If only “K” or “Z” is input without “UD” then it is recommended that the resulting stiffness represents the unsupported element, containing all of the rigid body modes. If not, then the “UD” option allows for the reintroduction of the rigid body modes with “S” which is provided by you or computed internally. a) If “K” and “UD” are specified then the program will form the complete stiffness as defined by the following equation:

Where the K matrix is formed from the KZmn values and the S matrix is formed from the Sij values or computed automatically.

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b) If “Z” and “UD” are specified then the program will form the complete stiffness as defined by the following equation:

Where the Z matrix is formed from the KZmn values and the S matrix is formed from the Sij values or computed automatically. Z must be nonsingular. 5.

PARAM,CK3 may be used to scale the stiffness produced by all GENEL elements.

6.

All lower triangular values in K and Z and all values in S have to be accounted for in the input. Zero values may be specified as 0.0 or be left blank, however if all entries in any continuation line are zero, then at least one visible character must appear on this line (it can be 0.0 in any field or the plus sign (+) in the first column) because blank lines are treated as comment. Unused fields (after the last matrix entry) must be blank.

7.

General elements are ignored in heat transfer analysis.

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GRAV Bulk Data Entry GRAV – Gravity Vector Description Defines the gravity vectors for use in determining gravity loading for the structural model. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

GRAV

SID

C ID

G

N1

N2

N3

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

3

32.2

0.0

0.0

-1.0

GRAV

Field

Contents

SID

Set identification number.

(8)

(9)

(10)

(Integer > 0) CID

Coordinate system identification number. (Integer > 0)

G

Gravity vector scale factor.

N1,N2, N3 Gravity vector components. (Real; at least one non-zero component)

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Comments 1.

The gravity vector is defined by g = G(N1, N2, N3). The direction of G is the direction of free fall. N1, N2, and N3 are in coordinate system CID.

2.

A CID of zero references the basic coordinate system.

3.

This card is represented as a loadcollector in HyperMesh.

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GRDSET Bulk Data Entry GRDSET – Grid Point Default Description Defines default options for fields 3, 7, and 8 of all GRID entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

GRDSET

blank

CP

blank

blank

blank

CD

PS

blank

Example

(1)

(2)

GRDSET

(3)

(4)

16

(5)

(6)

(7)

(8)

32

3456

(9)

Field

Contents

CP

Identification number of coordinate system in which the location of the grid point is defined.

(10)

(Integer > 0 or blank) CD

Identification number of coordinate system in which displacements are measured at grid point. (Integer > 0 or blank)

PS

Permanent single-point constraints associated with grid point (any of the digits 1-6 with no embedded blanks). (Integer > 0 or blank)

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Comments 1.

The contents of fields 3, 7, or 8 of this entry are assumed for the corresponding fields of any GRID entry whose field 3, 7, and 8 are blank. If any of these fields on the GRID entry are blank, the default option defined by this entry occurs for that field. If no permanent single-point constraints are desired or one of the coordinate systems is basic, the default may be overridden on the GRID entry by entering zero in the corresponding field. Only one GRDSET entry may appear in the bulk data section.

2.

The primary purpose of this entry is to minimize the burden of preparing data for problems with a large amount of repetition (for example, two-dimensional pinned-joint problems).

3.

At least one of the entries CP, CD, or PS must be non-zero.

4.

This card is represented as a control card in HyperMesh.

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GRID Bulk Data Entry GRID – Grid Point Description Defines the location of a geometric grid point of the structural model, the directions of its displacement, and its permanent single-point constraints. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

GRID

ID

CP

X1

X2

X3

CD

PS

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

GRID

2

3

1.0

-2.0

3.0

Field

Contents

ID

Unique grid point identification number.

(7)

(8)

(9)

(10)

316

(Integer > 0) CP

Identification number of coordinate system in which the location of the grid point is defined. (Integer > 0 or blank)

X1,X2,X3

Location of the grid point in coordinate system CP. (Real)

CD

Identification number of coordinate system in which the displacements, degrees-of-freedom, constraints, and solution vectors are defined at grid point.

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Field

Contents (Integer > -1 or blank)

PS

Permanent single-point constraints associated with grid point. Up to six unique digits may be placed in the field with no imbedded blanks. (Integer > 0 or blank)

See the GRDSET entry for default options for fields 3, 7, and 8. Comments 1.

All grid point identification numbers must be unique with respect to all other structural grid and scalar points. A duplicate identification number is only allowed if all fields on the duplicated entries are exactly the same, unless PARAM,DUPTOL is used. PARAM,DUPTOL can be used to set a tolerance that will allow a GRID with same ID, CP, CD, and PS to have slightly different coordinates. Refer to Guidelines for Bulk Data Entries.

2.

The meaning of X1, X2, and X3 depends on the type of coordinate system, CP, as follows: (see CORDI entry descriptions). Type

X1

X2

X3

Rectangular

X

Y

Z

Cylindrical

R

q(degrees)

Z

Spherical

R

q(degrees) f(degrees)

3.

The collection of all CD coordinate systems defined on all GRID entries is called the Global Coordinate System. All degrees-of-freedom, constraints, and solution vectors are expressed in the Global Coordinate System.

4.

If CD = -1, then this defines a fluid grid point in the coupled fluid-structural analysis. This type of point may only connect the CHEXA, CPENTA, and CTETRA elements to defined fluid elements.

5.

If CP, PS, or CD is blank, information from the GRDSET data will be used. If CP or CD contains a zero, the basic coordinate system will be used. If PS contains a zero, single point constraints on the GRDSET data are ignored.

6.

Input data replication is available for the GRID data. This can be used to generate additional GRID data, based on incrementing the GRID ID and coordinate locations.

7.

This card is represented as a node in HyperMesh.

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OptiStruct 13.0 Reference Guide 1073 Proprietary Information of Altair Engineering

GRIDS Bulk Data Entry GRIDS – Section Grid Point Description Defines a grid point on the y-z plane, using cartesian coordinates, for use in the definition of arbitrary beam cross-sections. Format (1)

(2)

(3)

(4)

GRIDS

ID

Y

Z

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

GRIDS

101

1.1

2.1

Field

Contents

ID

Identification number.

(5)

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) Y

Y location of the grid point. No default (Real)

Z

Z location of the grid point. No default (Real)

Comments 1.

All grid point identification numbers within a section definition must be unique with respect to all other grid point identification numbers within the same section definition.

2.

This entry is only valid when it appears between the BEGIN and END statements.

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GROUND Bulk Data Entry GROUND – Ground Body Definition for Multi-body Simulation Description Defines a ground body out of a list of finite element properties, elements, and grid points. Format (1)

(2)

GROUND

BID

(3)

(4)

(5)

(6)

(7)

(8)

(9)

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

…

TYPE2

ID1

ID2

TYPE#

…

(10)

BODY_NAME

TYPE1

…

…

Example 1

(1)

(2)

GROUND

3

(3)

(4)

(5)

(7)

(8)

(9)

(10)

SUPPORTING_BEAM

PSHELL

23

21

PBEAM

9

59

48

C ONM2

2345

GRID

400

401

402

Altair Engineering

(6)

OptiStruct 13.0 Reference Guide 1075 Proprietary Information of Altair Engineering

Example 2

(1)

(2)

(3)

GROUND

4

ANC HOR

PBAR

10

(4)

(5)

(6)

(7)

(8)

(9)

11

13

15

22

99

88

(10)

44

Field

Contents

BID

Unique body identification number. No default (Integer > 0)

BODY_NAME

Unique body name. The body name for this PRBODY. Default = OUTFILE_body_ (Character string)

TYPE#

Flag indicating that the following list of IDs refer to entities of this type. All property definitions; CELAS2, CONM2, PLTOEL, RBE2, RBE3, RBAR, RROD, and GRID are valid types for this field. No default (PBAR, PBARL, PBEAM, PBEAML, PBUSH, PCOMP, PDAMP, PELAS, PGAP, PROD, PSHEAR, PSHELL, PSOLID, PVISC, PWELD, CELAS2, CONM2, PLOTEL, RBE2, RBE3, RBAR, RROD, GRID)

ID#

Identification numbers of entities of the preceding TYPE flag. No default (Integer > 0)

Comments 1.

Any number of property definitions; CELAS2, CONM2, PLOTEL, RBAR, RBE2, RBE3, or RROD elements or grid points can be given.

2.

At least one property definition, element, or grid point must be given.

3.

A property definition, CELAS2, CONM2, PLOTEL, RBE2, REB3, RBAR, or RROD element or grid point can only belong to one ground or rigid or flexible body.

4.

The grid ID provided in the ground card is considered grounded.

5.

This card is represented as a group in HyperMesh.

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HYBDAMP Bulk Data Entry HYBDAMP – Apply Hybrid Damping to the Residual Structure in a Direct or Transient Frequency Response Analysis Description This bulk data entry defines the application of modal damping to the residual structure in a direct or transient frequency response analysis. Format (1)

(2)

(3)

(4)

(5)

HYBDAMP

SID

METHOD

SDAMP

KDAMP

(6)

(7)

(8)

(9)

(10)

Field

Contents

HYBDAMP

Keyword for applying modal damping on a direct analysis

SID

Unique hybrid damping SID (Referred to by the HYBDAMP I/O section data).

METHOD

Identification number of EIGRL/EIGRA data. Hybrid damping is applied on the modes determined by the eigenvalue analysis. No default (Integer > 0)

SDAMP

Identification number of TABDMP1 entry for modal damping. No default (Integer > 0)

KDAMP

If KDAMP is set to -1/YES, modal damping is entered into the complex stiffness matrix as material damping, instead of viscous damping. The default is 1/NO to enter the damping as viscous damping. Default = 1 (Integer)

Comments 1.

HYBDAMP SID can be set by the HYBDAMP I/O Options Entry in the I/O section of the input data.

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OptiStruct 13.0 Reference Guide 1077 Proprietary Information of Altair Engineering

2.

Hybrid damping can be defined as shown below: If KDAMP is set to 1/NO (Default), then:

If KDAMP is set to -1/YES, then:

Where, are the modes of the structure [M] is the structural mass matrix b( g(

) are the modal damping values ) are equal to twice the critical damping ratios calculated from the TABDMP1 entry is the natural frequency of mode

mi is the generalized mass of mode

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INCLUDE I/O Options and Bulk Data Entry This bulk data card is identical to the I/O options entry, INCLUDE.

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INSTNCE Bulk Data Entry INSTNCE – Defines part location within the global part Description The INSTNCE bulk data entry can be used to define the location of a part in the global structure. Each INSTNCE entry should reference a unique part name. Format (1)

(2)

(3)

(4)

INSTNC E

ID

name

NN

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

INSTNC E

2

C rankShaft

32

Field

Contents

ID

Set identification number.

(5)

(6)

(7)

(8)

(9)

(10)

(Integer > 0) name

This field specifies the unique name of a part that is to be attached to the global part (see comment 2). It should match the name of one of the parts defined using the BEGIN, FEMODEL, name entry. (Character String)

NN

ID of a RELOC bulk data entry. This field defines the actual location of the part in the final model via the RELOC entry. Default = Blank (Integer > 0)

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Comments 1.

The full model consists of several parts, one part is designated as global and the rest of the parts are attached to the global part using INSTNCE entries. The global part can have an arbitrary name (it is identified by the presence of INSTNCE entries). A minimum of one INSTNCE entry should always be present in the model.

2.

All INSTNCE entries should exist within a global part and no INSTNCE entry can reference the name of a global part on the “name” field.

3.

Each INSTNCE entry should reference a different part name. However, not every part has to be defined using an INSTNCE entry. Such parts are still contained within the full model without any relocation.

4.

A global part can be moved to a different location, however, this is not recommended as it may lead to inaccuracies in locating other parts.

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INVELB Bulk Data Entry INVELB – Initial Velocity of a Body Description Defines initial velocity in a multi-body situation. Format (1)

(2)

(3)

(4)

INVELB

SID

BID

C ID

VX

VY

VZ

(5)

(6)

(7)

WX

WY

WZ

(8)

(9)

(10)

Example

(1)

(2)

(3)

INVELB

1

3

(4)

(5)

(6)

(7)

(8)

(9)

(10)

1000.0

Field

Contents

SID

Load set identification number. (Integer > 0)

BID

Body identification number. (Integer > 0)

CID

Reference coordinate system. (Integer > 0)

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Field

Contents

VX, VY, VZ

Translational velocities. (Blank or Real)

WX, WY, WZ Rotational velocities. (Blank or Real) Comments 1.

Only one initial velocity per body can be defined in a load set.

2.

A CID of zero or blank references the basic coordinate system.

3.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1083 Proprietary Information of Altair Engineering

INVELJ Bulk Data Entry INVELJ – Initial Velocity of a Joint Description Defines initial velocity of a joint in a multi-body situation. Format (1)

(2)

(3)

(4)

(5)

(6)

INVELJ

SID

JID

JTYPE

VT

VR

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

INVELJ

1

3

REV

(5)

Field

Contents

SID

Load set identification number.

(6)

(7)

(8)

(9)

(10)

10.0

(Integer > 0) JID

Joint identification number. (Integer > 0)

JTYPE

Joint type. Options = ("REV", "CYL", or "TRANS") No default

VT

Translational velocity If JTYPE = TRANS, VT must be real.

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Field

Contents

VR

Rotational velocity If JTYPE = REV, VR must be real.

Comments 1.

Only one initial velocity per joint can be defined in a load set.

2.

Initial velocities of joints defined by INVELJ will be overwritten by MOTNJ, MOTNJE, or MOTNJC.

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JOINT Bulk Data Entry JOINT – Joint Definition for Multi-body Solution Sequence Description Defines a joint. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

JOINT

JID

JTYPE

G1

G2

X3, G3

Y3

Z3

blank

X4, G4

Y4

Z4

Example 1

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

JOINT

3

BALL

345

231

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

JOINT

4

UNIV

456

899

0.0

0.0

1.0

Example 2

399

Field

Contents

JID

Unique joint identification number. (Integer > 0)

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Field

Contents

JTYPE

Joint type (BALL, FIX, REV, TRANS, CYL, UNIV, CV, PLANAR, INLINE, PERP, PARA, INPLANE, or ORIENT).

G1, G2

Geometric grid point identification number. Used to identify the bodies to be connected and, for many JTYPEs, the location of the joint. (Integer > 0)

X3, Y3, Z3

First orientation vector of the joint. (Real)

G3

Grid point identification number to optionally supply X3, Y3, Z3 in conjunction with either G1 or G2 (depending on the JTYPE). (Integer > 0)

X4, Y4, Z4

Second orientation vector of the joint. (Real)

G4

Grid point identification number to optionally supply X4, Y4, Z4 in conjunction with G2. (Integer > 0)

Comments 1.

Joints are only valid in a multi-body solution sequence.

2.

G1 and G2 identify the bodies being joined and must, therefore, belong to different bodies.

3.

Definition of the different joint types: Joint Type

Description

Ball

Fixed

Required Fields

Joint Orientation

All translations are BALL fixed; all rotations are free.

G1, G2

·

G1 and G2 must coincide.

All translations

G1, G2

·

G1 and G2 must

Altair Engineering

JTYPE

FIX

OptiStruct 13.0 Reference Guide 1087 Proprietary Information of Altair Engineering

Joint Type

Description

JTYPE

Required Fields

Joint Orientation

and rotations are fixed. Revolute

Translational

Cylindrical

Universal

coincide.

Rotation about a single selected axis is free; other rotations and translations are fixed.

REV

Translation along a single selected axis is free; other translations and rotations are fixed.

TRANS

Translation along and rotation about a single selected axis is free; other translations and rotations are fixed.

CYL

Rotations about UNIV two selected perpendicular axes are free; translations and other rotations are fixed.

G1, G2, and either X3, Y3, Z3 or G3

·

G1, G2, and either X3, Y3, Z3 or G3

·

G1, G2, and either X3, Y3, Z3 or G3

·

G1, G2, and either X3, Y3, Z3 or G3 and either X4, Y4, Z4 or G4

·

·

·

·

·

·

·

Constant Vel Rotations about CV two selected axes are equal and opposite;

G1, G2, and either X3, Y3, Z3 or G3 and

· ·

G1 and G2 must coincide. The selected axis is defined by the vector X3, Y3, Z3 or alternatively the vector from G1 to G3. G1 and G2 must be along the joint axis. The selected axis is defined by the vector X3, Y3, Z3 or alternatively the vector from G1 to G3. G1 and G2 must be along the joint axis. The selected axis is defined by the vector X3, Y3, Z3 or alternatively the vector from G1 to G3.

G1 and G2 must coincide. The first selected (cross pin) axis is defined by the vector X3, Y3, Z3 or alternatively the vector from G1 to G3. The second selected (cross pin) axis is defined by the vector X4, Y4, Z4 or alternatively the vector from G2 to G4. The selected axes must be perpendicular. G1 and G2 must coincide. The first selected axis is defined by the vector X3, Y3, Z3 or

1088 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Joint Type

Description

JTYPE

Required Fields

Joint Orientation

translations and other rotations are fixed.

either X4, Y4, Z4 or G4

Translations on a PLANAR plane defined by a selected normal vector and the rotation about that normal vector are free, out-of-plane translations and rotations are fixed.

G1, G2, and either X3, Y3, Z3 or G3

·

Translation along INLINE a single selected axis and all rotations are free; other translations are fixed.

G1, G2, and either X3, Y3, Z3 or G3

·

Perpendicular Two perpendicular PERP axes are selected that are always to remain perpendicular. Therefore, rotations about both selected axes and all translations are free. Rotation about the crossproduct of the two selected vectors is fixed.

G1,G2 and either X3, Y3, Z3 or G3 and either X4, Y4, Z4 or G4

·

Parallel Axes

G1,G2 and either X3, Y3,

Planar

Inline

Two parallel axes are selected that are always to

Altair Engineering

PARA

·

·

·

·

·

·

alternatively the vector from G1 to G3. The second selected axis is defined by the vector X4, Y4, Z4 or alternatively the vector from G2 to G4. G1 and G2 must be in the joint plane. The vector X3, Y3, Z3 or the vector from G1 to G3 will define the normal to the plane.

G1 and G2 must be along the joint axis. The selected axis is defined by the vector X3, Y3, Z3 or alternatively the vector from G2 to G3. The first selected axis is defined by the vector X3, Y3, Z3 or alternatively the vector from G1 to G3. The second selected axis is defined by the vector X4, Y4, Z4 or alternatively the vector from G2 to G4. The selected vectors must be perpendicular to one another.

The first selected axis is defined by the vector X3, Y3, Z3 or alternatively the vector from G1 to

OptiStruct 13.0 Reference Guide 1089 Proprietary Information of Altair Engineering

Joint Type

Inplane

Description

JTYPE

Required Fields

remain parallel. Therefore, rotations about the selected parallel axes and all translations are free; other rotations are fixed.

Z3 or G3 and either X4, Y4, Z4 or G4

Two perpendicular INPLANE vectors are selected that describe a plane. Out-of-plane translations are fixed; all other translations and rotations are free.

G1,G2 and either X3, Y3, Z3 or G3 and either X4, Y4, Z4 or G4

Joint Orientation

·

·

·

·

·

Orient

4.

All rotations are fixed; all translations are free.

ORIENT

G3. The second selected axis is defined by the vector X4, Y4, Z4 or alternatively the vector from G2 to G4. The selected vectors must be parallel to one another. The first selected vector is defined by X3, Y3, Z3 or alternatively the vector from G2 to G3. The second selected vector is defined by X4, Y4, Z4 or alternatively the vector from G2 to G4. The selected vectors must be perpendicular to one another.

G1,G2

This card is represented as a joint element in HyperMesh.

1090 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

JOINTM Bulk Data Entry JOINTM – Joint Definition for Multi-body Solution Sequence using Marker Description Defines a joint using two grids which have a marker card associated with them. Format (1)

(2)

(3)

(4)

(5)

JOINTM

JID

JTYPE

M1

M2

(6)

(7)

(8)

(9)

(10)

Example 1

(1)

(2)

(3)

(4)

(5)

JOINTM

3

BALL

345

231

(1)

(2)

(3)

(4)

(5)

JOINTM

4

UNIV

456

899

(6)

(7)

(8)

(9)

(10)

(6)

(7)

(8)

(9)

(10)

Example 2

Field

Contents

JID

Unique joint identification number. (Integer > 0)

JTYPE

Joint type (BALL, FIX, REV, TRANS, CYL, UNIV, CV, PLANAR, INLINE, PERP, PARA, INPLANE, or ORIENT)

Altair Engineering

OptiStruct 13.0 Reference Guide 1091 Proprietary Information of Altair Engineering

Field

Contents

M1, M2

Marker identification numbers. (Integer > 0)

Comments 1.

Joints are only valid in a multi-body solution sequence.

2.

M1 and M2 must belong to different bodies and must have a marker card associated with them.

3.

Definition of the different joint types: Joint Type

JTYPE

Definition

Joint Orientation

Ball

BALL

M1, M2

·

M1, M2 must coincide.

Fixed

FIX

M1, M2

·

M1, M2 must coincide.

Revolute

REV

M1, M2

· ·

M1, M2 must coincide. The joint axis will be along the Z-axis of marker M1.

Translational

TRANS

M1, M2

·

M1, M2 must be along the joint axis. The joint axis will be along the Z-axis of marker M1.

·

Cylindrical

CYL

M1, M2

·

M1, M2 must be along the joint axis.

Universal

UNIV

M1, M2

·

M1, M2 must coincide.

Constant Velocity

CV

M1, M2

·

M1, M2 must coincide.

Planar

PLANAR

M1, M2

·

M1, M2 must be in the joint plane.

Inline

INLINE

M1, M2

Perpendicular

PERP

M1, M2

Parallel Axes

PARA

M1, M2

Inplane

INPLANE

M1, M2

1092 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Joint Type

JTYPE

Definition

Joint Orientation

Orient

ORIENT

M1, M2

No relative rotation.

Altair Engineering

OptiStruct 13.0 Reference Guide 1093 Proprietary Information of Altair Engineering

LINE Bulk Data Entry LINE – Line Definition Description Definition of a line. Format (1)

(2)

(3)

(4)

LINE

LINEID

EDGE

GA1

GB1

GA2

GB2

GA3

GB3

...

...

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

LINE

100

EDGE

33

34

34

35

35

36

(4)

(5)

(6)

(7)

(8)

1094 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(9)

(10)

Altair Engineering

Alternate Format In this format, line is represented as collection of 1-D, 2-D or 3-D elements. (1)

(2)

(3)

LINE

LINEID

ELEDGE

EID1

EID2

EID9

(4)

(5)

(6)

(7)

(8)

(9)

EID3

EID4

EID5

EID6

EID7

EID8

(10)

-etc-

Alternate Format (SET) In this format, a line is defined by a SET of elements. With this approach, the line is composed of all the edges of all selected 1-D, 2-D or 3-D elements in the SET. (1)

(2)

(3)

(4)

LINE

LINEID

SET

SID

(5)

(6)

(7)

Field

Contents

LINEID

Non-unique identification number of LINE.

(8)

(9)

(10)

No default (Integer > 0) EDGE

Flag indicating that a line is defined by two grids.

GA#

Grid point identification number of first grid A. No default (Integer > 0)

GB#

Grid point identification number of second grid B. No default (Integer > 0)

ELEDGE

Flag indicating that the line is composed of elements.

EID#

Element identification number. No default (Integer > 0)

SET

Flag indicating that the line is defined by a SET of elements.

Altair Engineering

OptiStruct 13.0 Reference Guide 1095 Proprietary Information of Altair Engineering

Field

Contents

SID

Set identification number. No default (Integer > 0)

Comments 1.

LINEID is not unique, multiple LINE cards with the same LINEID compose a line group.

2.

GA and GB should be two different grids.

3.

All nodes must belong to a shell, solid, truss or beam element.

4.

This card is represented as a contactsurf in HyperMesh.

1096 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

LOAD Bulk Data Entry LOAD – Static Load Combination (Superposition) Description Defines a static load as a linear combination of load sets defined via FORCE, MOMENT, FORCE1, MOMENT1, PLOAD, PLOAD1, PLOAD2, PLOAD4, RFORCE, DAREA and GRAV entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

LOAD

SID

S

S1

L1

S2

L2

S3

L3

S4

L4

(10)

-etc-

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

LOAD

101

-0.5

1.0

3

6.2

4

Field

Contents

SID

Load set identification number.

(8)

(9)

(10)

(Integer > 0) S

Scale factor. (Real)

Si

Scale factors. (Real)

Li

Load set identification numbers defined via entry typed enumerated above. (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1097 Proprietary Information of Altair Engineering

Comments 1.

The load vector defined is given by

2.

The Li must be unique.

3.

All data after the first blank field is ignored.

4.

Load sets must be selected in the Subcase Information section (LOAD=SID) if they are to be applied to the structural model.

5.

A LOAD entry may not reference a set identification number defined by another LOAD entry.

6.

SPCD load SIDs cannot be referenced by LOAD data.

7.

This card is represented as a loadcollector in HyperMesh.

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LOADADD Bulk Data Entry LOADADD – Static Load Combination (Superposition) Description Defines a static load as a linear combination of load sets defined via FORCE, MOMENT, FORCE1, MOMENT1, PLOAD, PLOAD1, PLOAD2, PLOAD4, RFORCE, DAREA, and GRAV entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

LOADADD

SID

S

S1

L1

S2

L2

S3

L3

S4

L4

(10)

-etc-

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

LOADADD

101

-0.5

1.0

3

6.2

4

Field

Contents

SID

Load set identification number.

(8)

(9)

(10)

(Integer > 0) S

Scale factor (See comment 1). (Real)

Si

Scale factors (See comment 1). (Real)

Li

Load set identification numbers defined via entry typed enumerated above

Altair Engineering

OptiStruct 13.0 Reference Guide 1099 Proprietary Information of Altair Engineering

Field

Contents (See comment 1). (Integer > 0)

Comments 1.

The load vector defined is given by:

r P

S

i

r Si PLi

Where,

r P is the static load as a linear combination of the defined load sets. S is the scale factor defined in Field 3.

Si

r PLi

are the scale factors defined in the S1, S2,…, Sn fields. are the loads, whose id’s, are referenced by the L1, L2,…, Ln fields.

2.

The Load Set identification numbers (Li) must be unique.

3.

All data after the first blank field is ignored.

4.

Load sets must be selected in the Subcase Information section (LOAD=SID) if they are to be applied to the structural model.

5.

A LOADADD entry may not reference a set identification number defined by another LOADADD entry.

6.

Only a single thermal load can be referenced by the LOADADD data.

7.

SPCD load SIDs cannot be referenced by LOADADD data.

8.

This card is represented as a loadcollector in HyperMesh.

1100 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MARKER Bulk Data Entry MARKER – Define a Marker by Associating a Grid and a Coordinate System Description Define a marker by associating a grid and a coordinate system. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

MARKER

MID1

GID1

C ID1

MID2

GID2

C ID2

MID3

GID3

C ID3

…

…

…

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

MARKER

3

345

123

Field

Contents

MIDi

Marker identification number.

(5)

(6)

(7)

(8)

(9)

(10)

(Integer > 0) GIDi

Grid identification number. (Integer > 0)

CIDi

Coordinate system identification number. (Integer > 0 or blank) Default (Blank, defaults to basic coordinate system)

Altair Engineering

OptiStruct 13.0 Reference Guide 1101 Proprietary Information of Altair Engineering

Comments 1.

Each marker has a unique ID. The marker gets its location from the grid corresponding to the GID and the orientation from the coordinate system (CID).

2.

Multiple markers can be located at the same grid with the same or with a different CID.

3.

This card is represented as a sensor in HyperMesh.

1102 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MAT1 Bulk Data Entry MAT1 – Material Property Definition, Form 1 Description Defines the material properties for linear, temperature-independent, and isotropic materials. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MAT1

MID

E

G

NU

RHO

A

TREF

GE

ST

SC

SS

(10)

Example

(1)

(2)

(3)

MAT1

17

3.+7

(4)

(5)

(6)

0.33

4.28

Field

Contents

MID

Unique material identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) E

Young’s Modulus. Default = blank (Real or blank)

G

Shear Modulus. Default = blank (Real or blank)

NU

Poisson’s Ratio. Default = blank (-1.0 < Real < 0.5 or blank)

Altair Engineering

OptiStruct 13.0 Reference Guide 1103 Proprietary Information of Altair Engineering

Field

Contents

RHO

Mass density. No default (Real)

A

Thermal expansion coefficient. No default (Real)

TREF

Reference temperature for thermal loading. Default = 0.0 (Real)

GE

Structural Element Damping coefficient. See comments 11 and 12. No default (Real)

ST, SC, SS Stress limits in tension, compression and shear. Used for composite ply failure calculations No default (Real) Comments 1.

The material identification number must be unique for all MAT1, MAT2, MAT8 and MAT9 entries.

2.

The mass density, RHO, is used to automatically compute mass for all structural elements.

3.

Either E or G must be specified (that is, nonblank).

4.

If any one of E, G, or NU is blank, it is computed to satisfy the identity E = 2(1+NU)G; otherwise, values supplied by you are used.

5.

If E and NU are both blank, they are both given the value 0.0.

6.

If G and NU are both blank, they are both given the value 0.0.

7.

Implausible data on one or more MAT1 entries result in a warning message. Implausible data is defined as: E < 0.0 or G < 0.0 or NU > 0.5 or NU < -1.0 or

1104 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

except for cases covered by comments 5 and 6. 8.

It is strongly recommended that only two of the three values E, G, and NU be input.

9.

A warning is issued if NU < 0.0.

10. The large field format may also be used. 11. To obtain the damping coefficient GE, multiply the critical damping ratio, C/C0 by 2.0. 12. TREF and GE are ignored if a MAT1 entry is referenced by a PCOMP entry. 13. This card is represented as a material in HyperMesh. Element Type

E

NU

G

CROD, CBAR, CBEAM, and CWELD

Axial and Bending

N/A

Transverse Shear and Torsion

CSHEAR

N/A

N/A

Shear

CQUAD and CTRIA

Membrane Membrane and Bending and Bending

Transverse Shear

CHEX, CTETRA, CPENTA, CPRYRA and CSEAM

Deformation

N/A

Altair Engineering

OptiStruct 13.0 Reference Guide 1105 Proprietary Information of Altair Engineering

MAT2 Bulk Data Entry MAT2 – Material Property Definition, Form 2 Description Defines the material properties for linear, temperature-independent, anisotropic materials for two-dimensional elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MAT2

MID

G11

G12

G13

G22

G23

G33

RHO

A1

A2

A12

TREF

GE

ST

SC

SS

Example

(1)

(2)

(3)

MAT2

13

6.2+3

6.5-6

6.5-6

(4)

(5)

(6) 6.2+3

(7)

(8)

(9)

5.1+3

0.056

(10)

-500.0

Field

Contents

MID

Unique material identification number. No default (Integer > 0)

Gij

The material property matrix. No default (Real)

RHO

Mass density. No default (Real)

1106 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

Ai

Thermal expansion coefficient vector. No default (Real)

TREF

Reference temperature for the calculation of thermal loads. See comment 6. Default = blank (Real or blank)

GE

Structural Element Damping Coefficient. See comments 7 and 8. No default (Real)

ST, SC, SS Stress limits in tension, compression and shear. Used for composite ply failure calculations. No default (Real) Comments 1.

The material identification number must be unique for all MAT1, MAT2, MAT8 and MAT9 entries.

2.

The mass density, RHO, is used to automatically compute mass for all structural elements.

3.

The convention for the Gij in fields 3 through 8 are represented by the matrix relationship:

4.

If this entry is referenced by the MID3 field (transverse shear) on the PSHELL, G13, G23, and G33 must be blank.

5.

Unlike the MAT1 entry, data from the MAT2 entry is used directly, without adjustment of equivalent E, G, or NU values.

6.

TREF is used as the reference temperature for the calculation of thermal loads.

7.

The long field format may be used.

8.

To obtain the damping coefficient GE, multiply the critical damping ratio, C/C0, by 2.0.

9.

TREF and GE are ignored if a MAT 2 entry is referenced by a PCOMP entry.

Altair Engineering

OptiStruct 13.0 Reference Guide 1107 Proprietary Information of Altair Engineering

10. If a MAT2 card is pointed to by a MID4 on PSHELL, and has a material ID greater than 400,000,000, then the thermal membrane-bending coefficients A1, A2, and A12 have a modified interpretation, and represent [G]*[alpha] rather then [alpha]. Here, [G] is a matrix composed of G11, G22 …G33. This is to maintain consistency with respective terms generated internally by the PCOMP card. 11. This card is represented as a material in HyperMesh.

1108 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MAT3 Bulk Data Entry MAT3 – Material Property Definition, Form 3 Description Defines the material properties for linear, temperature-independent, and orthotropic materials used by the CTAXI and CTRIAX6 axisymmetric elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MAT3

MID

EX

ETH

EZ

NUXTH

NUTHZ

NUZX

RHO

GZX

AX

ATH

AZ

TREF

GE

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MAT3

17

3.0+7

3.1+7

3.2+7

0.33

0.28

0.30

2.0e-5

7.0+6

1.1e-4

1.1e-4

1.2e-4

35.5

0.19

Field

Contents

MID

Unique material identification number.

(10)

No default (Integer > 0) EX, ETH, EZ

Young’s Moduli in the x, θ and z directions, respectively. No default (Real > 0.0)

NUXTH, NUTHZ, NUZX

Poisson’s Ratios: NUXTH = Poisson’s Ratio for strain in the θ direction when stress in the x

Altair Engineering

OptiStruct 13.0 Reference Guide 1109 Proprietary Information of Altair Engineering

Field

Contents direction. NUTHZ = Poisson’s Ratio for strain in the z direction when stress in the θ direction. NUZX = Poisson’s Ratio for strain in the x direction when stress in the z direction. No default (Real)

RHO

Mass density. No default (Real)

GZX

Shear Modulus in the x-z plane. No default (Real > 0.0)

AX, ATH, AZ

Thermal expansion coefficient in the x, θ, and z directions, respectively. No default (Real)

TREF

Reference temperature for thermal loading. Default = blank (Real or blank)

GE

Structural Element Damping coefficient. See comment 6. No default (Real)

Comments 1.

The material identification number must be unique for all MAT1, MAT2, MAT8 and MAT9 entries.

2.

Values of all seven elastic constants, EX, ETH, EZ, NUXTH, NUTHZ, NUZX and GZX must be present.

3.

A warning is issued if absolute value of NUXTH or NUTHZ is greater than 1.0.

4.

The x, θ and z directions are principal material directions of the material coordinate system. Each element (that is a CTAXI or CTRIAX6 element) supporting the use of MAT3 contains a “Theta” field to relate the principal material directions to the basic coordinate system.

5.

The strain-stress relationship is:

1110 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Note that the strain and stress here are both defined in the material coordinate system. 6.

To obtain the damping coefficient GE, multiply the critical damping ratio, C/C0, by 2.0.

7.

This card is represented as a material in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1111 Proprietary Information of Altair Engineering

MAT4 Bulk Data Entry MAT4 – Material Property Definition, Form 4 Description Defines constant thermal material properties for conductivity, density, and heat generation. Format (1)

(2)

(3)

(4)

(5)

(6)

MAT4

MID

K

CP

RHO

H

(7)

(8)

(9)

(10)

HGEN

Example

(1)

(2)

(3)

MAT4

24

200

(4)

Field

Contents

MID

Material identification number.

(5)

(6)

(7)

(8)

(9)

(10)

2e5

No default (Integer > 0) K

Thermal conductivity. Default = 0.0 (Real > 0.0)

CP

Heat capacity per unit mass (specific heat). (Real > 0.0 or blank)

RHO

Density. Default = 1.0 (Real > 0.0)

H

Free convection heat transfer coefficient. Default = 0.0 (Real)

1112 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Field

Contents

HGEN

Heat generation capability used with QVOL entries. HGEN is the scale factor used with QVOL (See comment 3). Default = 1.0 (Real > 0.0)

Comments 1.

The material identification number may be the shared with structural material property definitions (MAT1, MAT2, MAT8, MAT9 or MGASK) but must be unique with respect to other thermal material property definitions (MAT4 or MAT5).

2.

MAT4 may specify material properties for any conduction elements. MAT4 also provides the heat transfer coefficient for free convection (see CONV).

3.

HGEN is the scale factor and QVOL is the power generated per unit volume, Pin = volume *

HGEN * QVOL. 4.

This card is represented as a material in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1113 Proprietary Information of Altair Engineering

MAT5 Bulk Data Entry MAT5 – Material Property Definition, Form 5 Description Defines the thermal material properties for anisotropic materials. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MAT5

MID

KXX

KXY

KXZ

KYY

KYZ

KZZ

CP

RHO

HGEN

(10)

Example

(1)

(2)

(3)

MAT5

2

.300

(4)

(5)

(6)

(7)

100

(8)

(9)

(10)

200

2e5

Field

Contents

MID

Material identification number. No default (Integer > 0)

Kij

Thermal conductivity. Default = 0.0 (Real)

CP

Heat capacity per unit mass (specific heat). (Real > 0.0 or blank)

RHO

Density. Default = 1.0 (Real > 0.0)

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Field

Contents

HGEN

Heat generation capability used with QVOL entries. HGEN is the scale factor used with QVOL (See comment 3). Default = 1.0 (Real > 0.0)

Comments 1.

The material identification number may be the shared with structural material property definitions (MAT1, MAT2, MAT8, MAT9 or MGASK), but must be unique with respect to other thermal material property definitions (MAT4 or MAT5).

2.

The thermal conductivity matrix has the following form:

3.

HGEN is the scale factor and QVOL is the power generated per unit volume, Pin = volume *

HGEN * QVOL. 4.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1115 Proprietary Information of Altair Engineering

MAT8 Bulk Data Entry MAT8 – Material Property Definition, Form 8 Description Defines the material properties for linear temperature-independent orthotropic material for two-dimensional elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MAT8

MID

E1

E2

NU12

G12

G1,Z

G2,Z

RHO

A1

A2

TREF

Xt

Xc

Yt

Yc

S

GE

F12

STRN

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MAT8

171

30.+6

1.+6

0.3

2.+6

3.+6

1.5+6

0.056

28.-6

1.5-6

155.0

Field

Contents

MID

Material ID.

(10)

No default (Integer > 0) E1

Modulus of elasticity in longitudinal direction (also defined as fibre direction or 1direction) (See comment 8)

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Field

Contents

E2

Modulus of elasticity in lateral direction (also defined as matrix direction or 2direction) (See comment 8).

NU12 Poisson’s ratio (

for uniaxial loading in 1-direction). Note that

uniaxial loading in 2-direction is related to

for

by the relation

. No default (Real) G12

Inplane shear modulus. No default (Real > 0.0)

G1,Z

Transverse shear modulus for shear in 1-Z plane. Default = blank (Real > 0.0 or blank)

G2,Z

Transverse shear modulus for shear in 2-Z plane. Default = blank (Real > 0.0 or blank)

RHO

Mass density. No default (Real)

A1

Thermal expansion coefficient in 1-direction. No default (Real)

A2

Thermal expansion coefficient in 2-direction. No default (Real)

TREF

Reference temperature for the calculation of thermal loads. See comment 3. Default = blank (Real or blank)

Xt, Xc, Yt, Yc

Allowable stresses or strains in the longitudinal and lateral directions. Used for composite ply failure calculations.

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OptiStruct 13.0 Reference Guide 1117 Proprietary Information of Altair Engineering

Field

Contents No default (Real > 0.0)

S

Allowable for in-plane shear for composite ply failure calculations. No default (Real > 0.0)

GE

Structural Element Damping Coefficient. See comment 6. No default (Real)

F12

Tsai-Wu interaction term for composite failure. No default (Real)

STRN

Indicates whether Xt, Xc, Yt, or Yc are stress or strain allowables. Default = blank (Real = 1.0 for strain allowables, blank for stress allowables)

Comments 1.

The material identification number must be unique for all MAT1, MAT2, MAT8 and MAT9 entries.

2.

If G1, Z and G2, Z values are specified as zero or are not supplied, a penalty term is used to enforce very high transverse shear stiffness.

3.

An approximate value for G1, Z and G2, Z is the inplane shear modulus G12. If test data not available to accurately determine G1, Z and G2, Z for the material and transverse shear calculations, the value of G12 may be supplied for G1, Z and G2, Z.

4.

TREF is used as the reference temperature for calculations of thermal loads.

5.

Long field format can be used.

6.

TREF and GE are ignored if a MAT8 entry is referenced by a PCOMP entry.

7.

The option of interpreting Xt, Xc, Yt, and Yc as strains is only available for composite definitions (PCOMP or PCOMPG) using the STRN failure criterion. In this case, the STRN flag indicates whether Xt, Xc, Yt, and Yc are stress or strain allowables. For all other failure criteria Xt, Xc, Yt, and Yc are always interpreted as stresses, regardless of the value of the STRN flag.

8.

The value of E1 should be greater than that of E2 for the material to be stable. If E1 < E2, then the material matrix becomes indefinite leading to an unstable material.

9.

This card is represented as a material in HyperMesh.

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MAT9 Bulk Data Entry MAT9 – Material Property Definition, Form 9 Description Defines the material properties for linear, temperature-independent, and anisotropic materials for solid elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MAT9

MID

G11

G12

G13

G14

G15

G16

G22

G23

G24

G25

G26

G33

G34

G35

G36

G44

G45

G46

G55

G56

G66

RHO

A1

A2

A3

A4

A5

A6

TREF

GE

(10)

Example

(1)

(2)

(3)

MAT9

17

6.2+3

(4)

(5)

(6)

(7)

(8)

(9)

(10)

6.2+3

6.2+3

5.1+3

5.1+3

6.5-6

3.2

6.5 - 6

125.

Field

Contents

MID

Unique material identification number.

Altair Engineering

5.1 + 3

OptiStruct 13.0 Reference Guide 1119 Proprietary Information of Altair Engineering

Field

Contents No default (Integer > 0)

Gij

The material property matrix. No default (Real)

RHO

Mass density. No default (Real)

Ai

Thermal expansion coefficient vector. No default (Real)

TREF

Reference temperature for the calculation of thermal loads. See comment 6. Default = blank (Real or blank)

GE

Structural Element Damping Coefficient. See comment 9. No default (Real)

Comments 1.

The material identification number must be unique for all MAT1, MAT2, MAT8, MAT9ORT and MAT9 entries.

2.

The mass density, RHO, is used to automatically compute mass for all structural elements.

3.

The convention for the Gij in fields 3 through 8 are represented by the matrix relationship.

The subscripts 1 to 6 refer to x, y, z, xy, yz, and zx of the material coordinate system defined by the CORDM field on the PSOLID entry. 4.

Unlike the MAT1 entry, data from the MAT9 entry is used directly, without adjustment of equivalent E, G, or NU values.

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5.

If material data is to specified with the Engineering Constants E1, E2, E3, NU12, NU13, NU23, G12, G23, and G13, then use the MAT9ORT data.

6.

TREF is used as the reference temperature for the calculation of thermal loads.

7.

The last continuation is optional.

8.

Long field format can be used.

9.

To obtain the damping coefficient GE, multiply the critical damping ratio, C/C0, by 2.0.

10. This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1121 Proprietary Information of Altair Engineering

MAT9ORT Bulk Data Entry MAT9ORT – Material Property Definition, Form 9-Orthotropic Description Defines the material properties for linear, temperature-independent, and orthotropic materials for solid elements in terms of engineering constants. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MAT9ORT

MID

E1

E2

E3

NU12

NU23

NU31

RHO

G12

G23

G31

A1

A2

A3

TREF

GE

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MAT9ORT

21

1e6

1e3

1e3

0.1

0.1

1e3

1e3

1e-6

1e-6

1e-6

(8)

(9)

(10)

1e5

Field

Contents

MID

Material identification number. Must be unique with respect to other MAT1, MAT2, MAT8, MAT9, and MAT9ORT definitions No default (Integer > 0)

E1

Elastic modulus in 1-direction. No default (Real)

E2

Elastic modulus in 2-direction. No default (Real)

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Field

Contents

E3

Elastic modulus in 3-direction. No default (Real)

NU12

Poisson’s ratio for uniaxial loading in 1-direction. See comment 3. No default (Real)

NU23

Poisson’s ratio for uniaxial loading in 2-direction. See comment 3. No default (Real)

NU31

Poisson’s ratio for uniaxial loading in 3-direction. See comment 3. Default = NU23 (Real)

RHO

Mass density. No default (Real)

G12

Shear modulus on plane 1-2.

G23

Shear modulus on plane 2-3.

G31

Shear modulus on plane 3-1.

Ai

Coefficient of thermal expansion in the i-direction Default =0.0 (Real)

TREF

Reference temperature for the calculation of thermal loads. See comment 5. Default = blank (Real or blank)

GE

Structural Element Damping Coefficient. See comment 6. Default = 0.0 (Real)

Comments 1.

This input definition is internally converted to an equivalent MAT9 definition on reading (See comment 7). This is reflected in echoed (ECHO) input data and all messaging.

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OptiStruct 13.0 Reference Guide 1123 Proprietary Information of Altair Engineering

2.

The material identification number must be unique for all MAT1, MAT2, MAT8, MAT9 and MAT9ORT entries.

3.

In general,

is not the same as

, but they are related by

.

Furthermore, material stability requires that:

and

4.

It may be difficult to find all nine orthotropic constants. In some practical problems, the material properties may be reduced to normal anisotropy in which the material is isotropic in a plane (for example, plane 1-2), and has different properties in the direction normal to this plane. In the plane of isotropy, the properties are reduced to:

with

and

There are five independent material constants for normal anisotropy . In case the material has a planar anisotropy, in which the material is orthotropic only in a plane, the elastic constants are reduced to seven

.

5.

TREF is used as the reference temperature for the calculation of thermal loads.

6.

To obtain the damping coefficient GE, multiply the critical damping ratio, C/C0 by 2.0.

7.

Internal conversion from MAT9ORT to MAT9. The material property fields of the MAT9 entry are calculated internally from the MAT9ORT entry using the following formula:

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Where,

The values of , E and G for the expressions in the above equations in comment 7 are taken from the NUij , Ei and Gij fields respectively of this MAT9ORT entry where i, j € {1,2,3} and the values of (see above equations in comment 7) are used to populate the G11, G22, G33, G44, G55, G66, G12, G13, and G23 fields (G12=G21, G13=G31 and G23=G32 due to symmetry) of the MAT9 entry. The remaining elements of the MAT9 entry (that is G14, G15, G24, and so on) are equal to zero.

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OptiStruct 13.0 Reference Guide 1125 Proprietary Information of Altair Engineering

MAT10 Bulk Data Entry MAT10 – Material Property Definition, Form 10 Description Defines material properties for fluid elements in coupled fluid-structural analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MAT10

MID

BULK

RHO

C

GE

ALPHA

(9)

(10)

Example

(1)

(2)

(3)

(4)

MAT10

2

0.5

22.1

(5)

Field

Contents

MID

Material identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) BULK

Bulk modulus. No default (Real > 0.0)

RHO

Mass density. No default (Real > 0.0)

C

Speed of sound. No default (Real > 0.0)

GE

Fluid element damping coefficient. No default (Real)

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Field ALPHA

Contents Normalized porous material damping coefficient. See comment 6. No default (Real)

Comments 1.

MAT10 may be referenced by PSOLID entries with FCTN=’PFLUID’.

2.

The material identification number must be unique with respect to MAT1, MAT2, MAT3, MAT9, and MAT10 entries, but may be shared with MAT4, MAT5 or MATFAT.

3.

The mass density RHO will be used to compute the mass automatically.

4.

BULK, RHO, and C are related by BULK = C2 * RHO. Two out of the three must be specified, and the other will be calculated according to this equation.

5.

To obtain the damping coefficient GE, multiply the critical damping ratio C/C0 by 2.0.

6.

Since the admittance is a function of frequency, the value of ALPHA should be chosen for the frequency range of interest for the analysis.

7.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1127 Proprietary Information of Altair Engineering

MATFAT Bulk Data Entry MATFAT - Fatigue Material Data Description Defines material properties for fatigue analysis. Format (1)

(2)

(3)

(4)

MATFAT

MID

UNIT

STATIC

YS

(5)

(6)

(7)

(8)

FL

SE

np

Kp

(9)

(10)

UTS

Optional continuation lines for SN fatigue properties: SN

SR1

b1

Nc1

b2

Optional continuation lines for EN fatigue properties: EN

Sf

b

SEe

SEp

c

Ef

Nc

Optional continuation lines for factor of safety (FOS) analysis: FOS

Tfl

Hss

Field

Contents

MID

Material identification number that matches the identification number on a MAT1 bulk data entry. No default (Integer > 0)

UNIT

Defines the units of stress values specified on the YS, UTS, SRI1, FL, Sf, and Kp fields Default = MPa (MPa, PA, PSI, or KSI)

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Field

Contents

STATIC

STATIC flag indicates that static material properties are defined in the following fields.

YS

Yield strength. See comment 1. (Real > 0.0, or blank)

UTS

Ultimate tensile strength. See comment 1. (Real > 0.0, or blank)

SN

SN flag indicating that fatigue material properties for SN analysis are following.

SRI1

Fatigue strength coefficient. It is the stress range intercept of SN curve at 1 cycle in log-log scale. No default (Real > 0.0)

b1

The first fatigue strength exponent. It is the slope of the first segment of SN curve in log-log scale. No default (Real < 0.0)

Nc1

In one-segment S-N curve, this is the cycle limit of endurance (see NC1 in Figure 1). In two-segment S-N curve, this is the transition point (see NC1 in Figure 2). No default (Real > 1000.0)

b2

The second fatigue strength exponent. It is the slope of the second segment of SN curve in log-log scale. Default = 0.0 (Real < 0.0)

FL

Fatigue Limit; No damage occurs if the stress range is less than FL (see FL in Figures 1 and 2). See comment 6. (Real > 0.0, or blank)

SE

Standard Error of Log(N). Default = 0.0 (Real > 0.0)

EN

EN flag indicating that fatigue material properties for EN analysis are following.

Sf

Fatigue strength coefficient. No default (Real > 0.0)

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OptiStruct 13.0 Reference Guide 1129 Proprietary Information of Altair Engineering

Field

Contents

b

Fatigue strength exponent. No default (Real < 0.0)

c

Fatigue ductility exponent. No default (Real < 0.0)

Ef

Fatigue ductility coefficient. No default (Real > 0.0)

np

Cyclic strain-hardening exponent. No default (Real > 0.0)

Kp

Cyclic Strength coefficient. No default (Real > 0.0)

Nc

Reversal limit of endurance. One cycle contains two reversals. See comment 6. Default = 2.0E8 (Real > 1.0E5)

SEe

Standard Error of Log(N) from elastic strain. Default = 0.0 (Real > 0.0)

SEp

Standard Error of Log(N) from plastic strain. Default = 0.0 (Real > 0.0)

FOS

The FOS flag indicates that material properties for factor of safety analysis are defined in the following fields.

Tfl

Torsion fatigue limit. No default (Real > 0.0)

Hss

Hydrostatic stress sensitivity. No default (Real > 0.0)

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Figures

Figure 1a: One-segment S-N curve in log-log scale (b2=0) (Nc1 is not defined or less conservative than FL)

Figure 1b: One-segment S-N curve in log-log scale (b2=0) (FL is not defined or less conservative than Nc1)

Figure 2: Two-segment S-N curve in log-log scale

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OptiStruct 13.0 Reference Guide 1131 Proprietary Information of Altair Engineering

Figure 3: E-N curve in log-log scale

Comments 1.

UTS or YS is used in mean stress correction (SN) and surface finish correction (SN and EN). If both UTS and YS are defined, UTS will be used. It is not allowed that both UTS and YS are blanks.

2.

S-N data defined in the MATFAT card is expected to be obtained from standard experiments that are fully reversed bending on mirror-polished specimens.

3.

S-N curves are defined in Stress range – Cycle form. Stress range is the algebraic difference between the maximum and minimum stress in a cycle. SN curve is expressed as:

Where S r is the stress range, SRI1 is the fatigue strength coefficient, number, is the fatigue strength exponent. 4.

is the cycle

E-N curves are defined in Strain amplitude - Reversal form. Strain amplitude is half of the algebraic difference between the maximum and minimum strain in a cycle, and one strain cycle contains two reversals. EN curve is expressed as:

Where, modulus,

is the strain amplitude, is the cycle number,

is the fatigue strength coefficient, E is the Young's is the fatigue strength exponent,

1132 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

is the fatigue

Altair Engineering

ductility coefficient, and 5.

is the fatigue ductility exponent.

Empirical formula can be used to estimate SN/EN data from ultimate tensile strength (UTS) and Young’s modulus (E):

Table 1* Estimated S-N data from empirical formula (* Source: Yung-Li Lee, Jwo. Pan, Richard B. Hathaway and Mark E. Barekey. Fatigue testing and analysis: Theory and practice, Elsevier, 2005)

Table 2**. Estimate E-N data from UTS and E (** Source: Anton Baumel and T. Seeger, Materials Data for C yclic Loading, Elsevier, 1990)

6.

For one-segment SN curve (b2=0.0), if FL is blank, the fatigue limit is the stress range at Nc1. If both Nc1 and FL are defined, the more conservative value (larger damage) will be used (Figure 1). For two-segment SN curve, if FL is blank, the fatigue limit is 0.0. When fatigue optimization is performed, fatigue limit FL of S-N data and reversal limit Nc of E-N data will be ignored in order to get continuous changes in fatigue results when stress/strain changes.

7.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1133 Proprietary Information of Altair Engineering

MATF1 Bulk Data Entry MATF1 – Isotropic Material Frequency Dependence Description Specifies frequency-dependent material properties on MAT1 entry fields via TABLEDi entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MATF1

MID

T(E)

T(G)

T(NU)

T(RHO)

T(A)

T(ST)

T(SC )

T(SS)

(9)

(10)

T(GE)

Example

(1)

(2)

(3)

MATF1

17

32

(4)

(5)

(6)

(7)

(8)

17

(9)

(10)

53

Field

Contents

MID

Material property identification number that matches the identification number on the MAT1 entry. (Integer > 0)

T(E)

Identification number of a TABLEDi entry for the Young’s modulus. (Integer > 0 or blank)

T(G)

Identification number of a TABLEDi entry for the shear modulus. (Integer > 0 or blank)

T(NU)

Identification number of a TABLEDi entry for the Poisson’s ratio. (Integer > 0 or blank)

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Field

Contents

T(RHO)

Identification number of a TABLEDi entry for the mass density. (Integer > 0 or blank)

T(A)

Identification number of a TABLEDi entry for the thermal expansion coefficient. (Integer or blank)

T(GE)

Identification number of a TABLEDi entry for the damping coefficient. (Integer > 0 or blank)

T(ST)

Identification number of a TABLEDi entry for the tension stress limit. (Integer > 0 or blank)

T(SC)

Identification number of a TABLEDi entry for the compression limit. (Integer > 0 or blank)

T(SS)

Identification number of a TABLEDi entry for the shear limit. (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on of this entry correspond, field-by-field, to fields 3, 4, and so on of the MAT1 entry referenced in field 2. The value in a particular field of the MAT1 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, E is modified by TABLEDi 32, RHO is modified by TABLEDi 17 and GE is modified by TABLEDi 53. Blank or zero entries mean that there is no frequency dependence of the field on the MAT1 entry.

2.

The MATF1 entries may refer to blank entries on the respective MAT1 card. In this case, they will be applied to default values of respective parameters. Initial values of E, G, or NU will be supplied according to comment 4 on the MAT1 entry.

3.

Table references must be present for each item that is frequency dependent. For example, it is not sufficient to only give table references for fields 3 and 4 (Young’s modulus and shear modulus) if density is also frequency dependent.

4.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1135 Proprietary Information of Altair Engineering

MATF2 Bulk Data Entry MATF2 – Anisotropic Material Frequency Dependence Description Specifies frequency-dependent material properties on MAT2 entry fields via TABLEDi entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATF2

MID

T(G11)

T(G12)

T(G13)

T(G22)

T(G23)

T(G33)

T(RHO)

T(A1)

T(A2)

T(A3)

T(GE)

T(ST)

T(SC )

T(SS)

Example

(1)

(2)

(3)

MATF2

17

32

(4)

(5)

(6)

(7)

(8)

(9)

15

44

(10)

62

Field

Contents

MID

Material property identification number that matches the identification number on the MAT2 entry. (Integer > 0)

T(Gij)

Identification number of a TABLEDi entry for the shear modulus. (Integer > 0 or blank)

T(RHO)

Identification number of a TABLEDi entry for the mass density. (Integer > 0 or blank)

T(Ai)

Identification number of a TABLEDi entry for the thermal expansion

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Field

Contents coefficient. (Integer or blank)

T(GE)

Identification number of a TABLEDi entry for the damping coefficient. (Integer > 0 or blank)

T(ST)

Identification number of a TABLEDi entry for the tension stress limit. (Integer > 0 or blank)

T(SC)

Identification number of a TABLEDi entry for the compression limit. (Integer > 0 or blank)

T(SS)

Identification number of a TABLEDi entry for the shear limit. (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on of this entry correspond, field-by-field, to fields 3, 4, and so on of the MAT2 entry referenced in field 2. The value in a particular field of the MAT2 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, G11 is modified by TABLEDi 32; G33 is modified by TABLEDi 15; RHO is modified by TABLEDi 44 and GE is modified by TABLEDi 62. Blank or zero entries mean that there is no frequency dependence of the field on the MAT2 entry.

2.

The MATF2 entries may refer to blank entries on the respective MAT2 card. In this case, they will be applied to default values of respective parameters.

3.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1137 Proprietary Information of Altair Engineering

MATF3 Bulk Data Entry MATF3 – Orthotropic Material Frequency Dependence Description Specifies frequency-dependent material properties on MAT3 data entry fields via TABLEDi entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATF3

MID

T(EX)

T(ETH)

T(EZ)

T(NUXTH)

T(NUTHZ)

T(NUZX)

T(RHO)

T(GZX)

T(AX)

T(ATH)

T(AZ)

T(GE)

Example

(1)

(2)

(3)

MATF3

17

32

(4)

(5)

(6)

(7)

(8)

(9)

(10)

19

52

Field

Contents

MID

Material property identification number that matches the identification number on the MAT3 entry. (Integer > 0)

T(EX) T(ETH) T(EZ)

Identification numbers of TABLEDi entries for Young’s moduli in the x, θ and z directions.

T(EX) T(ETH)

Identification numbers of TABLEDi entries for Poisson’s ratios in the xθ, θz and zx directions.

Default = blank (Integer > 0 or blank)

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Field

Contents

T(EZ)

Default = blank (Integer > 0 or blank)

T(RHO)

Identification number of a TABLEDi entry for the mass density. Default = blank (Integer > 0 or blank)

T(GZX)

Identification number of a TABLEDi entry for the shear modulus. Default = blank (Integer > 0 or blank)

T(AX) T(ATH) T(AZ)

Identification numbers of TABLEDi entries for thermal expansion coefficients in the x, θ and z directions.

T(GE)

Identification number of a TABLEDi entry for the damping coefficient.

Default = blank (Integer or blank)

Default = blank (Integer > 0 or blank) Comments 1.

Fields 3, 4, and so on of this entry correspond, field-by-field, to fields 3, 4, and so on of the MAT3 entry referenced in field 2. The value in a particular field of the MAT3 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, EX is modified; TABLEDi 32, RHO is modified by TABLEDi 19; and GE is modified by TABLEDi 52.

2.

Blank or zero entries mean that there is no frequency dependence of the field on the MAT3 entry. Any quantity modified by this entry must have a value on the MAT3 entry.

3.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1139 Proprietary Information of Altair Engineering

MATF8 Bulk Data Entry MATF8 – Shell Orthotropic Material Frequency Dependence Description Specifies frequency-dependent material properties on MAT8 entry fields via TABLEDi entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATF8

MID

T(E1)

T(E2)

T(NU12)

T(G12)

T(G1Z)

T(G2Z)

T(RHO)

T(A1)

T(A2)

T(Xt)

T(Xc)

T(Yt)

T(Yc)

T(S)

T(GE)

T(F12)

Example

(1)

(2)

(3)

MATF8

17

32

(4)

(5)

(6)

(7)

(8)

(9)

(10)

15

52

Field

Contents

MID

Material property identification number that matches the identification number on the MAT1 entry. (Integer > 0)

T(E1)

Identification number of a TABLEDi entry for the Young’s modulus 1. (Integer > 0 or blank)

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Field

Contents

T(E2)

Identification number of a TABLEDi entry for the Young’s modulus 2. (Integer > 0 or blank)

T(NU12)

Identification number of a TABLEDi entry for the Poisson’s ratio 12. (Integer > 0 or blank)

T(G12)

Identification number of a TABLEDi entry for shear modulus 12. (Integer > 0 or blank)

T(G1Z)

Identification number of a TABLEDi entry for transverse shear modulus 1Z. (Integer > 0 or blank)

T(G2Z)

Identification number of a TABLEDi entry for transverse shear modulus 2Z. (Integer > 0 or blank)

T(RHO)

Identification number of a TABLEDi entry for mass density. (Integer > 0 or blank)

T(A1)

Identification number of a TABLEDi entry for the thermal expansion coefficient 1. See comment 3. (Integer or blank)

T(A2)

Identification number of a TABLEDi entry for the thermal expansion coefficient 2. (Integer or blank)

T(Xt)

Identification number of a TABLEDi entry for the tension stress/strain limit 1. (Integer > 0 or blank)

T(Xc)

Identification number of a TABLEDi entry for compression stress/strain limit 1. (Integer > 0 or blank)

T(Yt)

Identification number of a TABLEDi entry for tension stress/strain limit 2. (Integer > 0 or blank)

T(Yc)

Identification number of a TABLEDi entry for compression stress/strain limit 2. (Integer > 0 or blank)

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OptiStruct 13.0 Reference Guide 1141 Proprietary Information of Altair Engineering

Field

Contents

T(S)

Identification number of a TABLEDi entry for shear stress/strain limit. (Integer > 0 or blank)

T(GE)

Identification number of a TABLEDi entry for structural damping coefficient. (Integer > 0 or blank)

T(F12)

Identification number of a TABLEDi entry for Tsai-Wu interaction term. (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on of this entry correspond, field-by-field, to fields 3, 4, and so on of the MAT8 entry referenced in field 2. The value in a particular field of the MAT8 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, E1 is modified by TABLEDi 32; RHO is modified by TABLEDi 15; and GE is modified by TABLEDi 52.

2.

Blank or zero entries mean that there is no frequency dependence of the fields on the MAT8 entry. The MATF8 entries may refer to blank entries on the respective MAT8 card. In which case, they will be applied to default values of the respective parameters.

3.

This card is represented as a material in HyperMesh.

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MATF9 Bulk Data Entry MATF9 – Solid Element Anisotropic Material Frequency Dependence Description Specifies frequency-dependent material properties on MAT9 entry fields via TABLEDi entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATF9

MID

T(G11)

T(G12)

T(G13)

T(G14)

T(G15)

T(G16)

T(G22)

T(G23)

T(G24)

T(G25)

T(G26)

T(G33)

T(G34)

T(G35)

T(G36)

T(G44)

T(G45)

T(G46)

T(G55)

T(G56)

T(G66)

T(RHO)

T(A1)

T(A2)

T(A3)

T(A4)

T(A5)

T(A6)

T(GE)

Example

(1)

(2)

(3)

MATF9

17

32

(4)

(5)

(6)

(7)

(8)

18

12

(9)

(10)

17

5

10

Field

Contents

MID

Material property identification number that matches the identification number on the MAT9 entry. (Integer > 0)

T(Gij)

Identification number of a TABLEDi entry for the terms in the material

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Field

Contents property matrix. (Integer > 0 or blank)

T(RHO)

Identification number of a TABLEDi entry for the mass density. (Integer > 0 or blank)

T(Ai)

Identification number of a TABLEDi entry for the thermal expansion coefficient. (Integer or blank)

T(GE)

Identification number of a TABLEDi entry for the damping coefficient. (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on of this entry correspond, field-by-field, to fields 3, 4, and so on of the MAT9 entry referenced in field 2. The value recorded in a particular field of the MAT9 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, G11 is modified by TABLEDj 32; G14 is modified by TABLEDj 18; G22 is modified by TABLEDi 17; G26 is modified by TABLEDi 12; RHO is modified by TABLEDi 5 and GE is modified by TABLEDi 10.

2.

If the fields are zero or blank, there is no frequency dependence of the field on the MAT9 entry. The MATF9 entries may refer to blank entries on the respective MAT9 card. In which case, they will be applied to default values of respective parameters.

3.

The continuation entries are optional.

4.

This card is represented as a material in HyperMesh.

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MATF10 Bulk Data Entry MATF10 – Isotropic Material Frequency Dependence Description Specifies frequency-dependent material properties on MAT10 entry fields via TABLEDi entries. Format (1)

(2)

(3)

(4)

(5)

MATF10

MID

T(BULK)

T(RHO)

(6)

(7)

(8)

T(GE)

T(ALPHA)

(9)

(10)

Example

(1)

(2)

(3)

(4)

MATF10

2

10

13

(5)

(6)

(7)

17

19

(8)

(9)

Field

Contents

MID

Material property identification number that matches the identification number on the MAT10 entry.

(10)

(Integer > 0) T(BULK)

Identification number of a TABLEDi entry for the bulk modulus. (Integer > 0 or blank)

T(RHO)

Identification number of a TABLEDi entry for the mass density. (Integer > 0 or blank)

T(GE)

Identification number of a TABLEDi entry for fluid material damping coefficient. (Integer > 0 or blank)

T(ALPHA)

Identification number of a TABLEDi entry for normalized porous material

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OptiStruct 13.0 Reference Guide 1145 Proprietary Information of Altair Engineering

Field

Contents damping coefficient. (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on of this entry correspond, field-by-field, to fields 3, 4, and so on of the MAT10 entry referenced in field 2. The value recorded in a particular field of the MAT10 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, BULK modulus is modified by TABLEDj 10; RHO is modified by TABLEDj 18; G22 is modified by TABLEDi 17; G26 is modified by TABLEDi 12; RHO is modified by TABLEDi 13; GE is modified by TABLEDi 17 and ALPHA is modified by TABLEDi 19.

2.

If the fields are zero or blank, there is no frequency dependence of the field on the MAT10 entry. The MATF10 entries may refer to blank entries on the respective MAT10 card. In which case, they will be applied to default values of respective parameters.

3.

The continuation entries are optional.

4.

This card is represented as a material in HyperMesh.

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MATHE Bulk Data Entry MATHE – Nonlinear Hyperelastic Material Property Definition Description The MATHE bulk data entry defines material properties for nonlinear hyperelastic materials. The Polynomial form is available and various material types (comment 3) can be defined by specifying the corresponding coefficients. Format (1)

(2)

(3)

(4)

(5)

(6)

MATHE

MID

Model

C 10

(7)

C 01

D1

TAB1

TAB2

C 20

C 11

C 02

D2

NA

C 30

C 21

C 12

C 03

D3

C 40

C 31

C 22

C 13

C 04

D4

C 50

C 41

C 32

C 23

C 14

C 05

(8)

(9)

(10)

TAB4

ND

D5

Example

(1)

(2)

(3)

MATHE

2

MOONEY

80

20

(4)

(5)

(6)

(7)

(8)

(9)

(10)

0.001

Field

Contents

MID

Unique material identification number. No default (Integer > 0)

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Field

Contents

Model

Specifies the type of hyperelastic material model MOONEY – Selects the generalized Mooney-Rivlin hyperelastic model Default = MOONEY (Character, )

NA

Order of the distortional strain energy polynomial function No default (0 < Integer < 5)

ND

Order of the volumetric strain energy polynomial function (see comment 2). Default = 1 (Integer)

Cpq

Material constants related to distortional deformation (Model = MOONEY). Default = 0.0 (Real)

Dp

Material constants related to volumetric deformation (Model = MOONEY). Default = 0.0 (Real > 0.0)

TAB1

Table identification number of a TABLES1 entry that contains simple tensioncompression data to be used in the estimation of the material constants, Cpq, related to distortional deformation. The x-values in the TABLES1 entry should be the stretch ratios and y-values should be values of the engineering stress. (Integer > 0 or blank)

TAB2

Table identification number of a TABLES1 entry that contains equi-biaxial tension data to be used in the estimation of the material constants, Cpq, related to distortional deformation. The x-values in the TABLES1 entry should be the stretch ratios and y-values should be values of the engineering stress. (Integer > 0 or blank)

TAB4

Table identification number of a TABLES1 entry that contains pure shear data to be used in the estimation of the material constants, Cpq, related to distortional deformation. The x-values in the TABLES1 entry should be the stretch ratios and y-values should be values of the nominal stress. (Integer > 0 or blank)

Comments 1. curve fit values based on the corresponding TAB# tables. However, any Cpq values set to 0.0 are not overwritten.

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2.

The polynomial form of the Hyperelastic material model is written as a combination of the deviatoric and volumetric strain energy of the material. The potential (U) is written in polynomial form, as follows:

Where,

N1 is the order of the distortional strain energy polynomial function (NA) N2 is the order of the volumetric strain energy polynomial function (ND). Currently only first order volumetric strain energy functions are supported (ND=1).

Cpq are the material constants related to distortional deformation (Cpq) ,

are invariants internally calculated by OptiStruct

Dp are material constants related to volumetric deformation (Dp). These values define the compressibility of the material.

Jelas is the elastic volume strain calculated internally by OptiStruct 3.

The polynomial form can be used to model the following material types by specifying the corresponding coefficients (Cpq, Dp) on the MATHE entry: Mooney-Rivlin Material: N1 = N2 =1

U

C10 I1

3

C01 I 2

3

1 J elas D1

1

2

Reduced Polynomial: q=0 N1

U

C p 0 I1

3

N2

p

p 1

p

1 J elas 1 Dp

1

2p

Neo-Hooken Material N1= N2 =1, q=0

U

C10 I1

Altair Engineering

3

1 J elas D1

1

2

OptiStruct 13.0 Reference Guide 1149 Proprietary Information of Altair Engineering

Yeoh Material N1 = N2 =3, q=0

U

C10 I1

1 J elas D1

3

1

2

C20 I1

3

2

1 J elas D2

1

4

C30 I1

3

3

1 J elas D3

Three term Mooney-Rivlin Material:

U

C10 I1

3

C01 I 2

3

C11 I1

3 I2

3

C20 I1

3

C11 I1

3 I2

3

Signiorini Material:

U

C10 I1

3

C01 I 2

2

Third Order Invariant Material:

U

C10 I1

3

C01 I 2

3

3

C20 I1

3

2

Third Order Deformation Material (James-Green-Simpson):

U

C10 I1

3

C01 I 2

3

C11 I1

3 I2

3

C20 I1

3

2

C30 I1

3

3

4.

The MATHE hyperelastic material supports CTETRA (4, 10), CPENTA (6, 15), and CHEXA (8, 20) element types.

5.

This card is represented as a material in HyperMesh.

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1

6

MATHF Bulk Data Entry MATHF – Material Property Definition for One-step Stamping Simulation Description Defines the material properties in a one-step stamping simulation. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MATHF

MID

E

NU

Y

K

n

EPS0

R0

R45

R90

TABLEID

(9)

(10)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MATHF

17

21.0E4

0.3

184.297

549.03

0.22

0.007

1.6

1.6

1.6

Field

Contents

MID

Unique material identification number. No default (Integer > 0)

E

Young’s Modulus. No default (Real)

NU

Poisson’s Ratio. Default = blank (-1.0 < Real < 0.5 or blank)

Y

Yield stress. No default (Real)

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Field

Contents

K

Strength coefficient. No default (Real or blank)

n

Strain hardening component. No default (Real or blank)

EPS0

Pre-strain coefficient. No default (Real or blank)

R0, R45, R90

Lankford coefficients. No default (Real)

TABLEID

Table ID for stress-strain curve using a TABLES1 entry. No default (Integer > 0)

Comments 1.

This entry is only valid with a @HyperForm statement in the first line of the input file.

2.

The TABLEID and the corresponding curve are required only when material data is specified with a stress-strain curve. For such case, material parameter such as K, n and EPS0 are extracted from the stress strain curve.

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MATPE1 Bulk Data Entry MATPE1 – Material Property Definition Description Defines the material properties for poro-elastic materials. Format (1)

(2)

(3)

(4)

(5)

MATPE1

MID

MAT1

MAT10

BIOT

VISC

GAMMA

PRANDTL

POR

(6)

(7)

(8)

(9)

TOR

AFR

VLE

TLE

(10)

Example

(1)

(2)

(3)

(4)

(5)

MATPE1

17

1

10

1.0

1.8-8

1.41

7.0-1

8.0-1

Field

Contents

MID

Unique material identification number.

(6)

(7)

(8)

(9)

1.2

2.-5

1.0-1

9.3-2

(10)

No default (Integer > 0) MAT1

Material identification number of the MAT1 bulk data entry (or MATF1 if it is frequency-dependent) for the skeleton. No default (Integer > 0)

MAT10

Identification number of MAT10 bulk data entry for the porous material. No default (Integer > 0)

BIOT

BIOT factor

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OptiStruct 13.0 Reference Guide 1153 Proprietary Information of Altair Engineering

Field

Contents Default = 1.0 (Real > 0.0)

VISC

Fluid dynamic viscosity No default (Real > 0.0)

GAMMA

Fluid ratio of specific heats. Default = 1.402 (Real > 0.0)

PRANDTL

Fluid Prandtl number. Default = 0.71 (Real > 0.0)

POR

Porosity of the porous material. No default (Real > 0.0)

TOR

Tortuosity of the porous material. Default = 1.0 (Real > 0.0)

AFR

Air flow resistivity. No default (Real > 0.0)

VLE

Viscous characteristic length. No default (Real > 0.0)

TLE

Thermal characteristic length. No default (Real > 0.0)

Comments 1. This entry is represented as a material in HyperMesh.

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MATS1 Bulk Data Entry MATS1 – Stress-dependent and Temperature-dependent Material Definition Description Specifies stress-dependent and temperature-dependent material properties for use in applications involving nonlinear materials. This entry is used if a MAT1 entry is specified with the same MID in a nonlinear subcase. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MATS1

MID

TID

TYPE

H

YF

HR

LIMIT1

(10)

TYPSTRN

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MATS1

17

28

PLASTIC

0.0

1

1

2. + 4

Field

Contents

MID

Identification number of a MAT1 entry.

(9)

(10)

(Integer > 0) TID

Identification number of a TABLES1 or TABLEST entry. If H is given, then this field must be blank. See comment 3. (Integer > 0 or blank)

TYPE

Type of material nonlinearity. See comments. PLASTIC – Elastoplastic material

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OptiStruct 13.0 Reference Guide 1155 Proprietary Information of Altair Engineering

Field

Contents NLELAST – Nonlinear elastic material Default = NLELAST (PLATIC, NLELAST)

H

Work hardening slope (slope of stress versus plastic strain) in units of stress. For elastic-perfectly plastic cases, H = 0.0. For more than a single slope in the plastic range, the stress-strain data must be supplied on a TABLES1 entry referenced by TID, and this field must be blank. See comment 2. (Real > 0)

YF

Yield function criterion, selected by the following value (Integer): 1 = von Mises (Default) (Integer > 0 or blank)

HR

Hardening Rule, selected by the following value (Integer): 1 = Isotropic Hardening (Default) 2 = Kinematic Hardening 3 = Mixed Hardening with 30% contribution of the Kinematic Hardening and 70% contribution of the Isotropic Hardening Adjustable Mixed Hardening is selected by choosing (Real) value for HR: 0 < HR < 1 indicates a mixed combination of Isotropic and Kinematic Hardening. The contribution of the Kinematic Hardening is HR whereas the contribution of the Isotropic Hardening is 1 – HR. See comment 4. (Integer 0, 1, 2, 3 or blank, or Real > 0 and < 1)

LIMIT1

Initial yield point. See comment 6. (Real > 0 or Blank)

TYPSTRN

Specifies the type of strain used on the x-axis of the table pointed to by TID. The strain type is selected by one of the following values. See comment 5. 0 - total strain is used on the x-axis. 1 - plastic strain is used on the x-axis. Default = 0 (Integer, 0, or 1)

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Comments 1.

For nonlinear elastic material, the stress-strain data given in the TABLES1 entry will be used to determine the stress for a given value of strain. The values H, YF, HR, and LIMIT1 will not be used in this case. Nonlinear elastic material is only available in NLGEOM subcases.

2.

For elastoplastic materials, the elastic stress-strain matrix is computed from a MAT1 entry, and the isotropic plasticity theory is used to perform the plastic analysis. In this case, either the table identification TID or the work hardening slope H may be specified, but not both. If the TID is omitted, the work hardening slope H must be specified unless the material is perfectly plastic. The plasticity modulus (H) is related to the tangential modulus (ET ) by

where, E is the elastic modulus and curve in the plastic region.

is the slope of the uniaxial stress-strain

Stress-strain curve definition when H is specified in field 5.

3.

If TID is given, TABLES1 entries (Xi,Yi) of stress-strain data ( following rules:

) must conform to the

If TYPE = "PLASTIC", the curve must be defined in the first quadrant. The data points must be in ascending order. If the table is defined in terms of total strain (TYPSTRN = 0), the first point must be at the origin (X1 = 0, Y1 = 0) and the second point (X2, Y2) must be at the initial yield point (Y 1) specified on the MATS1 entry. The slope of the line joining the origin to the yield stress must be equal to the value of E. If the table is defined in terms of plastic strain (TYPSTRN = 1), the first point (X1, Y1), corresponding to yield point (Y 1), must be at X1=0. TID may reference a TABLEST entry. In this case, the above rules apply to all TABLES1 tables pointed to by TABLEST. If TYPE = “NLELAST”, the full stress-strain curve may be defined in the first and third quadrants to accommodate different uniaxial compression data. If the curve is defined only in the first quadrant, then the curve must start at the origin (X1 = 0.0, Y1 = 0.0). For analyses where small deformations are assumed, there should be little or no difference

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OptiStruct 13.0 Reference Guide 1157 Proprietary Information of Altair Engineering

between the true stress-strain curve and the engineering stress-strain curve, so either of them may be used in the TABLES1 definition. For analyses where small deformations are not assumed, the true stress-strain curve should be used. If the deformations go past the values defined in the table, the curve is extrapolated linearly. 4.

Kinematic hardening and Mixed hardening are supported only for solids.

5.

The conversion of the relation stress vs. total strain (TYPSTRN=0) into stress vs. plastic strain (TYPSTRN=1) is illustrated below. This is clearly different than simply shifting the entire table along the epsilon-axis.

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6.

The LIMIT1 field can be blank if the initial yield point value is defined via a referenced TABLES1 entry on the TID field. OptiStruct will error out if LIMIT1 is blank and TID does not reference a TABLES1 entry.

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OptiStruct 13.0 Reference Guide 1159 Proprietary Information of Altair Engineering

7.

The temperature-dependence of the MATS1 material is defined by referencing a TABLEST entry via the TID field.

8.

Large strain elasto-plasticity can be activated using MATS1 (TYPE=PLASTIC) in conjunction with PARAM, LGDISP, 1.

9.

Linear Buckling Analysis and Preloaded Analysis are not supported with models containing nonlinear (MATS1) material entries. However, you can use PARAM,PRESUBNL,YES to force OptiStruct to run in such models. Linear Buckling Analysis or Preloaded Analysis is not recommended in models with nonlinear materials or in large displacement nonlinear analysis. It is the user’s responsibility to interpret the results with caution.

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MATT1 Bulk Data Entry MATT1 – Isotropic Material Temperature Dependence Description Specifies temperature-dependent material properties on MAT1 entry fields via TABLEMi entries.

Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MATT1

MID

T(E)

T(G)

T(NU)

T(RHO)

T(A)

T(ST)

T(SC )

T(SS)

(9)

(10)

T(GE)

Example

(1)

(2)

(3)

MATT1

17

32

(4)

(5)

(6)

(7)

(8)

(9)

(10)

15

52

Field

Contents

MID

Material property identification number that matches the identification number on MAT1 entry. (Integer > 0)

T(E)

Identification number of a TABLEMi entry for the Young’s modulus. (Integer > 0 or blank)

T(G)

Identification number of a TABLEMi entry for the shear modulus. (Integer > 0 or blank)

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Field

Contents

T(NU)

Identification number of a TABLEMi entry for the Poisson’s ratio. (Integer > 0 or blank)

T(RHO)

Identification number of a TABLEMi entry for the mass density. (Integer > 0 or blank)

T(A)

Identification number of a TABLEMi entry for the thermal expansion coefficient. (Integer or blank)

T(GE)

Identification number of a TABLEMi entry for the damping coefficient. (Integer > 0 or blank)

T(ST)

Identification number of a TABLEMi entry for the tension stress limit. (Integer > 0 or blank)

T(SC)

Identification number of a TABLEMi entry for the compression limit. (Integer > 0 or blank)

T(SS)

Identification number of a TABLEMi entry for the shear limit. (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on, of this entry correspond, field-by-field, to fields 3, 4, and so on, of the MAT1 entry referenced in field 2. The value in a particular field of the MAT1 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, E is modified; TABLEMi 32, A is modified by TABLEMi 15; and ST is modified by TABLEMi 52. Blank or zero entries mean that there is no temperature dependence of the field on the MAT1 entry.

2.

The MATT1 entries may refer to blank entries on the respective MAT1 card. In this case, they will be applied to default values of respective parameters. Initial values of E, G, or NU will be supplied according to comment 4 on the MAT1 entry.

3.

Table references must be present for each item that is temperature dependent. For example, it is not sufficient to only give table references for fields 3 and 4 (Young’s modulus and shear modulus) if Poisson’s ratio is temperature dependent.

4.

The TEMPERATURE subcase information entry (with type = MATERIAL) is required to

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activate temperature-dependent material behavior and to define the temperature field (option = SID of TEMP, TEMPD or the SUBCASE ID of a thermal analysis subcase). 5.

This card is represented as a material in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1163 Proprietary Information of Altair Engineering

MATT2 Bulk Data Entry MATT2 – Anisotropic Material Temperature Dependence Description Specifies temperature-dependent material properties on MAT2 entry fields via TABLEMj entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATT2

MID

T(G11)

T(G12)

T(G13)

T(G22)

T(G23)

T(G33)

T(RHO)

T(A1)

T(A2)

T(A3)

T(GE)

T(ST)

T(SC )

T(SS)

Example

(1)

(2)

(3)

MATT2

17

32

(4)

(5)

(6)

(7)

(8)

(9)

(10)

15

62

Field

Contents

MID

Material property identification number that matches the identification number on a MAT2 entry. (Integer > 0)

T(Gij)

Identification number of a TABLEMk entry for the terms in the material property matrix. (Integer > 0 or blank)

T(RHO)

Identification number of a TABLEMk entry for the mass density.

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Field

Contents (Integer > 0 or blank)

T(Ai)

Identification number of a TABLEMk entry for the thermal expansion coefficient. (Integer or blank)

T(GE)

Identification number of a TABLEMk entry for the damping coefficient. (Integer > 0 or blank)

T(ST)

Identification number of a TABLEMk entry for the tension stress limit. (Integer > 0 or blank)

T(SC)

Identification number of a TABLEMk entry for the compression limit. (Integer > 0 or blank)

T(SS)

Identification number of a TABLEMk entry for the shear limit. (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on of this entry correspond, field-by-field, to fields 3, 4, and so on of the MAT2 entry referenced in field 2. The value in a particular field of the MAT2 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, G11 is modified by TABLEMk 32; G33 is modified by TABLEMk 15; and A1 is modified by TABLEMk 62. If Ri is zero or blank, there is no temperature dependence of the field on the MAT2 entry.

2.

The MATT2 entries may refer to blank entries on the respective MAT2 card. In which case, they will be applied to default values of respective parameters.

3.

The TEMPERATURE subcase information entry (with type = MATERIAL) is required to activate temperature-dependent material behavior and to define the temperature field (option = SID of TEMP, TEMPD or the SUBCASE ID of a thermal analysis subcase).

4.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1165 Proprietary Information of Altair Engineering

MATT3 Bulk Data Entry MATT3 – MAT3 Material Temperature Dependence Description Specifies temperature-dependent material properties on MAT3 entry fields via TABLEMi entries.

Format (1)

(2)

(3)

(4)

(5)

MATT3

MID

T(EX)

T(ETH)

T(EZ)

T(GZX)

T(AX)

(6)

(7)

(8)

(9)

(10)

T(NUXTH) T(NUTHZ) T(NUZX) T(RHO)

T(ATH)

T(AZ)

T(GE)

Example

(1)

(2)

(3)

MATT3

17

32

(4)

(5)

(6)

(7)

(8)

(9)

(10)

19

52

Field

Contents

MID

Material property identification number that matches the identification number on MAT3 entry. (Integer > 0)

T(EX), T(ETH), T(EZ)

Identification number of a TABLEMi entry for the Young’s moduli in the x, θ and z directions. Default = blank (Integer > 0 or blank)

T(NUXTH), Identification number of a TABLEMi entry for the Poisson’s ratios in the xθ, θz

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Field

Contents

T(NUTHZ), and zx directions. T(NUZX) Default = blank (Integer > 0 or blank) T(RHO)

Identification number of a TABLEMi entry for the mass density. Default = blank (Integer > 0 or blank)

T(GZX)

Identification number of a TABLEMi entry for the shear modulus. Default = blank (Integer > 0 or blank)

T(AX), T(ATH), T(AZ)

Identification number of a TABLEMi entry for the thermal expansion coefficients in the x, θ and z directions. Default = blank (Integer or blank)

T(GE)

Identification number of a TABLEMi entry for the damping coefficient. Default = blank (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on, of this entry correspond, field-by-field, to fields 3, 4, and so on, of the MAT3 entry referenced in field 2. The value in a particular field of the MAT3 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, EX is modified; TABLEMi 32, EZ is modified by TABLEMi 19; and GZX is modified by TABLEMi 52. Blank or zero entries mean that there is no temperature dependence of the field on the MAT3 entry.

2.

Any quantity modified by this entry must have a value on the MAT3 entry.

3.

The TEMPERATURE subcase information entry (with type = MATERIAL) is required to activate temperature-dependent material behavior and to define the temperature field (option = SID of TEMP, TEMPD or the SUBCASE ID of a thermal analysis subcase).

4.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1167 Proprietary Information of Altair Engineering

MATT4 Bulk Data Entry MATT4 – Temperature-Dependent Material Property Definition, Form 4 Description Defines temperature-dependent material properties for the corresponding MAT4 bulk data entry fields via TABLEMi entries. Format (1)

(2)

(3)

MATT4

MID

T(K)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

MATT4

24

200

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Field

Contents

MID

Material identification number of a MAT4 bulk data entry that is temperature dependent. No default (Integer > 0)

T(K)

Identification number of a TABLEMi entry that defines temperature-dependent thermal conductivity. Default = 0 (Integer > 0)

Comments 1.

The quantities defined on the MAT4 bulk data entry are multiplied by the tabular function referenced by the MATT4 bulk data card to generate the corresponding material properties.

2.

If the fields are blank or zero, then constant properties defined on the MAT4 bulk data card are used.

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MATT8 Bulk Data Entry MATT8 – Shell Orthotropic Material Temperature Dependence Description Specifies temperature-dependent material properties on MAT8 entry fields via TABLEMi entries.

Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATT8

MID

T(E1)

T(E2)

T(NU12)

T(G12)

T(G1Z)

T(G2Z)

T(RHO)

T(A1)

T(A2)

T(Xt)

T(Xc)

T(Yt)

T(Yc)

T(S)

T(GE)

T(F12)

Example

(1)

(2)

(3)

MATT8

17

32

(4)

15

(5)

(6)

(7)

(8)

(9)

(10)

15

52

Field

Contents

MID

Material property identification number that matches the identification number on MAT1 entry. (Integer > 0)

T(E1)

Identification number of a TABLEMi entry for the Young’s modulus 1. (Integer > 0 or blank)

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Field

Contents

T(E2)

Identification number of a TABLEMi entry for the Young’s modulus 2. (Integer > 0 or blank)

T(NU12)

Identification number of a TABLEMi entry for the Poisson’s ratio 12. (Integer > 0 or blank)

T(G12)

Identification number of a TABLEMi entry for shear modulus 12. (Integer > 0 or blank)

T(G1Z)

Identification number of a TABLEMi entry for transverse shear modulus 1Z. (Integer > 0 or blank)

T(G2Z)

Identification number of a TABLEMi entry for transverse shear modulus 2Z. (Integer > 0 or blank)

T(RHO)

Identification number of a TABLEMi entry for mass density. (Integer > 0 or blank)

T(A1)

Identification number of a TABLEMi entry for the thermal expansion coefficient 1. See comment 3. (Integer or blank)

T(A2)

Identification number of a TABLEMi entry for the thermal expansion coefficient 2. (Integer or blank)

T(Xt)

Identification number of a TABLEMi entry for the tension stress/strain limit 1. (Integer > 0 or blank)

T(Xc)

Identification number of a TABLEMi entry for compression stress/strain limit 1. (Integer > 0 or blank)

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Field

Contents

T(Yt)

Identification number of a TABLEMi entry for tension stress/strain limit 2. (Integer > 0 or blank)

T(Yc)

Identification number of a TABLEMi entry for compression stress/strain limit 2. (Integer > 0 or blank)

T(S)

Identification number of a TABLEMi entry for shear stress/strain limit. (Integer > 0 or blank)

T(GE)

Identification number of a TABLEMi entry for structural damping coefficient. (Integer > 0 or blank)

T(F12)

Identification number of a TABLEMi entry for Tsai-Wu interaction term. (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on of this entry correspond, field-by-field, to fields 3, 4, and so on of the MAT8 entry referenced in field 2. The value in a particular field of the MAT8 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, E1 is modified by TABLEMi 32; A1 is modified by TABLEMi 15; and Xt is modified by TABLEMi 52. Blank or zero entries mean that there is no temperature dependence of the fields on the MAT8 entry.

2.

The MATT8 entries may refer to blank entries on the respective MAT8 card. In which case, they will be applied to default values of respective parameters.

3.

The TEMPERATURE subcase information entry (with type = MATERIAL) is required to activate temperature-dependent material behavior and to define the temperature field (option = SID of TEMP, TEMPD or the SUBCASE ID of a thermal analysis subcase).

4.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1171 Proprietary Information of Altair Engineering

MATT9 Bulk Data Entry MATT9 – Solid Element Anisotropic Material Temperature Dependence Description Specifies temperature-dependent material properties on MAT9 entry fields via TABLEMk entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATT9

MID

T(G11)

T(G12)

T(G13)

T(G14)

T(G15)

T(G16)

T(G22)

T(G23)

T(G24)

T(G25)

T(G26)

T(G33)

T(G34)

T(G35)

T(G36)

T(G44)

T(G45)

T(G46)

T(G55)

T(G56)

T(G66)

T(RHO)

T(A1)

T(A2)

T(A3)

T(A4)

T(A5)

T(A6)

T(GE)

Example

(1)

(2)

(3)

MATT9

17

32

(4)

(5)

(6)

(7)

(8)

18

(9)

(10)

17

12

5

10

Field

Contents

MID

Material property identification number that matches the identification number on a MAT9 entry. (Integer > 0)

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Field

Contents

T(Gij)

Identification number of a TABLEMk entry for the terms in the material property matrix. (Integer > 0 or blank)

T(RHO)

Identification number of a TABLEMk entry for the mass density. (Integer > 0 or blank)

T(Ai)

Identification number of a TABLEMk entry for the thermal expansion coefficients. (Integer > 0 or blank)

T(GE)

Identification number of a TABLEMk entry for the damping coefficient. (Integer > 0 or blank)

Comments 1.

Fields 3, 4, and so on of this entry correspond, field-by-field, to fields 3, 4, and so on of the MAT9 entry referenced in field 2. The value recorded in a particular field of the MAT9 entry is replaced or modified by the table referenced in the corresponding field of this entry. In the example shown, G11 is modified by TABLEMj 32; G14 is modified by TABLEMj 18, and so on. If the fields are zero or blank, there is no temperature dependence of the field on the MAT9 entry.

2.

The MATT9 entries may refer to blank entries on the respective MAT9 card. In which case, they will be applied to default values of respective parameters.

3.

The continuation entries are optional.

4.

The TEMPERATURE subcase information entry (with type = MATERIAL) is required to activate temperature-dependent material behavior and to define the temperature field (option = SID of TEMP, TEMPD or the SUBCASE ID of a thermal analysis subcase).

5.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1173 Proprietary Information of Altair Engineering

MATX0 Bulk Data Entry MATX0 – Material Property Extension for Void Material for Geometric Nonlinear Analysis Description Defines void material for geometric nonlinear analysis. Format (1)

(2)

(3)

MATX0

MID

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

MAT1

102

10.0

MATX0

102

(4)

(5)

(6)

0.495

6.0E-10

(7)

Field

Contents

MID

Material ID of the associated MAT1. See comment 1.

(8)

(9)

(10)

No default (Integer > 0) Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATX0 material extension can be associated with a particular MAT1.

2.

MATX0 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN subcase entry. For all other subcases, it is treated as an elastic material defined by the associated MAT1.

3.

This card is represented as an extension to a MAT1 material in HyperMesh.

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MATX02 Bulk Data Entry MATX02 – Material Property Extension for Johnson-Cooke Elastic-plastic Material for Geometric Nonlinear Analysis Description Defines additional material properties for Johnson-Cooke elastic-plastic material for geometric nonlinear analysis. This is an elasto-plastic law with strain rate and temperature effects. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MATX02

MID

A

B

N

EPSMAX

SIGMAX

C

DEPS0

IC C

FSMOOTH

FC UT

M

TMELT

RC P

(10)

Example

(1)

(2)

(3)

MAT1

102

60.4

MATX02

102

0.09026

(4)

0.22313

(5)

(6)

0.33

2.70E-06

0.374618

100.0

(7)

(8)

(9)

(10)

0.175

Field

Contents

MID

Material ID of the associated MAT1. See comment 1. No default (Integer > 0)

A

Plasticity yield stress. (Real > 0)

B

Plasticity hardening parameter. (Real > 0)

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Field

Contents

N

Plasticity hardening exponent. Default = 1.0 (Real < 1.0)

EPSMAX

Failure plastic strain εmax Default = 1030 (Real > 0)

SIGMAX

Maximum plastic stress σmax0 Default = 1030 (Real > 0)

C

Strain rate coefficient. If zero, there is no strain rate effect. Default = 0.0 (Real)

DEPS0

Reference strain rate

.

Default = 0.0 (Real) If DESPS < DESPS0, no strain rate effect. ICC

Flag for strain rate dependency of σmax (See comment 5). Default = ON (ON or OFF)

FSMOOTH

Flag for strain rate smoothing. Default = OFF (ON or OFF)

FCUT

Cutoff frequency for strain rate filtering. Only for shell and solid elements. Default = 1030 (Real > 0)

M

Temperature exponent. Default = 0.0 (Real)

TMELT

Melting temperature. Default = 1030 (Real > 0)

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Field

Contents

RCP

Specific heat per unit of volume. Default = 0.0 (Real > 0)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX02 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

This is an elastic-plastic law with strain rate and thermal effects. It follows:

with:

= plastic strain = strain rate T = Temperature (in Kelvin) 4.

If the plastic strain reaches EPSMAX, shell elements are deleted. Solid elements are not deleted, but the deviatoric stress is set to zero.

5.

ICC controls the strain rate effect.

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OptiStruct 13.0 Reference Guide 1177 Proprietary Information of Altair Engineering

6.

No strain rate effects are considered in rod elements.

7.

Strain rate filtering is used to smooth strain rates. The input FCUT is available only for shell and solid elements.

8.

To take into account the temperature effect, strain rate dependence must be activated. If the temperature exponent M = 0; there is no temperature effect. No temperature effect is considered on rod, bar, and beam elements.

9.

The temperature is computed assuming adiabatic conditions:

where, Eint is the internal energy. If ρCp = 0, the temperature is constant: T = T i 10. This card is represented as an extension to a MAT1 material in HyperMesh.

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MATX13 Bulk Data Entry MATX13 – Material Property Extension for Rigid Material for Geometric Nonlinear Analysis Description Defines rigid material for geometric nonlinear analysis. Format (1)

(2)

(3)

MATX13

MID

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

MAT1

102

10.0

MATX13

102

(4)

(5)

(6)

0.495

6.0E-10

(7)

Field

Contents

MID

Material ID of the associated MAT1. See comment 1.

(8)

(9)

(10)

No default (Integer > 0) Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX13 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1179 Proprietary Information of Altair Engineering

MATX21 Bulk Data Entry MATX21 – Material Property Extension for Rock-Concrete Material for Geometric Nonlinear Analysis Description Defines additional material properties for Rock-Concrete material for geometric nonlinear analysis. This law is based on the Drücker-Prager yield criteria and is used to model materials with internal friction such as rock-concrete. The plastic behavior of these materials is dependent on the pressure in the material. This law is only applicable to solid elements. Format (1)

(2)

(3)

(4)

(5)

(6)

MATX21

MID

A0

A1

A2

AMAX

TPID

KT

FSC AL

PMIN

B

(7)

(8)

(9)

MUMAX

PEXT

(10)

Example

(1)

(2)

(3)

MAT1

102

3.1E10

MATX21

102 1

(4)

(5)

(6)

0.33

1000.0

(7)

(8)

(9)

(10)

3 1E10

Field

Contents

MID

Material ID of the associated MAT1. See comment 1. No default (Integer > 0)

A0

Coefficient. (Real)

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Field

Contents

A1

Coefficient. (Real)

A2

Coefficient. (Real)

AMAX

Von Mises limit. Default = 1030 (Real > 0)

TPID

Identification number of a TABLES1 that defines the volumetric strain vs. pressure function. No default (Integer > 0)

KT

Tensile bulk modulus. (Real > 0.0)

FSCAL

Scale factor for pressure function. Default = 1.0 (Real)

PMIN

Minimum pressure. Default = -1030 (Real)

B

Unloading bulk modulus. (Real > 0.0)

MUMAX

Maximum compression volumetric strain. (Real)

PEXT

External pressure (see comment 6). Default = 0.0 (Real)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATX21 material extension can be associated with a particular MAT1.

2.

MATX21 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

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OptiStruct 13.0 Reference Guide 1181 Proprietary Information of Altair Engineering

3.

Hydrodynamic behavior is given by a user-defined function P = f(µ) where, P is the pressure in the material, and µ is the volumetric strain.

4.

Drücker-Prager yield criteria uses a modified von Mises yield criteria to incorporate the effects of pressure for massive structures: F = J2 - (A0 + A1P + A2P2) where, J2: second invariant of deviatoric stress. P: pressure. A0, A1, A2: material coefficients. A1 = A2 = 0 means that the yield criteria is von Mises (

vm

3 A0

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)

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5.

It is recommended to set unloading bulk modulus, B equal to the initial slope of function describing P(µ) and tensile bulk modulus KT equal to 1/100 of unloading bulk modulus. B and KT must be positive.

6.

External pressure is required if relative pressure formulation is used. In this specific case, yield criteria and energy integration require the value of total pressure.

7.

This card is represented as an extension to a MAT1 material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1183 Proprietary Information of Altair Engineering

MATX25 Bulk Data Entry MATX25 – Material Property Extension for Tsai-Wu and CRASURVT Materials for Geometric Nonlinear Analysis Description Defines an elasto-plastic orthotropic material with Tsai-Wu and CRASURVT yield criteria for composite shell materials. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MATX25

MID

EPSF1

EPSF2

EPST1

EPSM1

EPST2

EPSM2

DTENDS

WPMAX

WPREF

IOFF

GAMINI

GAMMAX

DMAX

RATIO

FSMOOTH

FC UT

IFORM

(10)

Continuation line for IFORM = TSAI B

N

FMAX

SY1T

SY2T

SY1C

SY2C

ALFA

SY12C

SY12T

C 12

EPSR0

IC C

Continuation line for IFORM = CRAS C

EPSR0

ALFA

IC C G

SY1T

B1T

N1T

SMAX1T

EPS1T1

EPS2T1

SRST1

WMPT1

SY2T

B2T

N2T

SMAX2T

EPS1T2

EPS2T2

SRST2

WMPT2

C 1T

C 2T

1184 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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SY1C

B1C

N1C

SMAX1C

EPS1C 1

EPS2C 1

SRSC 1

WMPC 1

SY2C

B2C

N2C

SMAX2C

EPS1C 2

EPS2C 2

SRSC 2

WMPC 2

SY12T

B12T

N12T

SMAX12 T

EPS1T12

EPS2T12

SRST12

WMPT12

C 1C

C 2C

C 12T

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MAT8

102

70000

70000

0.3

26923.1

26923.1

26923.1

MATX25

102

0.15

0.2

(9)

(10)

0.95

2

0.2

1.0

2.0

1E10

1E10

1E10

1E10

1E10

1E10

Field

Contents

MID

Material ID of the associated MAT8. See comment 1. No default (Integer > 0)

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OptiStruct 13.0 Reference Guide 1185 Proprietary Information of Altair Engineering

Field

Contents

EPSF1

Total tensile failure in direction 1. Default = 1E30 (Real)

EPSF2

Total tensile failure in direction 2. Default = 1E30 (Real)

EPST1

Tensile failure strain in direction 1. (Real)

EPSM1

Maximum strain in direction 1. (Real)

EPST2

Tensile failure strain in direction 2. (Real)

EPSM2

Maximum strain in direction 2. (Real)

DTENDS

Maximum damage of composite tensile strength. Default = 0.999 (Real < 1.0)

WPMAX

Maximum plastic work. Default = 1E30 (Real)

WPREF

Reference plastic work. Default = 1.0 (Real)

IOFF

Total element failure criteria. Default = 0 (Integer) = 0: shell is deleted if Wp* > Wp*max for 1 layer = 1: shell is deleted if Wp* > Wp*max for all layers = 2: if for each layer, Wp* > Wp*max or tensile failure in direction 1(t1)

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Field

Contents = 3: if for each layer, Wp* > Wp*max or tensile failure in direction 2(t2) = 4: if for each layer, Wp* > Wp*max or tensile failure in directions 1(t1) and 2(t2) = 5: if for all layers: Wp* > Wp*max or tensile failure in direction 1(t1) or if for all layers: Wp* > Wp*max or tensile failure in direction 2(t2) = 6: if for each layer, Wp* > Wp*max or tensile failure in direction 1(t1) or 2(t2)

GAMINI

Delamination shear strain. See comment 11. Default = 1E30 (Real)

GAMMAX

Maximum shear strain. Default = 1.1E30 (Real)

DMAX

Maximum damage. Default = 1.0 (Real)

RATIO

Ratio parameter control to delete shell elements Default = 1.0 (Real) < 0.0: the element will be deleted if all of the layers but one fail (the number of layers that did not fail is equal to 1). > 0.0: the element will be deleted if:

FSMOOTH

Flag for strain rate smoothing. Default = OFF (ON or OFF)

FCUT

Cutoff frequency for strain rate filtering. Default = 1E30 (Real)

IFORM

Formulation flag. Default = TSAI (TSAI, CRAS)

IFORM = TSAI

Altair Engineering

OptiStruct 13.0 Reference Guide 1187 Proprietary Information of Altair Engineering

Field

Contents

B

Hardening parameter. (Real)

N

Hardening exponent. Default = 1.0 (Real)

FMAX

Maximum value of yield function. Default = 1E30 (Real)

SY1T

Tension in direction 1. (Real > 0)

SY2T

Tension in direction 2. (Real > 0)

SY1C

Compression yield stress in direction 1. (Real > 0)

SY2C

Compression yield stress in direction 2. (Real > 0)

ALFA

F12 reduction factor. Default = 1.0 (Real)

SY12C

Compression yield stress in direction 12. (Real > 0)

SY12T

Tension yield stress in direction 12. (Real > 0)

C12

Strain rate coefficient. (Real)

1188 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents = 0.0: no strain rate dependency.

EPSR0

Reference strain rate. (Real)

ICC

Flag for yield stress in shear and strain rate (See comment 9). (Integer) = 0: = 1: = 2: = 3: = 4:

Default set to 1 Strain rate effect on FMAX no effect on WPMAX No strain rate effect on FMAX and WPMAX Strain rate effect on FMAX and WPMAX No strain rate effect on FMAX effect on WPMAX

IFORM = CRAS C

Global strain rate coefficient for plastic work criteria. (Real)

EPSR0

Reference strain rate. (Real)

ALFA

F12 reduction factor. Default= 1.0 (Real)

ICCG

Global composite plasticity parameters flag for strain rate computation: (See comment 9). = 1: Strain rate effect on SMAX1T, SMAX2T, SMAX1C, SMAX2C, SMAX12T; no strain rate effect on WPMAX. = 2: No strain rate effect on SMAX1T, SMAX2T, SMAX1C, SMAX2C, SMAX12T; no strain rate effect on WPMAX. = 3: Strain rate effect on SMAX1T, SMAX2T, SMAX1C, SMAX2C, SMAX12T and strain rate effect on WPMAX. = 4: No strain rate effect on SMAX1T, SMAX2T, SMAX1C, SMAX2C, SMAX12T and strain rate effect on WPMAX. Default = 1 (Integer)

Altair Engineering

OptiStruct 13.0 Reference Guide 1189 Proprietary Information of Altair Engineering

Field

Contents

SY1T

Tension yield stress in direction 1. (Real > 0)

B1T

Hardening parameter in direction 1. (Real)

N1T

Hardening exponent in direction 1. Default = 1.0 (Real)

SMAX1T

Maximum stress in direction 1. Default = 1E30 (Real)

C1T

Strain rate coefficient in direction 1. 0: no strain rate dependency. Default = C (Real)

EPS1T1

Initial softening strain in direction 1. Default = 1E30 (Real)

EPS2T1

Maximum softening strain in direction 1. Default = 1.2 * EPS1T1 (Real)

SRST1

Residual stress in direction 1. Default = 10E-3*SY1T (Real)

WMPT1

Maximum plastic work in tension direction 1. Default = 1E30 (Real)

SY2T

Tension yield stress in direction 2. (Real > 0)

B2T

Hardening parameter in direction 2.

1190 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents Default = B1T (Real)

N2T

Hardening exponent in direction 2. Default = N1T (Real)

SMAX2T

Maximum stress in direction 2. Default = 1E30 (Real)

C2T

Strain rate coefficient in direction 2. 0: no strain rate dependency Default = C (Real)

EPS1T2

Initial softening strain in direction 2. Default = 1E30 (Real)

EPS2T2

Maximum softening strain in direction 2. Default = 1.2*EPS1T1 (Real)

SRST2

Residual stress in direction 2. Default = 10E-3 * SY2T (Real)

WMPT2

Maximum plastic work in tension direction 2. Default = 1E30 (Real)

SY1C

Compression yield stress in direction 1. (Real > 0)

B1C

Hardening parameter in direction 1. Default = B2T (Real)

N1C

Hardening exponent in direction 1. Default = N2T (Real)

Altair Engineering

OptiStruct 13.0 Reference Guide 1191 Proprietary Information of Altair Engineering

Field

Contents

SMAX1C

Maximum stress in direction 1. Default = 1E30 (Real)

C1C

Strain rate coefficient in direction 1. = 0.0: no strain rate dependency. Default = C (Real)

EPS1C1

Initial softening strain in direction 1. Default = 1E30 (Real)

ESP2C1

Maximum softening strain in direction 1. Default = 1.2*EPS1C1 (Real)

SRSC1

Residual stress in direction 1. Default = 10E-3*S1YC (Real)

WMPC1

Maximum plastic work in compression direction 1. Default = 1E30 (Real)

SY2C

Compression yield stress in direction 2. (Real > 0)

B2C

Hardening parameter in direction 2. Default = B1C (Real)

N2C

Hardening exponent in direction 2 Default = N1C (Real)

SMAX2C

Maximum stress in direction 2. Default = 1E30 (Real)

C2C

Strain rate coefficient in direction 2.

1192 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Field

Contents = 0.0: no strain rate dependency. Default = C (Real)

EPS1C2

Initial softening strain in direction 2. Default = 1E30 (Real)

EPS2C2

Maximum softening strain in direction 2. Default = 1.2*EPS1C2 (Real)

SRSC2

Residual stress in direction 2. Default = 10E-3*S2YC (Real)

WMPC2

Maximum plastic work in compression direction 2. Default = 1E30 (Real)

SY12T

Tension yield stress in direction 12. (Real > 0)

B12T

Hardening parameter in direction 12. Default = B2C (Real)

N12T

Hardening exponent in direction 12. Default = 1.0 (Real)

SMAX12T

Maximum stress in direction 12. Default = 1E30 (Real)

C12T

Strain rate coefficient in direction 12. = 0.0: no strain rate dependency. Default = C (Real)

EPS1T12

Initial softening strain in direction 12.

Altair Engineering

OptiStruct 13.0 Reference Guide 1193 Proprietary Information of Altair Engineering

Field

Contents Default = 1E30 (Real)

EPS2T12

Maximum softening strain in direction 12. Default = 1.2*EPS1T12 (Real)

SRST12

Residual stress in direction 12. Default = 10E-3*SY12T (Real)

WMPT12

Maximum plastic work in shear. Default = 1E30 (Real)

Comments 1.

The material identification number must be that of an existing MAT8 bulk data entry. Only one MATXi material extension can be associated with a particular MAT8.

2.

MATX25 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

Tsai-Wu formula (IFORM=TSAI) is not available with QEPH (ISHELL=24 on PCOMPX) shell elements, it is only available with Q4 (ISHELL=1,2,3,4 on PCOMPX) and QBAT(ISHELL=12 on PCOMPX) shell elements.

4.

The Lamina yield surface for Tsai-Wu criteria(IFORM=TSAI) is:

with: Wp is the plastic work is the reference plastic work

is the yield envelope evolution: where, b = Hardening parameter for plastic work n = Hardening exponent

1194 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

5.

The CRASURV model is an improved version of the former law based on the standard TsaiWu criteria. The main changes concern the expression of the yield surface before plastification and during work hardening. Firstly, in a CRASURV model, the coefficient F 44 depends only on one input parameter:

Another modification concerns the parameters F ij which are expressed now in function of plastic work and plastic work rate as below:

6.

If the total tensile failure value EPSF1 is reached in the direction 1 and respectively ε EPSF2 in the direction 2, the stresses tensor in the layer is permanently reset to 0.

Altair Engineering

OptiStruct 13.0 Reference Guide 1195 Proprietary Information of Altair Engineering

7.

If a shell has several layers with one material per layer (different materials, different IOFF), the IOFF used is the one that is associated to the shell in the shell element definition.

8.

Both Wp* and Wp*max are defined as follows:

9.

The plastic work criteria is:

When ICC=2,3,4 for Tsai-Wu formula, when ICCG=3,4 for CRASURV formula. 10. Delamination is a global model:

with

applies to the all shell and not independently per each layer.

11. Thereby, the coefficients GAMINI, GAMMAX, and DMAX considered, are the coefficients which are defined in the global material associated to the shell equivalent out-of-plane shear strain. 12. The IOFF and RATIO field values are utilized only if they are defined in the material assigned to a part, these fields are not considered if they are only defined in material used for a layer in the property entry. This option is not available for solid elements. 13. This card is represented as extension to a MAT8 material in HyperMesh.

1196 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MATX27 Bulk Data Entry MATX27 – Material Property Extension for Elastic-Plastic Brittle Material for Geometric Nonlinear Analysis Description Defines additional material properties for elastic-plastic brittle material for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATX27

MID

A

B

N

EPSMAX

SIGMAX

C

DEPS0

EPS1MAX

D1MAX

EPSD1

EPS2

EPS2MAX

D2MAX

ESPD2

IC C

EPS1

Example

(1)

(2)

(3)

MAT1

127

60.4

MATX27

127

0.09026

(4)

0.22313

(5)

(6)

0.33

2.70E-06

0.374618

100.0

(7)

(8)

(9)

(10)

0.175

Field

Contents

MID

Material ID of the associated MAT1. See comment 1. No default (Integer > 0)

A

Plasticity yield stress. (Real > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1197 Proprietary Information of Altair Engineering

Field

Contents

B

Plasticity hardening parameter. (Real > 0)

N

Plasticity hardening exponent. Default = 1.0 (Real < 1.0)

EPSMAX

Failure plastic strain εmax Default = 1030 (Real > 0)

SIGMAX

Maximum plastic stress σmax0 Default = 1030 (Real > 0)

C

Strain rate coefficient. Default = 0.0 (Real)

DEPS0

Reference strain rate

.

Default = 0.0 (Real) If DESPS < DESPS0, no strain rate effect. ICC

Flag for strain rate dependency of σmax . See comment 4. Default = ON (ON or OFF)

EPS1

Tensile failure strain in principal strain direction 1. Default = 1.0*1030

EPS1MAX

Maximum tensile failure strain in principal strain direction 1. Default = 1.1*1030

DMAX1

(Real > 0)

(Real > 0)

Maximum tensile failure damage in principal strain direction 1. Default = 0.999 (Real > 0)

1198 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

EPSD1

Tensile strain for element deletion in principal strain direction 2. Default = 1.2*1030 (Real > 0)

EPS2

Tensile failure strain in principal strain direction 2. Default = 1.0*1030

EPS2MAX

Maximum tensile failure strain in principal strain direction 2. Default = 1.1*1030

DMAX2

(Real > 0)

(Real > 0)

Maximum tensile failure damage in principal strain direction 2. Default = 0.999 (Real > 0)

EPSD2

Tensile strain for element deletion in principal strain direction 2. Default = 1.2*1030

(Real > 0)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX27 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

This law is only applicable with shell elements. The isotropic elasto-plastic model is the same as with MATX02. However, MATX27 allows material damage and brittle failure to be modeled.

4.

ICC controls the strain rate effect.

Altair Engineering

OptiStruct 13.0 Reference Guide 1199 Proprietary Information of Altair Engineering

5.

The failure plastic strain EPSMAX has no effect if the second continuation is defined.

6.

An element is removed if one layer reaches the tensile failure strain EPS1.

7.

This card is represented as an extension to a MAT1 material in HyperMesh.

1200 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MATX28 Bulk Data Entry MATX28 – Material Property Extension for Honeycomb Material for Geometric Nonlinear Analysis Description Defines additional material properties for Honeycomb material for geometric nonlinear analysis. This law is only applicable to solid elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MATX28

MID

(9)

TIID11

TIID22

TIID33

IFLAG1

FSC AI11

FSC AI22

FSC AI33

EPSFI11

EPSFI22

EPSFI33

TIID12

TIID23

TIID31

IFLAG2

FSC AI12

FSC AI23

FSC AI31

EPSFI12

EPSFI23

EPSFI31

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MAT9ORT

102

0.2

0.02

0.02

0.33

0.33

0.33

0.286E-7

0.1

0.01

0.1

11

22

33

NEGSTR

1.0

1.0

1.0

0

0

0

12

23

31

NEGSTR

1.0

1.0

1.0

MATX28

(10)

102

Altair Engineering

OptiStruct 13.0 Reference Guide 1201 Proprietary Information of Altair Engineering

0.0

0.0

0.0

Field

Contents

MID

Material ID of the associated MAT9ORT. See comment 1. No default (Integer > 0)

TIID11

Identification number of a TABLES1 that defines the initial yield stress function in direction 11. No default (Integer > 0)

TIID22

Identification number of a TABLES1 that defines the initial yield stress function in direction 22. No default (Integer > 0)

TIID33

Identification number of a TABLES1 that defines the initial yield stress function in direction 33. No default (Integer > 0)

IFLAG1

Strain formulation for yield functions 11, 22, and 33. See comment 4. Default = VOLSTR (VOLSTR, STR, or NEGSTR) VOLSTR - Yield stress is a function of volumetric strains. STR - Yield stress is a function of strains. NEGSTR - Yield stress is a function of negative strains.

FSCAI11

Scale factor on initial yield stress function in direction 11. Default = 1.0 (Real)

FSCAI22

Scale factor on initial yield stress function in direction 22. Default = 1.0 (Real)

FSCAI33

Scale factor on initial yield stress function in direction 33. Default = 1.0 (Real)

EPSFI11

Initial failure strain under tension or compression in direction 11. (Real)

EPSFI22

Initial failure strain under tension or compression in direction 22.

1202 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents (Real)

EPSFI33

Initial failure strain under tension or compression in direction 33. (Real)

TIID12

Identification number of a TABLES1 that defines the initial shear yield stress function in direction 12. No default (Integer > 0)

TIID23

Identification number of a TABLES1 that defines the initial shear yield stress function in direction 23. No default (Integer > 0)

TIID31

Identification number of a TABLES1 that defines the initial shear yield stress function in direction 31. No default (Integer > 0)

IFLAG2

Strain formulation for yield functions 12, 23, and 31. Default = VOLSTR (VOLSTR, STR, or NEGSTR) VOLSTR - Yield stress is a function of volumetric strains. STR - Yield stress is a function of strains. NEGSTR - Yield stress is a function of negative strains.

FSCAI12

Scale factor on initial shear yield stress function in direction 12. Default = 1.0 (Real)

FSCAI23

Scale factor on initial shear yield stress function in direction 23. Default = 1.0 (Real)

FSCAI31

Scale factor on initial shear yield stress function in direction 31. Default = 1.0 (Real)

EPSFI12

Initial failure strain under tension or compression in direction 12. (Real)

EPSFI23

Initial failure strain under tension or compression in direction 23. (Real)

Altair Engineering

OptiStruct 13.0 Reference Guide 1203 Proprietary Information of Altair Engineering

Field

Contents

EPSFI31

Initial failure strain under tension or compression in direction 31. (Real)

Comments 1.

The material identification number must be that of an existing MAT9ORT bulk data entry. Only one MATX28 material extension can be associated with a particular MAT9ORT.

2.

MATX28 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

This law is compatible with 10 node tetrahedron elements, and it is compatible with ISOLID = 1, 2, or 12 on PSOLIDX card.

4.

This law is not compatible with IFRAME = OFF, if it is referenced by the PSOLIDX card.

5.

When switching from a volumetric strain formulation to a strain formulation, IFLAGi = NEGSTR allows the same function definition to be retained.

6.

If one of the failure or shear failure strains is reached, the element is deleted.

7.

Transition strains define transition from initial yield stress function to residual yield stress function.

8.

If one of the transition or shear transition strains is reached, the element has yield stress described by residual functions in each direction. Transition is applied to the neighboring elements.

9.

This card is represented as an extension to a MAT9ORT material in HyperMesh.

1204 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MATX33 Bulk Data Entry MATX33 – Material Property Extension for Visco-Elastic Plastic Foam Material for Geometric Nonlinear Analysis Description Defines additional material properties for visco-elastic plastic foam material for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MATX33

MID

KA

TID

FSC ALE

P0

PHI

EPSV0

A

B

C

E1

E2

ET

ETAC

(10)

ETAS

Example

(1)

(2)

(3)

MAT1

133

0.11

MATX33

133

0

(4)

(5)

(6)

0.11

9.92E-07

(7)

Field

Contents

MID

Material ID of the associated MAT1 (See comment 1).

(8)

(9)

(10)

No default (Integer > 0) KA

Flag for analysis type. Default = ELAST (Character = ELAST, VISCO) ELAST: the skeletal behavior before yield is elastic. VISCO: the skeletal behavior before yield is visco-elastic.

Altair Engineering

OptiStruct 13.0 Reference Guide 1205 Proprietary Information of Altair Engineering

Field

Contents

TID

Identification number of TABLES1 entry that defines the yield stress vs. volumetric strain curve. No default (Integer > 0)

FSCALE

Scale factor for stress in yield curve. Default = 1.0 (Real)

P0

Initial air pressure (See comment 4). Default = 0.0 (Real)

PHI

Ratio of foam to polymer density. Default = 0.0 (Real)

EPSV0

Initial volumetric strain. Default = 0.0 (Real)

A

Yield parameter. Default = 0.0 (Real)

B

Yield parameter. Default = 1.0 (Real)

C

Yield parameter. Default = 1.0 (Real)

E1

Coefficient for Young's modulus update. No default (Real)

E2

Coefficient for Young's modulus update. No default (Real)

ET

Tangent modulus.

1206 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Field

Contents No default (Real > 0)

ETAC

Viscosity coefficient in pure compression. Default = 1.0 (Real > 0)

ETAS

Viscosity coefficient in pure shear. Default = 1.0 (Real > 0)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX33 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

This material can be used only with solid elements, typically used to model low density, closed cell polyurethane foams such as impact limiters.

4.

The air pressure is computed as Pair = P0 * where,

/ (1+

- Φ), with

= 0 + V/V0 - 1

is the volumetric strain, Φ is the porosity, P0 is the initial air pressure,

initial volumetric strain. The volumetric strain 5.

0 is the

< 0 in compression.

If TID is blank or zero, then σy = A + B(1+ Cγ ), with

= V/V0 - 1 = ρ/ρ0 - 1 = -µ/(1+µ)

6.

If TID is defined, σy vs.

7.

The Young’s modulus used in the calculation is E = max(E, E1

Altair Engineering

is read from input of the curve.

+ E2)

OptiStruct 13.0 Reference Guide 1207 Proprietary Information of Altair Engineering

This material assumes NU = 0 no matter what is defined on the corresponding MAT1. Hence, G = 0.5 * E. 8.

This card is represented as an extension to a MAT1 material in HyperMesh.

1208 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MATX36 Bulk Data Entry MATX36 – Material Property Extension for Piece-wise Linear Elastic-plastic Material for Geometric Nonlinear Analysis Description Defines additional material properties for piece-wise linear elastic-plastic material for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MATX36

MID

EPSMAX

EPST1

EPST2

EPSF

FSMOOTH

FC UT

IC H

TPID

PSC A

TID1

FSC A1

EPSR1

...

...

...

TIDi

FSC Ai

EPSRI

(10)

Example

(1)

(2)

(3)

MAT1

102

60.4

MATX36

102

10

1.0

7

1.0

Altair Engineering

(4)

(5)

(6)

0.33

2.70E-06

(7)

(8)

(9)

(10)

0.0

OptiStruct 13.0 Reference Guide 1209 Proprietary Information of Altair Engineering

Field

Contents

MID

Material identifier of the associated MAT1 (See comment 1). No default (Integer > 0)

EPSMAX

Failure plastic strain εmax Default = 1030 (Real > 0)

EPST1

Maximum tensile failure strain (See comment 5). Default = 1030

EPST2

(Real > 0)

Maximum tensile failure damage (See comment 6). Default = 2.0*1030

EPSF

(Real > 0)

Tensile strain for element deletion. Default = 3.0*1030 (Real > 0)

FSMOOTH

Flag for strain rate smoothing. Default = OFF (ON or OFF)

FCUT

Cutoff frequency for strain rate filtering. Only for shell and solid elements. Default = 1030 (Real > 0)

ICH

Hardening coefficient. Default = 0.0 (Real > 0) 0.0 - The hardening is a full isotropic model. 1.0 - Hardening uses the kinematic Prager-Ziegler model. Between 0.0 and 1.0 - Hardening is interpolated between the two models.

TPID

Identification number of a TABLES1 that defines pressure dependent yield stress function. No default (Integer > 0)

PSCA

Scale factor for stress in pressure dependent function.

1210 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents Default = 1.0 (Real)

TIDi

Identification number of a TABLES1 that defines the yield stress vs. plastic strain function corresponding to EPSRi. Separate functions must be defined for different strain rates. No default (Integer > 0)

FSCAi

Scale factor for TIDi. Default = 1.0 (Real)

EPSRi

Strain rate. Strain rate values must be given strictly in ascending order. (Real)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX36 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

The first point of yield stress functions (plastic strain vs. stress) should have a plastic strain value of zero. If the last point of the first (static) function equals 0 in stress, the default value of EPSMAX is set to the value of the corresponding plastic strain.

4.

When the plastic strain reaches EPSMAX, the element is deleted.

5.

If the first principal strain ε1 reaches εt1 = EPST1, the stress σ is reduced by

with εt2 = EPST2. 6.

If the first principal strain ε1 reaches εt2 = EPST2, the stress is reduced to 0 (but the element is not deleted).

7.

If the first principal strain ε1 reaches εf = EPSF, the element is deleted.

8.

Strain rate filtering is used to smooth strain rates. The input FCUT is available only for shell and solid elements.

9.

Hardening is defined by ICH. ICH = 0 – Fully isotropic hardening ICH = 1 – Prager-Ziegler kinematic hardening

Altair Engineering

OptiStruct 13.0 Reference Guide 1211 Proprietary Information of Altair Engineering

0 < ICH < 1 – Interpolation between the two models

10. The kinematic hardening model is not available with global formulation (NIP = 0 on PSHELX), that is hardening is fully isotropic. 11. In case of kinematic hardening and strain rate dependency, the yield stress depends on the strain rate. 12. TPID is used to distinguish the behavior in tension and compression for certain materials (that is pressure dependent yield). This is available for both shell and solid elements. The effective yield stress is then obtained by multiplying the nominal yield stress by the yield factor PSCA corresponding to the actual pressure. 13. The first function TID1 is used for strain rate values from 0 to the corresponding strain rate EPSR1. However, the last function used in the model does not extend to the maximum strain rate; for higher strain rates, a linear extrapolation will be applied. Hence, if < EPSRi, the yield stress is interpolated between TIDi and TIDi-1. If < EPSR1, TID1 is used. Above EPSRmax the yield stress is extrapolated. 14. Strain rate values must be given strictly in ascending order. Separate functions must be defined for different strain rates. 15. At least one strain rate is needed under which the yield stress vs. plastic strain function is defined. 16. This card is represented as a material in HyperMesh.

1212 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MATX42 Bulk Data Entry MATX42 – Material Property Extension for Ogden, Mooney-Rivlin Material for Geometric Nonlinear Analysis Description Defines additional material properties for Ogden, Mooney-Rivlin material for geometric nonlinear analysis. This material is used to model rubber, polymers, and elastomers. Format (1)

(2)

(3)

(4)

MATX42

MID

SC UT

LAW

MU1

MU4

(5)

(6)

TBID

FBULK

ALFA1

MU2

ALFA2

ALFA4

MU5

ALFA5

(7)

(8)

(9)

MU3

ALFA3

T3

(10)

Optional continuation lines for prony value: PRONY

G1

T1

G2

T2

G3

G4

T4

G5

T5

...

Example

(1)

(2)

(3)

MAT1

102

10.0

MATX42

102

LAW

Altair Engineering

0.10

(4)

2.0

(5)

(6)

0.495

6.0E-10

-0.010

-2.0

(7)

(8)

(9)

(10)

OptiStruct 13.0 Reference Guide 1213 Proprietary Information of Altair Engineering

Field

Contents

MID

Material ID of the associated MAT1 (See comment 1). No default (Integer > 0)

SCUT

Cut-off stress in tension. Default = 103 0 (Real > 0)

TBID

Identification number of a TABLES1 to define the bulk function f(J) that scales the bulk modulus vs. relative volume. If TBID = 0, f(J) = const. = 1.0. Default = 0 (Integer > 0)

FBULK

Scale factor for bulk function. Default = 1.0 (Real > 0)

LAW

Indicates that material parameters MUi and ALFAi follow.

MUi

Parameter µi (Real)

ALFAi

Parameter αi (Real)

PRONY

Indicates that prony model parameters Gi and Ti follow.

Gi

Parameter G for prony model. (Real)

Ti

Parameter T for prony model. (Real)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX42 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

1214 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

3.

Up to five pairs MUi, ALFAi are permitted.

4.

The recommended Poisson’s ratio for incompressible material is NU = 0.495. NU is defined on the corresponding MAT1.

5.

The strain energy density W is computed using the following equation

with λi being the ith principal stretch (λi = 1 + ε

i

, ε

i

is the ith principal engineering

strain). The Cauchy stress is computed as follows:

with J = λ1 * λ2 * λ3 being the relative volume:

The quantity P is the pressure: P = K * FBULK * f (J) * (J - 1) The Bulk Modulus K is:

with the ground shear modulus µ:

6.

An incompressible Mooney-Rivlin material is governed by W = C1 0 (I1 - 3) + C0 1 (I2 - 3) where, Ii is ith invariant of the right-hand Cauchy-Green Tensor. It can be modeled using the following parameters: µ1 = 2 * C1 0

Altair Engineering

OptiStruct 13.0 Reference Guide 1215 Proprietary Information of Altair Engineering

µ2 = -2 * C0 1 α1 = 2.0 α2 = -2.0 7.

The Kirchhoff viscous stress is given by the convolution integral:

and 8.

This card is represented as a material in HyperMesh.

1216 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MATX43 Bulk Data Entry MATX43 – Material Property Extension for Hill Orthotropic Material for Geometric Nonlinear Analysis Description Defines additional material properties for Hill Orthotropic material for geometric nonlinear analysis. This law is only applicable to two-dimensional elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATX43

MID

R00

R45

R90

C HARD

EPSPF

EPST1

EPST2

If strain rate dependent material, at least 1 time, at most 10 times TID1

FSC A1

EPSR1

TID2

FSC A2

EPSR2

…

…

…

Example

(1)

(2)

(3)

(4)

(5)

(6)

MAT8

102

0.7173

0.7173

0.3

0.4

MATX43

102

1.0

1.0

2.0

1

1.0

0.1

2

1.0

0.05

Altair Engineering

(7)

(8)

(9)

(10)

2.7

OptiStruct 13.0 Reference Guide 1217 Proprietary Information of Altair Engineering

Field

Contents

MID

Material ID of the associated MAT8. See comment 1. No default (Integer > 0)

R00

Lankford parameter at 0 degree. Default = 1.0 (Real)

R45

Lankford parameter at 45 degrees. Default = 1.0 (Real)

R90

Lankford parameter at 90 degrees. Default = 1.0 (Real)

CHARD

Hardening coefficient. 0.0 - The hardening is a full isotropic model. 1.0 - Hardening uses the kinematic Prager-Ziegler model. Between 0.0 and 1.0 - Hardening is interpolated between the two models. Default = 0.0 (1.0 > Real > 0.0)

EPSPF

Failure plastic strain. Default = 1030 (Real)

EPST1

Tensile failure strain. Default = 1030 (Real)

EPST2

Tensile failure strain. Default = 2.0*1030 (Real)

TIDi

Identification number of a TABLES1 that defines the yield stress vs. plastic strain function corresponding to EPSRi. Separate functions must be defined for different strain rates. Integer > 0

1218 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

FSCAi

Scale factor for ith function. Default= 1.0 (Real)

EPSRi

Strain rate for ith function. (Real)

Comments 1.

The material identification number must be that of an existing MAT8 bulk data entry. Only one MATX43 material extension can be associated with a particular MAT8. E1 must be equal to E2 on MAT8 that is extended by MATX43.

2.

MATX43 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

The yield stress is defined by a user function and the yield stress is compared to equivalent stress.

4.

Angles for Lankford parameters are defined with respect to orthotropic direction 1.

5.

The Lankford parameters rα are determined from a simple tensile test at an angle α to the orthotropic direction 1.

6.

The hardening coefficient is used to describe the hardening model. Its value must be between 0 and 1: if set to 0, the hardening is full isotropic. if set to 1, the hardening uses the kinematic Prager-Ziegler model.

Altair Engineering

OptiStruct 13.0 Reference Guide 1219 Proprietary Information of Altair Engineering

for any value between 0 and 1, the hardening is interpolated between the two models. 7.

If the last point of the first (static) function equals 0 in stress, default value of failure plastic strain EPSPF is set to the corresponding value of plastic strain, p.

8.

If plastic strain εp reaches failure plastic strain εpmax , the element is deleted.

9.

If ε1 (largest principal strain) > εt1(EPST1), stress is reduced according to the following relation:

10. If ε1 (largest principal strain) > εt2(EPST2), the stress is reduced to be 0 (but the element is not deleted). If

(EPSRn), yield is interpolated between ƒn and ƒn-1. If

(EPSR1), function ƒ1 is used. Above

, yield is extrapolated.

11. This card is represented as extension to a MAT8 material in HyperMesh.

1220 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MATX44 Bulk Data Entry MATX44 – Material Property Extension for Cowper-Symonds Elastic-plastic Material for Geometric Nonlinear Analysis Description Defines additional material properties for Cowper-Symonds elastic-plastic material for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MATX44

MID

A

B

N

IC H

SIGMAX

C

P

IC C

FSMOOTH

FC UT

EPSMAX

EPST1

EPST2

(10)

Example

(1)

(2)

(3)

MAT1

144

0.11

MATX44

144

(4)

(5)

(6)

0.11

9.92E-07

Field

Contents

MID

Material ID of the associated MAT1.

(7)

(8)

(9)

(10)

No default (Integer > 0) A

Plasticity yield stress. (Real > 0)

B

Plasticity hardening parameter. (Real > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1221 Proprietary Information of Altair Engineering

Field

Contents

N

Plasticity hardening exponent. Default = 1.0 (Real)

ICH

Hardening coefficient. 0.0: The hardening is a full isotropic model. 1.0: Hardening uses the kinematic Prager-Ziegler model. Between 0.0 and 1.0: Hardening is interpolated between the two models. Default = 0.0 (Real > 0)

SIGMAX

Maximum plastic stress σmax0 Default = 1030 (Real > 0)

C

Strain rate coefficient. Default = 0.0 (Real)

P

Strain rate exponent. Default = 1.0 (Real)

ICC

Flag for strain rate dependency of σmax (See comment 5). Default = ON (ON or OFF)

FSMOOTH

Flag for strain rate smoothing. Default = OFF (ON or OFF)

FCUT

Cutoff frequency for strain rate filtering. Default = 1030 (Real > 0)

EPSMAX

Failure plastic strain. Default = 1030 (Real > 0)

EPST1

Tensile rupture strain 1.

1222 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents Default = 1030 (Real > 0)

EPST2

Tensile rupture strain 2. Default = 2.0 * 1030 (Real > 0)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX44 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

The Cowper-Symonds models an elastic-plastic material, only for solids and shells. The basic principle is the same as the standard Johnson-Cook model; the only difference between the two lies in the expression for strain rate effect on flow stress

with εp being plastic strain, and 4.

being the strain rate.

Hardening is defined by ICH. ICH = 0 – Fully isotropic hardening. ICH = 1 – Prager-Ziegler kinematic hardening. 0 < ICH < 1 – Interpolation between the two models.

5.

ICC controls the strain rate effect.

Altair Engineering

OptiStruct 13.0 Reference Guide 1223 Proprietary Information of Altair Engineering

6.

No strain rate effects are considered in rod elements.

7.

Strain rate filtering is used to smooth strain rates. The input FCUT is available only for shell and solid elements.

8.

When the plastic strain reaches EPSMAX, the element is deleted.

9.

If the first principal strain ε1 reaches εt1 = EPST1, the stress σ is reduced by

with εt2 = EPST2. 10. If the first principal strain ε1 reaches εt2 = EPST2, the stress is reduced to 0 (but the element is not deleted). 11. If the first principal strain ε1 reaches εf = EPSF, the element is deleted. 12. This card is represented as an extension to a MAT1 material in HyperMesh.

1224 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MATX60 Bulk Data Entry MATX60 – Material Property Extension for Piece-wise Nonlinear Elastic-plastic Material for Geometric Nonlinear Analysis Description Defines additional material properties for piece-wise nonlinear elastic-plastic material for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

MATX60

MID

EPSPF

EPST1

EPST2

TPID

PSC A

(7)

FSMOOTH C HARD

(8)

(9)

(10)

FC UT

EPSF

Strain rate dependent material, at least 4 times, at most 10 times: TID1

FSC A1

EPSR1

TID2

FSC A2

EPSR2

...

...

...

Example

(1)

(2)

(3)

MAT1

102

900

MATX60

102

(4)

101

1.0

4.2E-7

102

1.0

4.2e6

Altair Engineering

(5)

(6)

0.33

1E1

(7)

(8)

(9)

(10)

OptiStruct 13.0 Reference Guide 1225 Proprietary Information of Altair Engineering

Field

Contents

MID

Material ID of the associated MAT1 (See comment 1). No default (Integer > 0)

EPSPF

Failure plastic strain. Default = 1030 (Real > 0)

EPST1

Maximum tensile failure strain (See comment 5). Default = 1030 (Real > 0)

EPST2

Maximum tensile failure damage (See comment 6). Default = 2.0*1030 (Real > 0)

FSMOOTH

Flag for strain rate smoothing. Default = OFF (ON or OFF)

CHARD

Hardening coefficient. 0.0: The hardening is a full isotropic model. 1.0: Hardening uses the kinematic Prager-Ziegler model. Between 0.0 and 1.0: Hardening is interpolated between the two models. Default = 0.0 (1.0 > Real > 0)

FCUT

Cutoff frequency for strain rate filtering. Only for shell and solid elements. Default = 1030 (Real > 0)

EPSF

Tensile strain for element deletion. Default = 3.0*1030 (Real > 0)

TPID

Identification number of a TABLES1 that defines pressure dependent yield stress function. No default (Integer > 0)

PSCA

Scale factor for stress in pressure dependent function.

1226 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents Default = 1.0 (Real)

TIDi

Identification number of a TABLES1 that defines the yield stress vs. plastic strain rate function corresponding to EPSRi. Separate functions must be defined for different strain rates. No default (Integer > 0)

FSCAi

Scale factor for TIDi. Default = 1.0 (Real)

EPSRi

Strain rate. Strain rate values must be given strictly in ascending order. (Real)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATX60 material extension can be associated with a particular MAT1.

2.

MATX60 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

The first point of yield stress functions (plastic strain vs. stress) should have a plastic strain value of zero. If the last point of the first (static) function equals 0 in stress, the default value of EPSMAX is set to the value of the corresponding plastic strain.

4.

When the plastic strain reaches EPSMAX, the element is deleted.

5.

If the first principal strain ε1 reaches εt1 (EPST1), the stress σ is reduced by

with εt2 = EPST2. 6.

If the first principal strain ε1 reaches εt2 (EPST2), the stress is reduced to 0 (but the element is not deleted).

7.

If the first principal strain ε1 reaches εf (EPSF), the element is deleted.

8.

Strain rate filtering is used to smooth strain rates. The input FCUT is available only for shell and solid elements.

9.

Hardening is defined by ICH.

Altair Engineering

OptiStruct 13.0 Reference Guide 1227 Proprietary Information of Altair Engineering

ICH = 0 – Fully isotropic hardening ICH = 1 – Prager-Ziegler kinematic hardening 0 < ICH < 1 – Interpolation between the two models

Isotropic Hardening

Prager-Ziegler Kinematic Hardening

10. The kinematic hardening model is not available with global formulation (NIP = 0 on PSHELX), that is hardening is fully isotropic. 11. In case of kinematic hardening and strain rate dependency, the yield stress depends on the strain rate. 12. TPID is used to distinguish the behavior in tension and compression for certain materials (that is pressure dependent yield). This is available for solid elements only. The effective yield stress is then obtained by multiplying the nominal yield stress by the yield factor PSCA corresponding to the actual pressure. 13. If

(

=EPSRn) , yield stress is a cubic interpolation between functions f n-

1, f n, f n+1 and f n+2.

If

, yield stress is interpolated between functions f 1, f 2, and f 3.

If , where Nfunc is the function number for strain rate, yield is extrapolated between functions f Nfunc-3, f Nfunc-2, f Nfunc-1 and f Nfunc. If

, yield is extrapolated between functions f Nfunc-2, f Nfunc-1, and f Nfunc.

14. Strain rate values must be given strictly in ascending order. Separate functions must be defined for different strain rates. 15. This card is represented as an extension to a MAT1 material in HyperMesh.

1228 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MATX62 Bulk Data Entry MATX62 – Material Property Extension for Hyper-visco-elastic Material for Geometric Nonlinear Analysis Description Defines additional material properties for Hyper-visco-elastic material for geometric nonlinear analysis. This material is used to model rubber, polymers, and elastomers. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MATX62

MID

MUMAX

LAW

(9)

MU1

ALFA1

MU2

ALFA2

MU3

ALFA3

MU4

ALFA4

MU5

ALFA5

...

(10)

Optional continuation lines for Maxwell value: MAXWELL

GAM1

T1

GAM2

T2

GAM3

GAM4

T4

GAM5

T5

...

T3

Example

(1)

(2)

(3)

MAT1

102

10.0

MATX62

102

LAW

Altair Engineering

0.10

(4)

2.0

(5)

(6)

0.495

6.0E-10

-0.010

-2.0

(7)

(8)

(9)

(10)

OptiStruct 13.0 Reference Guide 1229 Proprietary Information of Altair Engineering

Field

Contents

MID

Material ID of the associated MAT1 (See comment 1). No default (Integer > 0)

MUMAX

Maximum viscosity. Default = 1030 (Real)

LAW

Indicates that material parameters MUi and ALFAi follow.

MUi

Parameter µi (Real)

ALFAi

Parameter αi (Real)

MAXWELL

Indicates that MAXWELL model parameter pairs GAMi and Ti follow.

GAMi

Stiffness ratio γ i. (Real)

Ti

Time relaxation τi. (Real)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX62 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

This material is compatible with solid and shell elements.

4.

NU is defined on the corresponding MAT1.

5.

If no pair GAM1, T1 is given the law is hyper-elastic.

1230 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

6.

The strain energy density W is computed using the following equation:

with λi being the ith principal stretch, J = λ1 * λ2 * λ3 being the relative volume and

. O < NU < 0.5 The ground shear modulus is:

7.

This card is represented as a material in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1231 Proprietary Information of Altair Engineering

MATX65 Bulk Data Entry MATX65 – Material Property Extension for Tabulated Strain Rate Dependent Elastic-Plastic Material for Geometric Nonlinear Analysis Description Defines additional material properties for tabulated strain rate dependent elastic-plastic material for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

MATX65

MID

EPSMAX

FSMOOTH

FC UT

NLOAD

(8)

(9)

(10)

If NLOAD > 1, NLOAD times TIDL

TIDU

EPSR

FSC AL

Example

(1)

(2)

(3)

MAT1

91

60.4

MATX65

91

2.70E-06

1

2

(4)

(5)

(6)

0.33

2.70E-06

(7)

(8)

(9)

(10)

1

Field

Contents

MID

Material ID of the associated MAT1 (See comment 1). No default (Integer > 0)

1232 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

EPSMAX

Failure plastic strain εmax (Real > 0)

FSMOOTH

Strain rate filtering flag. Default = OFF (ON or OFF)

FCUT

Cutoff frequency for strain rate filtering. Default = 1.E30 (Real > 0)

NLOAD

Number of loading/unloading stress-strain function pairs. Default = 0 (Integer > 0)

TIDL

Identification number of TABLES1 entry that defines the loading stress-strain function. (Integer > 0)

TIDU

Identification number of TABLES1 entry that defines the unloading stressstrain function. (Integer > 0)

EPSR

Strain rate. Default = 1.0 (Real)

FSCAL

Scale factor for stress. Default = 1.0 (Real)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX65 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

The material law is defined by pairs of stress functions for loading and unloading at a constant strain rate. For each strain rate, the yield stress is defined by the intersection between loading and unloading curves. Unloading follows unloading curve shifted by plastic strain value. Strain rates are interpolated using input values. In the elastic range, stress smaller than the yield value, the material behavior is elastic with hysteresis. It is

Altair Engineering

OptiStruct 13.0 Reference Guide 1233 Proprietary Information of Altair Engineering

limited by loading and unloading curves.

Loading and unloading function sets for constant strain rates.

The Young's modulus must be greater than the maximum function slopes, and is used to follow loading and unloading paths between limiting curves.

For a constant strain rate, user defined functions set the limits for the cycling loading.

1234 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

4.

This card is represented as a material in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1235 Proprietary Information of Altair Engineering

MATX68 Bulk Data Entry MATX68 – Material Property Extension for Honeycomb Material for Geometric Nonlinear Analysis Description Defines additional material properties for Honeycomb material for geometric nonlinear analysis. This law is only applicable to solid elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MATX68

MID

TIID11

TIID22

TIID33

IFLAG1

FSC AI11

FSC AI22

FSC AI33

EPSFI11

EPSFI22

EPSFI33

TIID12

TIID23

TIID31

IFLAG2

FSC AI12

FSC AI23

FSC AI31

EPSFI12

EPSFI23

EPSFI31

TIID21

TIID32

TIID13

FSC AI21

FSC AI32

FSC AI13

TRID11

TRID22

TRID33

FSC AR11

FSC AR22

FSC AR33

EPST11

EPST22

EPST33

TRID12

TRID23

TRID31

FSC AR12

FSC AR23

FSC AR31

EPST12

EPST23

EPST31

TRID21

TRID32

TRID13

FSC AR21

FSC AR32

FSC AR13

(9)

(10)

Example

1236 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MAT9ORT

102

0.2

0.02

0.02

0.33

0.33

0.33

0.286E-7

0.1

0.01

0.1

11

22

33

NEGSTR

1.0

1.0

1.0

0

0

0

12

23

31

NEGSTR

1.0

1.0

1.0

0.0

0.0

0.0

21

32

13

1.0

1.0

1.0

11

22

33

1.0

1.0

1.0

0.8

0.0

0.0

12

23

31

1.0

1.0

1.0

0.0

0.0

0.0

21

32

13

1.0

1.0

1.0

MATX68

(10)

102

Field

Contents

MID

Material ID of the associated MAT9ORT. See comment 1. No default (Integer > 0)

TIID11

Identification number of a TABLES1 that defines initial yield stress function in direction 11. No default (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1237 Proprietary Information of Altair Engineering

Field

Contents

TIID22

Identification number of a TABLES1 that defines initial yield stress function in direction 22. No default (Integer > 0)

TIID33

Identification number of a TABLES1 that defines initial yield stress function in direction 33. No default (Integer > 0)

IFLAG1

Strain formulation for yield functions 11, 22, and 33. See comment 4. VOLSTR - Yield stress is a function of volumetric strains. STR - Yield stress is a function of strains. NEGSTR - Yield stress is a function of negative strains. Default = VOLSTR (VOLSTR, STR, NEGSTR)

FSCAI11

Scale factor on initial yield stress function in direction 11. Default = 1.0 (Real)

FSCAI22

Scale factor on initial yield stress function in direction 22. Default = 1.0 (Real)

FSCAI33

Scale factor on initial yield stress function in direction 33. Default = 1.0 (Real)

EPSFI11

Initial failure strain under tension or compression in direction 11. (Real)

EPSFI22

Initial failure strain under tension or compression in direction 22. (Real)

EPSFI33

Initial failure strain under tension or compression in direction 33. (Real)

TIID12

Identification number of a TABLES1 that defines initial shear yield stress

1238 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents function in direction 12. No default (Integer > 0)

TIID23

Identification number of a TABLES1 that defines Initial shear yield stress function in direction 23. No default (Integer > 0)

TIID31

Identification number of a TABLES1 that defines Initial shear yield stress function in direction 31. No default (Integer > 0)

IFLAG2

Strain formulation for yield functions 12, 23, and 31. VOLSTR - Yield stress is a function of volumetric strains. STR - Yield stress is a function of strains. NEGSTR - Yield stress is a function of negative strains. Default = VOLSTR (VOLSTR, STR, NEGSTR)

FSCAI12

Scale factor on initial shear yield stress function in direction 12. Default = 1.0 (Real)

FSCAI23

Scale factor on initial shear yield stress function in direction 23. Default = 1.0 (Real)

FSCAI31

Scale factor on initial shear yield stress function in direction 31. Default = 1.0 (Real)

EPSFI12

Initial failure strain under tension or compression in direction 12. (Real)

EPSFI23

Initial failure strain under tension or compression in direction 23. (Real)

EPSFI31

Initial failure strain under tension or compression in direction 31.

Altair Engineering

OptiStruct 13.0 Reference Guide 1239 Proprietary Information of Altair Engineering

Field

Contents (Real)

TIID21

Identification number of a TABLES1 that defines Initial shear yield stress function in direction 21. No default (Integer > 0)

TIID32

Identification number of a TABLES1 that defines Initial shear yield stress function in direction 32. No default (Integer > 0)

TIID13

Identification number of a TABLES1 that defines Initial shear yield stress function in direction 13. No default (Integer > 0)

FSCAI21

Scale factor on initial shear yield stress function in direction 21. Default = 1.0 (Real)

FSCAI32

Scale factor on initial shear yield stress function in direction 32. Default = 1.0 (Real)

FSCAI13

Scale factor on initial shear yield stress function in direction 13. Default = 1.0 (Real)

TRID11

Identification number of a TABLES1 that defines residual yield stress function in direction 11. No default (Integer > 0)

TRID22

Identification number of a TABLES1 that defines residual yield stress function in direction 22. No default (Integer > 0)

TRID33

Identification number of a TABLES1 that defines residual yield stress function in direction 33. No default (Integer > 0)

1240 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

FSCAR11

Scale factor on residual yield stress function in direction 11. Default = 1.0 (Real)

FSCAR22

Scale factor on residual yield stress function in direction 22. Default = 1.0 (Real)

FSCAR33

Scale factor on residual yield stress function in direction 33. Default = 1.0 (Real)

EPST11

Transition strain in direction 11. (Real)

EPST22

Transition strain in direction 22. (Real)

EPST33

Transition strain in direction 33. (Real)

TRID12

Identification number of a TABLES1 that defines residual shear yield stress function in direction 12. No default (Integer > 0)

TRID23

Identification number of a TABLES1 that defines residual shear yield stress function in direction 23. No default (Integer > 0)

TRID31

Identification number of a TABLES1 that defines residual shear yield stress function in direction 31. No default (Integer > 0)

FSCAR12

Scale factor on residual shear yield stress function in direction 12. Default = 1.0 (Real)

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Field

Contents

FSCAR23

Scale factor on residual shear yield stress function in direction 23. Default = 1.0 (Real)

FSCAR31

Scale factor on residual shear yield stress function in direction 31. Default = 1.0 (Real)

EPST12

Transition strain in direction 12. (Real)

EPST23

Transition strain in direction 23. (Real)

EPST31

Transition strain in direction 31. (Real)

TRID21

Identification number of a TABLES1 that defines residual shear yield stress function in direction 21. No default (Integer > 0)

TRID32

Identification number of a TABLES1 that defines residual shear yield stress function in direction 32. No default (Integer > 0)

TRID13

Identification number of a TABLES1 that defines residual shear yield stress function in direction 13. No default (Integer > 0)

FSCAR21

Scale factor on residual shear yield stress function in direction 21. Default = 1.0 (Real)

FSCAR32

Scale factor on residual shear yield stress function in direction 32. Default = 1.0 (Real)

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Field

Contents

FSCAR13

Scale factor on residual shear yield stress function in direction 13. Default = 1.0 (Real)

Comments 1.

The material identification number must be that of an existing MAT9ORT bulk data entry. Only one MATX68 material extension can be associated with a particular MAT9ORT.

2.

MATX68 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

This law is compatible with 8 node brick elements with ISOLID =1 or ISOLID =2 on PSOLIDX only.

4.

When switching from a volumetric strain formulation to a strain formulation, IFLAGi = NEGSTR allows the same function definition to be retained.

5.

If one of the failure or shear failure strains is reached, the element is deleted.

6.

Transition strains define transition from initial yield stress function to residual yield stress function.

7.

If one of the transition or shear transition strains is reached, the element has yield stress described by residual functions in each direction, Transition is applied to the neighbor elements.

8.

This card is represented as extension to a MAT9ORT material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1243 Proprietary Information of Altair Engineering

MATX70 Bulk Data Entry MATX70 – Material Property Extension for Tabulated Visco-elastic Foam Material for Geometric Nonlinear Analysis Description Defines additional material properties for tabulated visco-elastic foam material for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MATX70

MID

EMAX

EPSMAX

FSMOOTH

FC UT

NLOAD

NULOAD

IFLAG

SHAPE

HYS

If NLOAD > 1, NLOAD times TIDL

EPSRL

FSC ALL

If NULOAD > 0, NULOAD times TIDU

EPSRU

FSC ALU

Example

(1)

(2)

(3)

MAT1

170

0.1

MATX70

170

1.0

(4)

0.8

(5)

(6)

0.1

9.9E-07

(7)

1

(8)

(9)

(10)

4

2

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Field

Contents

MID

Material ID of the associated MAT1 (See comment 1). No default (Integer > 0)

EMAX

Maximum young modulus . (Real > 0)

EPSMAX

Maximum plastic (failure) strain. (Real > 0)

FSMOOTH

Strain rate smoothing flag. Default = OFF (ON or OFF)

FCUT

Cutoff frequency for strain rate filtering. Default = 1.E30 (Real > 0)

NLOAD

Number of loading stress-strain function. Default = 1 (Integer > 1)

NULOAD

Number of unloading stress-strain function. If FLAG in this card is 1, 2, 3, or 4, NULOAD must be zero. Default = 1, if FLAG = 0 Default = 0, if FLAG = 1, 2, 3, or 4 (Integer > 0)

IFLAG

Flag to control the loading/unloading behavior (See comment 5). Default = 0 (Integer) 0 – Behavior follows the loading and unloading curves respectively. 1 – Behavior follows the loading/unloading curves. For unloading, the deviatoric stress is modified. 2 – Behavior follows the loading/unloading curves. For unloading, the stress tensor is modified.

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Contents 3 – The loading curve is used for both loading and unloading. For unloading, the deviatoric stress is modified. The unloading curves are ignored. 4 - The loading curve is used for both loading and unloading. For unloading, the stress tensor is modified. The unloading curves are ignored.

SHAPE

Shape factor. Default = 1.0 (Real)

HYS

Hysteresis unloading factor. Default = 1.0 (Real)

TIDL

Identification number of TABLES1 entry that defines the loading function. (Integer > 0)

EPSRL

Strain rate for loading function. Default = 0.0 (Real)

FSCALL

Scale factor for loading function. Default = 1.0 (Real)

TIDU

Identification number of TABLES1 entry that defines the unloading function. No default (Integer > 0)

EPSRU

Strain rate for unloading function. Default = 0.0 (Real)

FSCALU

Scale factor for unloading function. Default = 1.0 (Real)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX70 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

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3.

This material law can be used only with solid elements. The corresponding PSOLIDX property must define ISOLID = 1 (Belytschko element), ISMSTR = 1 (small strain), and IFRAME = OFF (not co-rotational).

4.

The loading and unloading functions use engineering stress-strain curve.

Loading and unloading stress-strain curves

5.

The loading and unloading behavior is determined by IFLAG. IFLAG = 0 - The material behavior follows the defined curves for loading and unloading. NLOAD and NULOAD must be greater than 0. IFLAG = 1 - Both loading curves are used respectively. For unloading, the deviatoric stress is modified by using the quasi-static unloading curve σ = (1 - D)(σ + p*I) – p*I where, D is calculated from the quasi-static unloading curve,

are the current stresses computed respectively from the unloading and quasi-static curves. The pressure is: p = -(σxx + σyy + σzz) / 3 IFLAG = 2 - Both loading and unloading curves are used respectively. For unloading, the stress tensor is modified using the quasi-static unloading curve σ = (1 - D)σ, where D is calculated from the quasi-static unloading curve,

are the current stresses computed respectively from the unloading and quasi-static curves.

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OptiStruct 13.0 Reference Guide 1247 Proprietary Information of Altair Engineering

IFLAG = 3 - The loading curves are used for both loading and unloading behavior. The unloading curve is ignored. The deviatoric unloading stress is modified using σ = (1 - D)(σ + p*I) – p*I

where, Wcur and Wmax are the current and maximum energy, respectively. IFLAG = 4 - The loading curves are used for both loading and unloading behavior. The unloading curve is ignored. The unloading stress tensor is modified using σ = (1 - D)σ.

where, Wcur and Wmax are the current and maximum energy, respectively. For IFLAG = 3, 4 the unloading curves are not used. 6.

For stresses above the last load function, the behavior is extrapolated by using the two last load functions. In order to avoid huge stress values, it is recommended to repeat the last load function.

7.

When maximum plastic strain EPSMAX is reached, EMAX is used whatever the curve definition is.

8.

If EMAX is blank, EMAX is set and equal to Young modulus on MAT1 card.

9.

If EPSMAX is blank, it will be calculated automatically if EMAX is less than the maximum tangent according to the input stress-strain curves.

10. Young's modulus E on MAT1 card would be modified automatically if it is less than the initial value according to the input stress-strain curves' tangents. 11. This card is represented as a material in HyperMesh.

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MATX82 Bulk Data Entry MATX82 – Material Property Extension for Ogden Material for Geometric Nonlinear Analysis Description Defines additional material properties for Ogden material for geometric nonlinear analysis. This material is used to model rubber, polymers, and elastomers. Format (1)

(2)

MATX82

MID

LAW

(3)

(4)

(5)

(6)

(7)

(8)

MU1

ALFA1

D1

MU2

ALFA2

D2

MU3

ALFA3

D3

MU4

ALFA4

D4

(9)

(10)

...

Example

(1)

(2)

(3)

MAT1

102

10.0

MATX82

102

LAW

0.10

(4)

2.0

(5)

(6)

0.495

6.0E-10

-0.010

(7)

(8)

(9)

(10)

-2.0

Field

Contents

MID

Material ID of the associated MAT1 (See comment 1). No default (Integer > 0)

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Field

Contents

LAW

Indicates that material parameters MUi, ALFAi, and Di follow.

MUi

Parameter µi (Real)

ALFAi

Parameter αi (Real)

Di

Parameter Di (Real)

Comments 1.

The material identification number must be that of an existing MAT1 bulk data entry. Only one MATXi material extension can be associated with a particular MAT1.

2.

MATX82 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

NU is defined on the corresponding MAT1. For material without Poisson effect, a small NU (for example, =1.E-10) should be defined.

4.

The strain energy density W is computed using the following equation

with λi being the ith principal stretch, J = λ1 * λ2 * λ3 being the relative volume and

. 5.

The Bulk Modulus K is: If NU = 0, then

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1

is modified to respect

If NU = 0 and D1 = 0, then u = 0.475. 6.

The ground shear modulus is

7.

This card is represented as a material in HyperMesh.

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OptiStruct 13.0 Reference Guide 1251 Proprietary Information of Altair Engineering

MBACT Bulk Data Entry MBACT – Activate an Entity/set in the Multi-body System Description Defines the entity/set that needs to be activated in the multi-body system for the subsequent simulation. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

MBAC T

ID

ETYPE

ID1

ID2

ID3

…

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MBAC T

ID

ETYPE

IDST

THRU

IDEND

(8)

(9)

(10)

(8)

(9)

(10)

or

Example

(1)

(2)

(3)

(4)

MBAC T

ID

MOTION

92

(5)

Field

Contents

ID

Unique identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) ETYPE

Entity type that needs to be activated. (Option – "CMBEAM", "CMBUSH", "CMSPDP", "JOINT", "MLOAD", or "MOTION")

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Field

Contents

ID1, ID2, …

Entity/Set IDs that need to be activated. (Integer > 0)

IDST

Entity/Set ID range start. (Integer > 0)

THRU

Keyword to indicate entity/set ID range is specified.

IDEND

Entity/Set ID range end. (Integer > IDST)

Comments 1.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1253 Proprietary Information of Altair Engineering

MBCNTDS Bulk Data Entry MBCNTDS – Multi-body Contact with Deformable Surface Description Defines a Multi-body Contact between a set of nodes and a deformable surface. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBC NTDS

C ID

SID

SRFID

C NFTYPE

STIFF

DAMP

RADIUS

(9)

(10)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBC NTD S

2

21

4

LINEAR

1E6

10

.1

Field

Contents

CID

Contact identification number. No default (Integer > 0)

SID1

Set identification number of a set of nodes. No default (Integer > 0)

SRFID

Multi-body deformable surface (MBDSRF) identification number. No default (Integer > 0)

CNFTYPE

Contact Normal Force Type. Select from LINEAR and POISSON. No default (CHARACTER: LINEAR, POISSON)

STIFF

For CNFTYPE=LINEAR, this parameter specifies the interface stiffness coefficient. For CNFTYPE=POISSON, this parameter specifies the penalty parameter

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Field

Contents which is related to the stiffness RJTODO. Default = 0.0 (Real > 0.0)

DAMP

For CNFTYPE=LINEAR, this parameter specifies the interface damping. Default = 0.0 (Real > 0) For CNFTYPE=POISSON, this parameter specifies the coefficient of restitution value for the contact. Default = 1.0 (0.0 < Real < 1.0)

RADIUS

Radius of the sphere geometry centered at the origin of the I marker. Default = 0.0 (Real > 0)

Comments 1.

This card is represented as a group in HyperMesh.

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MBCNTR Bulk Data Entry MBCNTR – Multi-body Contact of Type Rigid to Rigid Description Defines a Multi-body Contact between rigid bodies. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MBC NTR

C ID

SID1

SID2

C NFTYPE

PENAL

C OR

MUSTAT

MUDYN

C FFTYPE

STVEL

FTVEL

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBC NTR

2

4

7

POISSON

1E6

.5

.7

.3

C OUL

.1

.8

Field

Contents

CID

Contact identification number.

(10)

No default (Integer > 0) SID1

Set identification number for a set of elements. No default (Integer > 0)

SID2

Set identification number for a set of elements.

CNFTYPE

Contact normal force type. Default = POISSON

PENAL

Penalty factor.

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Field

Contents Default = 1.0 (Real > 0.0)

COR

Coefficient of restitution. Default = 1.0 (0.0 < Real < 1.0)

MUSTAT

Coefficient of static friction. Default = 0.0 (Real > 0.0)

MUDYN

Coefficient of dynamic friction. Default = 0.0 (Real > 0.0)

CFFTYPE

Contact friction force type Default = (COUL, NONE, DYNA)

STVEL

Stiction transition velocity. Defines the slip velocity at which the static coefficient of friction MUSTAT is applied. Default = 0.0 (Real > 0.0)

FTVEL

Friction transition velocity. Defines the slip velocity at which the dynamic coefficient of friction MUDYN is applied. Default = 0.0 (Real > 0.0)

Comments 1.

This card is represented as a group in HyperMesh.

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OptiStruct 13.0 Reference Guide 1257 Proprietary Information of Altair Engineering

MBCRV Bulk Data Entry MBCRV – XY Curve Definition Description Specifies the data used to define a curve. Format (1)

(2)

(3)

MBC RV

C VID

LINEAR

X1

Y1

(4)

(5)

(6)

(7)

(8)

(9)

X2

Y2

…

…

Xn

Yn

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBC RV

399

1.0

1.1

2.0

0.0

3.0

14.2

4.0

19.9

5.0

12.1

Field

Contents

CVID

Curve identification number.

(10)

No default (Integer > 0) LINEAR

If the LINEAR keyword is specified, linear extrapolation is used to determine the curve data when the independent coordinate goes out of the range specified on the Xi fields. If this field is blank, no extrapolation is applied and an ERROR is output when the independent coordinate goes out of range.

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Field

Contents Default = blank

X1, X2, X3, …, Xn

Independent curve data. No default (Real, X1 < X2 < X3 < …)

Y1, Y2, Y3, …, Yn

Dependent curve data. No default (Real)

Comments 1.

This card is represented as a curve in HyperMesh.

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OptiStruct 13.0 Reference Guide 1259 Proprietary Information of Altair Engineering

MBCVCV Bulk Data Entry MBCVCV – Multi-body Curve to Curve Constraint Description Defines a Curve to Curve Constraint. Format (1)

(2)

(3)

(4)

(5)

(6)

MBC VC V

JID

blank

PC ID1

G3

V1

blank

blank

PC ID2

G4

V2

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

MBC VC V

1

1

0

0

2

0

1

Field

Contents

JID

Joint identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) PCID1

Parametric curve (MBPCRV) identification number. No default (Integer > 0)

PCID2

Parametric curve (MBPCRV) identification number. No default (Integer > 0)

G3

This grid specifies the guess for the initial contact point on the first curve.

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Field

Contents Although this parameter is optional, specifying it helps the solver in determining the initial contact point.

V1

Specifies the sliding velocity of the contact point relative to the part on which the curve is etched. V1 is positive when contact point is moving toward the start of the curve and vice-versa. Default = 0.0 (Real)

G4

This grid specifies the guess for the initial contact point on the second curve. Although this parameter is optional, specifying it helps the solver in determining the initial contact point.

V2

Specifies the sliding velocity of the contact point relative to the part on which the curve is etched. V2 is positive when contact point is moving toward the start of the curve and vice-versa. Default = 0.0 (Real)

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OptiStruct 13.0 Reference Guide 1261 Proprietary Information of Altair Engineering

MBDCRV Bulk Data Entry MBDCRV – Multi-body Deformable Curve Description Defines an ordered list of grids as a Multi-body Deformable Curve. Format (1)

(2)

MBDC RV

(3)

DC ID

G1

(4)

ENDTYPE LAMBDAL L

G2

(5)

(6)

(7)

ENDTYPE R

LAMBDA R

NSEG

G3

(8)

(9)

(10)

…

Example

(1) MBDC RV

(2)

(3)

1

NATURA L

201

202

(4)

(5)

(6)

(7)

(8)

C ANTILEVE R

0.5

100

5

204

205

203

Field

Contents

DCID

Curve identification number.

(9)

(10)

No default (Integer > 0) ENDTYPEL

Select from NATURAL, PARABOLIC, PERIODIC and CANTILEVER. See comment 1. Default = NATURAL

LAMBDAL

This parameter is only applicable for CANTILEVER type end condition. It should be left blank for other end conditions. A real valued parameter in the interval [0,1] that controls the left end condition for CUBIC spline interpolation. A value of 0 implies NATURAL end condition while a value of 1 implies PARABOLIC end condition.

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Field

Contents Default = 0.0 (0.0 < Real < 1.0)

ENDTYPER

Select from: NATURAL, PARABOLIC, PERIODIC and CANTILEVER. See comment 1. Default = NATURAL

LAMBDAR

This parameter is only applicable for CANTILEVER type end condition. It should be left blank for other end conditions. A real valued parameter in the interval [0,1] that controls the left end condition for CUBIC spline interpolation. A value of 0 implies NATURAL end condition while a value of 1 implies PARABOLIC end condition. Default = 0.0 (0.0 < Real < 1.0)

NSEG

Number of segments used to visualize the deformable curve in animation. No default (Integer > 0)

G1, G2, G3, …

Ordered list of grid IDs defining the curve.

Comments 1.

The deformable curve is generated using the CUBIC spline interpolation which requires assumptions on the second derivative of the interpolating function at either end of the curve. The keywords NATURAL, PARABOLIC, PERIODIC and CANTILEVER represent the four standard assumptions defined as follows:

Note that λ =0.0 implies NATURAL (or free) end conditions and λ =1.0 implies PARABOLIC end conditions. 2.

This card is represented as a set in HyperMesh.

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OptiStruct 13.0 Reference Guide 1263 Proprietary Information of Altair Engineering

MBDEACT Bulk Data Entry MBDEACT – Deactivate an Entity/set in the Multi-body System Description Defines the entity/set that needs to be deactivated in the multi-body system for the subsequent simulation. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

MBDEAC T

ID

ETYPE

ID1

ID2

ID3

…

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MBDEAC T

ID

ETYPE

IDST

THRU

IDEND

(8)

(9)

(10)

(8)

(9)

(10)

or

Example

(1)

(2)

(3)

(4)

(5)

(6)

MBDEAC T

ID

MOTION

92

94

199

Field

Contents

ID

Unique identification number.

(7)

(8)

(9)

(10)

(Integer > 0) ETYPE

Entity type that needs to be deactivated. (Option – "CMBEAM", "CMBUSH", "CMSPDP2", "JOINT", "MLOAD", or "MOTION")

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Field

Contents

ID1, ID2, …

Entity/Set ID that needs to be deactivated. (Integer > 0)

IDST

Entity/Set ID range start. (Integer > 0)

THRU

Keyword to indicate entity/set ID range is specified.

IDEND

Entity/Set ID range end. (Integer > IDST)

Comments 1.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1265 Proprietary Information of Altair Engineering

MBDSRF Bulk Data Entry MBDSRF – Multi-body Deformable Surface Description Defines a multi-body deformable surface. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBDSRF

SRFID

NROW

NC OL

ENDTYPE

NSEGU

NSEGV

G1

G2

G3

G4

G5

G6

(9)

(10)

…

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MBDSRF

1

3

6

NATURAL

100

100

201

202

203

204

205

209

210

211

212

213

217

218

Field

Contents

SRFID

Surface identification number.

(8)

(9)

206

207

206

214

215

216

(10)

No default (Integer > 0) NROW

Number of rows of nodes.

NCOL

Number of columns of nodes.

ENDTYPE

Select from: NATURAL, PARABOLIC and PERIODIC. See comment 1.

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Field

Contents Default = NATURAL

NSEGU, NSEGV Number of segments along the U and V coordinates used to discretize the deformable surface for animation purposes. No default (Integer > 0) G1, G2, …

Row-wise list of nodes. The first NROW IDs form the first row; the second NROW IDs form the second row, and so on. The list must contain a total of NROW*NCOL grid IDs.

Comments 1.

The deformable surface is generated using the CUBIC spline interpolation which requires assumptions on the second derivative of the interpolating function at the end of the surface. The keywords NATURAL, PARABOLIC and PERIODIC represent assumptions defined as follows:

2.

The MBDSRF element is not supported by the Force Imbalance method of static equilibrium.

3.

The MBDSRF element does not possess any inherent inertia, stiffness or damping.

4.

This card is represented as a set in HyperMesh.

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MBFRC Bulk Data Entry MBFRC – Force for Multi-body Solution Sequence Description Defines a constant force at a grid point by specifying a vector. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBFRC

SID

G1

C ID

F

G3/N1

N2

N3

G2

(10)

G4

Example

(1)

(2)

(3)

MBFRC

3

345

(4)

(5)

(6)

(7)

(8)

100.0

0.0

1.0

0.0

(9)

(10)

201

Field

Contents

SID

Load set identification number. No default (Integer > 0)

G1

Grid point identification number where the action force is applied. No default (Integer > 0)

CID

Coordinate system identification number. Blank or 0 infer the basic coordinate system. Default = 0 (Integer > 0 or blank)

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Field

Contents

F

Force magnitude. No default (Real)

G3

Grid point identification number to optionally supply N1, N2, N3 in conjunction with G1. (Integer > 0)

N1, N2, N3

Defines the direction of the force vector. At least one of the vector components must be non-zero. Default = 0.0 (Real)

G2

Grid point identification number where the reaction force is applied. If blank, then the force is an action-only force. Default = blank (Integer > 0 or blank)

G4

Grid point identification number whose parent body hosts the coordinate system with respect to which the force is defined. The force vector changes direction with the orientation of the body. See comment 1. Default = blank (Integer > 0 or blank)

Comments 1.

If G4 is not specified, the force is defined with respect to the ground body (that is the basic coordinate systems).

2.

This card is represented as a force load in HyperMesh.

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MBFRCC Bulk Data Entry MBFRCC – Curve Force for Multi-body Solution Sequence Description Defines a curve force at a grid point by specifying a vector. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBFRC C

SID

G1

C ID

C VID

G3/N1

N2

N3

G2

INT

EID

G4

(10)

Example

(1)

(2)

(3)

MBFRC C

3

345

AKIMA

41

(4)

(5)

(6)

(7)

(8)

9

0.0

1.0

0.0

(9)

(10)

201

Field

Contents

SID

Load set identification number. No default (Integer > 0)

G1

Grid point identification number where the action force is applied. No default (Integer > 0)

CID

Coordinate system identification number. Blank or 0 infer the basic coordinate system. Default = 0 (Integer > 0, or blank)

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Field

Contents

CVID

Set identification number of the MBCRV entry that gives the load vs. independent variable measured in the coordinate system defined by CID. (Integer > 0)

G3

Grid point identification number to optionally supply N1, N2, N3 in conjunction with G1. (Integer > 0)

N1, N2, N3

Defines the direction of the force vector. At least one of the vector components must be non-zero. Default = 0.0 (Real)

G2

Grid point identification number where the reaction force is applied. If blank or zero, then the force is an action-only force. Default = 0 (Integer > 0)

INT

Interpolation type (Character: LINEAR, CUBIC, AKIMA). Default = AKIMA

EID

Set identification number of the MBVAR for the independent variable expression. Default = TIME (Integer > 0 or blank)

G4

Grid point identification number whose parent body hosts the coordinate system with respect to which the force is defined. The force vector changes direction with the orientation of the body. See comment 1. Default = blank (Integer > 0 or blank)

Comments 1.

If G4 is undefined, the force is defined with respect to the ground body (that is the basic coordinate systems).

2.

This card is represented as a force load in HyperMesh.

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MBFRCE Bulk Data Entry MBFRCE – Expression Force for Multi-body Solution Sequence Description Defines an expression force at a grid point by specifying a vector. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBFRC E

SID

G1

C ID

EID

G3/N1

N2

N3

G2

(10)

G4

Example

(1)

(2)

(3)

MBFRC E

3

345

(4)

(5)

(6)

(7)

(8)

49

0.0

1.0

0.0

(9)

(10)

201

Field

Contents

SID

Load set identification number. No default (Integer > 0)

G1

Grid point identification number where the action force is applied. No default (Integer > 0)

CID

Coordinate system identification number. Blank or 0 infer the basic coordinate system. Default = 0 (Integer > 0, or blank)

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Field

Contents

EID

Expression identification number of the MBVAR entry that gives the load measured in the coordinate system defined by CID. No default (Integer > 0)

G3

Grid point identification number to optionally supply N1, N2, N3 in conjunction with G1. (Integer > 0)

N1, N2, N3

Defines the direction of the force vector. At least one of the vector components must be non-zero. Default = 0.0 (Real)

G2

Grid point identification number where the reaction force is applied. If blank or zero, then the force is an action-only force. Default = 0 (Integer > 0)

G4

Grid point identification number whose parent body hosts the coordinate system with respect to which the force is defined. The force vector changes direction with the orientation of the body. See comment 1. Default = blank (Integer > 0 or blank)

Comments 1.

If G4 is undefined, the force is defined with respect to the ground body (that is the basic coordinate systems).

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OptiStruct 13.0 Reference Guide 1273 Proprietary Information of Altair Engineering

MBLIN Bulk Data Entry MBLIN – Parameters for Multi-body System Linear Analysis Description Defines the parameters for a multi-body system linear analysis. Format (1)

(2)

(3)

(4)

(5)

MBLIN

ID

TYPE

ASC ALE

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

MBLIN

99

EIGEN

1.0

(5)

Field

Contents

ID

Unique identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) TYPE

Type of linear analysis. (Option – "EIGEN", "STMAT")

ASCALE

Animation scale. Default = 1.0 (Real > 0.0)

Comments 1.

This card is represented as a loadcollector in HyperMesh.

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MBMNT Bulk Data Entry MBMNT – Moment for Multi-body Solution Sequence Description Defines a constant moment at a grid point by specifying a vector. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBMNT

SID

G1

C ID

M

G3/N1

N2

N3

G2

(10)

Example

(1)

(2)

(3)

MBMNT

3

345

(4)

(5)

(6)

(7)

(8)

100.0

0.0

1.0

0.0

Field

Contents

SID

Load set identification number.

(9)

(10)

No default (Integer > 0) G1

Grid point identification number where the action force is applied. No default (Integer > 0)

CID

Coordinate system identification number. Blank or 0 infer the basic coordinate system. Default = 0 (Integer > 0, or blank)

M

Moment magnitude. No default (Real)

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Field

Contents

G3

Grid point identification number to optionally supply N1, N2, N3 in conjunction with G1. (Integer > 0)

N1,N2,N3

Defines the direction of the force vector. At least one of the vector components must be non-zero. Default = 0.0 (Real)

G2

Grid point identification number where the reaction force is applied. If blank or zero, then the force is an action-only force. Default = 0 (Integer > 0)

Comments 1.

This card is represented as a moment load in HyperMesh.

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MBMNTC Bulk Data Entry MBMNTC – Curve moment for Multi-body Solution Sequence Description Defines a curve moment at a grid point by specifying a vector. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBMNTC

SID

G1

C ID

C VID

G3/N1

N2

N3

G2

INT

EID

(10)

Example

(1)

(2)

(3)

MBMNTC

3

345

AKIMA

42

(4)

(5)

(6)

(7)

(8)

4

0.0

1.0

0.0

Field

Contents

SID

Load set identification number.

(9)

(10)

No default (Integer > 0) G1

Grid point identification number where the action force is applied. No default (Integer > 0)

CID

Coordinate system identification number. Blank or 0 infer the basic coordinate system. Default = 0 (Integer > 0, or blank)

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Field

Contents

CVID

Set identification number of the MBCRV entry that gives the load vs. independent variable measured in the coordinate system defined by CID. (Integer > 0)

G3

Grid point identification number to optionally supply N1, N2, N3 in conjunction with G1. (Integer > 0)

N1,N2,N3

Defines the direction of the force vector. At least one of the vector components must be non-zero. Default = 0.0 (Real)

G2

Grid point identification number where the reaction force is applied. If blank or zero, then the force is an action-only force. Default = 0 (Integer > 0)

INT

Interpolation type (Character: LINEAR, CUBIC, AKIMA) Default = AKIMA

EID

Set identification number of the MBVAR for the independent variable expression. Default = TIME (Integer > 0 or blank)

Comments 1.

This card is represented as a moment load in HyperMesh.

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MBMNTE Bulk Data Entry MBMNTE – Expression Moment for Multi-body Solution Sequence Description Defines an expression moment at a grid point by specifying a vector. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBMNTE

SID

G1

C ID

EID

G3/N1

N2

N3

G2

(10)

Example

(1)

(2)

(3)

MBMNT

3

345

(4)

(5)

(6)

(7)

(8)

4

0.0

1.0

0.0

Field

Contents

SID

Load set identification number.

(9)

(10)

No default (Integer > 0) G1

Grid point identification number where the action force is applied. No default (Integer > 0)

CID

Coordinate system identification number. Blank or 0 infer the basic coordinate system. Default = 0 (Integer > 0, or blank)

EID

Expression identification number of the MBVAR entry that gives the load measured in the coordinate system defined by CID. No default (Integer > 0)

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Field

Contents

G3

Grid point identification number to optionally supply N1, N2, N3 in conjunction with G1. (Integer > 0)

N1, N2, N3

Defines the direction of the force vector. At least one of the vector components must be non-zero. Default = 0.0 (Real)

G2

Grid point identification number where the reaction force is applied. If blank or zero, then the force is an action-only force. Default = 0 (Integer > 0)

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MBPCRV Bulk Data Entry MBPCRV – Multi-body Parametric Curve Description Defines a Multi-body Parametric Curve using node sets. Format (1)

(2)

(3)

(4)

MBPC RV

PC ID

UC LOSE D

C RVPTS

G1

G2

G3

(5)

(6)

G4

G5

(7)

(8)

(9)

(10)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

MBPC RV

1

1

0

1

5

201

202

203

204

205

Field

Contents

PCID

Parametric curve identification number.

(7)

(8)

No default (Integer > 0) UCLOSED

Specify 1 for closed and 0 for open curves.

CRVPTS

Curve points. Specify 1 if the curve must pass through the nodes, and 0 if the B-spline curve does not pass through the nodes, but stays close. Default = 0 (BOOLEAN: 0,1)

G1,G2,…

Ordered list of grids defining the curve.

Comments

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OptiStruct 13.0 Reference Guide 1281 Proprietary Information of Altair Engineering

1.

This card is represented as a set in HyperMesh.

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MBPTCV Bulk Data Entry MBPTCV – Multi-body Point to Curve Constraint Description Defines a Point to Parametric Curve Constraint. Format (1)

(2)

(3)

(4)

(5)

(6)

MBPTC V

JID

GID

PC ID

G3

V0

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

MBPTC V

1

21

2

25

0

Field

Contents

JID

Joint identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) GID

Grid identification number corresponding to the point which is sliding on a curve. No default (Integer > 0)

PCID

Parametric curve (MBPCRV) identification number. No default (Integer > 0)

G3

This grid specifies the guess for the initial contact point on the curve. Default is GID (Integer > 0)

V0

Specifies the initial sliding velocity of the contact point, as measured by an observer on the curve, placed at the contact point. Default = 0.0 (Real)

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OptiStruct 13.0 Reference Guide 1283 Proprietary Information of Altair Engineering

MBPTDCV Bulk Data Entry MBPTDCV – Multi-body Point to Deformable Curve Constraint Description Defines a Point to Deformable Curve Constraint. Format (1)

(2)

(3)

(4)

(5)

MBPTDC V

JID

GID

DC ID

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

MBPTDC V

1

21

2

(5)

Field

Contents

JID

Joint identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) GID

Grid identification number corresponding to the point which is sliding on the deformable curve. No default (Integer > 0)

DCID

Deformable curve (MBDCRV) identification number. No default (Integer > 0)

Comments 1.

The deformable curve is generated using the CUBIC spline interpolation which requires assumptions on the second derivative of the interpolating function at either end of the curve. The keywords NATURAL, PARABOLIC, PERIODIC and CANTILEVER represent the four standard assumptions defined as follows:

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Note that λ =0.0 implies NATURAL (or free) end conditions and λ =1.0 implies PARABOLIC end conditions. 2.

The MBPTDCV element is not supported by the Force Imbalance method of static equilibrium.

3.

In most cases, the interpolation produces a smooth curve but in some cases, it produces a curve that wiggles too much. In those cases, the TENSION parameter may be specified to smooth out the wiggles in the curve. A TENSION value of unity is a good first guess. After that, higher values of TENSION may be tried if necessary.

4.

The deformable element itself does not possess any inherent inertia, stiffness or damping properties. You must include other modeling elements to capture those effects.

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OptiStruct 13.0 Reference Guide 1285 Proprietary Information of Altair Engineering

MBPTDSF Bulk Data Entry MBPTDSF – Multi-body Dynamics Point to Deformable Surface Constraint Description Defines a Point to Deformable Surface Constraint. Format (1)

(2)

(3)

(4)

(5)

MBPTDSF

JID

GID

SRFID

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

MBPTDSF

1

21

2

(5)

Field

Contents

JID

Joint identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) GID

Grid identification number corresponding to the point which is sliding on a curve. No default (Integer > 0)

SRFID

Deformable surface identification number No default (Integer > 0)

Comments 1.

The deformable curve is generated using the CUBIC spline interpolation which requires assumptions on the second derivative of the interpolating function at either end of the curve. The keywords NATURAL, PARABOLIC, PERIODIC and CANTILEVER represent the four standard assumptions defined as follows:

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Note that λ =0.0 implies NATURAL (or free) end conditions and λ =1.0 implies PARABOLIC end conditions. 2.

The MBPTDCV element is not supported by the Force Imbalance method of static equilibrium.

3.

In most cases, the interpolation produces a smooth curve but in some cases, it produces a curve that wiggles too much. In those cases, the UTENSION and VTENSION parameters may be specified to smooth out the wiggles in the curve. A value of unity is a good first guess. After that, higher values may be tried if necessary.

4.

The deformable surface itself does not possess any inherent inertia, stiffness or damping properties. You must include other modeling elements to capture those effects. For example, you may use a deformable surface in conjunction with a flexible body to simulate contact with a rigid body.

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OptiStruct 13.0 Reference Guide 1287 Proprietary Information of Altair Engineering

MBREQ Bulk Data Entry MBREQ – Multi-body Request Combination Description Defines a multi-body as a combination of request sets defined via MBREQE and MBREQM. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBREQ

SID

R1

R2

R3

R4

R5

R6

R7

R8

R9

…

(10)

Example

(1)

(2)

(3)

(4)

(5)

MBREQ

3

31

34

35

(6)

Field

Contents

SID

Request set identification number.

(7)

(8)

(9)

(10)

(Integer > 0) Ri

Request set identification numbers defined via entry typed enumerated above. (Integer > 0)

Comments 1.

The Ri must be unique.

2.

Request sets must be selected in the Subcase Information section (REQUEST = SID) if they are to be applied.

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MBREQE Bulk Data Entry MBREQE – Multi-body Expression Output Request Description Defines a multi-body solver output request to output the results of a set of expressions. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MBREQE

RSID

RID

E1

E2

E3

E4

E5

E6

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

MBREQE

235

10

20

30

40

Field

Contents

RSID

Request set identification number.

(7)

(8)

(9)

(10)

(Integer > 0) RID

Request identification number. (Integer > 0)

E1

ID of MBVAR. (Integer > 0)

E2 … E6

Additional MBVAR IDs. Default = blank (blank or Integer > 0)

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OptiStruct 13.0 Reference Guide 1289 Proprietary Information of Altair Engineering

Comments 1.

The request evaluates the expression at every output step.

2.

The values are always set to 0 if the expression is not specified.

3.

Request set will be specified in the subcase definition.

4.

Request ID must be unique with respect to all other MBREQM and MBREQE cards.

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MBREQM Bulk Data Entry MBREQM – Multi-body Output Request based on Markers Description Defines a multi-body solver output request to output displacement, velocity, acceleration, or force with respect to markers. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBREQM

RSID

RID

TYPE

IMARK

JMARK

RMARK

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MBREQM

20

234

DISP

20

30

10

Field

Contents

RSID

Request set identification number.

(8)

(9)

(10)

(Integer > 0) RID

Request identification number. (Integer > 0)

TYPE

Output type DIS - Displacement request VEL - Velocity request ACC - Acceleration request FRC - Force request No default

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Field

Contents

IMARK

Marker ID. (Integer > 0) – See comment 1

JMARK

Marker ID. Default = blank; (blank or Integer > 0) – See comments 1 and 2

RMARK

Reference marker ID. Default = blank; (blank or Integer > 0) – See comment 3

Comments 1.

The output request is usually of IMARK with respect to JMARK resolved in RMARK.

2.

If the JMARK is not specified, the results are with respect to global frame.

3.

If the RMARK is not specified, the results are resolved in the global frame.

4.

Request set will be specified in the subcase definition.

5.

Request ID must be unique with respect to all other MBREQM and MBREQE cards.

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MBSEQ Bulk Data Entry MBSEQ – Multi-body System Simulation Sequence Description Defines the simulation sequence for the multi-body solver. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

MBSEQ

ID

SID1

SID2

SID3

…

…

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

MBSEQ

9

99

12

43

Field

Contents

ID

Unique identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) SID1, SID2, …

IDs of the simulation sequence. (Integer > 0) (Valid IDs are: MBSIM, MBLIN, MBSIMP, MBACT, or MBDEACT)

Comments 1.

Every time an MBSIM card is encountered, a simulation is performed on the multi-body model. The initial condition for the next MBSIM will be the ending condition of the current simulation.

2.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1293 Proprietary Information of Altair Engineering

MBSFRC Bulk Data Entry MBSFRC – Scalar Load for Multi-body Solution Sequence Description Defines a constant scalar load on two grid points. Format (1)

(2)

(3)

(4)

(5)

MBSFRC

SID

G1

G2

F

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

MBSFRC

3

345

346

1.0

Field

Contents

SID

Load set identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) G1

Grid point identification number. No default (Integer > 0)

G2

Grid point identification number. No default (Integer > 0)

F

Value of load (Real)

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Comments 1.

MBSFRC applies a translational action-reaction force along the line of action defined by the line segment connecting G1 and G2.

2.

The action force is applied to G1 and the reaction force is applied to G2.

3.

Tensile force is positive.

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MBSFRCC Bulk Data Entry MBSFRCC – Curve Scalar Load for Multi-body Solution Sequence Description Defines a curve scalar load on two grid points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

MBSFRC C

SID

G1

G2

C VID

INT

EID

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MBSFRC C

3

345

346

1

AKIMA

1

Field

Contents

SID

Load set identification number.

(8)

(9)

(10)

No default (Integer > 0) G1

Grid point identification number. No default (Integer > 0)

G2

Grid point identification number. No default (Integer > 0)

CVID

Set identification number of the MBCRV entry that gives the load vs. independent variable measured in the coordinate system defined by CID. (Integer > 0)

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Field

Contents

INT

Interpolation type (Character: LINEAR, CUBIC, AKIMA). Default = AKIMA

EID

Set identification number of the MBVAR for the independent variable expression. Default = TIME (Integer > 0 or blank)

Comments 1.

MBSFRCC applies a translational action-reaction force along the line of action defined by the line segment connecting G1 and G2.

2.

The action force is applied to G1 and the reaction force is applied to G2.

3.

Tensile force is positive.

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OptiStruct 13.0 Reference Guide 1297 Proprietary Information of Altair Engineering

MBSFRCE Bulk Data Entry MBSFRCE – Expression Scalar Load for Multi-body Solution Sequence Description Defines an expression scalar load on two grid points. Format (1)

(2)

(3)

(4)

(5)

MBSFRC E

SID

G1

G2

EID

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

MBSFRC E

3

345

346

1

Field

Contents

SID

Load set identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) G1

Grid point identification number. No default (Integer > 0)

G2

Grid point identification number. No default (Integer > 0

EID

Expression identification number of the MBVAR entry. No default (Integer > 0)

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Comments 1.

MBSFRCE applies a translational action-reaction force along the line of action defined by the line segment connecting G1 and G2.

2.

The action force is applied to G1 and the reaction force is applied to G2.

3.

Tensile force is positive.

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MBSIM Bulk Data Entry MBSIM – Parameters for Multi-body Simulation Description Defines the parameters for a multi-body simulation. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

MBSIM

ID

TYPE

TTYPE

TIME

STYPE

DELTA/ NSTEP/ PRINC R

ITYPE

DTOL

H0

HMAX

HMIN

VTOLFAC

DAEIDX

DC NTOL

DC RMXI T

DC RMNI T

DVC TRL

KETOL/ RESTOL

DQTOL/ FITOL

NITER

TLIMIT

ALIMIT

(8)

(9)

(10)

MAXODR

DJAC EVL DEVLEXP

or STTYPE

Example 1

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MBSIM

99

TRAN

END

5.0

NSTEPS

250

VSTIFF

0.001

0.001

0.01

1000.0

(8)

(9)

(10)

5

Example 2

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(1)

(2)

(3)

(4)

(5)

(6)

(7)

MBSIM

99

TRAN

END

5.0

NSTEPS

250

DSTIFF

0.001

0.001

3

1000.0

4

(8)

(9)

(10)

(9)

(10)

9

TRUE

Example 3

(1)

(2)

(3)

MBSIM

91

STAT

1.0e-6

0.0001

(4)

(5)

(6)

(7)

(8)

100

Field

Contents

ID

Unique identification number. (Integer > 0)

TYPE

Simulation type. Options = ("TRANS", "STATIC") No default

TTYPE

Termination type. Options = ("END", "DUR") – See comment 2. No default

TIME

Termination time or duration based on TTYPE. (Real > 0.0) – See comment 2.

STYPE

Output step type.

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OptiStruct 13.0 Reference Guide 1301 Proprietary Information of Altair Engineering

Field

Contents Options = ("DELTA", "NSTEPS", "PRINCR") – See comments 2 and 3. No default

DELTA

Output time step. (Real > 0.0) – See comments 2 and 3.

NSTEPS

Maximum number of time steps. (Integer > 0) – See comments 2 and 3.

ITYPE

Integrator type. Options = ("ABAM", "VSTIFF", "MSTIFF", "DSTIFF") – See comment 4. Default = DSTIFF

DTOL

Integrator tolerance. Default = 0.001 (Real > 0.0) – See comment 4.

H0

Initial time step for the integrator. Default = 1e-8 (Real > 0.0) – See comment 4.

HMAX

Max step size the integrator is allowed to take. Default = 0.01 (Real > 0.0) – See comment 4.

HMIN

Min step size the integrator is allowed to take. Default = 1.0e-6 (Real > 0.0) – See comment 4.

VTOLFAC

A factor that multiplies DTOL to yield the error tolerance for velocity states. Default = 1000 (Real > 0.0) – See comment 4.

MAXODR

The maximum order that the integrator is to take. Default depends on ITYPE (Integer > 0) – See comment 4.

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Field

Contents

DAEIDX

The index of the DAE formulation. Default = 3 (Integer > 0) – See comment 4.

DCNTOL

A tolerance on all algebraic constraint equations that the corrector must satisfy at convergence. Default = 0.001 (Real > 0.0) – See comment 4.

DCRMXIT

The maximum number of iterations that the corrector is allowed to take to achieve convergence. Default = 4 (Integer > 0) – See comment 4.

DCRMNIT

The minimum number of iterations that the corrector is allowed to take before it checks for corrector divergence. Default = 1 (Integer > 0) – See comment 4.

DVCTRL

A logical flag that controls whether the velocity states are checked for local integration error at each step. (True or False, Default = True if DAEIDX is 3, otherwise False) – See comment 4.

DJCEVL

An attribute to control the frequency of evaluation of the Jacobian matrix during corrector iterations. Default is determined by MotionSolve (Integer > 0) – See comment 4.

DEVLXP

The number of integration steps after which the evaluation pattern defined by DJCEVL is ignored, and the default evaluation pattern is to be used. Default = 0 (Integer > 0) – See comment 4.

KETOL

Maximum residual kinetic energy tolerance. Default = 1.0e-5 (Real > 0.0) – See comment 5.

RESTOL

Maximum residual tolerance for force imbalance method. Default = 1.0e-4 (Real > 0.0) – See comment 6.

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OptiStruct 13.0 Reference Guide 1303 Proprietary Information of Altair Engineering

Field

Contents

DQTOL

Maximum coordinate difference tolerance. Default = 0.001 (Real > 0.0) – See comment 5.

FITOL

Maximum force imbalance tolerance. Default = 0.001 (Real > 0.0) – See comment 6.

NITER

Max number of iterations for static solution to converge. Default = 50 (Integer > 1) – See comment 5.

TLIMIT

Max translational limit for force imbalance static solution. Default = 10000 (Real > 1) – See comment 6.

ALIMIT

Max angular limit for force imbalance static solution. Default = 30 (Real > 1) – See comment 6.

STTYPE

Static solver type Options = ("FIM", "MKM") – See comments 7 and 8. Default = MKM

Comments 1.

The continuation card is used to distinguish between either a TRANS or STAT simulation type. The reader will look for appropriate options based on the type of simulation specified.

2.

When the simulation type is static (STAT), the solver will perform a static simulation if the termination type, termination time/duration, step type, delta/nsteps are not provided. A quasi-static simulation will be performed if that information is provided.

3.

If the output step type is DELTA, then the next argument is expected to be a positive real value, and it is the output step time during the simulation run. If the step type is NSTEPS, then the next argument is expected to be a positive integer value which will be the number of output steps during the simulation. If the step type is PRINCR, then the next argument is expected to be a positive integer value which will be print increment. Solver will output at every intermediate print increment value. If the PRINCR is set to 1, then the solver will output intermediate results at every integrator step.

4.

ITYPE, DTOL, H0, HMAX, HMIN, VTOLFAC, MAXODR, DAEIDX, DCNTOL, DCRMXIT, DCRMNIT, DVCTRL, DJACEVL, and DEVLEXP are only applicable for TRANS simulation types. The 2nd continuation card (DAEIDX, DCNTOL, DCRMXIT, DCRMNIT, DVCTRL, DJACEVL,

1304 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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and DEVLEXP) are available when ITYPE = DSTIFF. See the comments in the Param_Transient in the online help for more details. 5.

KETOL, DQTOL, NITER are only applicable for STATIC simulation type.

6.

RESTOL, FITOL, NITER, TLIMIT, ALIMIT are applicable for the force imbalance static method used for quasi-static solutions.

7.

Static solver type is used to select from the two static solution types currently offered. FIM represents the Force Imbalance Method and MKM represents the Maximum Kinetic Energy Attrition Method.

8.

Note that when quasi-static simulation is requested (STAT with termination time), then the STTYPE option is ignored and the quasi-static simulation will be performed using the force imbalance method.

9.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1305 Proprietary Information of Altair Engineering

MBSIMP Bulk Data Entry MBSIMP – Simulation Parameters for Subsequent Multi-body Simulation Description Defines the simulation parameters for subsequent multi-body simulation. Format (1)

(2)

(3)

(4)

(5)

MBSIMP

ID

C TOL

IDTOL

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

MBSIMP

99

0.001

1.0E-8

(5)

Field

Contents

ID

Unique identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) CTOL

Constraint tolerance. Default = 1.0E-10 (Real > 0.0)

IDTOL

Implicit differentiation tolerance. Default = 1.0E-6 (Real > 0.0)

Comments 1.

This card is represented as a loadcollector in HyperMesh.

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MBSMNT Bulk Data Entry MBSMNT – Scalar Moment for Multi-body Solution Sequence Description Defines a constant scalar moment on two gird points along the specified vector. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBSMNT

SID

G1

G2

T

G3/Vx

Vy

Vz

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBSMNT

3

345

346

1.0

0

1.0

1.0

Field

Contents

SID

Load set identification number.

(9)

(10)

No default (Integer > 0) G1

Grid point identification number. No default (Integer > 0)

G2

Grid point identification number. No default (Integer > 0)

T

Value of moment. (Real)

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OptiStruct 13.0 Reference Guide 1307 Proprietary Information of Altair Engineering

Field

Contents

G3

Grid point identification number to optionally supply Vx, Vy, and Vz in conjunction with G1. (Integer > 0)

Vx

X component of vector V.

Vy

Y component of vector V.

Vz

Z component of vector V.

Comments 1.

MBSMNT applies a scalar action-reaction moment on G1 and G2 along the vector defined by Vx, Vy, and Vz.

2.

The action moment is applied to G1 and the reaction moment is applied to G2.

3.

Right hand rule defines the positive moment.

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MBSMNTC Bulk Data Entry MBSMNTC – Curve Scalar Moment for Multi-body Solution Sequence Description Defines a curve scalar moment on two grid points along the specified vector. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBSMNTC

SID

G1

G2

C VID

G3/Vx

Vy

Vz

INT

EID

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBSMNTC

3

345

346

2

0

1.0

1.0

AKIMA

1

Field

Contents

SID

Load set identification number.

(9)

(10)

No default (Integer > 0) G1

Grid point identification number. No default (Integer > 0)

G2

Grid point identification number. No default (Integer > 0)

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OptiStruct 13.0 Reference Guide 1309 Proprietary Information of Altair Engineering

Field

Contents

CVID

Set identification number of the MBCRV entry that gives the load vs. independent variable measured in the coordinate system defined by CID. (Integer > 0)

G3

Grid point identification number to optionally supply Vx, Vy, and Vz in conjunction with G1. (Integer > 0)

Vx

X component of vector V.

Vy

Y component of vector V.

Vz

Z component of vector V.

INT

Interpolation type (Character: LINEAR, CUBIC, AKIMA) Default = AKIMA

EID

Set identification number of the MBVAR for the independent variable expression. Default = TIME (Integer > 0 or blank)

Comments 1.

MBSCMTC applies a scalar action-reaction moment on G1 and G2 along the vector defined by Vx, Vy, and Vz.

2.

The action moment is applied to G1 and the reaction moment is applied to G2.

3.

Right hand rule defines the positive moment.

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Altair Engineering

MBSMNTE Bulk Data Entry MBSMNTE– Expression Moment for a Multi-body Solution Sequence Description Defines an expression scalar moment on two grid points along the specified vector Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBSMNTE

SID

G1

G2

EID

Vx

Vy

Vz

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MBSMNTE

3

345

346

2

0

1.0

1.0

Field

Contents

SID

Load set identification number.

(9)

(10)

No default (Integer > 0) G1

Grid point identification number. No default (Integer > 0)

G2

Grid point identification number. No default (Integer > 0)

EID

Expression identification number of the MBVAR entry. No default (Integer > 0)

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OptiStruct 13.0 Reference Guide 1311 Proprietary Information of Altair Engineering

Field

Contents

G3

Grid point identification number to optionally supply Vx, Vy, and Vz in conjunction with G1. (Integer > 0)

Vx

X component of Vector V.

Vy

Y component of Vector V.

Vz

Z component of Vector V.

Comments 1.

MBSMNTE applies a scalar action-reaction moment on G1 and G2 along the vector defined by Vx, Vy, and Vz.

2.

The action moment is applied to G1 and the reaction moment is applied to G2.

3.

Right hand rule defines the positive moment.

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MBVAR Bulk Data Entry MBVAR– Multi-body Solver Variable Description Defines a multi-body solver variable which can be referred to by multiple Expressions. Format (1)

(2)

MBVAR

VID

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

EXPR

Example

(1)

(2)

MBVAR

3

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

IMPAC T(Dz(30301020,30302040),VZ(30301020,30302040),0.0,4 00,1.0,0.5,0.000)

Field

Contents

VID

Variable identification number. (Integer > 0)

EXPR

Character string expression. The expression can spawn multiple lines. The continuation lines will start from the second column. Refer to Function Expressions.

Comments 1.

The variable ID can be referenced by VARVAL(VID) in multiple expressions in the model.

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OptiStruct 13.0 Reference Guide 1313 Proprietary Information of Altair Engineering

METADATA Bulk Data Entry METADATA – Indicates the beginning of metadata that is to be passed to the metadata output file. Description METADATA indicates the beginning of metadata that is to be passed to the metadata output file. Metadata between the METADATA and ENDMETADATA commands is passed to the _metadata.xml file.

Example

METADATA This line will be passed to the filename_metadata.xml file. So will this information: Color=blue ENDMETADATA Comments 1.

There can be two sections of metadata; one in the Solution Control section and one in the Bulk Data section.

2.

Metadata can be used to pass information from the pre-processor seamlessly through the solver to a post-processing program.

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MFLUID Bulk Data Entry MFLUID – Fluid Volume Description Defines the parameters and damp shell elements for a fluid volume. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MFLUID

SID

C ID

ZFS

RHO

WSURF1

WSURF2

PLANE1

PLANE2

RMAX

Example

(1)

(2)

MFLUID

25

(3)

(4)

(5)

(6)

32.0

42.0

45

Field

Contents

SID

Unique set of identification numbers.

(7)

(8)

(9)

(10)

No default (Integer > 0) CID

Coordinate system identification number in which its z-axis is assumed to be normal to the free surface. Default = 0 (Integer > 0, or blank)

ZFS

Location of the free surface on the z-axis of the CID coordinate system. Default = 1030 (Real)

RHO

Fluid density.

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OptiStruct 13.0 Reference Guide 1315 Proprietary Information of Altair Engineering

Field

Contents No default (Real > 0.0)

WSURF1

Set identification number of a SURF or SET bulk data entry. This list identifies shell elements that are damp on only one side of the element or an exterior face of solid elements (see SURF,ELFACE). Default = 0 (Integer > 0, or blank)

WSURF2

Set identification number of a SURF or SET bulk data entry. This list identifies shell elements that are damp on both sides of the element. Default = 0 (Integer > 0, or blank)

PLANE1

Type of symmetry on x-z plane of fluid coordinate system (CID). N - no symmetry S - symmetric A - antisymmetric Default = N (Character = N, S, A)

PLANE2

Type of symmetry on y-z plane of fluid coordinate system (CID). N - no symmetry S - symmetric A - antisymmetric Default = N (Character = N, S, A)

RMAX

Interaction between two elements is ignored, if the distance between them is greater than RMAX. Default = 1010 (Real > 0.0)

Comments 1.

An MFLUID entry must be selected by the MFLUID = SID command in the Subcase Information section.

2.

More than one MFLUID entry may be specified to define multiple fluid volumes.

3.

Either WSURF1 or WSURF2, or both must be specified and non-zero. In other words, WSURF1 and WSURF2 cannot be both blank or zero.

4.

An element with all its vertices located on or above the free surface will be ignored in the fluid volume’s mass calculation. An element vertex is considered to be located on the free surface, if the vertex is located within a distance that is

1316 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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from the free surface. 5.

By default for elements referenced by WSURF1, the damp side of the element is assumed to be on the same side as the element’s normal. If this condition is not true for a given element, then the standard SURF entry format with “ELFACE” (not the alternative SET format) must be used to redefine the normal into the fluid by setting NORMAL=1 on SURF entry.

6.

ELIST is an alternative to SET and SURF, but ELIST is intended only to provide compatibility with Nastran decks and therefore is considered deprecated. Also, The SURF and SET entries may not be combined with ELIST entries to define damp elements. ELIST entries are internally converted to SET entries. If ELIST is used, then all MFLUID entries must reference ELIST entries. This means that if an MFLUID references a missing ELIST,25, then the program will not search for a SET,25.

7.

Planes of symmetry may be defined with PLANE1 and PLANE2. "S” means zero displacement normal to the plane. “A” means zero pressure normal to the plane. Consistent structural boundary conditions should be applied to grids located on the planes of symmetry. If PLANE1 is “S” or “A”, then all damp elements must not cross the X-Z plane and be on the same side of the X-Z plane as all other damp elements. If PLANE2 is “S” or “A”, then all damp elements must not cross the Y-Z plane and be on the same side of the Y-Z plane as all other damp elements.

8.

Dry mode output in the .out file is available only when PARAM,VMOPT,2 is specified.

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OptiStruct 13.0 Reference Guide 1317 Proprietary Information of Altair Engineering

MGASK Bulk Data Entry MGASK – Gasket Material Property Definition Description Defining the material properties for gasket-like materials. Format 1 (no temperature dependency) (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MGASK

MID

BEHAV

YPRS

EPL

GPL

ALPHA

EPLTYPE GPLUNIT

TABLD

TABLU1

TABLU2

TABLU3

TABLU4

TABLU5

TABLU6

TABLU7

(8)

(9)

(10)

TABLU8

Format 2 (temperature dependency defined) (1)

(2)

(3)

(4)

(5)

(6)

(7)

MGASK

MID

BEHAV

YPRS

EPL

GPL

ALPHA

EPLTYPE GPLUNIT

TABLD

TABLU1

TABLU2

TABLU3

TABLU4

TABLU5

TABLU6

TABLU7

TABLU8

TABLU9

-etc.-

"T"

TEMP1

YPRS

EPL

GPL

ALPHA

TABLU3

TABLU4

TABLU5

TABLU6

TABLU7

"PLUS"

TABLD

TABLU1

TABLU2

TABLU8

TABLU9

-etc.-

"T"

TEMP2

(10)

-etc.-

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Example 1

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MGASK

2

1

1.0e-3

200.0

1.0e-5

1001

1002

1003

1004

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MGASK

2

1

1.0e-3

200.0

1.0e-5

1001

1002

T

20.0

(8)

(9)

(10)

(8)

(9)

(10)

Example 2

1003

1004

2003

2004

PLUS

2001

2002

T

100.0

2005

PLUS

3001

3002

T

300.0

3003

Field

Contents

MID

Material identification number. No default (Integer > 0)

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OptiStruct 13.0 Reference Guide 1319 Proprietary Information of Altair Engineering

Field

Contents

BEHAV

Behavior type. See comment 12. Default = 0 (Integer (0 or 1 only)) 0 – elasto-plastic material 1 – elastic material with damage

YPRS

Initial yield pressure for the thickness direction of the gasket material. Applies only to elasto-plastic behavior (BEHAV=0). If blank, it is determined automatically. For the groups of data starting with “PLUS”, default is the corresponding field value defined at the first line.

EPL

Tension stabilization coefficient or direct tensile modulus (depends on the value of the EPLTYPE field) for the thickness direction of the gasket material. See comment 5. Default = 0.0 (Real > 0.0) For the groups of data starting with “PLUS”, default is the corresponding field value defined at the first line.

GPL

Transverse shear modulus of the gasket material (the unit of measure depends on the value of the GPLUNIT field). Default = 0.0 (Real > 0.0) For the groups of data starting with “PLUS”, default is the corresponding field value defined at the first line.

ALPHA

Coefficient of thermal expansion in the normal direction. Default = 0.0 (Real > 0.0) For the groups of data starting with “PLUS”, default is the corresponding field value defined at the first line.

EPLTYPE

Type of definition of EPL. See comment 12. Default = 0 (Integer (0 or 1 only)) 0 – EPL is defined as a tension stabilization coefficient 1 – EPL is defined as a direct tensile modulus

GPLUNIT

Type of the unit of measure of GPL. See comment 12. Default = 0 (Integer (0 or 1 only))

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Field

Contents 0 – stress per unit displacement 1 – force per unit area

TABLD

Identifier of a TABLES1 table providing loading path of the gasket material (pressure vs. closure). No default (Integer > 0)

TABLUi

Identifier of TABLES1 table providing unloading/reloading path of the gasket material (pressure vs. closure). If there is no unloading, leave the fields blank. Default = blank (Integer > 0 or blank)

T

Temperature flag indicating that a temperature value will be defined in the next field.

TEMPj

Temperature for the group of data above. See comment 11. No default (Real)

PLUS

Keyword indicating that the following is a group of data defined at another temperature. See comment 12.

Comments 1.

The material identification number must be unique for all MAT1, MAT2, MAT3, MAT8, MAT9 and MGASK entries.

2.

MGASK mainly defines nonlinear properties in the thickness direction for gasket-like materials under compression. MGASK has anisotropy only in the thickness direction, which is called normal anisotropy. For linear analysis, the thickness-direction modulus (stress per unit displacement) is defined by the slope of the first segment of the loading pressure-closure curve TABLD.

3.

MGASK also defines the transverse shear and thickness-direction tension behaviors with linear properties. (The membrane properties of the gasket are defined by a MAT1, referenced from the PGASK property.)

4.

The thickness direction of gasket material is the principal direction (local 3-direction) in 3D solids.

5.

If EPL is defined as a tension stabilization coefficient (EPLTYPE = 0), the tensile modulus will be calculated as the initial slope of the first segment of the loading curve TABLD multiplied by EPL. If EPL is defined as a direct tensile modulus (EPLTYPE = 1), its unit of measure is stress per unit displacement. If EPL is zero, a small tensile modulus will be used automatically for stabilization (no matter EPLTYPE is 0 or 1).

6.

All the data points in tables TABLD and TABLUi are specified in the first quadrant. Points

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OptiStruct 13.0 Reference Guide 1321 Proprietary Information of Altair Engineering

on loading (TABLD) and unloading/reloading (TABLUi) paths must be defined in order of increasing pressure and distance. 7.

For elasto-plastic material (BEHAV = 0), The initial yield pressure should match a point in table TABLD. If the initial yield pressure is not specified, it will be determined automatically by finding the first point on the TABLD curve where the slope changes by more than 10%. The loading path starts from the origin to initial yield pressure (nonlinear elastic range) and continues with strain hardening slope into the plastic region. All unloading/reloading paths must start with zero pressure and positive closure distance, and end at the loading path in the plastic region. Subsequent unloading/ reloading curves must start with larger closure distances (when pressure is zero) and end with larger closure distances than previous unloading/reloading curves.

8.

For elastic material with damage (BEHAV = 1), All loading and unloading/reloading curves must start at the origin of the coordinate system (0, 0). All unloading/reloading paths must end at the loading path. Subsequent unloading/ reloading curves must end with larger closure distances than previous unloading/ reloading curves.

9.

Unloading/reloading behavior at undefined paths will be interpolated between two adjacent unloading/reloading paths.

10. For closures larger than the last user-specified closure, the pressure-closure relationship is calculated as follows: For elasto-plastic material (BEHAV = 0), it follows the last segment of the furthest unloading/reloading curve. This behavior is fully elastic and represents crushed gasket. For elastic material with damage (BEHAV = 1), it follows last slope computed from the user-specified data.

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Elasto-plastic gasket material

Elastic gasket material with damage

11. If temperature dependency is defined, TEMPj should be provided in ascending order and the loading path (and unloading/reloading paths, if required) should be provided for each

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OptiStruct 13.0 Reference Guide 1323 Proprietary Information of Altair Engineering

temperature. If temperature dependency is defined but the temperature field for material property is not provided, the first group of data will be used to calculate the material property. TEMPj are defined for all MGASK data fields (data groups) that lie between the respective TEMPj and its previous PLUS field. TEMP1 is an exception to this rule as it is defined for all data fields that lie between itself and MID. Example

12. BEHAV, EPLTYPE and GPLUNIT fields after any “PLUS” field should remain blank because their values are always the same as those of the first-group data.

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MLOAD Bulk Data Entry MLOAD – Multi-body Load Combination Description Defines a multi-body as a linear combination of load sets defined via GRAV, MBFRC, MBFRCC, MBFRCE, MBMNT, MBMNTC, MBMNTE, MBSFRC, MBSFRCC, MBSFRCE, MBSMNT, MBSMNTC, and MBSMNTE. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MLOAD

SID

L1

L2

L3

L4

L5

L6

L7

L8

L9

…

(10)

Example

(1)

(2)

(3)

(4)

(5)

MLOAD

3

31

34

35

Field

Contents

SID

Load set identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) Li

Load set identification numbers defined via entry typed enumerated above. (Integer > 0)

Comments 1.

The Li must be unique.

2.

Load sets must be selected in the Subcase Information section (MLOAD = SID) if they are to be applied.

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OptiStruct 13.0 Reference Guide 1325 Proprietary Information of Altair Engineering

3.

An MLOAD entry may not reference a set identification number defined by another MLOAD entry.

4.

This card is represented as a loadcollector in HyperMesh.

1326 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MOMENT Bulk Data Entry MOMENT – Static Moment Description Defines a static moment at a grid point by specifying a vector. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOMENT

SID

G

C ID

M

N1

N2

N3

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOMENT

2

5

6

2.9

0.0

1.0

0.0

Field

Contents

SID

Load set identification number.

(9)

(10)

(Integer > 0) G

Grid point identification number. (Integer > 0 or ) See comment 3.

CID

Coordinate system identification number. (Integer > 0 or blank)

M

Scale factor.

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OptiStruct 13.0 Reference Guide 1327 Proprietary Information of Altair Engineering

Field

Contents (Real)

N1,N2,N3

Components of vector measured in coordinate system defined by CID. (Real; at least one non-zero component)

Comments 1.

The static moment applied to grid point G is given by

where,

is the vector defined in fields 6, 7, and 8.

2.

A CID of zero or blank references the basic coordinate system.

3.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on MOMENT entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

4.

This card is represented as a moment load in HyperMesh.

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MOMENT1 Bulk Data Entry MOMENT1 – Static Moment, Alternate Form 1 Description Defines a static moment by specification of a value and two grid points, which determine the direction. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

MOMENT1

SID

G

M

G1

G2

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

MOMENT1

6

13

-2.93

16

13

Field

Contents

SID

Load set identification number.

(7)

(8)

(9)

(10)

(Integer > 0) G

Grid point identification number. (Integer > 0)

M

Value of moment. (Real)

G1,G2

Grid point identification numbers.

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OptiStruct 13.0 Reference Guide 1329 Proprietary Information of Altair Engineering

Comments 1. The static moment applied to grid point G is

where,

is a unit vector parallel to a vector from G1 to G2.

2. This card is represented as a moment load in HyperMesh.

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Altair Engineering

MOMENT2 Bulk Data Entry MOMENT2 – Static Moment, Alternate Form 2 Description Defines a static moment by specification of a value and four grid points, which determine the direction. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOMENT2

SID

G

M

G1

G2

G3

G4

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOMENT2

6

13

-2.93

16

13

18

19

Field

Contents

SID

Load set identification number.

(9)

(10)

(Integer > 0) G

Loaded grid point identification number. (Integer > 0)

M

Value of moment. (Real)

G1,G2

Grid point identification numbers. (Integer > 0; G1 and G2 cannot coincident; G3 and G4 cannot be coincident)

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OptiStruct 13.0 Reference Guide 1331 Proprietary Information of Altair Engineering

Comments 1.

The static moment applied to grid point G is

where, is a unit vector parallel to a vector calculated from the cross product of the vectors from G1 to G2 and G3 to G4. 2.

This card is represented as a moment load in HyperMesh.

1332 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

MOTION Bulk Data Entry MOTION – Multi-body Motion Combination Description Defines a multi-body as a combination of motion sets defined via MOTNJ, MOTNJC, MOTNJE, MOTNG, MOTNGC, and MOTNGE. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MOTION

SID

M1

M2

M3

M4

M5

M6

M7

M8

M9

…

(10)

Example

(1)

(2)

(3)

(4)

(5)

MOTION

3

31

34

35

Field

Contents

SID

Motion set identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) Mi

Motion set identification numbers defined via entry typed enumerated above. (Integer > 0)

Comments 1.

The Mi must be unique.

2.

Motion sets must be selected in the Subcase Information section (MOTION=SID) if they are to be applied.

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OptiStruct 13.0 Reference Guide 1333 Proprietary Information of Altair Engineering

3.

This card is represented as a loadcollector in HyperMesh.

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MOTNG Bulk Data Entry MOTNG – Constant Grid Point Motion for Multi-body Solution Sequence Description Defines a constant grid point motion. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOTNG

SID

G1

C1

G2

D

D0

V0

(9)

(10)

Example

(1)

(2)

(3)

(4)

MOTNG

3

345

3

Field

Contents

SID

Load set identification number.

(5)

(6)

(7)

(8)

(9)

(10)

1.0

(Integer > 0) G1

Grid point identification number. (Integer > 0)

C1

Component number (Integer 1 through 18). The component refers to the direction and type of motion of the grid point G1 in the Basic Coordinate System (not the Local Coordinate System).

G2

Grid point identification number to define relative motion. (Integer > 0 or blank)

D

Scale factor.

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OptiStruct 13.0 Reference Guide 1335 Proprietary Information of Altair Engineering

(Real) D0

Initial displacement if motion data is of type velocity or acceleration, ignored otherwise.

V0

Initial velocity if motion data type is acceleration, ignored otherwise.

Comments 1.

If G1 and G2 are defined, the motion is a relative motion between the two grid points; if G2 is blank, absolute motion of G1 is defined.

2.

The types and directions of motion for the component numbers are given in the following table. Component Number(s)

Type of Motion

Direction(s) of Motion

1, 2, and 3

Displacement

X, Y, Z

4, 5, and 6

Rotation

X, Y, Z

7, 8, and 9

Translational Velocity

X, Y, Z

10, 11, and 12

Angular Velocity

X, Y, Z

13, 14, and 15

Translational Acceleration

X, Y, Z

16, 17, and 18

Angular Acceleration

X, Y, Z

The component numbers and directions of motion are in the format: 1->X, 2->Y and 3->Z for Displacement and this format is followed for all the types in the table. 3.

This card is represented as a constraint load in HyperMesh.

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MOTNGC Bulk Data Entry MOTNGC – Grid Point Motion vs. Time Curve for Multi-body Solution Sequence Description Defines a grid point motion vs. time by specifying a curve. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOTNGC

SID

G1

C1

G2

C VID

INT

EID

D0

V0

(9)

(10)

Example

(1)

(2)

(3)

(4)

MOTNGC

3

345

3

Field

Contents

SID

Load set identification number.

(5)

(6)

(7)

(8)

1

AKIMA

2

(9)

(10)

(Integer > 0) G1

Grid point identification number. (Integer > 0)

C1

Component number (Integer 1 through 18). The component refers to the direction and type of motion of the grid point G1 in the Basic Coordinate System (not the Local Coordinate System).

G2

Grid point identification number to define relative motion. (Integer > 0 or blank)

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OptiStruct 13.0 Reference Guide 1337 Proprietary Information of Altair Engineering

Field

Contents

CVID

Set identification number of the MBCRV entry that gives the motion vs. time. (Integer > 0)

INT

Interpolation type (Character: LINEAR, CUBIC, AKIMA). Default = AKIMA

EID

Set identification number of the MBVAR for the independent variable expression. Default = TIME (Integer > 0 or blank)

D0

Initial displacement if motion data is of type velocity or acceleration, ignored otherwise.

V0

Initial velocity if motion data type is acceleration, ignored otherwise.

Comments 1.

If G1 and G2 are defined, the motion is a relative motion between the two grid points; if G2 is blank, absolute motion of G1 is defined.

2.

The types and directions of motion for the component numbers are given in the following table. Component Number(s)

Type of Motion

Direction(s) of Motion

1, 2, and 3

Displacement

X, Y, Z

4, 5, and 6

Rotation

X, Y, Z

7, 8, and 9

Translational Velocity

X, Y, Z

10, 11, and 12

Angular Velocity

X, Y, Z

13, 14, and 15

Translational Acceleration

X, Y, Z

16, 17, and 18

Angular Acceleration

X, Y, Z

The component numbers and directions of motion are in the format: 1->X, 2->Y and 3->Z for Displacement and this format is followed for all the types in the table. 3.

This card is represented as a constraint load in HyperMesh.

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Altair Engineering

MOTNGE Bulk Data Entry MOTNGE – Expression Grid Point Motion for Multi-body Solution Sequence Description Defines a grid point motion through an expression. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOTNGE

SID

G1

C1

G2

EID

D0

V0

(9)

(10)

Example

(1)

(2)

(3)

(4)

MOTNGE

3

345

3

Field

Contents

SID

Load set identification number.

(5)

(6)

(7)

(8)

(9)

(10)

4

(Integer > 0) G1

Grid point identification number. (Integer > 0)

C1

Component number (Integer 1 through 18). The component refers to the direction and type of motion of the grid point G1 in the Basic Coordinate System (not the Local Coordinate System).

G2

Grid point identification number to define relative motion. (Integer > 0 or blank)

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OptiStruct 13.0 Reference Guide 1339 Proprietary Information of Altair Engineering

Field

Contents

EID

Expression identification number of the MBVAR entry that gives the motion vs. time. (Integer > 0)

D0

Initial displacement if motion data is of type velocity or acceleration, ignored otherwise.

V0

Initial velocity if motion data type is acceleration, ignored otherwise.

Comments 1.

A CID of zero or blank references the basic coordinate system.

2.

The types and directions of motion for the component numbers are given in the following table. Component Number(s)

Type of Motion

Direction(s) of Motion

1, 2, and 3

Displacement

X, Y, Z

4, 5, and 6

Rotation

X, Y, Z

7, 8, and 9

Translational Velocity

X, Y, Z

10, 11, and 12

Angular Velocity

X, Y, Z

13, 14, and 15

Translational Acceleration

X, Y, Z

16, 17, and 18

Angular Acceleration

X, Y, Z

The component numbers and directions of motion are in the format: 1->X, 2->Y and 3->Z for Displacement and this format is followed for all the types in the table.

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Altair Engineering

MOTNJ Bulk Data Entry MOTNJ – Constant Joint Motion for Multi-body Solution Sequence Description Defines a constant joint motion. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOTNJ

SID

JID

MTYPE

D

DTYPE

D0

V0

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

MOTNJ

3

345

TRANS

1.0

DIS

Field

Contents

SID

Load set identification number.

(7)

(8)

(9)

(10)

(Integer > 0) JID

Joint identification number. (Integer > 0)

MTYPE

TRANS or ROT, ignored for revolute and translational joints.

D

Value of motion. (Real)

DTYPE

Motion data type (DIS or VEL or ACC), blank means displacement motion.

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OptiStruct 13.0 Reference Guide 1341 Proprietary Information of Altair Engineering

Field

Contents

D0

Initial displacement if motion data is of type velocity or acceleration, ignored otherwise.

V0

Initial velocity if motion data type is acceleration, ignored otherwise.

Comments 1.

Joint motion can only be applied to cylindrical joints (MTYPE = TRANS or ROT), revolute joints (MTYPE = ROT), and translational joints (MTYPE = TRANS).

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Altair Engineering

MOTNJC Bulk Data Entry MOTNJC – Joint Motion vs. Time Curve for Multi-body Solution Sequence Description Defines a joint motion vs. time by specifying a curve. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOTNJC

SID

JID

MTYPE

C VID

INT

EID

DTYPE

D0

V0

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MOTNJC

3

345

ROT

2

AKIMA

99

Field

Contents

SID

Load set identification number.

(8)

(9)

(10)

(Integer > 0) JID

Grid point identification number. (Integer > 0)

MTYPE

TRANS or ROT, ignored for revolute and translational joints.

CVID

Set identification number of the MBCRV entry that gives the motion vs. time. (Integer > 0)

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OptiStruct 13.0 Reference Guide 1343 Proprietary Information of Altair Engineering

Field

Contents

INT

Interpolation type (Character: LINEAR, CUBIC, AKIMA). Default = AKIMA

EID

Set identification number of the MBVAR for the independent variable expression. Default = TIME (Integer > 0 or blank)

DTYPE

Motion data type (DIS or VEL or ACC), blank means displacement motion.

D0

Initial displacement if motion data is of type velocity or acceleration, ignored otherwise.

V0

Initial velocity if motion data type is acceleration, ignored otherwise.

Comments 1.

Joint motion can only be applied to cylindrical joints (MTYPE = TRANS or ROT), revolute joints (MTYPE = ROT), and translational joints (MTYPE = TRANS).

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MOTNJE Bulk Data Entry MOTNJE – Expression Joint Motion for Multi-body Solution Sequence Description Defines a joint motion through an expression. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MOTNJE

SID

JID

MTYPE

EID

DTYPE

D0

V0

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

MOTNJE

3

345

3

1

Field

Contents

SID

Load set identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) JID

Joint identification number. (Integer > 0)

MTYPE

TRANS or ROT, ignored for revolute and translational joints.

EID

Expression identification number of the MBVAR entry that gives the motion vs. time. If blank or zero, a constant motion of D is applied. Default = constant motion D (Integer > 0 or blank)

DTYPE

Motion data type (DIS or VEL or ACC), blank means displacement

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OptiStruct 13.0 Reference Guide 1345 Proprietary Information of Altair Engineering

Field

Contents motion.

D0

Initial displacement if motion data is of type velocity or acceleration, ignored otherwise.

V0

Initial velocity if motion data type is acceleration, ignored otherwise.

Comments 1.

Joint motion can only be applied to cylindrical joints (MTYPE = TRANS or ROT), revolute joints (MTYPE = ROT), and translational joints (MTYPE = TRANS).

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Altair Engineering

MPC Bulk Data Entry MPC – Multipoint Constraint Description The MPC bulk data entry defines a multipoint constraint equation of the form.

Aj u j

0

j

Where,

Aj

is the coefficient that can be used to define the relationship between the degrees of freedom associated with grid points (or a scalar point) in the model.

uj

is the degree of freedom associated with a grid point (or a scalar point).

Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

MPC

SID

G

C

A

G

C

A

blank

blank

G

C

A

-etc.-

blank

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

MPC

3

28

3

6.2

2

2

4.29

1

4

-2.91

Field

Contents

SID

Set identification number.

Altair Engineering

(9)

(10)

OptiStruct 13.0 Reference Guide 1347 Proprietary Information of Altair Engineering

Field

Contents (Integer > 0)

G

Identification number of a grid point or a scalar point. (Integer > 0 or ) See comment 5.

C

Component number. See comment 3. (Integer zero or blank for scalar points, or any one of the digits 1-6 for grid points)

A

Coefficient that can be used to define the relationship between the degrees of freedom associated with grid points (or a scalar point). (Real; the first A must be non-zero)

Comments 1.

The first coordinate in the sequence is assumed to be the dependent coordinate. A dependent degree-of-freedom assigned by one MPC entry cannot be assigned dependent by another MPC entry or by a rigid element.

2.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

3.

The component refers to the coordinate system referenced by the grid point.

4.

Illustrative Example: Figure 1 can be used to illustrate an MPC application. Independent grid points G1 and G2 of a 2D quad element are connected with the help of an MPC; where Gd is the dependent grid point. The objective of this example is to force the displacement of Gd to be equal to the sum of the displacements of grid points G1 and G2 in the X (1) direction using an MPC.

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Figure : MPC Example Illustration

Rewriting the MPC equation for three grid points:

A1u1

A2 u2

A3 u3

0

Substituting A1 = 1.0, A2 = -1.0 and A3 = -1.0 in the equation above:

(1.0)ud

( 1.0)u1

( 1.0)u2

0

Rearranging equation terms:

ud

u1

u2

Where,

ud u1 u2

is the displacement of grid point Gd in X direction is the displacement of grid point G1 in X direction is the displacement of grid point G2 in X direction

5.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on MPC entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

6.

This card is represented as an equation in HyperMesh.

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OptiStruct 13.0 Reference Guide 1349 Proprietary Information of Altair Engineering

MPCADD Bulk Data Entry MPCADD – Multipoint Constraint Set Combination Description Defines a multipoint constraint set as a union of multipoint constraint sets defined via MPC entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

MPC ADD

SID

S1

S2

S3

S4

S5

S6

S7

S8

S9

etc.

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

MPC ADD

101

2

3

1

6

4

Field

Contents

SID

Set identification number.

(8)

(9)

(10)

(Integer > 0) Sj

Set identification numbers of multipoint constraint sets defined via MPC entries. (Integer > 0 or ) See comment 5.

Comments 1.

Multipoint constraint sets must be selected with the Subcase Information command MPC=SID.

2.

The Sj field should not reference the identification number of a multipoint constraint set

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Altair Engineering

defined by another MPCADD entry. 3.

MPCADD entries take precedence over MPC entries. If both have the same SID, only the MPCADD entry will be used.

4.

If all Si are non-existent, the solver will exit with an error termination.

5.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on MPCADD entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

6.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1351 Proprietary Information of Altair Engineering

NLOAD Bulk Data Entry NLOAD – Nonlinear Load Combination or Superposition Description Defines a loading condition for nonlinear problems as a linear combination of load sets defined via NLOAD1. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

NLOAD

SID

S

S1

L1

S2

L2

S3

L3

S4

L4

...

...

...

...

...

...

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

NLOAD

5

1.0

2.0

101

2.0

102

2.0

103

-2.0

201

Field

Contents

SID

Load set identification number.

(10)

No default (Integer > 0) S

Scale factor. No default (Real)

Si

Scale factors. No default (Real)

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Field

Contents

Li

Load set identification numbers of NLOAD1. No default (Integer > 0)

Comments 1.

Dynamic load sets must be selected in the I/O Options or Subcase Information sections with NLOAD=SID.

2.

The load vector being defined by this entry is given by:

. 3.

Each Li must be unique from any other Li on the same entry.

4.

SID must be unique from all NLOAD1 entries.

5.

An NLOAD entry may not reference a set identification number defined by another NLOAD entry.

6.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1353 Proprietary Information of Altair Engineering

NLOAD1 Bulk Data Entry NLOAD1 – Time Dependent Load or Motion for Geometric Nonlinear Analysis Description Defines a time-dependent load or enforced motion for use in geometric nonlinear analysis.

f(t) = A * C * F(t/B) Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

NLOAD1

SID

EXC ITEID

SENSID

TYPE

TID

B

C

C ID

TSTART

TEND

(10)

Example

(1)

(2)

(3)

NLOAD1

5

7

(4)

(5)

(6)

LOAD

13

Field

Contents

SID

Load set identification number.

(7)

(8)

(9)

(10)

(Integer > 0) EXCITEID SID number of DAREA, SPCD or static load set that defines A. See comments 2 and 3. (Integer > 0) SENSID

Identification number of a sensor. Load application is activated once the referenced sensor is activated.

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Field

Contents (Integer > 0)

TYPE

Defines the type of the dynamic excitation. See comments 2 and 3. Default = 0 (Integer, character or blank)

TID

Identification number of TABLEDi entry defining the load history F(t). (Integer > 0) TID=0 implies F(t) is a linear function passing through (TTERM-TTERMS, 0) and (TTERM, 1). TTERMS is the duration of each subcase. TTERM is the termination time. TID = 0 is only for geometric nonlinear implicit (quasi-) static analysis (NLGEOM).

B

Scale factor of the time in f(t). Default = 1.0 (Real > 0)

C

Scale factor for the function value in f(t). Default = 1.0 (Real)

CID

Identification number of coordinate system defining a frame in which the imposed velocity is defined. Applies only for TYPE = 2, V, VE, VEL, or VELO. Only CORD1R and CORD2R systems are allowed. (Integer > 0 or blank)

TSTART

Start time. See comment 4. Default = 0.0 (Real > 0.0)

TEND

End time. Default = 1030 (Real > TSTART)

Comments 1.

Time-dependent load sets must be selected with the Subcase Information command NLOAD = SID. It can only be selected in geometric nonlinear analysis subcases which are defined by an ANALYSIS = NLGEOM, IMPDYN or EXPDYN subcase entry.

2.

The type of the dynamic excitation is specified by TYPE (field 5) according to the following table:

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TYPE

TYPE of Dynamic Excitation

O, L, LO, LOA, or LOAD

Applied load (force, moment, pressure). (Default)

3.

1, D, DI, DIS, or DISP

Enforced displacement using SPC/SPCD data.

2, V, VE, VEL, or VELO

Enforced velocity using SPC/SPCD data.

3, A, AC, ACC, or ACCE

Enforced acceleration using SPC/SPCD data

TYPE (field 5) also determines the manner in which EXCITEID (field 3) is used by the program as described below. Excitation specified by TYPE is applied load. The EXCITEID may reference DAREA, or (and) static load set entries. If EXCITEID references both DAREA and static load set, the two loads will be super-imposed. Excitation specified by TYPE is enforced motion. The EXCITEID must reference SPCD entries.

4.

TSTART and TEND are only considered for enforced displacement, velocity, and acceleration. The continuation line is optional.

5.

This card is represented as a loadcollector in HyperMesh.

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NLPARM Bulk Data Entry NLPARM – Parameters for Nonlinear Static Analysis or Heat Transfer Analysis Description The NLPARM bulk data entry defines parameters for nonlinear static analysis or heat transfer analysis solution control. Format (1)

(2)

(3)

(4)

NLPARM

ID

NINC

EPSU

EPSP

(5)

(6)

(7)

(8)

KSTEP

MAXITER

C ONV

EPSW

(9)

MAXLS

(10)

LSTOL

Example

(1)

(2)

(3)

NLPARM

99

5

(4)

(5)

(6)

(7)

Field

Contents

ID

Each NLPARM bulk data card must have a unique ID.

(8)

(9)

(10)

No default (Integer > 0) NINC

Number of implicit load sub-increments (see comments 2 and 3). Default = 1 (no increments) for ANALYSIS = NLSTAT and ANALYSIS=NLHEAT Default = 10 for ANALYSIS = NLGEOM (Integer > 0)

KSTEP

Number of iterations before stiffness update (see comment 3). Default = 6 for ANALYSIS = NLGEOM and BCS solver

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Field

Contents Default = 3 for ANALYSIS = NLGEOM and PCG solver (Integer > 0)

MAXITER

Limit on number of implicit iterations for each load increment. If reached, the solution is terminated (ANALYSIS = NLSTAT and ANALYSIS=NLHEAT). Default = 25 (Integer > 0)

CONV

Flags to select implicit convergence criteria. Default = UPW for ANALYSIS = NLSTAT Default = PW for ANALYSIS = NLGEOM (Any combination of U, P and W)

EPSU

Error tolerance for displacement (U) criterion. Default = 1.0E-3 for ANALYSIS = NLSTAT Default = 1.0E-2 for ANALYSIS = NLGEOM (Real > 0.0)

EPSP

Error tolerance for load (P) criterion. Default = 1.0E-3 for ANALYSIS = NLSTAT and ANALYSIS=NLHEAT Default = 1.0E-2 for ANALYSIS = NLGEOM (Real > 0.0)

EPSW

Error tolerance for work (W) criterion. Default = 1.0E-7 for ANALYSIS = NLSTAT and ANALYSIS=NLHEAT Default = 1.0E-3 for ANALYSIS = NLGEOM (Real > 0.0)

MAXLS

Maximum number of line searches allowed for each iteration. Default = 20 (Integer > 0)

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Field

Contents

LSTOL

Line search tolerance. Default = 1.0E-3 (Real > 0.0)

Comments 1.

The NLPARM bulk data entry is selected by the Subcase Information command NLPARM=option. Each subcase for which nonlinear analysis is desired requires an NLPARM command.

2.

The solution method for quasi-static nonlinear analysis (ANALYSIS = NLSTAT) is full Newton. The stiffness matrix is updated at each iteration. NINC > 0 represents the number of equal subdivisions that the total load in a given subcase will be divided into. If NINC is blank, the entire load for a given subcase is applied at once. The Newton method will be applied to consecutive load levels until the final load is reached.

3.

Additional control for geometric nonlinear implicit static solution schemes (ANALYSIS = NLGEOM) can be defined using the NLPARMX bulk data entry. Defaults will be used if NLPARMX is not present.

4.

The solution method for geometric nonlinear implicit analysis (ANALYSIS = NLGEOM) is modified or Quasi-Newton. The frequency of stiffness matrix updates is controlled by KSTEP. For highly nonlinear problems, it is recommended to reduce KSTEP for better performance. KSTEP = 1 means full Newton. If the loading is defined using NLOAD, the termination time TTERM must defined by a TTERM subcase entry. The initial implicit time step is TTERMS/NINC with TTERMS = TTERM – T0. All subsequent time steps will be determined automatically. In a simulation with multiple nonlinear subcases, T0 is the end time of the previous load step. If there is only a single nonlinear subcase, T0 = 0.0. If the loading is defined using LOAD, TTERM is not mandatory. These loads are treated as linear ramp-up. If TTERM is defined, the load ramps up from the end time of the previous subcase to TTERM. If TTERM is absent, it will be determined from the subcase sequence such that the duration of each subcase TTERMS = 1.0. In this case, the initial time step is 1.0/NINC.

5.

For Nastran compatibility, NLPCI is imported if present. Only the fields ID, TYPE are interpreted. With NLPCI present, the default for NLPARMX, SACC will be reset to RIKS. TYPE will be translated into CTYPE; all other entries are set to default. A warning will be issued. NLPCI and NLPARMX cannot be used simultaneously. It is recommended to remove NLPCI and use NLPARMX with the appropriate definitions.

6.

For more information about nonlinear quasi-static analysis, see the Nonlinear Quasi-static Analysis section.

7.

For more information about geometric nonlinear analysis, see the Geometric Nonlinear Analysis section.

8.

For more information about nonlinear steady-state heat transfer analysis, see the Nonlinear Steady-State Heat Transfer Analysis section.

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9.

This card is represented as a loadcollector in HyperMesh.

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NLPARMX Bulk Data Entry NLPARMX – Optional Parameters for Geometric Nonlinear Implicit Static Analysis Control Description Defines additional parameters for geometric nonlinear implicit static analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

NLPARMX

ID

TA0

DTA

DTTH

NPRINT

RFILE

SOLV

TSC TRL

DTMIN

DTMAX

LSMETH

KINER

DTSC Q

ILIN

SMDISP

SPRBK

ITW

DTSC I

LDTN

DTSC D

LARC

(10)

RREFIF

NC YC LE

FIXTID/ TOUT

C TYP

WSC AL

Example 1

(1)

(2)

NLPARM

99

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Example 2

(1)

(2)

NLPARM

99

NLPARMX

99

NEWT

Altair Engineering

0.1

ARC

1.e-4

0.1

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Example 3

(1)

(2)

NLPARM

99

0.01

NLPARMX

(3)

(5)

(6)

(7)

3

0.01

99

NEWT

(4)

(8)

(9)

(10)

PW

0.01

0.1

ARC

1.e-4

0.1

NEWM

0.25

0.5

Field

Contents

ID

Identification number of an associated NLPARM entry. No default (Integer > 0)

TA0

Start time for writing animation files. Default = 0.0 (Real > 0)

DTA

Output time step for animation files. If zero, no output (See comment 3). Default = DTINI (Real > 0)

DTTH

Output time step for time history files. If zero, no output (See comment 3). Default = 0.1*DTINI (Real > 0)

NPRINT

Print every NPRINT iterations. If negative, to .out and standard output; if positive, only to .out file. Default = -1 (Integer)

RFILE

Cycle frequency to write restart file for nonlinear iteration. Default = 5000 (Integer > 0)

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Field

Contents

SOLV

Geometric nonlinear implicit solution method. NEWT – Modified Newton BFGS – BFGS quasi-Newton method Default = NEWT (Character = NEWT or BFGS)

TSCTRL

Time step control. ARC – Arc-length is used to accelerate and control the convergence. The time step is determined by displacement norm control (arc-length). SIMP – Simple time step control. RIKS – Riks method for post-buckling analysis (only with SOLV = NEWT). NONE – No time step control. A warning will be issued. In the case of divergence the time step will be repeated with half the step size. The run will be terminated according to DTMIN and NCYCLE. Default = ARC (Character)

DTMIN

Minimum implicit time step. If DTMIN is reached, simulation will be terminated (See comment 3). Default = 1e-4*DTINI (Real > 0)

DTMAX

Maximum implicit time step from which time step is set constant (See comment 3). Default = 3*DTINI (Real > 0)

LSMETH

Line search method. Default = ENERGY (Character = NONE, FORCE, ENERGY, or AUTO)

RREFIF

Special residual force computation with contact interfaces present. Default = no special treatment (Integer = 0, …, 5) 0 1 2 3

– – – –

Aggressive (modified entirely by the out-of-balance value) Average (modified each time with 200% maximum) Light (modified each time with 20% maximum) No modification

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Field

Contents 4 – No modification; except for the first contact. 5 – Modified automatically (for imposed displacement only)

NCYCLE

Maximum number of time steps. If reached, solution will be terminated. NCYCLE = 0 means no limit. Default = no limit (Integer > 0)

FIXTID

Identification number of a TABLEDi entry. The x values of the table define fixed time points that the automatic time step control will adhere to. (Integer > 0)

TOUT

The method to determine the fixed time point. AUTO – Fully automatic time step control. NLOAD - The time points in all TABLEDi that are referenced by NLOAD1 in one subcase. Default = AUTO (AUTO or NLOAD)

KINER

Inertia Stiffness for handling models that are not sufficiently constrained. May require definition of DTSCQ (See comment 4). Default = OFF (Character = ON, OFF)

DTSCQ

Scale factor for inertia stiffness matrix used in quasi-static analysis (KINER = ON, See comment 4). Default = 1.0 (Real > 0)

ILIN

Perform linear instead of nonlinear analysis. For debugging purposes. (ANALYSIS = NLGEOM, See comment 5). LIN – Linear analysis without contact. LINC – Linear analysis with contact. Default is nonlinear analysis (Character = LIN, LINC)

SMDISP

Perform small displacement and rotation analysis instead of geometric nonlinear analysis. PARAM, SMDISP, 1 overwrites this definition. OFF – Geometric nonlinear analysis.

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Field

Contents ON – Small displacements and small rotations analysis. Default = OFF (Character = ON, OFF)

SPRBK

Perform spring back analysis. Equilibrium is reached when the internal forces are less or equal to the tolerances given on NLPARM. OFF – Regular analysis. ON – Spring back analysis. Default = OFF (Character = ON, OFF)

ITW

If the solution of a time step converges within ITW iterations the next time step will be increased by a factor controlled by DTSCI. Default = 6 for TSCTRL = ARC Default = 2 for TSCTRL = SIMP Default = 12 for TSCTRL = RIKS Default = 6 (Integer > 0)

DTSCI

Maximum scale factor for increasing the time step (TSCTRL = ARC, RIKS). Scale factor for TSCTRL = SIMP. Default = 1.1 (Real > 0)

LDTN

Maximum number of iterations before resetting and decreasing the time step by a factor of DTSCD. Default = 20 for TSCTRL = ARC Default = 15 for TSCTRL = SIMP Default = 25 for TSCTRL = RIKS (Integer > 0)

DTSCD

Scale factor for decreasing the time step (TSCTRL = ARC, SIMP, RIKS). Default = 0.67 (Real > 0)

LARC

Input arc-length for TSCTRL = ARC, RIKS

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Field

Contents Default = automatic computation (Real)

CTYP

Constraint type (See comment 6). CRIS – Crisfield constraint equation. MFSRIKS –- Modified Forde & Stiemer equation. Default = CRIS (CRIS or MFSRIKS)

WSCAL

Scale factor for controlling the loading contribution in the constraint equation. Default = 0.0 (Real > 0.0)

Comments 1.

The NLPARMX bulk data entry is selected by the Subcase Information command NLPARM = option. There must also be an NLPARM bulk data entry with the same ID. It is only used in geometric nonlinear implicit static analysis (ANALYSIS = NLGEOM); it is ignored in other analyses.

2.

The solution method for geometric nonlinear implicit analysis is selected by SOLV. The frequency of stiffness matrix updates is controlled by KSTEP. For highly nonlinear problems, it is recommended to reduce KSTEP for better performance. KSTEP = 1 means full Newton.

3.

If the loading is defined using NLOAD, the termination time TTERM must be defined by a TTERM subcase entry. The initial implicit time step is DTINI = TTERMS/NINC with TTERMS = TTERM – T0. All subsequent time steps will be determined automatically. In a simulation with multiple nonlinear subcases, T0 is the end time of the previous load step. If there is only a single nonlinear subcase, T0 = 0.0. If the loading is defined using LOAD, TTERM is not mandatory. These loads are treated as linear ramp-up. If TTERM is defined, the load ramps up from the end time of the previous subcase to TTERM. If TTERM is absent, it will be determined from the subcase sequence such that the duration of each subcase TTERMS = 1.0. In this case, the initial time step is DTINI = 1.0/NINC.

4.

For models that are not sufficiently constrained, inertia stiffness can be used to overcome a singular stiffness matrix. The inertia stiffness [K]inertia = 1/(DTSCQ*dt)^2[M] is added to the stiffness matrix [K]. Care needs to be taken in the selection of DTSCQ. Too large of an added mass may lead to wrong results.

5.

Linear static and normal modes analysis within geometric nonlinear analysis (ILIN = LIN, LINC) are provided for debugging purposes. They may help detecting modeling errors. All materials are linearized, and linear displacements are assumed as well. The load is taken at the termination time. To run normal modes analysis, a METHOD subcase entry that refers to an EIGL bulk data entry must be provided.

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6.

The constraint equation for CTYP = CRIS is:

Where, u is displacement, j the scale factor (WSCAL) , l a load factor, and r the arclength. The constraint equation for CTYP = MFSRIKS is:

Where, is the displacement, due to a unit load factor, and is the displacement increment from the conventional Newton type method. The meaning of u, j, l, and r are the same as those above. 7.

For Nastran compatibility, NLPCI is imported if present. Only the fields ID, TYPE are interpreted. With NLPCI present, the default for TSCTRL will be reset to RIKS. TYPE will be translated into CTYP; all other entries are set to default. A warning will be issued. NLPCI and NLPARMX cannot be used simultaneously. It is recommended to remove NLPCI and use NLPARMX with the appropriate definitions

8.

For more information about geometric nonlinear analysis, see the Geometric Nonlinear Analysis section.

9.

This card is represented as an extension to an NLPARMX loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 1367 Proprietary Information of Altair Engineering

NLPCI Bulk Data Entry NLPCI – Implicit Time Step Control for Riks Type Arc-Length Method Description Define implicit automatic time step control with Riks type arc-length method. Format (1)

(2)

(3)

(4)

NLPC I

ID

TYPE

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

NLPC I

5

C RIS

(4)

(5)

(6)

(7)

Field

Contents

ID

Identification number of an associated NLPARM entry.

(8)

(9)

(10)

No default (Integer > 0) TYPE

Constraint type Default = CRIS (CRIS, RIKS, or MRIKS)

Comments 1.

The NLPCI bulk data entry is selected by the Subcase Information command NLPARM = option. There must also be an NLPARM entry with the same ID. It is only used in geometric nonlinear (quasi-)static analysis (ANALYSIS = NLGEOM).

2.

NLPCI is implemented for Nastran compatibility and imported if present. Only the fields ID, TYPE are interpreted. With NLPCI present, the default for NLPARMX, SACC will be reset to RIKS. TYPE will be translated into CTYPE; all other entries are set to default. A warning will be issued. NLPCI and NLPARMX cannot be used simultaneously. It is

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recommended to remove NLPCI and use NLPARMX with the appropriate definitions. 3.

This card is an unsupported bulk data entry in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1369 Proprietary Information of Altair Engineering

NLRGAP Bulk Data Entry NLRGAP – Nonlinear Load Proportional to Gap Description Defines a nonlinear radial (circular) gap for direct transient response analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

NLRGAP

SID

GA

GB

PLANE

TABK

TABG

TABU

RADIUS

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

NOLIN1

21

3

4

XY

3

10

6

1.6

Field

Contents

SID

Nonlinear load set identification number.

(10)

No default (Integer > 0) GA

Inner grid for radial gap (shaft). No default (Integer > 0)

GB

Outer grid for radial gap (housing). No default (Integer > 0)

PLANE

Radial gap orientation plane. Default = XY (XY, YZ or ZX)

TABK

Table ID defining either (See comment 11): Gap stiffness vs. time

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Field

Contents Gap force vs. penetration No default (Integer > 0)

TABG

Table ID for radial gap clearance as a function of time. No default (Integer > 0)

TABU

Table ID for radial coefficient of friction as a function of time. No default (Integer > 0)

RADIUS

Shaft radius. Default = 0.0 (Real > 0.0)

Comments 1.

Nonlinear radial gap must be selected by the Subcase Information data selector NONLINEAR.

2.

Multiple NLRGAP entries with the same SID are allowed.

3.

The NLRGAP is not an element, but a nonlinear load similar to the NOLIN1, NOLIN2, NOLIN3 and NOLIN4 entries. It computes the relative displacements of GA and GB in the selected plane and applies appropriate nonlinear loads to simulate the radial contact.

4.

The degrees of freedom in the XY, YZ and ZX planes (depending on the PLANE defined) of GA and GB must be members of the solution set. This means that they must not be dependent degrees of freedom and the must not have SPCs applied to them. If RADIUS is > 0.0, then the in-plane rotation degree of freedom must also be in the solution set.

5.

The NLRGAP is limited to use in direct transient response analysis.

6.

The XY, YZ and ZX planes are relative to the displacement coordinate systems of GA and GB.

7.

GA and GB must both be grid points, they must both be coincident, and they must have parallel displacement coordinate systems. If any of these conditions are not met, an error termination will occur.

8.

The shaft radius is used only for the computation of friction induced torque.

9.

A positive coefficient of friction is consistent with a counter-clockwise shaft rotation.

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OptiStruct 13.0 Reference Guide 1371 Proprietary Information of Altair Engineering

10. The time step algorithm in transient solution sequences may loose unconditional stability when this load entry is used. In most practical cases, the time step size chosen to reach a certain accuracy is below the stability limit. It is recommended to decrease the time step if results diverge. 11. If the integer entered in the TABK field is positive, it is the ID of a TABLED1 entry defining time vs. gap stiffness. If the integer is negative, then the absolute value of the integer is the ID of a TABLED1 entry defining gap penetration vs. gap force. 12. Forces due to TABK and TABU at GA and GB are only present when the gap is closed. A moment is applied only when the gap is closed and RADIUS > 0.0.

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NOLIN1 Bulk Data Entry NOLIN1 – Nonlinear Transient Load as a Tabular Function Description Defines nonlinear transient forcing functions of the form

Function of displacement:

Function of velocity:

where,

and

are the displacement and velocity at point GJ in the direction of CJ.

Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

NOLIN1

SID

GI

CI

S

GJ

CJ

TID

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

NOLIN1

21

3

4

2.1

3

10

6

Field

Contents

SID

Nonlinear load set identification number.

(9)

(10)

No default (Integer > 0) GI

Grid or scalar point identification number at which nonlinear load is to be applied. No default (Integer > 0)

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OptiStruct 13.0 Reference Guide 1373 Proprietary Information of Altair Engineering

Field

Contents

CI

Component number for GI. No default (1 < Integer < 6; blank or 0 if GI is a scalar point)

S

Scale factor. No default (Real)

GJ

Grid or scalar point identification number. No default (Integer > 0)

CJ

Component number for GJ, according to the following table:

TID

Type

Displacement

Velocity

Grid

1 < Integer < 6

11 < Integer < 16

Scalar

Blank or 0

Integer = 10

Identification number of a TABLED1, TABLED2, TABLED3, or TABLED4 entry. No default (Integer > 0)

Comments 1.

Nonlinear loads must be selected by the Subcase Information data selector NONLINEAR.

2.

Nonlinear loads may not be referenced on a DLOAD entry.

3.

All degrees-of-freedom referenced on NOLIN1 entries must be members of the solution set.

4.

Nonlinear loads as a function of velocity are denoted by components ten greater than the actual component number; that is the component 11 indicates velocity in the 1 component direction. The velocity is determined by:

where, is the time step interval and previous time step. 5.

is the displacement of GJ-CJ for the

The time step algorithm in transient solution sequences may loose unconditional stability

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when this load entry is used. In most practical cases, the time step size chosen to reach a certain accuracy is below the stability limit. It is recommended to decrease the time step if results diverge.

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OptiStruct 13.0 Reference Guide 1375 Proprietary Information of Altair Engineering

NOLIN2 Bulk Data Entry NOLIN1 – Nonlinear Transient Load as the Product of Two Variables Description Defines nonlinear transient forcing functions of the form

where, and can be either displacement or velocity at points GJ and GK, respectively, in the directions of CJ and CK, respectively. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

NOLIN2

SID

GI

CI

S

GJ

CJ

GK

CK

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

NOLIN2

14

2

1

2.9

2

1

2

Field

Contents

SID

Nonlinear load set identification number.

(9)

(10)

No default (Integer > 0) GI

Grid or scalar point identification number at which nonlinear load is to be applied. No default (Integer > 0)

CI

Component number for GI.

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Field

Contents No default (1 < Integer < 6; blank or 0 if GI is a scalar point)

S

Scale factor. No default (Real)

GJ, GK

Grid or scalar point identification number. No default (Integer > 0)

CJ, CK

Component number for GJ, GK according to the following table: Displacement

Velocity

Grid

1 < Integer < 6

11 < Integer < 16

Scalar

Blank or 0

Integer = 10

Type

Comments 1.

Nonlinear loads must be selected by the Subcase Information data selector NONLINEAR.

2.

Nonlinear loads may not be referenced on a DLOAD entry.

3.

All degrees-of-freedom referenced on NOLIN2 entries must be members of the solution set.

4.

GI-CI, GJ-CJ and GK-CK may be the same degree-of-freedom.

5.

Nonlinear loads may be a function of displacement or velocity . Velocities are denoted by a component number ten greater than the actual component number; that is the component 11 indicates velocity in the 1 component direction. The velocity is determined by:

where, is the time step interval and previous time step. 6.

is the displacement of GJ-CJ or GK-CK for the

The time step algorithm in transient solution sequences may loose unconditional stability when this load entry is used. In most practical cases, the time step size chosen to reach a certain accuracy is below the stability limit. It is recommended to decrease the time step if results diverge.

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OptiStruct 13.0 Reference Guide 1377 Proprietary Information of Altair Engineering

NOLIN3 Bulk Data Entry NOLIN1 – Nonlinear Transient Load as a Positive Variable Raised to a Power Description Defines nonlinear transient forcing functions of the form

where,

may be a displacement or a velocity at point GJ in the direction of CJ.

Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

NOLIN3

SID

GI

CI

S

GJ

CJ

A

(9)

(10)

Example

(1)

(2)

(3)

NOLIN3

4

102

(4)

(5)

(6)

(7)

(8)

-6.1

2

15

-3.5

Field

Contents

SID

Nonlinear load set identification number.

(9)

(10)

No default (Integer > 0) GI

Grid or scalar point identification number at which nonlinear load is to be applied. No default (Integer > 0)

CI

Component number for GI.

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Field

Contents No default (1 < Integer < 6; blank or 0 if GI is a scalar point)

S

Scale factor. No default (Real)

GJ

Grid or scalar point identification number. No default (Integer > 0)

CJ

Component number for GJ, GK according to the following table:

A

Type

Displacement

Velocity

Grid

1 < Integer < 6

11 < Integer < 16

Scalar

Blank or 0

Integer = 10

Exponent of the forcing function. No default (Real)

Comments 1.

Nonlinear loads must be selected by the Subcase Information data selector NONLINEAR.

2.

Nonlinear loads may not be referenced on a DLOAD entry.

3.

All degrees-of-freedom referenced on NOLIN3 entries must be members of the solution set.

4.

Nonlinear loads may be a function of displacement or velocity . Velocities are denoted by components ten greater than the actual component number; that is the component 11 indicates velocity in the 1 component direction. The velocity is determined by:

where, is the time step interval and previous time step.

Altair Engineering

is the displacement of GJ-CJ for the

OptiStruct 13.0 Reference Guide 1379 Proprietary Information of Altair Engineering

5.

Use a NOLIN4 entry for the negative range of

.

6.

The time step algorithm in transient solution sequences may loose unconditional stability when this load entry is used. In most practical cases, the time step size chosen to reach a certain accuracy is below the stability limit. It is recommended to decrease the time step if results diverge.

1380 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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NOLIN4 Bulk Data Entry NOLIN1 – Nonlinear Transient Load as a Negative Variable Raised to a Power Description Defines nonlinear transient forcing functions of the form

where,

may be a displacement or a velocity at point GJ in the direction of CJ.

Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

NOLIN4

SID

GI

CI

S

GJ

CJ

A

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

NOLIN4

2

4

6

2.0

101

Field

Contents

SID

Nonlinear load set identification number.

(7)

(8)

(9)

(10)

16.3

No default (Integer > 0) GI

Grid or scalar point identification number at which nonlinear load is to be applied. No default (Integer > 0)

CI

Component number for GI.

Altair Engineering

OptiStruct 13.0 Reference Guide 1381 Proprietary Information of Altair Engineering

Field

Contents No default (1 < Integer < 6; blank or 0 if GI is a scalar point)

S

Scale factor. No default (Real)

GJ

Grid or scalar point identification number. No default (Integer > 0)

CJ

Component number for GJ, GK according to the following table:

A

Type

Displacement

Velocity

Grid

1 < Integer < 6

11 < Integer < 16

Scalar

Blank or 0

Integer = 10

Exponent of the forcing function. No default (Real)

Comments 1.

Nonlinear loads must be selected by the Subcase Information data selector NONLINEAR.

2.

Nonlinear loads may not be referenced on a DLOAD entry.

3.

All degrees-of-freedom referenced on NOLIN4 entries must be members of the solution set.

4.

Nonlinear loads may be a function of displacement or velocity . Velocities are denoted by components ten greater than the actual component number; that is the component 11 indicates velocity in the 1 component direction. The velocity is determined by

where, is the time step interval and previous time step.

is the displacement of GJ-CJ for the

1382 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

5.

Use a NOLIN3 entry for the positive range of

6.

The time step algorithm in transient solution sequences may loose unconditional stability when this load entry is used. In most practical cases, the time step size chosen to reach a certain accuracy is below the stability limit. It is recommended to decrease the time step if results diverge.

Altair Engineering

.

OptiStruct 13.0 Reference Guide 1383 Proprietary Information of Altair Engineering

NSM Bulk Data Entry NSM – Non-structural Mass per Unit Area or per Unit Length Description Defines non-structural mass per unit area or per unit length for a list of elements or properties. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

NSM

SID

TYPE

ID

VALUE

ID

VALUE

ID

VALUE

Example 1

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

NSM

4

PSHELL

155

0.06

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

NSM

6

ELEMENT

12

0.03

13

0.03

14

0.03

Example 2

Field

Contents

SID

Identification number of non-structural mass set. No default (Integer > 0)

TYPE

This can be one of the properties PSHELL, PCOMP, PBAR, PBARL, PBEAM, PBEAML, PROD, CONROD, PSHEAR, or PTUBE, in which case the list of IDs will

1384 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Field

Contents refer to properties of the stated type, or it can be ELEMENT, in which case the list is of individual element IDs of elements that can have NSM. No default (PSHELL, PCOMP, PBAR, PBARL, PBEAM, PBEAML, PROD, CONROD, PSHEAR, PTUBE, or ELEMENT).

ID

Property or Element ID, depending on the TYPE definition No default (Integer > 0)

VALUE

Non-structural mass per unit area or per unit length No default (Real)

Comments 1.

Refer to the User's Guide section on Non-structural Mass for more information on the use of this card.

2.

Non-structural mass in this format must be selected by the NSM Subcase Information selector.

Altair Engineering

OptiStruct 13.0 Reference Guide 1385 Proprietary Information of Altair Engineering

NSM1 Bulk Data Entry NSM1 – Non-structural Mass per Unit Area or per Unit Length, Alternate Form 1 Description Defines non-structural mass per unit area or per unit length for a list of elements or properties. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

NSM1

SID

TYPE

VALUE

ID

ID

ID

ID

ID

ID

ID

ID

-etc.-

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

NSM1

2

ELEMENT

0.063

1

8

(7)

(8)

(9)

(10)

Alternate Format and Example (1)

(2)

(3)

(4)

(5)

(6)

(7)

NSM1

SID

TYPE

VALUE

ID

THRU

ID

NSM1

3

PSHELL

0.03

9

THRU

12

Field

Contents

SID

Identification number of non-structural mass set.

(8)

1386 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(9)

(10)

Altair Engineering

No default (Integer > 0) TYPE

This can be one of the properties PSHELL, PCOMP, PBAR, PBARL, PBEAM, PBEAML, PROD, CONROD, PSHEAR, or PTUBE, in which case the list of IDs will refer to properties of the stated type, or it can be ELEMENT, in which case the list is of individual element IDs of elements that can have NSM. No default (PSHELL, PCOMP, PBAR, PBARL, PBEAM, PBEAML, PROD, CONROD, PSHEAR, PTUBE, or ELEMENT).

VALUE

Non-structural mass per unit area or per unit length No default (Real)

ID

Property or Element ID, depending on the TYPE definition No default (Integer > 0, or "THRU")

Comments 1.

Refer to the User's Guide section on Non-structural Mass for more information on the use of this card.

2.

Non-structural mass in this format must be selected by the NSM Subcase Information selector.

Altair Engineering

OptiStruct 13.0 Reference Guide 1387 Proprietary Information of Altair Engineering

NSMADD Bulk Data Entry NSMADD – Non-structural Mass Set Combination Description Defines non-structural mass as the sum of the sets listed. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

NSMADD

SID

S1

S2

S3

S4

S5

S6

S7

S8

S9

S10

-etc.-

(10)

Example

(1)

(2)

(3)

(4)

NSMADD

4

100

200

(5)

(6)

Field

Contents

SID

Identification number of non-structural mass set.

(7)

(8)

(9)

(10)

No default (Integer > 0) S#

Identification number of nonstructural mass sets defined via NSM, NSM1, NSML, and NSML1 entries.

VALUE

A lumped mass value to be distributed over all the listed elements and elements referencing listed properties. No default (Real)

1388 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

ID

Property or Element ID, depending on the TYPE definition No default (Integer > 0, or "THRU")

Comments 1.

Refer to the User's Guide section on Non-structural Mass for more information on the use of this card.

2.

Non-structural mass in this format must be selected by the NSM Subcase Information selector.

3.

No S# may be the identification number of a non-structural mass set defined by another NSMADD entry.

4.

NSMADD entries take precedence over NSM, NSML, NSM1 or NSML1 entries. If both have the same SID, only the NSMADD entry will be used.

Altair Engineering

OptiStruct 13.0 Reference Guide 1389 Proprietary Information of Altair Engineering

NSML Bulk Data Entry NSML – Lumped Non-structural Mass Description Defines lumped non-structural mass for a list of elements or properties. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

NSML

SID

TYPE

ID

VALUE

ID

VALUE

ID

VALUE

Example

(1)

(2)

(3)

(4)

(5)

NSML

6

PSHELL

16

0.29

(6)

Field

Contents

SID

Identification number of non-structural mass set.

(7)

(8)

(9)

(10)

No default (Integer > 0) TYPE

This can be one of the properties PSHELL, PCOMP, PBAR, PBARL, PBEAM, PBEAML, PROD, CONROD, PSHEAR, or PTUBE, in which case the list of IDs will refer to properties of the stated type, or it can be ELEMENT, in which case the list is of individual element IDs of elements that can have NSM. No default (PSHELL, PCOMP, PBAR, PBARL, PBEAM, PBEAML, PROD, CONROD, PSHEAR, PTUBE, or ELEMENT).

ID

Property or Element ID, depending on the TYPE definition No default (Integer > 0)

1390 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

VALUE

A lumped mass value to be distributed over all the listed elements and elements referencing listed properties. No default (Real)

Comments 1.

Refer to the User's Guide section on Non-structural Mass for more information on the use of this card.

2.

Non-structural mass in this format must be selected by the NSM Subcase Information selector.

3.

This entry will calculated an equivalent non-structural mass per unit area or per unit length using the lumped mass values provided. For "area" elements, the calculation is:

and for "line" elements, the calculation is:

4.

You cannot mix "area" and "line" elements on the same entry. The "area" elements are: CQUAD4, CQUAD8, CTRIA3, CTRIA6, and CSHEAR; and the "line" elements are: CBAR, CBEAM, CTUBE, CROD, and CONROD.

Altair Engineering

OptiStruct 13.0 Reference Guide 1391 Proprietary Information of Altair Engineering

NSML1 Bulk Data Entry NSML1 – Lumped Non-structural Mass, Alternate Form 1 Description Defines lumped non-structural mass for a list of elements or properties. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

NSML

SID

TYPE

VALUE

ID

ID

ID

ID

ID

ID

ID

ID

-etc.-

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

NSML

3

ELEMENT

0.06

1

2

3

4

(9)

(10)

Alternate Format and Example (1)

(2)

(3)

(4)

(5)

(6)

(7)

NSML

SID

TYPE

VALUE

ID

THRU

ID

NSML

3

ELEMENT

0.06

1

THRU

4

Field

Contents

SID

Identification number of non-structural mass set.

(8)

(9)

(10)

No default (Integer > 0)

1392 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

TYPE

This can be one of the properties PSHELL, PCOMP, PBAR, PBARL, PBEAM, PBEAML, PROD, CONROD, PSHEAR, or PTUBE, in which case the list of IDs will refer to properties of the stated type, or it can be ELEMENT, in which case the list is of individual element IDs of elements that can have NSM. No default (PSHELL, PCOMP, PBAR, PBARL, PBEAM, PBEAML, PROD, CONROD, PSHEAR, PTUBE, or ELEMENT).

VALUE

A lumped mass value to be distributed over all the listed elements and elements referencing listed properties. No default (Real)

ID

Property or Element ID, depending on the TYPE definition No default (Integer > 0, or "THRU")

Comments 1.

Refer to the User's Guide section on Non-structural Mass for more information on the use of this card.

2.

Non-structural mass in this format must be selected by the NSM Subcase Information selector.

3.

This entry will calculated an equivalent non-structural mass per unit area or per unit length using the lumped mass values provided. For "area" elements, the calculation is:

and for "line" elements, the calculation is:

4.

You cannot mix "area" and "line" elements on the same entry. The "area" elements are: CQUAD4, CQUAD8, CTRIA3, CTRIA6, and CSHEAR; and the "line" elements are: CBAR, CBEAM, CTUBE, CROD, and CONROD.

Altair Engineering

OptiStruct 13.0 Reference Guide 1393 Proprietary Information of Altair Engineering

PAABSF Bulk Data Entry PAABSF – Frequency-Dependant Fluid Acoustic Absorber Property Description Defines the properties of the fluid acoustic absorber element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PAABSF

PID

TZREID

TSIMID

S

A

B

K

RHOC

Example

(1)

(2)

(3)

(4)

(5)

(6)

PAABSF

4

3

4

1.0

0.5

Field

Contents

PID

Property identification number.

(7)

(8)

(9)

(10)

(Integer > 0) TZREID

Identification of the TABLEDi entry that defines the resistance as a function of frequency. The real part of the impedance. (Integer > 0 or Blank)

TZIMID

Identification of the TABLEDi entry that defines the reactance as a function of frequency. The imaginary part of impedance. (Integer > 0 or Blank)

S

Impedance scale factor. Default = 1.0 (Real)

1394 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Field

Contents

A

Area factor when 1 or 2 grid points are specified in the CAABSF entry. Default = 1.0 (Real > 0.0)

B

Equivalent damping coefficient. Default = 0.0 (Real)

K

Equivalent stiffness coefficient. Default = 0.0 (Real)

RHOC

Constant used in data recovery for calculating an absorption coefficient. RHO is the media density and C is the speed of sound in the media. Default = 1.0; current unused (Real)

Input File - mdcaabsf.parm $$ $$ Optistruct Input Deck Generated by HyperMesh Version : 10.0build60 $$ Generated using HyperMesh-Optistruct Template Version : 10.0-SA1-120 $$ $$ Template: optistruct $$ $$ $ DISPLACEMENT(PHASE) = 1 OUTPUT,HGFREQ,ALL OUTPUT,OPTI,ALL OUTPUT,H3D,ALL OUTPUT,PUNCH,ALL $$------------------------------------------------------------------------------$ $$ Case Control Cards $ $$------------------------------------------------------------------------------$ $ $HMNAME LOADSTEP 1"Piston_Load" 6 $ SUBCASE 1 LABEL Piston_Load SPC = 12 METHOD(STRUCTURE) = 4 METHOD(FLUID) = 5 FREQUENCY = 3 DLOAD = 9 XYPUNCH DISP 1/ 11(T1) XYPUNCH DISP 1/ 43(T1) XYPUNCH DISP 1/ 55(T1) XYPUNCH DISP 1/ 67(T1) XYPUNCH DISP 1/ 79(T1) XYPUNCH DISP 1/ 91(T1) XYPUNCH DISP 1/ 103(T1) XYPUNCH DISP 1/ 115(T1)

Altair Engineering

OptiStruct 13.0 Reference Guide 1395 Proprietary Information of Altair Engineering

XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH XYPUNCH $ $HMSET SET 1 =

DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP DISP

1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/ 1/

127(T1) 139(T1) 151(T1) 163(T1) 175(T1) 187(T1) 199(T1) 531(T1) 543(T1) 555(T1) 567(T1) 579(T1) 591(T1) 603(T1) 615(T1) 627(T1) 639(T1) 651(T1) 663(T1) 675(T1) 687(T1)

1 1 "pressure" 43,55,67,79,91,103,115, 127,139,151,163,175,187,199, 531,543,555,567,579,591,603, 615,627,639,651,663,675,687, 6798

$ $$-------------------------------------------------------------$$ HYPERMESH TAGS $$-------------------------------------------------------------$$BEGIN TAGS $$END TAGS $ BEGIN BULK ACMODL $$ $$ Stacking Information for Ply-Based Composite Definition $$ PARAM,AUTOSPC,YES PARAM,POST,-1 $$ $$ DESVARG Data $$ $$ $$ GRID Data $$ GRID 9 GRID 10 GRID 11 GRID 12 GRID 13 GRID 14 GRID 15 GRID 16 GRID 17 GRID 18 GRID 19 GRID 20 GRID 21 GRID 22 GRID 23 GRID 24 GRID 25 GRID 26

0.492 0.246 0.0 -0.246 -0.492 -0.492 -0.492 -0.246 0.0 0.246 0.492 0.492 0.0 -0.246 0.246 0.492 0.492 0.246

0.0 0.0 0.0 0.0 0.0 0.246 0.492 0.492 0.492 0.492 0.492 0.246 0.246 0.246 0.246 -0.246 -0.492 -0.492

-1.72-15 -8.59-16 0.0 8.589-16 1.718-15 1.718-15 1.718-15 8.589-16 0.0 -8.59-16 -1.72-15 -1.72-15 0.0 8.589-16 -8.59-16 -1.72-15 -1.72-15 -8.59-16

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1396 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95

Altair Engineering

0.0 -0.492 0.0 -0.246 -0.492 8.589-16 -0.492 -0.492 1.718-15 -0.492 -0.246 1.718-15 0.0 -0.246 0.0 0.246 -0.246 -8.59-16 -0.246 -0.246 8.589-16 0.246 5.049-29-.300073 -5.99-130.0 -.300073 -5.62-130.246 -.300073 0.246 0.246 -.300073 0.246 2.524-29-.600146 -1.2-12 0.0 -.600146 -1.12-120.246 -.600146 0.246 0.246 -.600146 0.246 2.919-29-0.90022 -1.79-120.0 -.900219 -1.68-120.246 -.900219 0.246 0.246 -0.90022 0.246 3.787-29-1.20029 -2.39-120.0 -1.20029 -2.24-120.246 -1.20029 0.246 0.246 -1.20029 0.246 4.733-29-1.50037 -3.0-12 0.0 -1.50037 -2.81-120.246 -1.50037 0.246 0.246 -1.50037 0.246 5.364-29-1.80044 -3.6-12 0.0 -1.80044 -3.37-120.246 -1.80044 0.246 0.246 -1.80044 0.246 6.311-29-2.10051 -4.2-12 0.0 -2.10051 -3.93-120.246 -2.10051 0.246 0.246 -2.10051 0.246 7.258-29-2.40059 -4.79-120.0 -2.40059 -4.49-120.246 -2.40059 0.246 0.246 -2.40059 0.246 8.204-29-2.70066 -5.39-120.0 -2.70066 -5.06-120.246 -2.70066 0.246 0.246 -2.70066 0.246 8.835-29-3.00073 -5.99-120.0 -3.00073 -5.62-120.246 -3.00073 0.246 0.246 -3.00073 0.246 9.782-29-3.30081 -6.59-120.0 -3.30081 -6.18-120.246 -3.30081 0.246 0.246 -3.30081 0.246 1.073-28-3.60088 -7.19-120.0 -3.60088 -6.74-120.246 -3.60088 0.246 0.246 -3.60088 0.246 1.136-28-3.90095 -7.78-120.0 -3.90095 -7.3-12 0.246 -3.90095 0.246 0.246 -3.90095 0.246 1.231-28-4.20102 -8.38-120.0 -4.20102 -7.86-120.246 -4.20102 0.246 0.246 -4.20102 0.246 1.294-28-4.5011 -8.99-120.0 -4.5011 -8.43-120.246 -4.5011 0.246 0.246 -4.5011 0.246 1.388-28-4.80117 -9.59-120.0 -4.80117

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1397 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161 162 163 164

-8.99-120.246 -4.80117 0.246 0.246 -4.80117 0.246 1.452-28-5.10124 -1.02-110.0 -5.10124 -9.55-120.246 -5.10124 0.246 0.246 -5.10124 0.246 1.515-28-5.40132 -1.08-110.0 -5.40132 -1.01-110.246 -5.40132 0.246 0.246 -5.40132 0.246 1.609-28-5.70139 -1.14-110.0 -5.70139 -1.07-110.246 -5.70139 0.246 0.246 -5.70139 0.246 1.672-28-6.00146 -1.2-11 0.0 -6.00146 -1.12-110.246 -6.00146 0.246 0.246 -6.00146 0.246 1.735-28-6.30154 -1.26-110.0 -6.30154 -1.18-110.246 -6.30154 0.246 0.246 -6.30154 0.246 1.83-28 -6.60161 -1.32-110.0 -6.60161 -1.23-110.246 -6.60161 0.246 0.246 -6.60161 0.246 1.893-28-6.90168 -1.38-110.0 -6.90168 -1.29-110.246 -6.90168 0.246 0.246 -6.90168 0.246 1.956-28-7.20176 -1.44-110.0 -7.20176 -1.35-110.246 -7.20176 0.246 0.246 -7.20176 0.246 2.019-28-7.50183 -1.5-11 0.0 -7.50183 -1.4-11 0.246 -7.50183 0.246 0.246 -7.50183 0.246 2.083-28-7.8019 -1.55-110.0 -7.8019 -1.46-110.246 -7.8019 0.246 0.246 -7.8019 0.246 2.146-28-8.10198 -1.61-110.0 -8.10198 -1.51-110.246 -8.10198 0.246 0.246 -8.10198 0.246 2.209-28-8.40205 -1.67-110.0 -8.40205 -1.57-110.246 -8.40205 0.246 0.246 -8.40205 0.246 2.272-28-8.70212 -1.73-110.0 -8.70212 -1.63-110.246 -8.70212 0.246 0.246 -8.70212 0.246 2.335-28-9.0022 -1.79-110.0 -9.0022 -1.68-110.246 -9.0022 0.246 0.246 -9.0022 0.246 2.398-28-9.30227 -1.85-110.0 -9.30227 -1.74-110.246 -9.30227 0.246 0.246 -9.30227 0.246 2.461-28-9.60234 -1.91-110.0 -9.60234 -1.79-110.246 -9.60234 0.246 0.246 -9.60234 0.246 2.524-28-9.90241 -1.97-110.0 -9.90241 -1.85-110.246 -9.90241

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1398 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

165 166 167 168 169 170 171 172 173 174 175 176 177 178 179 180 181 182 183 184 185 186 187 188 189 190 191 192 193 194 195 196 197 198 199 200 201 522 523 524 525 526 527 528 529 530 531 532 533 534 535 536 537 538 539 540 541 542 543 544 545 546 547 548 549 550 551 552 553

Altair Engineering

0.246 0.246 -9.90241 0.246 2.556-28-10.2025 -2.03-110.0 -10.2025 -1.91-110.246 -10.2025 0.246 0.246 -10.2025 0.246 2.619-28-10.5026 -2.09-110.0 -10.5026 -1.96-110.246 -10.5026 0.246 0.246 -10.5026 0.246 2.682-28-10.8026 -2.15-110.0 -10.8026 -2.02-110.246 -10.8026 0.246 0.246 -10.8026 0.246 2.745-28-11.1027 -2.21-110.0 -11.1027 -2.07-110.246 -11.1027 0.246 0.246 -11.1027 0.246 2.777-28-11.4028 -2.27-110.0 -11.4028 -2.13-110.246 -11.4028 0.246 0.246 -11.4028 0.246 2.84-28 -11.7029 -2.33-110.0 -11.7029 -2.19-110.246 -11.7029 0.246 0.246 -11.7029 0.246 2.871-28-12.0029 -2.39-110.0 -12.0029 -2.24-110.246 -12.0029 0.246 0.246 -12.0029 0.246 2.935-28-12.303 -2.45-110.0 -12.303 -2.3-11 0.246 -12.303 0.246 0.246 -12.303 0.246 2.966-28-12.6031 -2.51-110.0 -12.6031 -2.35-110.246 -12.6031 0.246 0.246 -12.6031 0.246 2.935-28-12.903 -7.36-110.0 -12.903 -6.9-11 0.246 -12.903 0.246 0.246 -12.903 0.246 2.903-28-13.2031 -7.42-110.0 -13.2031 -6.95-110.246 -13.2031 0.246 0.246 -13.2031 0.246 2.84-28 -13.5032 -7.48-110.0 -13.5032 -7.01-110.246 -13.5032 0.246 0.246 -13.5032 0.246 2.777-28-13.8032 -7.54-110.0 -13.8032 -7.06-110.246 -13.8032 0.246 0.246 -13.8032 0.246 2.745-28-14.1033 -7.6-11 0.0 -14.1033 -7.12-110.246 -14.1033 0.246 0.246 -14.1033 0.246 2.682-28-14.4034 -7.67-110.0 -14.4034 -7.19-110.246 -14.4034 0.246 0.246 -14.4034 0.246 2.619-28-14.7034 -7.73-110.0 -14.7034 -7.24-110.246 -14.7034 0.246 0.246 -14.7034 0.246 2.587-28-15.0035 -7.78-110.0 -15.0035 -7.3-11 0.246 -15.0035 0.246 0.246 -15.0035

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1399 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

554 555 556 557 558 559 560 561 562 563 564 565 566 567 568 569 570 571 572 573 574 575 576 577 578 579 580 581 582 583 584 585 586 587 588 589 590 591 592 593 594 595 596 597 598 599 600 601 602 603 604 605 606 607 608 609 610 611 612 613 614 615 616 617 618 619 620 621 622

0.246 2.524-28-15.3036 -7.84-110.0 -15.3036 -7.35-110.246 -15.3036 0.246 0.246 -15.3036 0.246 2.461-28-15.6037 -7.9-11 0.0 -15.6037 -7.41-110.246 -15.6037 0.246 0.246 -15.6037 0.246 2.398-28-15.9037 -7.96-110.0 -15.9037 -7.47-110.246 -15.9037 0.246 0.246 -15.9037 0.246 2.335-28-16.2038 -8.02-110.0 -16.2038 -7.52-110.246 -16.2038 0.246 0.246 -16.2038 0.246 2.272-28-16.5039 -8.08-110.0 -16.5039 -7.58-110.246 -16.5039 0.246 0.246 -16.5039 0.246 2.209-28-16.804 -8.14-110.0 -16.804 -7.63-110.246 -16.804 0.246 0.246 -16.804 0.246 2.146-28-17.104 -8.2-11 0.0 -17.104 -7.69-110.246 -17.104 0.246 0.246 -17.104 0.246 2.083-28-17.4041 -8.26-110.0 -17.4041 -7.75-110.246 -17.4041 0.246 0.246 -17.4041 0.246 2.019-28-17.7042 -8.32-110.0 -17.7042 -7.8-11 0.246 -17.7042 0.246 0.246 -17.7042 0.246 1.956-28-18.0042 -8.38-110.0 -18.0042 -7.86-110.246 -18.0042 0.246 0.246 -18.0042 0.246 1.893-28-18.3043 -8.44-110.0 -18.3043 -7.91-110.246 -18.3043 0.246 0.246 -18.3043 0.246 1.83-28 -18.6044 -8.5-11 0.0 -18.6044 -7.97-110.246 -18.6044 0.246 0.246 -18.6044 0.246 1.735-28-18.9045 -8.56-110.0 -18.9045 -8.03-110.246 -18.9045 0.246 0.246 -18.9045 0.246 1.672-28-19.2045 -8.62-110.0 -19.2045 -8.08-110.246 -19.2045 0.246 0.246 -19.2045 0.246 1.609-28-19.5046 -8.68-110.0 -19.5046 -8.14-110.246 -19.5046 0.246 0.246 -19.5046 0.246 1.515-28-19.8047 -8.74-110.0 -19.8047 -8.19-110.246 -19.8047 0.246 0.246 -19.8047 0.246 1.452-28-20.1048 -8.8-11 0.0 -20.1048 -8.25-110.246 -20.1048 0.246 0.246 -20.1048 0.246 1.388-28-20.4048

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1400 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

623 624 625 626 627 628 629 630 631 632 633 634 635 636 637 638 639 640 641 642 643 644 645 646 647 648 649 650 651 652 653 654 655 656 657 658 659 660 661 662 663 664 665 666 667 668 669 670 671 672 673 674 675 676 677 678 679 680 681 682 683 684 685 686 687 688 689 690 691

Altair Engineering

-8.86-110.0 -20.4048 -8.31-110.246 -20.4048 0.246 0.246 -20.4048 0.246 1.294-28-20.7049 -8.92-110.0 -20.7049 -8.36-110.246 -20.7049 0.246 0.246 -20.7049 0.246 1.231-28-21.005 -8.98-110.0 -21.005 -8.42-110.246 -21.005 0.246 0.246 -21.005 0.246 1.136-28-21.3051 -9.04-110.0 -21.3051 -8.47-110.246 -21.3051 0.246 0.246 -21.3051 0.246 1.073-28-21.6051 -9.1-11 0.0 -21.6051 -8.53-110.246 -21.6051 0.246 0.246 -21.6051 0.246 9.782-29-21.9052 -9.16-110.0 -21.9052 -8.59-110.246 -21.9052 0.246 0.246 -21.9052 0.246 8.835-29-22.2053 -9.22-110.0 -22.2053 -8.64-110.246 -22.2053 0.246 0.246 -22.2053 0.246 8.204-29-22.5053 -9.28-110.0 -22.5053 -8.7-11 0.246 -22.5053 0.246 0.246 -22.5053 0.246 7.258-29-22.8054 -9.34-110.0 -22.8054 -8.75-110.246 -22.8054 0.246 0.246 -22.8054 0.246 6.311-29-23.1055 -9.4-11 0.0 -23.1055 -8.81-110.246 -23.1055 0.246 0.246 -23.1055 0.246 5.364-29-23.4056 -9.46-110.0 -23.4056 -8.87-110.246 -23.4056 0.246 0.246 -23.4056 0.246 4.733-29-23.7056 -9.52-110.0 -23.7056 -8.92-110.246 -23.7056 0.246 0.246 -23.7056 0.246 3.787-29-24.0057 -9.58-110.0 -24.0057 -8.98-110.246 -24.0057 0.246 0.246 -24.0057 0.246 2.84-29 -24.3058 -9.64-110.0 -24.3058 -9.04-110.246 -24.3058 0.246 0.246 -24.3058 0.246 1.893-29-24.6059 -9.7-11 0.0 -24.6059 -9.09-110.246 -24.6059 0.246 0.246 -24.6059 0.246 9.466-30-24.9059 -9.76-110.0 -24.9059 -9.15-110.246 -24.9059 0.246 0.246 -24.9059 0.246 4.151-12-25.206 -9.82-112.767-12-25.206 -9.16-110.246 -25.206 0.246 0.246 -25.206 0.492 4.323-13-.300073 0.492 0.246 -.300073

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1401 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

692 693 694 695 696 697 698 699 700 701 702 703 704 705 706 707 708 709 710 711 712 713 714 715 716 717 718 719 720 721 722 723 724 725 726 727 728 729 730 731 732 733 734 735 736 737 738 739 740 741 742 743 744 745 746 747 748 749 750 751 752 753 754 755 756 757 758 759 760

0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492

1.621-13-.600146 0.246 -.600146 1.592-13-0.90022 0.246 -0.90022 2.009-13-1.20029 0.246 -1.20029 2.5-13 -1.50037 0.246 -1.50037 3.004-13-1.80044 0.246 -1.80044 3.51-13 -2.10051 0.246 -2.10051 4.016-13-2.40059 0.246 -2.40059 4.522-13-2.70066 0.246 -2.70066 5.028-13-3.00073 0.246 -3.00073 5.534-13-3.30081 0.246 -3.30081 6.041-13-3.60088 0.246 -3.60088 6.547-13-3.90095 0.246 -3.90095 7.053-13-4.20102 0.246 -4.20102 7.559-13-4.5011 0.246 -4.5011 8.066-13-4.80117 0.246 -4.80117 8.572-13-5.10124 0.246 -5.10124 9.078-13-5.40132 0.246 -5.40132 9.584-13-5.70139 0.246 -5.70139 1.009-12-6.00146 0.246 -6.00146 1.06-12 -6.30154 0.246 -6.30154 1.11-12 -6.60161 0.246 -6.60161 1.161-12-6.90168 0.246 -6.90168 1.212-12-7.20176 0.246 -7.20176 1.262-12-7.50183 0.246 -7.50183 1.313-12-7.8019 0.246 -7.8019 1.363-12-8.10198 0.246 -8.10198 1.414-12-8.40205 0.246 -8.40205 1.465-12-8.70212 0.246 -8.70212 1.515-12-9.0022 0.246 -9.0022 1.566-12-9.30227 0.246 -9.30227 1.616-12-9.60234 0.246 -9.60234 1.667-12-9.90242 0.246 -9.90242 1.718-12-10.2025 0.246 -10.2025 1.768-12-10.5026 0.246 -10.5026 1.819-12-10.8026

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1402 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

761 762 763 764 765 766 767 768 769 770 771 772 773 934 935 936 937 938 939 940 941 942 943 944 945 946 947 948 949 950 951 952 953 954 955 956 957 958 959 960 961 962 963 964 965 966 967 968 969 970 971 972 973 974 975 976 977 978 979 980 981 982 983 984 985 986 987 988 989

Altair Engineering

0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492

0.246 -10.8026 1.87-12 -11.1027 0.246 -11.1027 1.92-12 -11.4028 0.246 -11.4028 1.971-12-11.7029 0.246 -11.7029 2.021-12-12.0029 0.246 -12.0029 2.072-12-12.303 0.246 -12.303 2.123-12-12.6031 0.246 -12.6031 6.223-12-12.903 0.246 -12.903 6.274-12-13.2031 0.246 -13.2031 6.324-12-13.5032 0.246 -13.5032 6.375-12-13.8032 0.246 -13.8032 6.425-12-14.1033 0.246 -14.1033 6.476-12-14.4034 0.246 -14.4034 6.527-12-14.7034 0.246 -14.7034 6.577-12-15.0035 0.246 -15.0035 6.628-12-15.3036 0.246 -15.3036 6.679-12-15.6037 0.246 -15.6037 6.729-12-15.9037 0.246 -15.9037 6.78-12 -16.2038 0.246 -16.2038 6.83-12 -16.5039 0.246 -16.5039 6.881-12-16.804 0.246 -16.804 6.932-12-17.104 0.246 -17.104 6.982-12-17.4041 0.246 -17.4041 7.033-12-17.7042 0.246 -17.7042 7.083-12-18.0042 0.246 -18.0042 7.134-12-18.3043 0.246 -18.3043 7.185-12-18.6044 0.246 -18.6044 7.235-12-18.9045 0.246 -18.9045 7.286-12-19.2045 0.246 -19.2045 7.337-12-19.5046 0.246 -19.5046 7.387-12-19.8047 0.246 -19.8047 7.438-12-20.1048 0.246 -20.1048 7.488-12-20.4048 0.246 -20.4048 7.539-12-20.7049 0.246 -20.7049 7.59-12 -21.005 0.246 -21.005

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1403 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

990 991 992 993 994 995 996 997 998 999 1000 1001 1002 1003 1004 1005 1006 1007 1008 1009 1010 1011 1012 1013 1014 1015 1016 1017 1018 1019 1020 1021 1022 1023 1024 1025 1026 1027 1028 1029 1030 1031 1032 1033 1034 1035 1036 1037 1038 1039 1040 1041 1042 1043 1044 1045 1046 1047 1048 1049 1050 1051 1052 1053 1054 1055 1056 1057 1058

0.492 7.64-12 -21.3051 0.492 0.246 -21.3051 0.492 7.691-12-21.6051 0.492 0.246 -21.6051 0.492 7.742-12-21.9052 0.492 0.246 -21.9052 0.492 7.792-12-22.2053 0.492 0.246 -22.2053 0.492 7.843-12-22.5053 0.492 0.246 -22.5053 0.492 7.893-12-22.8054 0.492 0.246 -22.8054 0.492 7.944-12-23.1055 0.492 0.246 -23.1055 0.492 7.995-12-23.4056 0.492 0.246 -23.4056 0.492 8.045-12-23.7056 0.492 0.246 -23.7056 0.492 8.096-12-24.0057 0.492 0.246 -24.0057 0.492 8.146-12-24.3058 0.492 0.246 -24.3058 0.492 8.197-12-24.6059 0.492 0.246 -24.6059 0.492 8.248-12-24.9059 0.492 0.246 -24.9059 0.492 5.534-12-25.206 0.492 0.246 -25.206 -5.24-130.492 -.300073 0.246 0.492 -.300073 -1.05-120.492 -.600146 0.246 0.492 -.600146 -1.57-120.492 -.900219 0.246 0.492 -0.90022 -2.09-120.492 -1.20029 0.246 0.492 -1.20029 -2.63-120.492 -1.50037 0.246 0.492 -1.50037 -3.15-120.492 -1.80044 0.246 0.492 -1.80044 -3.67-120.492 -2.10051 0.246 0.492 -2.10051 -4.19-120.492 -2.40059 0.246 0.492 -2.40059 -4.72-120.492 -2.70066 0.246 0.492 -2.70066 -5.24-120.492 -3.00073 0.246 0.492 -3.00073 -5.76-120.492 -3.30081 0.246 0.492 -3.30081 -6.29-120.492 -3.60088 0.246 0.492 -3.60088 -6.81-120.492 -3.90095 0.246 0.492 -3.90095 -7.33-120.492 -4.20102 0.246 0.492 -4.20102 -7.87-120.492 -4.5011 0.246 0.492 -4.5011 -8.39-120.492 -4.80117 0.246 0.492 -4.80117 -8.91-120.492 -5.10124 0.246 0.492 -5.10124 -9.44-120.492 -5.40132 0.246 0.492 -5.40132 -9.96-120.492 -5.70139 0.246 0.492 -5.70139 -1.05-110.492 -6.00146 0.246 0.492 -6.00146 -1.1-11 0.492 -6.30154

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1404 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1059 1060 1061 1062 1063 1064 1065 1066 1067 1068 1069 1070 1071 1072 1073 1074 1075 1076 1077 1078 1079 1080 1081 1082 1083 1084 1085 1086 1087 1088 1089 1090 1091 1092 1093 1094 1095 1096 1097 1098 1099 1100 1101 1262 1263 1264 1265 1266 1267 1268 1269 1270 1271 1272 1273 1274 1275 1276 1277 1278 1279 1280 1281 1282 1283 1284 1285 1286 1287

Altair Engineering

0.246 0.492 -1.15-110.492 0.246 0.492 -1.2-11 0.492 0.246 0.492 -1.26-110.492 0.246 0.492 -1.31-110.492 0.246 0.492 -1.36-110.492 0.246 0.492 -1.41-110.492 0.246 0.492 -1.46-110.492 0.246 0.492 -1.52-110.492 0.246 0.492 -1.57-110.492 0.246 0.492 -1.62-110.492 0.246 0.492 -1.67-110.492 0.246 0.492 -1.73-110.492 0.246 0.492 -1.78-110.492 0.246 0.492 -1.83-110.492 0.246 0.492 -1.88-110.492 0.246 0.492 -1.94-110.492 0.246 0.492 -1.99-110.492 0.246 0.492 -2.04-110.492 0.246 0.492 -2.09-110.492 0.246 0.492 -2.14-110.492 0.246 0.492 -2.2-11 0.492 0.246 0.492 -6.43-110.492 0.246 0.492 -6.49-110.492 0.246 0.492 -6.54-110.492 0.246 0.492 -6.59-110.492 0.246 0.492 -6.64-110.492 0.246 0.492 -6.71-110.492 0.246 0.492 -6.76-110.492 0.246 0.492 -6.81-110.492 0.246 0.492 -6.86-110.492 0.246 0.492 -6.91-110.492 0.246 0.492 -6.97-110.492 0.246 0.492 -7.02-110.492 0.246 0.492 -7.07-110.492 0.246 0.492

-6.30154 -6.60161 -6.60161 -6.90168 -6.90168 -7.20176 -7.20176 -7.50183 -7.50183 -7.8019 -7.8019 -8.10198 -8.10198 -8.40205 -8.40205 -8.70212 -8.70212 -9.0022 -9.0022 -9.30227 -9.30227 -9.60234 -9.60234 -9.90241 -9.90241 -10.2025 -10.2025 -10.5026 -10.5026 -10.8026 -10.8026 -11.1027 -11.1027 -11.4028 -11.4028 -11.7029 -11.7029 -12.0029 -12.0029 -12.303 -12.303 -12.6031 -12.6031 -12.903 -12.903 -13.2031 -13.2031 -13.5032 -13.5032 -13.8032 -13.8032 -14.1033 -14.1033 -14.4034 -14.4034 -14.7034 -14.7034 -15.0035 -15.0035 -15.3036 -15.3036 -15.6037 -15.6037 -15.9037 -15.9037 -16.2038 -16.2038 -16.5039 -16.5039

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1405 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1288 1289 1290 1291 1292 1293 1294 1295 1296 1297 1298 1299 1300 1301 1302 1303 1304 1305 1306 1307 1308 1309 1310 1311 1312 1313 1314 1315 1316 1317 1318 1319 1320 1321 1322 1323 1324 1325 1326 1327 1328 1329 1330 1331 1332 1333 1334 1335 1336 1337 1338 1339 1340 1341 1342 1343 1344 1345 1346 1347 1348 1349 1350 1351 1352 1353 1354 1355 1356

-7.12-110.492 0.246 0.492 -7.18-110.492 0.246 0.492 -7.23-110.492 0.246 0.492 -7.28-110.492 0.246 0.492 -7.33-110.492 0.246 0.492 -7.39-110.492 0.246 0.492 -7.44-110.492 0.246 0.492 -7.49-110.492 0.246 0.492 -7.54-110.492 0.246 0.492 -7.59-110.492 0.246 0.492 -7.65-110.492 0.246 0.492 -7.7-11 0.492 0.246 0.492 -7.75-110.492 0.246 0.492 -7.8-11 0.492 0.246 0.492 -7.86-110.492 0.246 0.492 -7.91-110.492 0.246 0.492 -7.96-110.492 0.246 0.492 -8.01-110.492 0.246 0.492 -8.07-110.492 0.246 0.492 -8.12-110.492 0.246 0.492 -8.17-110.492 0.246 0.492 -8.22-110.492 0.246 0.492 -8.27-110.492 0.246 0.492 -8.33-110.492 0.246 0.492 -8.38-110.492 0.246 0.492 -8.43-110.492 0.246 0.492 -8.48-110.492 0.246 0.492 -8.54-110.492 0.246 0.492 -8.59-110.492 0.246 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492

-16.804 -16.804 -17.104 -17.104 -17.4041 -17.4041 -17.7042 -17.7042 -18.0042 -18.0042 -18.3043 -18.3043 -18.6044 -18.6044 -18.9045 -18.9045 -19.2045 -19.2045 -19.5046 -19.5046 -19.8047 -19.8047 -20.1048 -20.1048 -20.4048 -20.4048 -20.7049 -20.7049 -21.005 -21.005 -21.3051 -21.3051 -21.6051 -21.6051 -21.9052 -21.9052 -22.2053 -22.2053 -22.5053 -22.5053 -22.8054 -22.8054 -23.1055 -23.1055 -23.4056 -23.4056 -23.7056 -23.7056 -24.0057 -24.0057 -24.3058 -24.3058 -24.6059 -24.6059 -24.9059 -24.9059 -25.206 -25.206 -.300073 -.600146 -0.90022 -1.20029 -1.50037 -1.80044 -2.10051 -2.40059 -2.70066 -3.00073 -3.30081

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1406 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1357 1358 1359 1360 1361 1362 1363 1364 1365 1366 1367 1368 1369 1370 1371 1372 1373 1374 1375 1376 1377 1378 1379 1380 1381 1382 1383 1384 1385 1386 1387 1468 1469 1470 1471 1472 1473 1474 1475 1476 1477 1478 1479 1480 1481 1482 1483 1484 1485 1486 1487 1488 1489 1490 1491 1492 1493 1494 1495 1496 1497 1498 1499 1500 1501 1502 1503 1504 1505

Altair Engineering

0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492

0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492

-3.60088 -3.90095 -4.20102 -4.5011 -4.80117 -5.10124 -5.40132 -5.70139 -6.00146 -6.30154 -6.60161 -6.90168 -7.20176 -7.50183 -7.8019 -8.10198 -8.40205 -8.70212 -9.0022 -9.30227 -9.60234 -9.90242 -10.2025 -10.5026 -10.8026 -11.1027 -11.4028 -11.7029 -12.0029 -12.303 -12.6031 -12.903 -13.2031 -13.5032 -13.8032 -14.1033 -14.4034 -14.7034 -15.0035 -15.3036 -15.6037 -15.9037 -16.2038 -16.5039 -16.804 -17.104 -17.4041 -17.7042 -18.0042 -18.3043 -18.6044 -18.9045 -19.2045 -19.5046 -19.8047 -20.1048 -20.4048 -20.7049 -21.005 -21.3051 -21.6051 -21.9052 -22.2053 -22.5053 -22.8054 -23.1055 -23.4056 -23.7056 -24.0057

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1407 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1506 1507 1508 1509 1510 1511 1512 1513 1514 1515 1516 1517 1518 1519 1520 1521 1522 1523 1524 1525 1526 1527 1528 1529 1530 1531 1532 1533 1534 1535 1536 1537 1538 1539 1540 1541 1542 1543 1544 1545 1546 1547 1548 1549 1550 1551 1552 1553 1554 1555 1556 1557 1558 1559 1560 1561 1562 1563 1564 1565 1566 1567 1568 1569 1570 1571 1572 1573 1574

0.492 0.492 0.492 0.492 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246

0.492 -24.3058 0.492 -24.6059 0.492 -24.9059 0.492 -25.206 0.0 -.300073 8.522-26-.300073 0.246 -.300073 0.246 -.300073 0.0 -.600146 1.441-26-.600146 0.246 -.600146 0.246 -.600146 0.0 -.900219 2.685-27-.900219 0.246 -.900219 0.246 -.900219 0.0 -1.20029 8.709-28-1.20029 0.246 -1.20029 0.246 -1.20029 0.0 -1.50037 6.595-28-1.50037 0.246 -1.50037 0.246 -1.50037 0.0 -1.80044 7.258-28-1.80044 0.246 -1.80044 0.246 -1.80044 0.0 -2.10051 7.936-28-2.10051 0.246 -2.10051 0.246 -2.10051 0.0 -2.40058 8.993-28-2.40058 0.246 -2.40058 0.246 -2.40058 0.0 -2.70066 1.01-27 -2.70066 0.246 -2.70066 0.246 -2.70066 0.0 -3.00073 1.185-27-3.00073 0.246 -3.00073 0.246 -3.00073 0.0 -3.3008 1.313-27-3.3008 0.246 -3.3008 0.246 -3.3008 0.0 -3.60088 1.341-27-3.60088 0.246 -3.60088 0.246 -3.60088 0.0 -3.90095 1.36-27 -3.90095 0.246 -3.90095 0.246 -3.90095 0.0 -4.20102 1.447-27-4.20102 0.246 -4.20102 0.246 -4.20102 0.0 -4.5011 1.549-27-4.5011 0.246 -4.5011 0.246 -4.5011 0.0 -4.80117 1.775-27-4.80117 0.246 -4.80117 0.246 -4.80117 0.0 -5.10124

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1408 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1575 1576 1577 1578 1579 1580 1581 1582 1583 1584 1585 1586 1587 1588 1589 1590 1591 1592 1593 1594 1595 1596 1597 1598 1599 1600 1601 1602 1603 1604 1605 1606 1607 1608 1609 1610 1611 1612 1613 1614 1615 1616 1617 1618 1619 1620 1621 1622 1623 1624 1625 1626 1627 1628 1629 1630 1631 1632 1633 1634 1635 1636 1637 1638 1639 1640 1641 1642 1643

Altair Engineering

-0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492

1.907-27-5.10124 0.246 -5.10124 0.246 -5.10124 0.0 -5.40132 2.023-27-5.40132 0.246 -5.40132 0.246 -5.40132 0.0 -5.70139 2.136-27-5.70139 0.246 -5.70139 0.246 -5.70139 0.0 -6.00146 2.248-27-6.00146 0.246 -6.00146 0.246 -6.00146 0.0 -6.30154 2.36-27 -6.30154 0.246 -6.30154 0.246 -6.30154 0.0 -6.60161 2.474-27-6.60161 0.246 -6.60161 0.246 -6.60161 0.0 -6.90168 2.551-27-6.90168 0.246 -6.90168 0.246 -6.90168 0.0 -7.20176 2.693-27-7.20176 0.246 -7.20176 0.246 -7.20176 0.0 -7.50183 2.965-27-7.50183 0.246 -7.50183 0.246 -7.50183 0.0 -7.8019 3.113-27-7.8019 0.246 -7.8019 0.246 -7.8019 0.0 -8.10198 3.067-27-8.10198 0.246 -8.10198 0.246 -8.10198 0.0 -8.40205 2.979-27-8.40205 0.246 -8.40205 0.246 -8.40205 0.0 -8.70212 3.233-27-8.70212 0.246 -8.70212 0.246 -8.70212 0.0 -9.0022 3.323-27-9.00219 0.246 -9.00219 0.246 -9.0022 0.0 -9.30227 3.67-27 -9.30227 0.246 -9.30227 0.246 -9.30227 0.0 -9.60234 3.58-27 -9.60234 0.246 -9.60234 0.246 -9.60234 0.0 -9.90241 3.454-27-9.90241 0.246 -9.90241 0.246 -9.90241 0.0 -10.2025 3.782-27-10.2025

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1409 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1644 1645 1646 1647 1648 1649 1650 1651 1652 1653 1654 1655 1656 1657 1658 1659 1660 1661 1662 1663 1664 1665 1666 1667 1668 1669 1670 1671 1672 1673 1674 1675 1676 1677 1998 1999 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022 2023 2024 2025 2026 2027 2028 2029 2030 2031 2032

-0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492

0.246 -10.2025 0.246 -10.2025 0.0 -10.5026 3.659-27-10.5026 0.246 -10.5026 0.246 -10.5026 0.0 -10.8026 4.003-27-10.8026 0.246 -10.8026 0.246 -10.8026 0.0 -11.1027 4.154-27-11.1027 0.246 -11.1027 0.246 -11.1027 0.0 -11.4028 4.274-27-11.4028 0.246 -11.4028 0.246 -11.4028 0.0 -11.7029 4.388-27-11.7028 0.246 -11.7028 0.246 -11.7029 0.0 -12.0029 4.5-27 -12.0029 0.246 -12.0029 0.246 -12.0029 0.0 -12.303 4.358-27-12.303 0.246 -12.303 0.246 -12.303 0.0 -12.6031 4.424-27-12.6031 0.246 -12.6031 0.246 -12.6031 0.0 -12.903 1.381-26-12.903 0.246 -12.903 0.246 -12.903 0.0 -13.2031 1.395-26-13.2031 0.246 -13.2031 0.246 -13.2031 0.0 -13.5032 1.407-26-13.5031 0.246 -13.5031 0.246 -13.5032 0.0 -13.8032 1.418-26-13.8032 0.246 -13.8032 0.246 -13.8032 0.0 -14.1033 1.429-26-14.1033 0.246 -14.1033 0.246 -14.1033 0.0 -14.4034 1.441-26-14.4034 0.246 -14.4034 0.246 -14.4034 0.0 -14.7034 1.452-26-14.7034 0.246 -14.7034 0.246 -14.7034 0.0 -15.0035 1.463-26-15.0035 0.246 -15.0035 0.246 -15.0035 0.0 -15.3036 1.454-26-15.3036 0.246 -15.3036

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1410 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2033 2034 2035 2036 2037 2038 2039 2040 2041 2042 2043 2044 2045 2046 2047 2048 2049 2050 2051 2052 2053 2054 2055 2056 2057 2058 2059 2060 2061 2062 2063 2064 2065 2066 2067 2068 2069 2070 2071 2072 2073 2074 2075 2076 2077 2078 2079 2080 2081 2082 2083 2084 2085 2086 2087 2088 2089 2090 2091 2092 2093 2094 2095 2096 2097 2098 2099 2100 2101

Altair Engineering

-0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246

0.246 -15.3036 0.0 -15.6037 1.38-26 -15.6037 0.246 -15.6037 0.246 -15.6037 0.0 -15.9037 1.479-26-15.9037 0.246 -15.9037 0.246 -15.9037 0.0 -16.2038 1.505-26-16.2038 0.246 -16.2038 0.246 -16.2038 0.0 -16.5039 1.519-26-16.5039 0.246 -16.5039 0.246 -16.5039 0.0 -16.804 1.531-26-16.804 0.246 -16.804 0.246 -16.804 0.0 -17.104 1.542-26-17.104 0.246 -17.104 0.246 -17.104 0.0 -17.4041 1.553-26-17.4041 0.246 -17.4041 0.246 -17.4041 0.0 -17.7042 1.564-26-17.7042 0.246 -17.7042 0.246 -17.7042 0.0 -18.0042 1.576-26-18.0042 0.246 -18.0042 0.246 -18.0042 0.0 -18.3043 1.477-26-18.3043 0.246 -18.3043 0.246 -18.3043 0.0 -18.6044 1.58-26 -18.6044 0.246 -18.6044 0.246 -18.6044 0.0 -18.9045 1.606-26-18.9045 0.246 -18.9045 0.246 -18.9045 0.0 -19.2045 1.62-26 -19.2045 0.246 -19.2045 0.246 -19.2045 0.0 -19.5046 1.632-26-19.5046 0.246 -19.5046 0.246 -19.5046 0.0 -19.8047 1.643-26-19.8047 0.246 -19.8047 0.246 -19.8047 0.0 -20.1048 1.655-26-20.1048 0.246 -20.1048 0.246 -20.1048 0.0 -20.4048 1.666-26-20.4048 0.246 -20.4048 0.246 -20.4048

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1411 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2102 2103 2104 2105 2106 2107 2108 2109 2110 2111 2112 2113 2114 2115 2116 2117 2118 2119 2120 2121 2122 2123 2124 2125 2126 2127 2128 2129 2130 2131 2132 2133 2134 2135 2136 2137 2138 2139 2140 2141 2142 2143 2144 2145 2146 2147 2148 2149 2150 2151 2152 2153 2154 2155 2156 2157 2158 2159 2160 2161 2162 2163 2164 2165 2166 2167 2168 2169 2170

-0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.246 -0.492 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492

0.0 -20.7049 1.677-26-20.7049 0.246 -20.7049 0.246 -20.7049 0.0 -21.005 1.572-26-21.005 0.246 -21.005 0.246 -21.005 0.0 -21.3051 1.68-26 -21.3051 0.246 -21.3051 0.246 -21.3051 0.0 -21.6051 1.708-26-21.6051 0.246 -21.6051 0.246 -21.6051 0.0 -21.9052 1.722-26-21.9052 0.246 -21.9052 0.246 -21.9052 0.0 -22.2053 1.733-26-22.2053 0.246 -22.2053 0.246 -22.2053 0.0 -22.5053 1.745-26-22.5053 0.246 -22.5053 0.246 -22.5053 0.0 -22.8054 1.756-26-22.8054 0.246 -22.8054 0.246 -22.8054 0.0 -23.1055 1.767-26-23.1055 0.246 -23.1055 0.246 -23.1055 0.0 -23.4056 1.778-26-23.4056 0.246 -23.4056 0.246 -23.4056 0.0 -23.7056 1.666-26-23.7056 0.246 -23.7056 0.246 -23.7056 0.0 -24.0057 1.78-26 -24.0057 0.246 -24.0057 0.246 -24.0057 0.0 -24.3058 1.809-26-24.3058 0.246 -24.3058 0.246 -24.3058 0.0 -24.6059 1.823-26-24.6059 0.246 -24.6059 0.246 -24.6059 0.0 -24.9059 1.835-26-24.9059 0.246 -24.9059 0.246 -24.9059 1.384-12-25.206 1.272-26-25.206 0.246 -25.206 0.246 -25.206 0.492 -.300073 0.492 -.300073 0.492 -.600146 0.492 -.600146 0.492 -.900219

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1412 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2171 2172 2173 2174 2175 2176 2177 2178 2179 2180 2181 2182 2183 2184 2185 2186 2187 2188 2189 2190 2191 2192 2193 2194 2195 2196 2197 2198 2199 2200 2201 2202 2203 2204 2205 2206 2207 2208 2209 2210 2211 2212 2213 2214 2215 2216 2217 2218 2219 2220 2221 2222 2223 2224 2225 2226 2227 2228 2229 2230 2231 2232 2233 2234 2235 2236 2237 2238 2239

Altair Engineering

-0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246

0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492

-.900219 -1.20029 -1.20029 -1.50037 -1.50037 -1.80044 -1.80044 -2.10051 -2.10051 -2.40058 -2.40058 -2.70066 -2.70066 -3.00073 -3.00073 -3.3008 -3.3008 -3.60088 -3.60088 -3.90095 -3.90095 -4.20102 -4.20102 -4.5011 -4.5011 -4.80117 -4.80117 -5.10124 -5.10124 -5.40132 -5.40132 -5.70139 -5.70139 -6.00146 -6.00146 -6.30154 -6.30154 -6.60161 -6.60161 -6.90168 -6.90168 -7.20176 -7.20176 -7.50183 -7.50183 -7.8019 -7.8019 -8.10198 -8.10198 -8.40205 -8.40205 -8.70212 -8.70212 -9.00219 -9.0022 -9.30227 -9.30227 -9.60234 -9.60234 -9.90241 -9.90241 -10.2025 -10.2025 -10.5026 -10.5026 -10.8026 -10.8026 -11.1027 -11.1027

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1413 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2240 2241 2242 2243 2244 2245 2246 2247 2248 2249 2410 2411 2412 2413 2414 2415 2416 2417 2418 2419 2420 2421 2422 2423 2424 2425 2426 2427 2428 2429 2430 2431 2432 2433 2434 2435 2436 2437 2438 2439 2440 2441 2442 2443 2444 2445 2446 2447 2448 2449 2450 2451 2452 2453 2454 2455 2456 2457 2458 2459 2460 2461 2462 2463 2464 2465 2466 2467 2468

-0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492

0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492 0.492

-11.4028 -11.4028 -11.7028 -11.7029 -12.0029 -12.0029 -12.303 -12.303 -12.6031 -12.6031 -12.903 -12.903 -13.2031 -13.2031 -13.5031 -13.5032 -13.8032 -13.8032 -14.1033 -14.1033 -14.4034 -14.4034 -14.7034 -14.7034 -15.0035 -15.0035 -15.3036 -15.3036 -15.6037 -15.6037 -15.9037 -15.9037 -16.2038 -16.2038 -16.5039 -16.5039 -16.804 -16.804 -17.104 -17.104 -17.4041 -17.4041 -17.7042 -17.7042 -18.0042 -18.0042 -18.3043 -18.3043 -18.6044 -18.6044 -18.9045 -18.9045 -19.2045 -19.2045 -19.5046 -19.5046 -19.8047 -19.8047 -20.1048 -20.1048 -20.4048 -20.4048 -20.7049 -20.7049 -21.005 -21.005 -21.3051 -21.3051 -21.6051

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1414 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2469 2470 2471 2472 2473 2474 2475 2476 2477 2478 2479 2480 2481 2482 2483 2484 2485 2486 2487 2488 2489 2490 2491 2492 2493 2494 2495 2496 2497 2498 2499 2500 2501 2502 2503 2504 2505 2506 2507 2508 2509 2510 2511 2512 2513 2514 2515 2516 2517 2518 2519 2520 2521 2522 2523 2524 2525 2526 2527 2528 2529 2530 2531 2532 2533 2534 2535 2536 2537

Altair Engineering

-0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.492 0.492 -0.246 0.492 -0.246 -0.246 -5.62-13-0.246 -0.246 -0.246 -1.12-12-0.246 -0.246 -0.246 -1.68-12-0.246 -0.246 -0.246 -2.24-12-0.246 -0.246 -0.246 -2.81-12-0.246 -0.246 -0.246 -3.37-12-0.246 -0.246 -0.246 -3.93-12-0.246 -0.246 -0.246 -4.49-12-0.246 -0.246 -0.246 -5.06-12-0.246 -0.246 -0.246 -5.62-12-0.246 -0.246 -0.246 -6.18-12-0.246 -0.246 -0.246 -6.74-12-0.246 -0.246 -0.246 -7.3-12 -0.246 -0.246 -0.246 -7.86-12-0.246 -0.246 -0.246 -8.43-12-0.246 -0.246 -0.246 -8.99-12-0.246 -0.246 -0.246 -9.55-12-0.246 -0.246 -0.246 -1.01-11-0.246 -0.246 -0.246 -1.07-11-0.246 -0.246 -0.246 -1.12-11-0.246 -0.246 -0.246 -1.18-11-0.246 -0.246 -0.246 -1.23-11-0.246

-21.6051 -21.9052 -21.9052 -22.2053 -22.2053 -22.5053 -22.5053 -22.8054 -22.8054 -23.1055 -23.1055 -23.4056 -23.4056 -23.7056 -23.7056 -24.0057 -24.0057 -24.3058 -24.3058 -24.6059 -24.6059 -24.9059 -24.9059 -25.206 -25.206 -.300073 -.300073 -.600146 -.600146 -.900219 -.900219 -1.20029 -1.20029 -1.50037 -1.50037 -1.80044 -1.80044 -2.10051 -2.10051 -2.40058 -2.40059 -2.70066 -2.70066 -3.00073 -3.00073 -3.3008 -3.30081 -3.60088 -3.60088 -3.90095 -3.90095 -4.20102 -4.20102 -4.5011 -4.5011 -4.80117 -4.80117 -5.10124 -5.10124 -5.40132 -5.40132 -5.70139 -5.70139 -6.00146 -6.00146 -6.30154 -6.30154 -6.60161 -6.60161

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1415 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2538 2539 2540 2541 2542 2543 2544 2545 2546 2547 2548 2549 2550 2551 2552 2553 2554 2555 2556 2557 2558 2559 2560 2561 2562 2563 2564 2565 2566 2567 2568 2569 2570 2571 2572 2573 2574 2575 2576 2577 2738 2739 2740 2741 2742 2743 2744 2745 2746 2747 2748 2749 2750 2751 2752 2753 2754 2755 2756 2757 2758 2759 2760 2761 2762 2763 2764 2765 2766

-0.246 -0.246 -1.29-11-0.246 -0.246 -0.246 -1.35-11-0.246 -0.246 -0.246 -1.4-11 -0.246 -0.246 -0.246 -1.46-11-0.246 -0.246 -0.246 -1.51-11-0.246 -0.246 -0.246 -1.57-11-0.246 -0.246 -0.246 -1.63-11-0.246 -0.246 -0.246 -1.68-11-0.246 -0.246 -0.246 -1.74-11-0.246 -0.246 -0.246 -1.79-11-0.246 -0.246 -0.246 -1.85-11-0.246 -0.246 -0.246 -1.91-11-0.246 -0.246 -0.246 -1.96-11-0.246 -0.246 -0.246 -2.02-11-0.246 -0.246 -0.246 -2.07-11-0.246 -0.246 -0.246 -2.13-11-0.246 -0.246 -0.246 -2.19-11-0.246 -0.246 -0.246 -2.24-11-0.246 -0.246 -0.246 -2.3-11 -0.246 -0.246 -0.246 -2.35-11-0.246 -0.246 -0.246 -6.9-11 -0.246 -0.246 -0.246 -6.95-11-0.246 -0.246 -0.246 -7.01-11-0.246 -0.246 -0.246 -7.06-11-0.246 -0.246 -0.246 -7.12-11-0.246 -0.246 -0.246 -7.19-11-0.246 -0.246 -0.246 -7.24-11-0.246 -0.246 -0.246 -7.3-11 -0.246 -0.246 -0.246 -7.35-11-0.246 -0.246 -0.246 -7.41-11-0.246 -0.246 -0.246 -7.47-11-0.246 -0.246 -0.246 -7.52-11-0.246 -0.246 -0.246 -7.58-11-0.246 -0.246 -0.246 -7.63-11-0.246 -0.246 -0.246

-6.90168 -6.90168 -7.20176 -7.20176 -7.50183 -7.50183 -7.8019 -7.8019 -8.10198 -8.10198 -8.40205 -8.40205 -8.70212 -8.70212 -9.0022 -9.0022 -9.30227 -9.30227 -9.60234 -9.60234 -9.90241 -9.90241 -10.2025 -10.2025 -10.5026 -10.5026 -10.8026 -10.8026 -11.1027 -11.1027 -11.4028 -11.4028 -11.7029 -11.7029 -12.0029 -12.0029 -12.303 -12.303 -12.6031 -12.6031 -12.903 -12.903 -13.2031 -13.2031 -13.5032 -13.5032 -13.8032 -13.8032 -14.1033 -14.1033 -14.4034 -14.4034 -14.7034 -14.7034 -15.0035 -15.0035 -15.3036 -15.3036 -15.6037 -15.6037 -15.9037 -15.9037 -16.2038 -16.2038 -16.5039 -16.5039 -16.804 -16.804 -17.104

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1416 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2767 2768 2769 2770 2771 2772 2773 2774 2775 2776 2777 2778 2779 2780 2781 2782 2783 2784 2785 2786 2787 2788 2789 2790 2791 2792 2793 2794 2795 2796 2797 2798 2799 2800 2801 2802 2803 2804 2805 2806 2807 2808 2809 2810 2811 2812 2813 2814 2815 2816 2817 2818 2819 2820 2821 2822 2823 2824 2825 2826 2827 2828 2829 2830 2831 2832 2833 2834 2835

Altair Engineering

-7.69-11-0.246 -0.246 -0.246 -7.75-11-0.246 -0.246 -0.246 -7.8-11 -0.246 -0.246 -0.246 -7.86-11-0.246 -0.246 -0.246 -7.91-11-0.246 -0.246 -0.246 -7.97-11-0.246 -0.246 -0.246 -8.03-11-0.246 -0.246 -0.246 -8.08-11-0.246 -0.246 -0.246 -8.14-11-0.246 -0.246 -0.246 -8.19-11-0.246 -0.246 -0.246 -8.25-11-0.246 -0.246 -0.246 -8.31-11-0.246 -0.246 -0.246 -8.36-11-0.246 -0.246 -0.246 -8.42-11-0.246 -0.246 -0.246 -8.47-11-0.246 -0.246 -0.246 -8.53-11-0.246 -0.246 -0.246 -8.59-11-0.246 -0.246 -0.246 -8.64-11-0.246 -0.246 -0.246 -8.7-11 -0.246 -0.246 -0.246 -8.75-11-0.246 -0.246 -0.246 -8.81-11-0.246 -0.246 -0.246 -8.87-11-0.246 -0.246 -0.246 -8.92-11-0.246 -0.246 -0.246 -8.98-11-0.246 -0.246 -0.246 -9.04-11-0.246 -0.246 -0.246 -9.09-11-0.246 -0.246 -0.246 -9.15-11-0.246 -0.246 -0.246 -9.16-11-0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246 -0.492 -0.246

-17.104 -17.4041 -17.4041 -17.7042 -17.7042 -18.0042 -18.0042 -18.3043 -18.3043 -18.6044 -18.6044 -18.9045 -18.9045 -19.2045 -19.2045 -19.5046 -19.5046 -19.8047 -19.8047 -20.1048 -20.1048 -20.4048 -20.4048 -20.7049 -20.7049 -21.005 -21.005 -21.3051 -21.3051 -21.6051 -21.6051 -21.9052 -21.9052 -22.2053 -22.2053 -22.5053 -22.5053 -22.8054 -22.8054 -23.1055 -23.1055 -23.4056 -23.4056 -23.7056 -23.7056 -24.0057 -24.0057 -24.3058 -24.3058 -24.6059 -24.6059 -24.9059 -24.9059 -25.206 -25.206 -.300074 -.600146 -.900219 -1.20029 -1.50037 -1.80044 -2.10051 -2.40058 -2.70066 -3.00073 -3.3008 -3.60088 -3.90095 -4.20102

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1417 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2836 2837 2838 2839 2840 2841 2842 2843 2844 2845 2846 2847 2848 2849 2850 2851 2852 2853 2854 2855 2856 2857 2858 2859 2860 2861 2862 2863 2944 2945 2946 2947 2948 2949 2950 2951 2952 2953 2954 2955 2956 2957 2958 2959 2960 2961 2962 2963 2964 2965 2966 2967 2968 2969 2970 2971 2972 2973 2974 2975 2976 2977 2978 2979 2980 2981 2982 2983 2984

-0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492

-0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246 -0.246

-4.5011 -4.80117 -5.10124 -5.40132 -5.70139 -6.00146 -6.30154 -6.60161 -6.90168 -7.20176 -7.50183 -7.8019 -8.10198 -8.40205 -8.70212 -9.00219 -9.30227 -9.60234 -9.90241 -10.2025 -10.5026 -10.8026 -11.1027 -11.4028 -11.7028 -12.0029 -12.303 -12.6031 -12.903 -13.2031 -13.5031 -13.8032 -14.1033 -14.4034 -14.7034 -15.0035 -15.3036 -15.6037 -15.9037 -16.2038 -16.5039 -16.804 -17.104 -17.4041 -17.7042 -18.0042 -18.3043 -18.6044 -18.9045 -19.2045 -19.5046 -19.8047 -20.1048 -20.4048 -20.7049 -21.005 -21.3051 -21.6051 -21.9052 -22.2053 -22.5053 -22.8054 -23.1055 -23.4056 -23.7056 -24.0057 -24.3058 -24.6059 -24.9059

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1418 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

2985 2986 2987 2988 2989 2990 2991 2992 2993 2994 2995 2996 2997 2998 2999 3000 3001 3002 3003 3004 3005 3006 3007 3008 3009 3010 3011 3012 3013 3014 3015 3016 3017 3018 3019 3020 3021 3022 3023 3024 3025 3026 3027 3028 3029 3030 3031 3032 3033 3034 3035 3036 3037 3038 3039 3040 3041 3042 3043 3044 3045 3046 3047 3048 3049 3050 3051 3052 3053

Altair Engineering

-0.492 -0.246 -0.246 -0.492 -5.24-13-0.492 -0.246 -0.492 -1.05-12-0.492 -0.246 -0.492 -1.57-12-0.492 -0.246 -0.492 -2.09-12-0.492 -0.246 -0.492 -2.63-12-0.492 -0.246 -0.492 -3.15-12-0.492 -0.246 -0.492 -3.67-12-0.492 -0.246 -0.492 -4.19-12-0.492 -0.246 -0.492 -4.72-12-0.492 -0.246 -0.492 -5.24-12-0.492 -0.246 -0.492 -5.76-12-0.492 -0.246 -0.492 -6.29-12-0.492 -0.246 -0.492 -6.81-12-0.492 -0.246 -0.492 -7.33-12-0.492 -0.246 -0.492 -7.87-12-0.492 -0.246 -0.492 -8.39-12-0.492 -0.246 -0.492 -8.91-12-0.492 -0.246 -0.492 -9.44-12-0.492 -0.246 -0.492 -9.96-12-0.492 -0.246 -0.492 -1.05-11-0.492 -0.246 -0.492 -1.1-11 -0.492 -0.246 -0.492 -1.15-11-0.492 -0.246 -0.492 -1.2-11 -0.492 -0.246 -0.492 -1.26-11-0.492 -0.246 -0.492 -1.31-11-0.492 -0.246 -0.492 -1.36-11-0.492 -0.246 -0.492 -1.41-11-0.492 -0.246 -0.492 -1.46-11-0.492 -0.246 -0.492 -1.52-11-0.492 -0.246 -0.492 -1.57-11-0.492 -0.246 -0.492 -1.62-11-0.492 -0.246 -0.492 -1.67-11-0.492 -0.246 -0.492 -1.73-11-0.492 -0.246 -0.492 -1.78-11-0.492

-25.206 -.300073 -.300073 -.600146 -.600146 -.900219 -.900219 -1.20029 -1.20029 -1.50037 -1.50037 -1.80044 -1.80044 -2.10051 -2.10051 -2.40058 -2.40059 -2.70066 -2.70066 -3.00073 -3.00073 -3.3008 -3.30081 -3.60088 -3.60088 -3.90095 -3.90095 -4.20102 -4.20102 -4.5011 -4.5011 -4.80117 -4.80117 -5.10124 -5.10124 -5.40132 -5.40132 -5.70139 -5.70139 -6.00146 -6.00146 -6.30154 -6.30154 -6.60161 -6.60161 -6.90168 -6.90168 -7.20176 -7.20176 -7.50183 -7.50183 -7.8019 -7.8019 -8.10198 -8.10198 -8.40205 -8.40205 -8.70212 -8.70212 -9.0022 -9.0022 -9.30227 -9.30227 -9.60234 -9.60234 -9.90241 -9.90241 -10.2025 -10.2025

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1419 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3054 3055 3056 3057 3058 3059 3060 3061 3062 3063 3064 3065 3066 3067 3068 3069 3230 3231 3232 3233 3234 3235 3236 3237 3238 3239 3240 3241 3242 3243 3244 3245 3246 3247 3248 3249 3250 3251 3252 3253 3254 3255 3256 3257 3258 3259 3260 3261 3262 3263 3264 3265 3266 3267 3268 3269 3270 3271 3272 3273 3274 3275 3276 3277 3278 3279 3280 3281 3282

-0.246 -0.492 -1.83-11-0.492 -0.246 -0.492 -1.88-11-0.492 -0.246 -0.492 -1.94-11-0.492 -0.246 -0.492 -1.99-11-0.492 -0.246 -0.492 -2.04-11-0.492 -0.246 -0.492 -2.09-11-0.492 -0.246 -0.492 -2.14-11-0.492 -0.246 -0.492 -2.2-11 -0.492 -0.246 -0.492 -6.43-11-0.492 -0.246 -0.492 -6.49-11-0.492 -0.246 -0.492 -6.54-11-0.492 -0.246 -0.492 -6.59-11-0.492 -0.246 -0.492 -6.64-11-0.492 -0.246 -0.492 -6.71-11-0.492 -0.246 -0.492 -6.76-11-0.492 -0.246 -0.492 -6.81-11-0.492 -0.246 -0.492 -6.86-11-0.492 -0.246 -0.492 -6.91-11-0.492 -0.246 -0.492 -6.97-11-0.492 -0.246 -0.492 -7.02-11-0.492 -0.246 -0.492 -7.07-11-0.492 -0.246 -0.492 -7.12-11-0.492 -0.246 -0.492 -7.18-11-0.492 -0.246 -0.492 -7.23-11-0.492 -0.246 -0.492 -7.28-11-0.492 -0.246 -0.492 -7.33-11-0.492 -0.246 -0.492 -7.39-11-0.492 -0.246 -0.492 -7.44-11-0.492 -0.246 -0.492 -7.49-11-0.492 -0.246 -0.492 -7.54-11-0.492 -0.246 -0.492 -7.59-11-0.492 -0.246 -0.492 -7.65-11-0.492 -0.246 -0.492 -7.7-11 -0.492 -0.246 -0.492 -7.75-11-0.492 -0.246 -0.492

-10.5026 -10.5026 -10.8026 -10.8026 -11.1027 -11.1027 -11.4028 -11.4028 -11.7029 -11.7029 -12.0029 -12.0029 -12.303 -12.303 -12.6031 -12.6031 -12.903 -12.903 -13.2031 -13.2031 -13.5032 -13.5032 -13.8032 -13.8032 -14.1033 -14.1033 -14.4034 -14.4034 -14.7034 -14.7034 -15.0035 -15.0035 -15.3036 -15.3036 -15.6037 -15.6037 -15.9037 -15.9037 -16.2038 -16.2038 -16.5039 -16.5039 -16.804 -16.804 -17.104 -17.104 -17.4041 -17.4041 -17.7042 -17.7042 -18.0042 -18.0042 -18.3043 -18.3043 -18.6044 -18.6044 -18.9045 -18.9045 -19.2045 -19.2045 -19.5046 -19.5046 -19.8047 -19.8047 -20.1048 -20.1048 -20.4048 -20.4048 -20.7049

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1420 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3283 3284 3285 3286 3287 3288 3289 3290 3291 3292 3293 3294 3295 3296 3297 3298 3299 3300 3301 3302 3303 3304 3305 3306 3307 3308 3309 3310 3311 3312 3313 3314 3315 3316 3317 3318 3319 3320 3321 3322 3323 3324 3325 3326 3327 3328 3329 3330 3331 3332 3333 3334 3335 3336 3337 3338 3339 3340 3341 3342 3343 3344 3345 3346 3347 3348 3349 3350 3351

Altair Engineering

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-20.7049 -21.005 -21.005 -21.3051 -21.3051 -21.6051 -21.6051 -21.9052 -21.9052 -22.2053 -22.2053 -22.5053 -22.5053 -22.8054 -22.8054 -23.1055 -23.1055 -23.4056 -23.4056 -23.7056 -23.7056 -24.0057 -24.0057 -24.3058 -24.3058 -24.6059 -24.6059 -24.9059 -24.9059 -25.206 -25.206 -.300073 -.600146 -.900219 -1.20029 -1.50037 -1.80044 -2.10051 -2.40058 -2.70066 -3.00073 -3.3008 -3.60088 -3.90095 -4.20102 -4.5011 -4.80117 -5.10124 -5.40132 -5.70139 -6.00146 -6.30154 -6.60161 -6.90168 -7.20176 -7.50183 -7.8019 -8.10198 -8.40205 -8.70212 -9.00219 -9.30227 -9.60234 -9.90241 -10.2025 -10.5026 -10.8026 -11.1027 -11.4028

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1421 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3352 3353 3354 3355 3436 3437 3438 3439 3440 3441 3442 3443 3444 3445 3446 3447 3448 3449 3450 3451 3452 3453 3454 3455 3456 3457 3458 3459 3460 3461 3462 3463 3464 3465 3466 3467 3468 3469 3470 3471 3472 3473 3474 3475 3476 3477 3478 3479 3480 3481 3482 3483 3484 3485 3486 3487 3488 3489 3490 3491 3492 3493 3494 3495 3496 3497 3498 3499 3500

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-11.7028 -12.0029 -12.303 -12.6031 -12.903 -13.2031 -13.5031 -13.8032 -14.1033 -14.4034 -14.7034 -15.0035 -15.3036 -15.6037 -15.9037 -16.2038 -16.5039 -16.804 -17.104 -17.4041 -17.7042 -18.0042 -18.3043 -18.6044 -18.9045 -19.2045 -19.5046 -19.8047 -20.1048 -20.4048 -20.7049 -21.005 -21.3051 -21.6051 -21.9052 -22.2053 -22.5053 -22.8054 -23.1055 -23.4056 -23.7056 -24.0057 -24.3058 -24.6059 -24.9059 -25.206 -.300073 -.300074 -.600146 -.600146 -0.90022 -0.90022 -1.20029 -1.20029 -1.50037 -1.50037 -1.80044 -1.80044 -2.10051 -2.10051 -2.40059 -2.40059 -2.70066 -2.70066 -3.00073 -3.00073 -3.30081 -3.30081 -3.60088

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1422 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3501 3502 3503 3504 3505 3506 3507 3508 3509 3510 3511 3512 3513 3514 3515 3516 3517 3518 3519 3520 3521 3522 3523 3524 3525 3526 3527 3528 3529 3530 3531 3532 3533 3534 3535 3536 3537 3538 3539 3540 3541 3542 3543 3544 3545 3546 3547 3548 3549 3550 3551 3552 3553 3554 3555 3556 3557 3558 3559 3560 3561 3722 3723 3724 3725 3726 3727 3728 3729

Altair Engineering

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-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1423 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3730 3731 3732 3733 3734 3735 3736 3737 3738 3739 3740 3741 3742 3743 3744 3745 3746 3747 3748 3749 3750 3751 3752 3753 3754 3755 3756 3757 3758 3759 3760 3761 3762 3763 3764 3765 3766 3767 3768 3769 3770 3771 3772 3773 3774 3775 3776 3777 3778 3779 3780 3781 3782 3783 3784 3785 3786 3787 3788 3789 3790 3791 3792 3793 3794 3795 3796 3797 3798

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1424 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3799 3800 3801 3802 3803 3804 3805 3806 3807 3808 3809 3810 3811 3812 3813 3814 3815 3816 3817 3818 3819 3820 3821 3822 3823 3824 3825 3826 3827 3828 3829 3830 3831 3832 3833 3834 3835 3836 3837 3838 3839 3840 3841 3842 3843 3844 3845 3846 3847 3848 3849 3850 3851 3852 3853 3854 3855 3856 3857 3858 3859 3860 3861 3862 3863 3864 3865 3866 3867

Altair Engineering

0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492

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-24.3058 -24.6059 -24.6059 -24.9059 -24.9059 -25.206 -25.206 -.300073 -.300074 -.600146 -.600146 -0.90022 -0.90022 -1.20029 -1.20029 -1.50037 -1.50037 -1.80044 -1.80044 -2.10051 -2.10051 -2.40059 -2.40059 -2.70066 -2.70066 -3.00073 -3.00073 -3.30081 -3.30081 -3.60088 -3.60088 -3.90095 -3.90095 -4.20102 -4.20102 -4.5011 -4.5011 -4.80117 -4.80117 -5.10124 -5.10124 -5.40132 -5.40132 -5.70139 -5.70139 -6.00146 -6.00146 -6.30154 -6.30154 -6.60161 -6.60161 -6.90168 -6.90168 -7.20176 -7.20176 -7.50183 -7.50183 -7.8019 -7.8019 -8.10198 -8.10198 -8.40205 -8.40205 -8.70212 -8.70212 -9.0022 -9.0022 -9.30227 -9.30227

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1425 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

3868 3869 3870 3871 3872 3873 3874 3875 3876 3877 3878 3879 3880 3881 3882 3883 3884 3885 3886 3887 3888 3889 4050 4051 4052 4053 4054 4055 4056 4057 4058 4059 4060 4061 4062 4063 4064 4065 4066 4067 4068 4069 4070 4071 4072 4073 4074 4075 4076 4077 4078 4079 4080 4081 4082 4083 4084 4085 4086 4087 4088 4089 4090 4091 4092 4093 4094 4095 4096

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-9.60234 -9.60234 -9.90241 -9.90242 -10.2025 -10.2025 -10.5026 -10.5026 -10.8026 -10.8026 -11.1027 -11.1027 -11.4028 -11.4028 -11.7029 -11.7029 -12.0029 -12.0029 -12.303 -12.303 -12.6031 -12.6031 -12.903 -12.903 -13.2031 -13.2031 -13.5032 -13.5032 -13.8032 -13.8032 -14.1033 -14.1033 -14.4034 -14.4034 -14.7034 -14.7034 -15.0035 -15.0035 -15.3036 -15.3036 -15.6037 -15.6037 -15.9037 -15.9037 -16.2038 -16.2038 -16.5039 -16.5039 -16.804 -16.804 -17.104 -17.104 -17.4041 -17.4041 -17.7042 -17.7042 -18.0042 -18.0042 -18.3043 -18.3043 -18.6044 -18.6044 -18.9045 -18.9045 -19.2045 -19.2045 -19.5046 -19.5046 -19.8047

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1426 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID 4097 GRID 4098 GRID 4099 GRID 4100 GRID 4101 GRID 4102 GRID 4103 GRID 4104 GRID 4105 GRID 4106 GRID 4107 GRID 4108 GRID 4109 GRID 4110 GRID 4111 GRID 4112 GRID 4113 GRID 4114 GRID 4115 GRID 4116 GRID 4117 GRID 4118 GRID 4119 GRID 4120 GRID 4121 GRID 4122 GRID 4123 GRID 4124 GRID 4125 GRID 4126 GRID 4127 GRID 4128 GRID 4129 GRID 4130 GRID 4131 GRID 4132 GRID 4133 GRID 6776 GRID 6777 GRID 6778 GRID 6779 GRID 6780 GRID 6781 GRID 6782 GRID 6783 GRID 6784 GRID 6785 GRID 6786 GRID 6787 GRID 6788 GRID 6789 GRID 6790 GRID 6791 GRID 6792 GRID 6793 GRID 6794 GRID 6795 GRID 6796 GRID 6797 GRID 6798 GRID 6799 GRID 6800 $$ $$ SPOINT Data $$ $ $ CQUAD4 Elements $ CQUAD4 5627

Altair Engineering

0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 0.246 0.492 -0.246 0.246 0.0 -0.492 -0.492 -0.246 0.0 0.246 0.492 0.492 0.246 -0.246 0.0 0.492 0.492 0.246 0.0 -0.246 -0.492 -0.492 -0.492 -0.246 0.0 0.246 0.492

1

-0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.492 -0.246 -0.246 -0.246 -0.246 -0.492 -0.492 -0.492 -0.492 -0.492 -0.246 0.246 0.246 0.246 0.246 0.492 0.492 0.492 0.492 0.492 0.246 0.0 0.0 0.0 0.0 0.0

6778

-19.8047 -20.1048 -20.1048 -20.4048 -20.4048 -20.7049 -20.7049 -21.005 -21.005 -21.3051 -21.3051 -21.6051 -21.6051 -21.9052 -21.9052 -22.2053 -22.2053 -22.5053 -22.5053 -22.8054 -22.8054 -23.1055 -23.1055 -23.4056 -23.4056 -23.7056 -23.7056 -24.0057 -24.0057 -24.3058 -24.3058 -24.6059 -24.6059 -24.9059 -24.9059 -25.206 -25.206 8.589-16 -8.59-16 0.0 1.718-15 1.718-15 8.589-16 0.0 -8.59-16 -1.72-15 -1.72-15 -8.59-16 8.589-16 0.0 -1.72-15 -1.72-15 -8.59-16 0.0 8.589-16 1.718-15 1.718-15 1.718-15 8.589-16 0.0 -8.59-16 -1.72-15

6798

6799

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

6777

OptiStruct 13.0 Reference Guide 1427 Proprietary Information of Altair Engineering

CQUAD4 5629 1 6782 CQUAD4 6116 1 6777 CQUAD4 6122 1 6783 CQUAD4 6125 1 6799 CQUAD4 6520 1 6779 CQUAD4 6521 1 6776 CQUAD4 6523 1 6780 CQUAD4 6528 1 6781 CQUAD4 6954 1 6797 CQUAD4 7220 1 6788 CQUAD4 7647 1 6787 CQUAD4 7652 1 6798 CQUAD4 7945 1 6786 CQUAD4 7948 1 6789 CQUAD4 7955 1 6800 $ $HMMOVE 5 $ 5627 5629 6116 $ 6528 6954 7220 $ $ $ CHEXA Elements: First Order $ CHEXA 17 2 10 + 36 37 CHEXA 18 2 34 + 40 41 CHEXA 19 2 38 + 44 45 CHEXA 20 2 42 + 48 49 CHEXA 21 2 46 + 52 53 CHEXA 22 2 50 + 56 57 CHEXA 23 2 54 + 60 61 CHEXA 24 2 58 + 64 65 CHEXA 25 2 62 + 68 69 CHEXA 26 2 66 + 72 73 CHEXA 27 2 70 + 76 77 CHEXA 28 2 74 + 80 81 CHEXA 29 2 78 + 84 85 CHEXA 30 2 82 + 88 89 CHEXA 31 2 86 + 92 93 CHEXA 32 2 90 + 96 97 CHEXA 33 2 94 + 100 101 CHEXA 34 2 98 + 104 105 CHEXA 35 2 102 + 108 109 CHEXA 36 2 106 + 112 113 CHEXA 37 2 110 + 116 117 CHEXA 38 2 114 + 120 121 CHEXA 39 2 118 + 124 125

6778 6799 6777 6798 6796 6797 6779 6776 6796 6787 6795 6797 6788 6786 6799

6777 6800 6785 6788 6797 6798 6776 6778 6795 6793 6794 6787 6792 6791 6786

6783 6785 6784 6786 6776 6778 6781 6782 6787 6792 6793 6788 6791 6790 6789

6122 7647

6125 7652

6520THRU 7945 7948

11

21

23

34

35

35

36

37

38

39

39

40

41

42

43

43

44

45

46

47

47

48

49

50

51

51

52

53

54

55

55

56

57

58

59

59

60

61

62

63

63

64

65

66

67

67

68

69

70

71

71

72

73

74

75

75

76

77

78

79

79

80

81

82

83

83

84

85

86

87

87

88

89

90

91

91

92

93

94

95

95

96

97

98

99

99

100

101

102

103

103

104

105

106

107

107

108

109

110

111

111

112

113

114

115

115

116

117

118

119

119

120

121

122

123

1428 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

6521 7955

6523

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

40 128 41 132 42 136 43 140 44 144 45 148 46 152 47 156 48 160 49 164 50 168 51 172 52 176 53 180 54 184 55 188 56 192 57 196 58 200 139 524 140 528 141 532 142 536 143 540 144 544 145 548 146 552 147 556 148 560 149 564 150 568 151 572 152 576 153 580 154

Altair Engineering

2 129 2 133 2 137 2 141 2 145 2 149 2 153 2 157 2 161 2 165 2 169 2 173 2 177 2 181 2 185 2 189 2 193 2 197 2 201 2 525 2 529 2 533 2 537 2 541 2 545 2 549 2 553 2 557 2 561 2 565 2 569 2 573 2 577 2 581 2

122

123

124

125

126

127

126

127

128

129

130

131

130

131

132

133

134

135

134

135

136

137

138

139

138

139

140

141

142

143

142

143

144

145

146

147

146

147

148

149

150

151

150

151

152

153

154

155

154

155

156

157

158

159

158

159

160

161

162

163

162

163

164

165

166

167

166

167

168

169

170

171

170

171

172

173

174

175

174

175

176

177

178

179

178

179

180

181

182

183

182

183

184

185

186

187

186

187

188

189

190

191

190

191

192

193

194

195

194

195

196

197

198

199

198

199

200

201

522

523

522

523

524

525

526

527

526

527

528

529

530

531

530

531

532

533

534

535

534

535

536

537

538

539

538

539

540

541

542

543

542

543

544

545

546

547

546

547

548

549

550

551

550

551

552

553

554

555

554

555

556

557

558

559

558

559

560

561

562

563

562

563

564

565

566

567

566

567

568

569

570

571

570

571

572

573

574

575

574

575

576

577

578

579

578

579

580

581

582

583

OptiStruct 13.0 Reference Guide 1429 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

584 155 588 156 592 157 596 158 600 159 604 160 608 161 612 162 616 163 620 164 624 165 628 166 632 167 636 168 640 169 644 170 648 171 652 172 656 173 660 174 664 175 668 176 672 177 676 178 680 179 684 180 688 181 37 182 41 183 45 184 49 185 53 186 57 187 61 188 65

585 2 589 2 593 2 597 2 601 2 605 2 609 2 613 2 617 2 621 2 625 2 629 2 633 2 637 2 641 2 645 2 649 2 653 2 657 2 661 2 665 2 669 2 673 2 677 2 681 2 685 2 689 2 691 2 693 2 695 2 697 2 699 2 701 2 703 2 705

582

583

584

585

586

587

586

587

588

589

590

591

590

591

592

593

594

595

594

595

596

597

598

599

598

599

600

601

602

603

602

603

604

605

606

607

606

607

608

609

610

611

610

611

612

613

614

615

614

615

616

617

618

619

618

619

620

621

622

623

622

623

624

625

626

627

626

627

628

629

630

631

630

631

632

633

634

635

634

635

636

637

638

639

638

639

640

641

642

643

642

643

644

645

646

647

646

647

648

649

650

651

650

651

652

653

654

655

654

655

656

657

658

659

658

659

660

661

662

663

662

663

664

665

666

667

666

667

668

669

670

671

670

671

672

673

674

675

674

675

676

677

678

679

678

679

680

681

682

683

682

683

684

685

686

687

9

10

23

20

690

34

690

34

37

691

692

38

692

38

41

693

694

42

694

42

45

695

696

46

696

46

49

697

698

50

698

50

53

699

700

54

700

54

57

701

702

58

702

58

61

703

704

62

1430 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

189 69 190 73 191 77 192 81 193 85 194 89 195 93 196 97 197 101 198 105 199 109 200 113 201 117 202 121 203 125 204 129 205 133 206 137 207 141 208 145 209 149 210 153 211 157 212 161 213 165 214 169 215 173 216 177 217 181 218 185 219 189 220 193 221 197 222 201 303

Altair Engineering

2 707 2 709 2 711 2 713 2 715 2 717 2 719 2 721 2 723 2 725 2 727 2 729 2 731 2 733 2 735 2 737 2 739 2 741 2 743 2 745 2 747 2 749 2 751 2 753 2 755 2 757 2 759 2 761 2 763 2 765 2 767 2 769 2 771 2 773 2

704

62

65

705

706

66

706

66

69

707

708

70

708

70

73

709

710

74

710

74

77

711

712

78

712

78

81

713

714

82

714

82

85

715

716

86

716

86

89

717

718

90

718

90

93

719

720

94

720

94

97

721

722

98

722

98

101

723

724

102

724

102

105

725

726

106

726

106

109

727

728

110

728

110

113

729

730

114

730

114

117

731

732

118

732

118

121

733

734

122

734

122

125

735

736

126

736

126

129

737

738

130

738

130

133

739

740

134

740

134

137

741

742

138

742

138

141

743

744

142

744

142

145

745

746

146

746

146

149

747

748

150

748

150

153

749

750

154

750

154

157

751

752

158

752

158

161

753

754

162

754

162

165

755

756

166

756

166

169

757

758

170

758

170

173

759

760

174

760

174

177

761

762

178

762

178

181

763

764

182

764

182

185

765

766

186

766

186

189

767

768

190

768

190

193

769

770

194

770

194

197

771

772

198

772

198

201

773

934

522

OptiStruct 13.0 Reference Guide 1431 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

525 304 529 305 533 306 537 307 541 308 545 309 549 310 553 311 557 312 561 313 565 314 569 315 573 316 577 317 581 318 585 319 589 320 593 321 597 322 601 323 605 324 609 325 613 326 617 327 621 328 625 329 629 330 633 331 637 332 641 333 645 334 649 335 653 336 657 337 661

935 2 937 2 939 2 941 2 943 2 945 2 947 2 949 2 951 2 953 2 955 2 957 2 959 2 961 2 963 2 965 2 967 2 969 2 971 2 973 2 975 2 977 2 979 2 981 2 983 2 985 2 987 2 989 2 991 2 993 2 995 2 997 2 999 2 1001 2 1003

934

522

525

935

936

526

936

526

529

937

938

530

938

530

533

939

940

534

940

534

537

941

942

538

942

538

541

943

944

542

944

542

545

945

946

546

946

546

549

947

948

550

948

550

553

949

950

554

950

554

557

951

952

558

952

558

561

953

954

562

954

562

565

955

956

566

956

566

569

957

958

570

958

570

573

959

960

574

960

574

577

961

962

578

962

578

581

963

964

582

964

582

585

965

966

586

966

586

589

967

968

590

968

590

593

969

970

594

970

594

597

971

972

598

972

598

601

973

974

602

974

602

605

975

976

606

976

606

609

977

978

610

978

610

613

979

980

614

980

614

617

981

982

618

982

618

621

983

984

622

984

622

625

985

986

626

986

626

629

987

988

630

988

630

633

989

990

634

990

634

637

991

992

638

992

638

641

993

994

642

994

642

645

995

996

646

996

646

649

997

998

650

998

650

653

999

1000

654

1000

654

657

1001

1002

658

1432 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

338 665 339 669 340 673 341 677 342 681 343 685 344 689 345 1018 346 1020 347 1022 348 1024 349 1026 350 1028 351 1030 352 1032 353 1034 354 1036 355 1038 356 1040 357 1042 358 1044 359 1046 360 1048 361 1050 362 1052 363 1054 364 1056 365 1058 366 1060 367 1062 368 1064 369 1066 370 1068 371 1070 372

Altair Engineering

2 1005 2 1007 2 1009 2 1011 2 1013 2 1015 2 1017 2 1019 2 1021 2 1023 2 1025 2 1027 2 1029 2 1031 2 1033 2 1035 2 1037 2 1039 2 1041 2 1043 2 1045 2 1047 2 1049 2 1051 2 1053 2 1055 2 1057 2 1059 2 1061 2 1063 2 1065 2 1067 2 1069 2 1071 2

1002

658

661

1003

1004

662

1004

662

665

1005

1006

666

1006

666

669

1007

1008

670

1008

670

673

1009

1010

674

1010

674

677

1011

1012

678

1012

678

681

1013

1014

682

1014

682

685

1015

1016

686

23

21

17

18

37

36

37

36

1018

1019

41

40

41

40

1020

1021

45

44

45

44

1022

1023

49

48

49

48

1024

1025

53

52

53

52

1026

1027

57

56

57

56

1028

1029

61

60

61

60

1030

1031

65

64

65

64

1032

1033

69

68

69

68

1034

1035

73

72

73

72

1036

1037

77

76

77

76

1038

1039

81

80

81

80

1040

1041

85

84

85

84

1042

1043

89

88

89

88

1044

1045

93

92

93

92

1046

1047

97

96

97

96

1048

1049

101

100

101

100

1050

1051

105

104

105

104

1052

1053

109

108

109

108

1054

1055

113

112

113

112

1056

1057

117

116

117

116

1058

1059

121

120

121

120

1060

1061

125

124

125

124

1062

1063

129

128

129

128

1064

1065

133

132

133

132

1066

1067

137

136

137

136

1068

1069

141

140

141

140

1070

1071

145

144

OptiStruct 13.0 Reference Guide 1433 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1072 373 1074 374 1076 375 1078 376 1080 377 1082 378 1084 379 1086 380 1088 381 1090 382 1092 383 1094 384 1096 385 1098 386 1100 467 1262 468 1264 469 1266 470 1268 471 1270 472 1272 473 1274 474 1276 475 1278 476 1280 477 1282 478 1284 479 1286 480 1288 481 1290 482 1292 483 1294 484 1296 485 1298 486 1300

1073 2 1075 2 1077 2 1079 2 1081 2 1083 2 1085 2 1087 2 1089 2 1091 2 1093 2 1095 2 1097 2 1099 2 1101 2 1263 2 1265 2 1267 2 1269 2 1271 2 1273 2 1275 2 1277 2 1279 2 1281 2 1283 2 1285 2 1287 2 1289 2 1291 2 1293 2 1295 2 1297 2 1299 2 1301

145

144

1072

1073

149

148

149

148

1074

1075

153

152

153

152

1076

1077

157

156

157

156

1078

1079

161

160

161

160

1080

1081

165

164

165

164

1082

1083

169

168

169

168

1084

1085

173

172

173

172

1086

1087

177

176

177

176

1088

1089

181

180

181

180

1090

1091

185

184

185

184

1092

1093

189

188

189

188

1094

1095

193

192

193

192

1096

1097

197

196

197

196

1098

1099

201

200

201

200

1100

1101

525

524

525

524

1262

1263

529

528

529

528

1264

1265

533

532

533

532

1266

1267

537

536

537

536

1268

1269

541

540

541

540

1270

1271

545

544

545

544

1272

1273

549

548

549

548

1274

1275

553

552

553

552

1276

1277

557

556

557

556

1278

1279

561

560

561

560

1280

1281

565

564

565

564

1282

1283

569

568

569

568

1284

1285

573

572

573

572

1286

1287

577

576

577

576

1288

1289

581

580

581

580

1290

1291

585

584

585

584

1292

1293

589

588

589

588

1294

1295

593

592

593

592

1296

1297

597

596

597

596

1298

1299

601

600

1434 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

487 1302 488 1304 489 1306 490 1308 491 1310 492 1312 493 1314 494 1316 495 1318 496 1320 497 1322 498 1324 499 1326 500 1328 501 1330 502 1332 503 1334 504 1336 505 1338 506 1340 507 1342 508 1344 509 1019 510 1021 511 1023 512 1025 513 1027 514 1029 515 1031 516 1033 517 1035 518 1037 519 1039 520 1041 521

Altair Engineering

2 1303 2 1305 2 1307 2 1309 2 1311 2 1313 2 1315 2 1317 2 1319 2 1321 2 1323 2 1325 2 1327 2 1329 2 1331 2 1333 2 1335 2 1337 2 1339 2 1341 2 1343 2 1345 2 1346 2 1347 2 1348 2 1349 2 1350 2 1351 2 1352 2 1353 2 1354 2 1355 2 1356 2 1357 2

601

600

1300

1301

605

604

605

604

1302

1303

609

608

609

608

1304

1305

613

612

613

612

1306

1307

617

616

617

616

1308

1309

621

620

621

620

1310

1311

625

624

625

624

1312

1313

629

628

629

628

1314

1315

633

632

633

632

1316

1317

637

636

637

636

1318

1319

641

640

641

640

1320

1321

645

644

645

644

1322

1323

649

648

649

648

1324

1325

653

652

653

652

1326

1327

657

656

657

656

1328

1329

661

660

661

660

1330

1331

665

664

665

664

1332

1333

669

668

669

668

1334

1335

673

672

673

672

1336

1337

677

676

677

676

1338

1339

681

680

681

680

1340

1341

685

684

685

684

1342

1343

689

688

20

23

18

19

691

37

691

37

1019

1346

693

41

693

41

1021

1347

695

45

695

45

1023

1348

697

49

697

49

1025

1349

699

53

699

53

1027

1350

701

57

701

57

1029

1351

703

61

703

61

1031

1352

705

65

705

65

1033

1353

707

69

707

69

1035

1354

709

73

709

73

1037

1355

711

77

711

77

1039

1356

713

81

713

81

1041

1357

715

85

OptiStruct 13.0 Reference Guide 1435 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1043 522 1045 523 1047 524 1049 525 1051 526 1053 527 1055 528 1057 529 1059 530 1061 531 1063 532 1065 533 1067 534 1069 535 1071 536 1073 537 1075 538 1077 539 1079 540 1081 541 1083 542 1085 543 1087 544 1089 545 1091 546 1093 547 1095 548 1097 549 1099 550 1101 631 1263 632 1265 633 1267 634 1269 635 1271

1358 2 1359 2 1360 2 1361 2 1362 2 1363 2 1364 2 1365 2 1366 2 1367 2 1368 2 1369 2 1370 2 1371 2 1372 2 1373 2 1374 2 1375 2 1376 2 1377 2 1378 2 1379 2 1380 2 1381 2 1382 2 1383 2 1384 2 1385 2 1386 2 1387 2 1468 2 1469 2 1470 2 1471 2 1472

715

85

1043

1358

717

89

717

89

1045

1359

719

93

719

93

1047

1360

721

97

721

97

1049

1361

723

101

723

101

1051

1362

725

105

725

105

1053

1363

727

109

727

109

1055

1364

729

113

729

113

1057

1365

731

117

731

117

1059

1366

733

121

733

121

1061

1367

735

125

735

125

1063

1368

737

129

737

129

1065

1369

739

133

739

133

1067

1370

741

137

741

137

1069

1371

743

141

743

141

1071

1372

745

145

745

145

1073

1373

747

149

747

149

1075

1374

749

153

749

153

1077

1375

751

157

751

157

1079

1376

753

161

753

161

1081

1377

755

165

755

165

1083

1378

757

169

757

169

1085

1379

759

173

759

173

1087

1380

761

177

761

177

1089

1381

763

181

763

181

1091

1382

765

185

765

185

1093

1383

767

189

767

189

1095

1384

769

193

769

193

1097

1385

771

197

771

197

1099

1386

773

201

773

201

1101

1387

935

525

935

525

1263

1468

937

529

937

529

1265

1469

939

533

939

533

1267

1470

941

537

941

537

1269

1471

943

541

1436 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

636 1273 637 1275 638 1277 639 1279 640 1281 641 1283 642 1285 643 1287 644 1289 645 1291 646 1293 647 1295 648 1297 649 1299 650 1301 651 1303 652 1305 653 1307 654 1309 655 1311 656 1313 657 1315 658 1317 659 1319 660 1321 661 1323 662 1325 663 1327 664 1329 665 1331 666 1333 667 1335 668 1337 669 1339 670

Altair Engineering

2 1473 2 1474 2 1475 2 1476 2 1477 2 1478 2 1479 2 1480 2 1481 2 1482 2 1483 2 1484 2 1485 2 1486 2 1487 2 1488 2 1489 2 1490 2 1491 2 1492 2 1493 2 1494 2 1495 2 1496 2 1497 2 1498 2 1499 2 1500 2 1501 2 1502 2 1503 2 1504 2 1505 2 1506 2

943

541

1271

1472

945

545

945

545

1273

1473

947

549

947

549

1275

1474

949

553

949

553

1277

1475

951

557

951

557

1279

1476

953

561

953

561

1281

1477

955

565

955

565

1283

1478

957

569

957

569

1285

1479

959

573

959

573

1287

1480

961

577

961

577

1289

1481

963

581

963

581

1291

1482

965

585

965

585

1293

1483

967

589

967

589

1295

1484

969

593

969

593

1297

1485

971

597

971

597

1299

1486

973

601

973

601

1301

1487

975

605

975

605

1303

1488

977

609

977

609

1305

1489

979

613

979

613

1307

1490

981

617

981

617

1309

1491

983

621

983

621

1311

1492

985

625

985

625

1313

1493

987

629

987

629

1315

1494

989

633

989

633

1317

1495

991

637

991

637

1319

1496

993

641

993

641

1321

1497

995

645

995

645

1323

1498

997

649

997

649

1325

1499

999

653

999

653

1327

1500

1001

657

1001

657

1329

1501

1003

661

1003

661

1331

1502

1005

665

1005

665

1333

1503

1007

669

1007

669

1335

1504

1009

673

1009

673

1337

1505

1011

677

1011

677

1339

1506

1013

681

OptiStruct 13.0 Reference Guide 1437 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1341 671 1343 672 1345 673 1512 674 1516 675 1520 676 1524 677 1528 678 1532 679 1536 680 1540 681 1544 682 1548 683 1552 684 1556 685 1560 686 1564 687 1568 688 1572 689 1576 690 1580 691 1584 692 1588 693 1592 694 1596 695 1600 696 1604 697 1608 698 1612 699 1616 700 1620 701 1624 702 1628 703 1632 704 1636

1507 2 1508 2 1509 2 1513 2 1517 2 1521 2 1525 2 1529 2 1533 2 1537 2 1541 2 1545 2 1549 2 1553 2 1557 2 1561 2 1565 2 1569 2 1573 2 1577 2 1581 2 1585 2 1589 2 1593 2 1597 2 1601 2 1605 2 1609 2 1613 2 1617 2 1621 2 1625 2 1629 2 1633 2 1637

1013

681

1341

1507

1015

685

1015

685

1343

1508

1017

689

12

13

14

22

1510

1511

1510

1511

1512

1513

1514

1515

1514

1515

1516

1517

1518

1519

1518

1519

1520

1521

1522

1523

1522

1523

1524

1525

1526

1527

1526

1527

1528

1529

1530

1531

1530

1531

1532

1533

1534

1535

1534

1535

1536

1537

1538

1539

1538

1539

1540

1541

1542

1543

1542

1543

1544

1545

1546

1547

1546

1547

1548

1549

1550

1551

1550

1551

1552

1553

1554

1555

1554

1555

1556

1557

1558

1559

1558

1559

1560

1561

1562

1563

1562

1563

1564

1565

1566

1567

1566

1567

1568

1569

1570

1571

1570

1571

1572

1573

1574

1575

1574

1575

1576

1577

1578

1579

1578

1579

1580

1581

1582

1583

1582

1583

1584

1585

1586

1587

1586

1587

1588

1589

1590

1591

1590

1591

1592

1593

1594

1595

1594

1595

1596

1597

1598

1599

1598

1599

1600

1601

1602

1603

1602

1603

1604

1605

1606

1607

1606

1607

1608

1609

1610

1611

1610

1611

1612

1613

1614

1615

1614

1615

1616

1617

1618

1619

1618

1619

1620

1621

1622

1623

1622

1623

1624

1625

1626

1627

1626

1627

1628

1629

1630

1631

1630

1631

1632

1633

1634

1635

1438 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

705 1640 706 1644 707 1648 708 1652 709 1656 710 1660 711 1664 712 1668 713 1672 714 1676 795 2000 796 2004 797 2008 798 2012 799 2016 800 2020 801 2024 802 2028 803 2032 804 2036 805 2040 806 2044 807 2048 808 2052 809 2056 810 2060 811 2064 812 2068 813 2072 814 2076 815 2080 816 2084 817 2088 818 2092 819

Altair Engineering

2 1641 2 1645 2 1649 2 1653 2 1657 2 1661 2 1665 2 1669 2 1673 2 1677 2 2001 2 2005 2 2009 2 2013 2 2017 2 2021 2 2025 2 2029 2 2033 2 2037 2 2041 2 2045 2 2049 2 2053 2 2057 2 2061 2 2065 2 2069 2 2073 2 2077 2 2081 2 2085 2 2089 2 2093 2

1634

1635

1636

1637

1638

1639

1638

1639

1640

1641

1642

1643

1642

1643

1644

1645

1646

1647

1646

1647

1648

1649

1650

1651

1650

1651

1652

1653

1654

1655

1654

1655

1656

1657

1658

1659

1658

1659

1660

1661

1662

1663

1662

1663

1664

1665

1666

1667

1666

1667

1668

1669

1670

1671

1670

1671

1672

1673

1674

1675

1674

1675

1676

1677

1998

1999

1998

1999

2000

2001

2002

2003

2002

2003

2004

2005

2006

2007

2006

2007

2008

2009

2010

2011

2010

2011

2012

2013

2014

2015

2014

2015

2016

2017

2018

2019

2018

2019

2020

2021

2022

2023

2022

2023

2024

2025

2026

2027

2026

2027

2028

2029

2030

2031

2030

2031

2032

2033

2034

2035

2034

2035

2036

2037

2038

2039

2038

2039

2040

2041

2042

2043

2042

2043

2044

2045

2046

2047

2046

2047

2048

2049

2050

2051

2050

2051

2052

2053

2054

2055

2054

2055

2056

2057

2058

2059

2058

2059

2060

2061

2062

2063

2062

2063

2064

2065

2066

2067

2066

2067

2068

2069

2070

2071

2070

2071

2072

2073

2074

2075

2074

2075

2076

2077

2078

2079

2078

2079

2080

2081

2082

2083

2082

2083

2084

2085

2086

2087

2086

2087

2088

2089

2090

2091

2090

2091

2092

2093

2094

2095

OptiStruct 13.0 Reference Guide 1439 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2096 820 2100 821 2104 822 2108 823 2112 824 2116 825 2120 826 2124 827 2128 828 2132 829 2136 830 2140 831 2144 832 2148 833 2152 834 2156 835 2160 836 2164 837 1513 838 1517 839 1521 840 1525 841 1529 842 1533 843 1537 844 1541 845 1545 846 1549 847 1553 848 1557 849 1561 850 1565 851 1569 852 1573 853 1577

2097 2 2101 2 2105 2 2109 2 2113 2 2117 2 2121 2 2125 2 2129 2 2133 2 2137 2 2141 2 2145 2 2149 2 2153 2 2157 2 2161 2 2165 2 36 2 40 2 44 2 48 2 52 2 56 2 60 2 64 2 68 2 72 2 76 2 80 2 84 2 88 2 92 2 96 2 100

2094

2095

2096

2097

2098

2099

2098

2099

2100

2101

2102

2103

2102

2103

2104

2105

2106

2107

2106

2107

2108

2109

2110

2111

2110

2111

2112

2113

2114

2115

2114

2115

2116

2117

2118

2119

2118

2119

2120

2121

2122

2123

2122

2123

2124

2125

2126

2127

2126

2127

2128

2129

2130

2131

2130

2131

2132

2133

2134

2135

2134

2135

2136

2137

2138

2139

2138

2139

2140

2141

2142

2143

2142

2143

2144

2145

2146

2147

2146

2147

2148

2149

2150

2151

2150

2151

2152

2153

2154

2155

2154

2155

2156

2157

2158

2159

2158

2159

2160

2161

2162

2163

11

12

22

21

35

1510

35

1510

1513

36

39

1514

39

1514

1517

40

43

1518

43

1518

1521

44

47

1522

47

1522

1525

48

51

1526

51

1526

1529

52

55

1530

55

1530

1533

56

59

1534

59

1534

1537

60

63

1538

63

1538

1541

64

67

1542

67

1542

1545

68

71

1546

71

1546

1549

72

75

1550

75

1550

1553

76

79

1554

79

1554

1557

80

83

1558

83

1558

1561

84

87

1562

87

1562

1565

88

91

1566

91

1566

1569

92

95

1570

95

1570

1573

96

99

1574

1440 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

854 1581 855 1585 856 1589 857 1593 858 1597 859 1601 860 1605 861 1609 862 1613 863 1617 864 1621 865 1625 866 1629 867 1633 868 1637 869 1641 870 1645 871 1649 872 1653 873 1657 874 1661 875 1665 876 1669 877 1673 878 1677 959 2001 960 2005 961 2009 962 2013 963 2017 964 2021 965 2025 966 2029 967 2033 968

Altair Engineering

2 104 2 108 2 112 2 116 2 120 2 124 2 128 2 132 2 136 2 140 2 144 2 148 2 152 2 156 2 160 2 164 2 168 2 172 2 176 2 180 2 184 2 188 2 192 2 196 2 200 2 524 2 528 2 532 2 536 2 540 2 544 2 548 2 552 2 556 2

99

1574

1577

100

103

1578

103

1578

1581

104

107

1582

107

1582

1585

108

111

1586

111

1586

1589

112

115

1590

115

1590

1593

116

119

1594

119

1594

1597

120

123

1598

123

1598

1601

124

127

1602

127

1602

1605

128

131

1606

131

1606

1609

132

135

1610

135

1610

1613

136

139

1614

139

1614

1617

140

143

1618

143

1618

1621

144

147

1622

147

1622

1625

148

151

1626

151

1626

1629

152

155

1630

155

1630

1633

156

159

1634

159

1634

1637

160

163

1638

163

1638

1641

164

167

1642

167

1642

1645

168

171

1646

171

1646

1649

172

175

1650

175

1650

1653

176

179

1654

179

1654

1657

180

183

1658

183

1658

1661

184

187

1662

187

1662

1665

188

191

1666

191

1666

1669

192

195

1670

195

1670

1673

196

199

1674

199

1674

1677

200

523

1998

523

1998

2001

524

527

2002

527

2002

2005

528

531

2006

531

2006

2009

532

535

2010

535

2010

2013

536

539

2014

539

2014

2017

540

543

2018

543

2018

2021

544

547

2022

547

2022

2025

548

551

2026

551

2026

2029

552

555

2030

555

2030

2033

556

559

2034

OptiStruct 13.0 Reference Guide 1441 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2037 969 2041 970 2045 971 2049 972 2053 973 2057 974 2061 975 2065 976 2069 977 2073 978 2077 979 2081 980 2085 981 2089 982 2093 983 2097 984 2101 985 2105 986 2109 987 2113 988 2117 989 2121 990 2125 991 2129 992 2133 993 2137 994 2141 995 2145 996 2149 997 2153 998 2157 999 2161 1000 2165 1001 2166 1002 2168

560 2 564 2 568 2 572 2 576 2 580 2 584 2 588 2 592 2 596 2 600 2 604 2 608 2 612 2 616 2 620 2 624 2 628 2 632 2 636 2 640 2 644 2 648 2 652 2 656 2 660 2 664 2 668 2 672 2 676 2 680 2 684 2 688 2 2167 2 2169

559

2034

2037

560

563

2038

563

2038

2041

564

567

2042

567

2042

2045

568

571

2046

571

2046

2049

572

575

2050

575

2050

2053

576

579

2054

579

2054

2057

580

583

2058

583

2058

2061

584

587

2062

587

2062

2065

588

591

2066

591

2066

2069

592

595

2070

595

2070

2073

596

599

2074

599

2074

2077

600

603

2078

603

2078

2081

604

607

2082

607

2082

2085

608

611

2086

611

2086

2089

612

615

2090

615

2090

2093

616

619

2094

619

2094

2097

620

623

2098

623

2098

2101

624

627

2102

627

2102

2105

628

631

2106

631

2106

2109

632

635

2110

635

2110

2113

636

639

2114

639

2114

2117

640

643

2118

643

2118

2121

644

647

2122

647

2122

2125

648

651

2126

651

2126

2129

652

655

2130

655

2130

2133

656

659

2134

659

2134

2137

660

663

2138

663

2138

2141

664

667

2142

667

2142

2145

668

671

2146

671

2146

2149

672

675

2150

675

2150

2153

676

679

2154

679

2154

2157

680

683

2158

683

2158

2161

684

687

2162

22

14

15

16

1513

1512

1513

1512

2166

2167

1517

1516

1442 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1003 2170 1004 2172 1005 2174 1006 2176 1007 2178 1008 2180 1009 2182 1010 2184 1011 2186 1012 2188 1013 2190 1014 2192 1015 2194 1016 2196 1017 2198 1018 2200 1019 2202 1020 2204 1021 2206 1022 2208 1023 2210 1024 2212 1025 2214 1026 2216 1027 2218 1028 2220 1029 2222 1030 2224 1031 2226 1032 2228 1033 2230 1034 2232 1035 2234 1036 2236 1037

Altair Engineering

2 2171 2 2173 2 2175 2 2177 2 2179 2 2181 2 2183 2 2185 2 2187 2 2189 2 2191 2 2193 2 2195 2 2197 2 2199 2 2201 2 2203 2 2205 2 2207 2 2209 2 2211 2 2213 2 2215 2 2217 2 2219 2 2221 2 2223 2 2225 2 2227 2 2229 2 2231 2 2233 2 2235 2 2237 2

1517

1516

2168

2169

1521

1520

1521

1520

2170

2171

1525

1524

1525

1524

2172

2173

1529

1528

1529

1528

2174

2175

1533

1532

1533

1532

2176

2177

1537

1536

1537

1536

2178

2179

1541

1540

1541

1540

2180

2181

1545

1544

1545

1544

2182

2183

1549

1548

1549

1548

2184

2185

1553

1552

1553

1552

2186

2187

1557

1556

1557

1556

2188

2189

1561

1560

1561

1560

2190

2191

1565

1564

1565

1564

2192

2193

1569

1568

1569

1568

2194

2195

1573

1572

1573

1572

2196

2197

1577

1576

1577

1576

2198

2199

1581

1580

1581

1580

2200

2201

1585

1584

1585

1584

2202

2203

1589

1588

1589

1588

2204

2205

1593

1592

1593

1592

2206

2207

1597

1596

1597

1596

2208

2209

1601

1600

1601

1600

2210

2211

1605

1604

1605

1604

2212

2213

1609

1608

1609

1608

2214

2215

1613

1612

1613

1612

2216

2217

1617

1616

1617

1616

2218

2219

1621

1620

1621

1620

2220

2221

1625

1624

1625

1624

2222

2223

1629

1628

1629

1628

2224

2225

1633

1632

1633

1632

2226

2227

1637

1636

1637

1636

2228

2229

1641

1640

1641

1640

2230

2231

1645

1644

1645

1644

2232

2233

1649

1648

1649

1648

2234

2235

1653

1652

1653

1652

2236

2237

1657

1656

OptiStruct 13.0 Reference Guide 1443 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2238 1038 2240 1039 2242 1040 2244 1041 2246 1042 2248 1123 2410 1124 2412 1125 2414 1126 2416 1127 2418 1128 2420 1129 2422 1130 2424 1131 2426 1132 2428 1133 2430 1134 2432 1135 2434 1136 2436 1137 2438 1138 2440 1139 2442 1140 2444 1141 2446 1142 2448 1143 2450 1144 2452 1145 2454 1146 2456 1147 2458 1148 2460 1149 2462 1150 2464 1151 2466

2239 2 2241 2 2243 2 2245 2 2247 2 2249 2 2411 2 2413 2 2415 2 2417 2 2419 2 2421 2 2423 2 2425 2 2427 2 2429 2 2431 2 2433 2 2435 2 2437 2 2439 2 2441 2 2443 2 2445 2 2447 2 2449 2 2451 2 2453 2 2455 2 2457 2 2459 2 2461 2 2463 2 2465 2 2467

1657

1656

2238

2239

1661

1660

1661

1660

2240

2241

1665

1664

1665

1664

2242

2243

1669

1668

1669

1668

2244

2245

1673

1672

1673

1672

2246

2247

1677

1676

1677

1676

2248

2249

2001

2000

2001

2000

2410

2411

2005

2004

2005

2004

2412

2413

2009

2008

2009

2008

2414

2415

2013

2012

2013

2012

2416

2417

2017

2016

2017

2016

2418

2419

2021

2020

2021

2020

2420

2421

2025

2024

2025

2024

2422

2423

2029

2028

2029

2028

2424

2425

2033

2032

2033

2032

2426

2427

2037

2036

2037

2036

2428

2429

2041

2040

2041

2040

2430

2431

2045

2044

2045

2044

2432

2433

2049

2048

2049

2048

2434

2435

2053

2052

2053

2052

2436

2437

2057

2056

2057

2056

2438

2439

2061

2060

2061

2060

2440

2441

2065

2064

2065

2064

2442

2443

2069

2068

2069

2068

2444

2445

2073

2072

2073

2072

2446

2447

2077

2076

2077

2076

2448

2449

2081

2080

2081

2080

2450

2451

2085

2084

2085

2084

2452

2453

2089

2088

2089

2088

2454

2455

2093

2092

2093

2092

2456

2457

2097

2096

2097

2096

2458

2459

2101

2100

2101

2100

2460

2461

2105

2104

2105

2104

2462

2463

2109

2108

2109

2108

2464

2465

2113

2112

1444 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1152 2468 1153 2470 1154 2472 1155 2474 1156 2476 1157 2478 1158 2480 1159 2482 1160 2484 1161 2486 1162 2488 1163 2490 1164 2492 1165 2167 1166 2169 1167 2171 1168 2173 1169 2175 1170 2177 1171 2179 1172 2181 1173 2183 1174 2185 1175 2187 1176 2189 1177 2191 1178 2193 1179 2195 1180 2197 1181 2199 1182 2201 1183 2203 1184 2205 1185 2207 1186

Altair Engineering

2 2469 2 2471 2 2473 2 2475 2 2477 2 2479 2 2481 2 2483 2 2485 2 2487 2 2489 2 2491 2 2493 2 1018 2 1020 2 1022 2 1024 2 1026 2 1028 2 1030 2 1032 2 1034 2 1036 2 1038 2 1040 2 1042 2 1044 2 1046 2 1048 2 1050 2 1052 2 1054 2 1056 2 1058 2

2113

2112

2466

2467

2117

2116

2117

2116

2468

2469

2121

2120

2121

2120

2470

2471

2125

2124

2125

2124

2472

2473

2129

2128

2129

2128

2474

2475

2133

2132

2133

2132

2476

2477

2137

2136

2137

2136

2478

2479

2141

2140

2141

2140

2480

2481

2145

2144

2145

2144

2482

2483

2149

2148

2149

2148

2484

2485

2153

2152

2153

2152

2486

2487

2157

2156

2157

2156

2488

2489

2161

2160

2161

2160

2490

2491

2165

2164

21

22

16

17

36

1513

36

1513

2167

1018

40

1517

40

1517

2169

1020

44

1521

44

1521

2171

1022

48

1525

48

1525

2173

1024

52

1529

52

1529

2175

1026

56

1533

56

1533

2177

1028

60

1537

60

1537

2179

1030

64

1541

64

1541

2181

1032

68

1545

68

1545

2183

1034

72

1549

72

1549

2185

1036

76

1553

76

1553

2187

1038

80

1557

80

1557

2189

1040

84

1561

84

1561

2191

1042

88

1565

88

1565

2193

1044

92

1569

92

1569

2195

1046

96

1573

96

1573

2197

1048

100

1577

100

1577

2199

1050

104

1581

104

1581

2201

1052

108

1585

108

1585

2203

1054

112

1589

112

1589

2205

1056

116

1593

116

1593

2207

1058

120

1597

OptiStruct 13.0 Reference Guide 1445 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2209 1187 2211 1188 2213 1189 2215 1190 2217 1191 2219 1192 2221 1193 2223 1194 2225 1195 2227 1196 2229 1197 2231 1198 2233 1199 2235 1200 2237 1201 2239 1202 2241 1203 2243 1204 2245 1205 2247 1206 2249 1287 2411 1288 2413 1289 2415 1290 2417 1291 2419 1292 2421 1293 2423 1294 2425 1295 2427 1296 2429 1297 2431 1298 2433 1299 2435 1300 2437

1060 2 1062 2 1064 2 1066 2 1068 2 1070 2 1072 2 1074 2 1076 2 1078 2 1080 2 1082 2 1084 2 1086 2 1088 2 1090 2 1092 2 1094 2 1096 2 1098 2 1100 2 1262 2 1264 2 1266 2 1268 2 1270 2 1272 2 1274 2 1276 2 1278 2 1280 2 1282 2 1284 2 1286 2 1288

120

1597

2209

1060

124

1601

124

1601

2211

1062

128

1605

128

1605

2213

1064

132

1609

132

1609

2215

1066

136

1613

136

1613

2217

1068

140

1617

140

1617

2219

1070

144

1621

144

1621

2221

1072

148

1625

148

1625

2223

1074

152

1629

152

1629

2225

1076

156

1633

156

1633

2227

1078

160

1637

160

1637

2229

1080

164

1641

164

1641

2231

1082

168

1645

168

1645

2233

1084

172

1649

172

1649

2235

1086

176

1653

176

1653

2237

1088

180

1657

180

1657

2239

1090

184

1661

184

1661

2241

1092

188

1665

188

1665

2243

1094

192

1669

192

1669

2245

1096

196

1673

196

1673

2247

1098

200

1677

200

1677

2249

1100

524

2001

524

2001

2411

1262

528

2005

528

2005

2413

1264

532

2009

532

2009

2415

1266

536

2013

536

2013

2417

1268

540

2017

540

2017

2419

1270

544

2021

544

2021

2421

1272

548

2025

548

2025

2423

1274

552

2029

552

2029

2425

1276

556

2033

556

2033

2427

1278

560

2037

560

2037

2429

1280

564

2041

564

2041

2431

1282

568

2045

568

2045

2433

1284

572

2049

572

2049

2435

1286

576

2053

1446 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1301 2439 1302 2441 1303 2443 1304 2445 1305 2447 1306 2449 1307 2451 1308 2453 1309 2455 1310 2457 1311 2459 1312 2461 1313 2463 1314 2465 1315 2467 1316 2469 1317 2471 1318 2473 1319 2475 1320 2477 1321 2479 1322 2481 1323 2483 1324 2485 1325 2487 1326 2489 1327 2491 1328 2493 1329 35 1330 39 1331 43 1332 47 1333 51 1334 55 1335

Altair Engineering

2 1290 2 1292 2 1294 2 1296 2 1298 2 1300 2 1302 2 1304 2 1306 2 1308 2 1310 2 1312 2 1314 2 1316 2 1318 2 1320 2 1322 2 1324 2 1326 2 1328 2 1330 2 1332 2 1334 2 1336 2 1338 2 1340 2 1342 2 1344 2 2495 2 2497 2 2499 2 2501 2 2503 2 2505 2

576

2053

2437

1288

580

2057

580

2057

2439

1290

584

2061

584

2061

2441

1292

588

2065

588

2065

2443

1294

592

2069

592

2069

2445

1296

596

2073

596

2073

2447

1298

600

2077

600

2077

2449

1300

604

2081

604

2081

2451

1302

608

2085

608

2085

2453

1304

612

2089

612

2089

2455

1306

616

2093

616

2093

2457

1308

620

2097

620

2097

2459

1310

624

2101

624

2101

2461

1312

628

2105

628

2105

2463

1314

632

2109

632

2109

2465

1316

636

2113

636

2113

2467

1318

640

2117

640

2117

2469

1320

644

2121

644

2121

2471

1322

648

2125

648

2125

2473

1324

652

2129

652

2129

2475

1326

656

2133

656

2133

2477

1328

660

2137

660

2137

2479

1330

664

2141

664

2141

2481

1332

668

2145

668

2145

2483

1334

672

2149

672

2149

2485

1336

676

2153

676

2153

2487

1338

680

2157

680

2157

2489

1340

684

2161

684

2161

2491

1342

688

2165

33

12

11

31

2494

1510

2494

1510

35

2495

2496

1514

2496

1514

39

2497

2498

1518

2498

1518

43

2499

2500

1522

2500

1522

47

2501

2502

1526

2502

1526

51

2503

2504

1530

2504

1530

55

2505

2506

1534

OptiStruct 13.0 Reference Guide 1447 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

59 1336 63 1337 67 1338 71 1339 75 1340 79 1341 83 1342 87 1343 91 1344 95 1345 99 1346 103 1347 107 1348 111 1349 115 1350 119 1351 123 1352 127 1353 131 1354 135 1355 139 1356 143 1357 147 1358 151 1359 155 1360 159 1361 163 1362 167 1363 171 1364 175 1365 179 1366 183 1367 187 1368 191 1369 195

2507 2 2509 2 2511 2 2513 2 2515 2 2517 2 2519 2 2521 2 2523 2 2525 2 2527 2 2529 2 2531 2 2533 2 2535 2 2537 2 2539 2 2541 2 2543 2 2545 2 2547 2 2549 2 2551 2 2553 2 2555 2 2557 2 2559 2 2561 2 2563 2 2565 2 2567 2 2569 2 2571 2 2573 2 2575

2506

1534

59

2507

2508

1538

2508

1538

63

2509

2510

1542

2510

1542

67

2511

2512

1546

2512

1546

71

2513

2514

1550

2514

1550

75

2515

2516

1554

2516

1554

79

2517

2518

1558

2518

1558

83

2519

2520

1562

2520

1562

87

2521

2522

1566

2522

1566

91

2523

2524

1570

2524

1570

95

2525

2526

1574

2526

1574

99

2527

2528

1578

2528

1578

103

2529

2530

1582

2530

1582

107

2531

2532

1586

2532

1586

111

2533

2534

1590

2534

1590

115

2535

2536

1594

2536

1594

119

2537

2538

1598

2538

1598

123

2539

2540

1602

2540

1602

127

2541

2542

1606

2542

1606

131

2543

2544

1610

2544

1610

135

2545

2546

1614

2546

1614

139

2547

2548

1618

2548

1618

143

2549

2550

1622

2550

1622

147

2551

2552

1626

2552

1626

151

2553

2554

1630

2554

1630

155

2555

2556

1634

2556

1634

159

2557

2558

1638

2558

1638

163

2559

2560

1642

2560

1642

167

2561

2562

1646

2562

1646

171

2563

2564

1650

2564

1650

175

2565

2566

1654

2566

1654

179

2567

2568

1658

2568

1658

183

2569

2570

1662

2570

1662

187

2571

2572

1666

2572

1666

191

2573

2574

1670

1448 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1370 199 1451 523 1452 527 1453 531 1454 535 1455 539 1456 543 1457 547 1458 551 1459 555 1460 559 1461 563 1462 567 1463 571 1464 575 1465 579 1466 583 1467 587 1468 591 1469 595 1470 599 1471 603 1472 607 1473 611 1474 615 1475 619 1476 623 1477 627 1478 631 1479 635 1480 639 1481 643 1482 647 1483 651 1484

Altair Engineering

2 2577 2 2739 2 2741 2 2743 2 2745 2 2747 2 2749 2 2751 2 2753 2 2755 2 2757 2 2759 2 2761 2 2763 2 2765 2 2767 2 2769 2 2771 2 2773 2 2775 2 2777 2 2779 2 2781 2 2783 2 2785 2 2787 2 2789 2 2791 2 2793 2 2795 2 2797 2 2799 2 2801 2 2803 2

2574

1670

195

2575

2576

1674

2576

1674

199

2577

2738

1998

2738

1998

523

2739

2740

2002

2740

2002

527

2741

2742

2006

2742

2006

531

2743

2744

2010

2744

2010

535

2745

2746

2014

2746

2014

539

2747

2748

2018

2748

2018

543

2749

2750

2022

2750

2022

547

2751

2752

2026

2752

2026

551

2753

2754

2030

2754

2030

555

2755

2756

2034

2756

2034

559

2757

2758

2038

2758

2038

563

2759

2760

2042

2760

2042

567

2761

2762

2046

2762

2046

571

2763

2764

2050

2764

2050

575

2765

2766

2054

2766

2054

579

2767

2768

2058

2768

2058

583

2769

2770

2062

2770

2062

587

2771

2772

2066

2772

2066

591

2773

2774

2070

2774

2070

595

2775

2776

2074

2776

2074

599

2777

2778

2078

2778

2078

603

2779

2780

2082

2780

2082

607

2781

2782

2086

2782

2086

611

2783

2784

2090

2784

2090

615

2785

2786

2094

2786

2094

619

2787

2788

2098

2788

2098

623

2789

2790

2102

2790

2102

627

2791

2792

2106

2792

2106

631

2793

2794

2110

2794

2110

635

2795

2796

2114

2796

2114

639

2797

2798

2118

2798

2118

643

2799

2800

2122

2800

2122

647

2801

2802

2126

2802

2126

651

2803

2804

2130

OptiStruct 13.0 Reference Guide 1449 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

655 1485 659 1486 663 1487 667 1488 671 1489 675 1490 679 1491 683 1492 687 1493 1510 1494 1514 1495 1518 1496 1522 1497 1526 1498 1530 1499 1534 1500 1538 1501 1542 1502 1546 1503 1550 1504 1554 1505 1558 1506 1562 1507 1566 1508 1570 1509 1574 1510 1578 1511 1582 1512 1586 1513 1590 1514 1594 1515 1598 1516 1602 1517 1606 1518 1610

2805 2 2807 2 2809 2 2811 2 2813 2 2815 2 2817 2 2819 2 2821 2 2494 2 2496 2 2498 2 2500 2 2502 2 2504 2 2506 2 2508 2 2510 2 2512 2 2514 2 2516 2 2518 2 2520 2 2522 2 2524 2 2526 2 2528 2 2530 2 2532 2 2534 2 2536 2 2538 2 2540 2 2542 2 2544

2804

2130

655

2805

2806

2134

2806

2134

659

2807

2808

2138

2808

2138

663

2809

2810

2142

2810

2142

667

2811

2812

2146

2812

2146

671

2813

2814

2150

2814

2150

675

2815

2816

2154

2816

2154

679

2817

2818

2158

2818

2158

683

2819

2820

2162

30

13

12

33

2822

1511

2822

1511

1510

2494

2823

1515

2823

1515

1514

2496

2824

1519

2824

1519

1518

2498

2825

1523

2825

1523

1522

2500

2826

1527

2826

1527

1526

2502

2827

1531

2827

1531

1530

2504

2828

1535

2828

1535

1534

2506

2829

1539

2829

1539

1538

2508

2830

1543

2830

1543

1542

2510

2831

1547

2831

1547

1546

2512

2832

1551

2832

1551

1550

2514

2833

1555

2833

1555

1554

2516

2834

1559

2834

1559

1558

2518

2835

1563

2835

1563

1562

2520

2836

1567

2836

1567

1566

2522

2837

1571

2837

1571

1570

2524

2838

1575

2838

1575

1574

2526

2839

1579

2839

1579

1578

2528

2840

1583

2840

1583

1582

2530

2841

1587

2841

1587

1586

2532

2842

1591

2842

1591

1590

2534

2843

1595

2843

1595

1594

2536

2844

1599

2844

1599

1598

2538

2845

1603

2845

1603

1602

2540

2846

1607

2846

1607

1606

2542

2847

1611

1450 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1519 1614 1520 1618 1521 1622 1522 1626 1523 1630 1524 1634 1525 1638 1526 1642 1527 1646 1528 1650 1529 1654 1530 1658 1531 1662 1532 1666 1533 1670 1534 1674 1615 1998 1616 2002 1617 2006 1618 2010 1619 2014 1620 2018 1621 2022 1622 2026 1623 2030 1624 2034 1625 2038 1626 2042 1627 2046 1628 2050 1629 2054 1630 2058 1631 2062 1632 2066 1633

Altair Engineering

2 2546 2 2548 2 2550 2 2552 2 2554 2 2556 2 2558 2 2560 2 2562 2 2564 2 2566 2 2568 2 2570 2 2572 2 2574 2 2576 2 2738 2 2740 2 2742 2 2744 2 2746 2 2748 2 2750 2 2752 2 2754 2 2756 2 2758 2 2760 2 2762 2 2764 2 2766 2 2768 2 2770 2 2772 2

2847

1611

1610

2544

2848

1615

2848

1615

1614

2546

2849

1619

2849

1619

1618

2548

2850

1623

2850

1623

1622

2550

2851

1627

2851

1627

1626

2552

2852

1631

2852

1631

1630

2554

2853

1635

2853

1635

1634

2556

2854

1639

2854

1639

1638

2558

2855

1643

2855

1643

1642

2560

2856

1647

2856

1647

1646

2562

2857

1651

2857

1651

1650

2564

2858

1655

2858

1655

1654

2566

2859

1659

2859

1659

1658

2568

2860

1663

2860

1663

1662

2570

2861

1667

2861

1667

1666

2572

2862

1671

2862

1671

1670

2574

2863

1675

2863

1675

1674

2576

2944

1999

2944

1999

1998

2738

2945

2003

2945

2003

2002

2740

2946

2007

2946

2007

2006

2742

2947

2011

2947

2011

2010

2744

2948

2015

2948

2015

2014

2746

2949

2019

2949

2019

2018

2748

2950

2023

2950

2023

2022

2750

2951

2027

2951

2027

2026

2752

2952

2031

2952

2031

2030

2754

2953

2035

2953

2035

2034

2756

2954

2039

2954

2039

2038

2758

2955

2043

2955

2043

2042

2760

2956

2047

2956

2047

2046

2762

2957

2051

2957

2051

2050

2764

2958

2055

2958

2055

2054

2766

2959

2059

2959

2059

2058

2768

2960

2063

2960

2063

2062

2770

2961

2067

2961

2067

2066

2772

2962

2071

OptiStruct 13.0 Reference Guide 1451 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2070 1634 2074 1635 2078 1636 2082 1637 2086 1638 2090 1639 2094 1640 2098 1641 2102 1642 2106 1643 2110 1644 2114 1645 2118 1646 2122 1647 2126 1648 2130 1649 2134 1650 2138 1651 2142 1652 2146 1653 2150 1654 2154 1655 2158 1656 2162 1657 2495 1658 2497 1659 2499 1660 2501 1661 2503 1662 2505 1663 2507 1664 2509 1665 2511 1666 2513 1667 2515

2774 2 2776 2 2778 2 2780 2 2782 2 2784 2 2786 2 2788 2 2790 2 2792 2 2794 2 2796 2 2798 2 2800 2 2802 2 2804 2 2806 2 2808 2 2810 2 2812 2 2814 2 2816 2 2818 2 2820 2 2987 2 2989 2 2991 2 2993 2 2995 2 2997 2 2999 2 3001 2 3003 2 3005 2 3007

2962

2071

2070

2774

2963

2075

2963

2075

2074

2776

2964

2079

2964

2079

2078

2778

2965

2083

2965

2083

2082

2780

2966

2087

2966

2087

2086

2782

2967

2091

2967

2091

2090

2784

2968

2095

2968

2095

2094

2786

2969

2099

2969

2099

2098

2788

2970

2103

2970

2103

2102

2790

2971

2107

2971

2107

2106

2792

2972

2111

2972

2111

2110

2794

2973

2115

2973

2115

2114

2796

2974

2119

2974

2119

2118

2798

2975

2123

2975

2123

2122

2800

2976

2127

2976

2127

2126

2802

2977

2131

2977

2131

2130

2804

2978

2135

2978

2135

2134

2806

2979

2139

2979

2139

2138

2808

2980

2143

2980

2143

2142

2810

2981

2147

2981

2147

2146

2812

2982

2151

2982

2151

2150

2814

2983

2155

2983

2155

2154

2816

2984

2159

2984

2159

2158

2818

2985

2163

28

33

31

27

2986

2494

2986

2494

2495

2987

2988

2496

2988

2496

2497

2989

2990

2498

2990

2498

2499

2991

2992

2500

2992

2500

2501

2993

2994

2502

2994

2502

2503

2995

2996

2504

2996

2504

2505

2997

2998

2506

2998

2506

2507

2999

3000

2508

3000

2508

2509

3001

3002

2510

3002

2510

2511

3003

3004

2512

3004

2512

2513

3005

3006

2514

1452 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1668 2517 1669 2519 1670 2521 1671 2523 1672 2525 1673 2527 1674 2529 1675 2531 1676 2533 1677 2535 1678 2537 1679 2539 1680 2541 1681 2543 1682 2545 1683 2547 1684 2549 1685 2551 1686 2553 1687 2555 1688 2557 1689 2559 1690 2561 1691 2563 1692 2565 1693 2567 1694 2569 1695 2571 1696 2573 1697 2575 1698 2577 1779 2739 1780 2741 1781 2743 1782

Altair Engineering

2 3009 2 3011 2 3013 2 3015 2 3017 2 3019 2 3021 2 3023 2 3025 2 3027 2 3029 2 3031 2 3033 2 3035 2 3037 2 3039 2 3041 2 3043 2 3045 2 3047 2 3049 2 3051 2 3053 2 3055 2 3057 2 3059 2 3061 2 3063 2 3065 2 3067 2 3069 2 3231 2 3233 2 3235 2

3006

2514

2515

3007

3008

2516

3008

2516

2517

3009

3010

2518

3010

2518

2519

3011

3012

2520

3012

2520

2521

3013

3014

2522

3014

2522

2523

3015

3016

2524

3016

2524

2525

3017

3018

2526

3018

2526

2527

3019

3020

2528

3020

2528

2529

3021

3022

2530

3022

2530

2531

3023

3024

2532

3024

2532

2533

3025

3026

2534

3026

2534

2535

3027

3028

2536

3028

2536

2537

3029

3030

2538

3030

2538

2539

3031

3032

2540

3032

2540

2541

3033

3034

2542

3034

2542

2543

3035

3036

2544

3036

2544

2545

3037

3038

2546

3038

2546

2547

3039

3040

2548

3040

2548

2549

3041

3042

2550

3042

2550

2551

3043

3044

2552

3044

2552

2553

3045

3046

2554

3046

2554

2555

3047

3048

2556

3048

2556

2557

3049

3050

2558

3050

2558

2559

3051

3052

2560

3052

2560

2561

3053

3054

2562

3054

2562

2563

3055

3056

2564

3056

2564

2565

3057

3058

2566

3058

2566

2567

3059

3060

2568

3060

2568

2569

3061

3062

2570

3062

2570

2571

3063

3064

2572

3064

2572

2573

3065

3066

2574

3066

2574

2575

3067

3068

2576

3068

2576

2577

3069

3230

2738

3230

2738

2739

3231

3232

2740

3232

2740

2741

3233

3234

2742

3234

2742

2743

3235

3236

2744

OptiStruct 13.0 Reference Guide 1453 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2745 1783 2747 1784 2749 1785 2751 1786 2753 1787 2755 1788 2757 1789 2759 1790 2761 1791 2763 1792 2765 1793 2767 1794 2769 1795 2771 1796 2773 1797 2775 1798 2777 1799 2779 1800 2781 1801 2783 1802 2785 1803 2787 1804 2789 1805 2791 1806 2793 1807 2795 1808 2797 1809 2799 1810 2801 1811 2803 1812 2805 1813 2807 1814 2809 1815 2811 1816 2813

3237 2 3239 2 3241 2 3243 2 3245 2 3247 2 3249 2 3251 2 3253 2 3255 2 3257 2 3259 2 3261 2 3263 2 3265 2 3267 2 3269 2 3271 2 3273 2 3275 2 3277 2 3279 2 3281 2 3283 2 3285 2 3287 2 3289 2 3291 2 3293 2 3295 2 3297 2 3299 2 3301 2 3303 2 3305

3236

2744

2745

3237

3238

2746

3238

2746

2747

3239

3240

2748

3240

2748

2749

3241

3242

2750

3242

2750

2751

3243

3244

2752

3244

2752

2753

3245

3246

2754

3246

2754

2755

3247

3248

2756

3248

2756

2757

3249

3250

2758

3250

2758

2759

3251

3252

2760

3252

2760

2761

3253

3254

2762

3254

2762

2763

3255

3256

2764

3256

2764

2765

3257

3258

2766

3258

2766

2767

3259

3260

2768

3260

2768

2769

3261

3262

2770

3262

2770

2771

3263

3264

2772

3264

2772

2773

3265

3266

2774

3266

2774

2775

3267

3268

2776

3268

2776

2777

3269

3270

2778

3270

2778

2779

3271

3272

2780

3272

2780

2781

3273

3274

2782

3274

2782

2783

3275

3276

2784

3276

2784

2785

3277

3278

2786

3278

2786

2787

3279

3280

2788

3280

2788

2789

3281

3282

2790

3282

2790

2791

3283

3284

2792

3284

2792

2793

3285

3286

2794

3286

2794

2795

3287

3288

2796

3288

2796

2797

3289

3290

2798

3290

2798

2799

3291

3292

2800

3292

2800

2801

3293

3294

2802

3294

2802

2803

3295

3296

2804

3296

2804

2805

3297

3298

2806

3298

2806

2807

3299

3300

2808

3300

2808

2809

3301

3302

2810

3302

2810

2811

3303

3304

2812

1454 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1817 2815 1818 2817 1819 2819 1820 2821 1821 2494 1822 2496 1823 2498 1824 2500 1825 2502 1826 2504 1827 2506 1828 2508 1829 2510 1830 2512 1831 2514 1832 2516 1833 2518 1834 2520 1835 2522 1836 2524 1837 2526 1838 2528 1839 2530 1840 2532 1841 2534 1842 2536 1843 2538 1844 2540 1845 2542 1846 2544 1847 2546 1848 2548 1849 2550 1850 2552 1851

Altair Engineering

2 3307 2 3309 2 3311 2 3313 2 2986 2 2988 2 2990 2 2992 2 2994 2 2996 2 2998 2 3000 2 3002 2 3004 2 3006 2 3008 2 3010 2 3012 2 3014 2 3016 2 3018 2 3020 2 3022 2 3024 2 3026 2 3028 2 3030 2 3032 2 3034 2 3036 2 3038 2 3040 2 3042 2 3044 2

3304

2812

2813

3305

3306

2814

3306

2814

2815

3307

3308

2816

3308

2816

2817

3309

3310

2818

3310

2818

2819

3311

3312

2820

29

30

33

28

3314

2822

3314

2822

2494

2986

3315

2823

3315

2823

2496

2988

3316

2824

3316

2824

2498

2990

3317

2825

3317

2825

2500

2992

3318

2826

3318

2826

2502

2994

3319

2827

3319

2827

2504

2996

3320

2828

3320

2828

2506

2998

3321

2829

3321

2829

2508

3000

3322

2830

3322

2830

2510

3002

3323

2831

3323

2831

2512

3004

3324

2832

3324

2832

2514

3006

3325

2833

3325

2833

2516

3008

3326

2834

3326

2834

2518

3010

3327

2835

3327

2835

2520

3012

3328

2836

3328

2836

2522

3014

3329

2837

3329

2837

2524

3016

3330

2838

3330

2838

2526

3018

3331

2839

3331

2839

2528

3020

3332

2840

3332

2840

2530

3022

3333

2841

3333

2841

2532

3024

3334

2842

3334

2842

2534

3026

3335

2843

3335

2843

2536

3028

3336

2844

3336

2844

2538

3030

3337

2845

3337

2845

2540

3032

3338

2846

3338

2846

2542

3034

3339

2847

3339

2847

2544

3036

3340

2848

3340

2848

2546

3038

3341

2849

3341

2849

2548

3040

3342

2850

3342

2850

2550

3042

3343

2851

3343

2851

2552

3044

3344

2852

OptiStruct 13.0 Reference Guide 1455 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

2554 1852 2556 1853 2558 1854 2560 1855 2562 1856 2564 1857 2566 1858 2568 1859 2570 1860 2572 1861 2574 1862 2576 1943 2738 1944 2740 1945 2742 1946 2744 1947 2746 1948 2748 1949 2750 1950 2752 1951 2754 1952 2756 1953 2758 1954 2760 1955 2762 1956 2764 1957 2766 1958 2768 1959 2770 1960 2772 1961 2774 1962 2776 1963 2778 1964 2780 1965 2782

3046 2 3048 2 3050 2 3052 2 3054 2 3056 2 3058 2 3060 2 3062 2 3064 2 3066 2 3068 2 3230 2 3232 2 3234 2 3236 2 3238 2 3240 2 3242 2 3244 2 3246 2 3248 2 3250 2 3252 2 3254 2 3256 2 3258 2 3260 2 3262 2 3264 2 3266 2 3268 2 3270 2 3272 2 3274

3344

2852

2554

3046

3345

2853

3345

2853

2556

3048

3346

2854

3346

2854

2558

3050

3347

2855

3347

2855

2560

3052

3348

2856

3348

2856

2562

3054

3349

2857

3349

2857

2564

3056

3350

2858

3350

2858

2566

3058

3351

2859

3351

2859

2568

3060

3352

2860

3352

2860

2570

3062

3353

2861

3353

2861

2572

3064

3354

2862

3354

2862

2574

3066

3355

2863

3355

2863

2576

3068

3436

2944

3436

2944

2738

3230

3437

2945

3437

2945

2740

3232

3438

2946

3438

2946

2742

3234

3439

2947

3439

2947

2744

3236

3440

2948

3440

2948

2746

3238

3441

2949

3441

2949

2748

3240

3442

2950

3442

2950

2750

3242

3443

2951

3443

2951

2752

3244

3444

2952

3444

2952

2754

3246

3445

2953

3445

2953

2756

3248

3446

2954

3446

2954

2758

3250

3447

2955

3447

2955

2760

3252

3448

2956

3448

2956

2762

3254

3449

2957

3449

2957

2764

3256

3450

2958

3450

2958

2766

3258

3451

2959

3451

2959

2768

3260

3452

2960

3452

2960

2770

3262

3453

2961

3453

2961

2772

3264

3454

2962

3454

2962

2774

3266

3455

2963

3455

2963

2776

3268

3456

2964

3456

2964

2778

3270

3457

2965

3457

2965

2780

3272

3458

2966

1456 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

1966 2784 1967 2786 1968 2788 1969 2790 1970 2792 1971 2794 1972 2796 1973 2798 1974 2800 1975 2802 1976 2804 1977 2806 1978 2808 1979 2810 1980 2812 1981 2814 1982 2816 1983 2818 1984 2820 1985 690 1986 692 1987 694 1988 696 1989 698 1990 700 1991 702 1992 704 1993 706 1994 708 1995 710 1996 712 1997 714 1998 716 1999 718 2000

Altair Engineering

2 3276 2 3278 2 3280 2 3282 2 3284 2 3286 2 3288 2 3290 2 3292 2 3294 2 3296 2 3298 2 3300 2 3302 2 3304 2 3306 2 3308 2 3310 2 3312 2 3479 2 3481 2 3483 2 3485 2 3487 2 3489 2 3491 2 3493 2 3495 2 3497 2 3499 2 3501 2 3503 2 3505 2 3507 2

3458

2966

2782

3274

3459

2967

3459

2967

2784

3276

3460

2968

3460

2968

2786

3278

3461

2969

3461

2969

2788

3280

3462

2970

3462

2970

2790

3282

3463

2971

3463

2971

2792

3284

3464

2972

3464

2972

2794

3286

3465

2973

3465

2973

2796

3288

3466

2974

3466

2974

2798

3290

3467

2975

3467

2975

2800

3292

3468

2976

3468

2976

2802

3294

3469

2977

3469

2977

2804

3296

3470

2978

3470

2978

2806

3298

3471

2979

3471

2979

2808

3300

3472

2980

3472

2980

2810

3302

3473

2981

3473

2981

2812

3304

3474

2982

3474

2982

2814

3306

3475

2983

3475

2983

2816

3308

3476

2984

3476

2984

2818

3310

3477

2985

32

10

9

24

3478

34

3478

34

690

3479

3480

38

3480

38

692

3481

3482

42

3482

42

694

3483

3484

46

3484

46

696

3485

3486

50

3486

50

698

3487

3488

54

3488

54

700

3489

3490

58

3490

58

702

3491

3492

62

3492

62

704

3493

3494

66

3494

66

706

3495

3496

70

3496

70

708

3497

3498

74

3498

74

710

3499

3500

78

3500

78

712

3501

3502

82

3502

82

714

3503

3504

86

3504

86

716

3505

3506

90

3506

90

718

3507

3508

94

OptiStruct 13.0 Reference Guide 1457 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

720 2001 722 2002 724 2003 726 2004 728 2005 730 2006 732 2007 734 2008 736 2009 738 2010 740 2011 742 2012 744 2013 746 2014 748 2015 750 2016 752 2017 754 2018 756 2019 758 2020 760 2021 762 2022 764 2023 766 2024 768 2025 770 2026 772 2107 934 2108 936 2109 938 2110 940 2111 942 2112 944 2113 946 2114 948

3509 2 3511 2 3513 2 3515 2 3517 2 3519 2 3521 2 3523 2 3525 2 3527 2 3529 2 3531 2 3533 2 3535 2 3537 2 3539 2 3541 2 3543 2 3545 2 3547 2 3549 2 3551 2 3553 2 3555 2 3557 2 3559 2 3561 2 3723 2 3725 2 3727 2 3729 2 3731 2 3733 2 3735 2 3737

3508

94

720

3509

3510

98

3510

98

722

3511

3512

102

3512

102

724

3513

3514

106

3514

106

726

3515

3516

110

3516

110

728

3517

3518

114

3518

114

730

3519

3520

118

3520

118

732

3521

3522

122

3522

122

734

3523

3524

126

3524

126

736

3525

3526

130

3526

130

738

3527

3528

134

3528

134

740

3529

3530

138

3530

138

742

3531

3532

142

3532

142

744

3533

3534

146

3534

146

746

3535

3536

150

3536

150

748

3537

3538

154

3538

154

750

3539

3540

158

3540

158

752

3541

3542

162

3542

162

754

3543

3544

166

3544

166

756

3545

3546

170

3546

170

758

3547

3548

174

3548

174

760

3549

3550

178

3550

178

762

3551

3552

182

3552

182

764

3553

3554

186

3554

186

766

3555

3556

190

3556

190

768

3557

3558

194

3558

194

770

3559

3560

198

3560

198

772

3561

3722

522

3722

522

934

3723

3724

526

3724

526

936

3725

3726

530

3726

530

938

3727

3728

534

3728

534

940

3729

3730

538

3730

538

942

3731

3732

542

3732

542

944

3733

3734

546

3734

546

946

3735

3736

550

1458 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

2115 950 2116 952 2117 954 2118 956 2119 958 2120 960 2121 962 2122 964 2123 966 2124 968 2125 970 2126 972 2127 974 2128 976 2129 978 2130 980 2131 982 2132 984 2133 986 2134 988 2135 990 2136 992 2137 994 2138 996 2139 998 2140 1000 2141 1002 2142 1004 2143 1006 2144 1008 2145 1010 2146 1012 2147 1014 2148 1016 2149

Altair Engineering

2 3739 2 3741 2 3743 2 3745 2 3747 2 3749 2 3751 2 3753 2 3755 2 3757 2 3759 2 3761 2 3763 2 3765 2 3767 2 3769 2 3771 2 3773 2 3775 2 3777 2 3779 2 3781 2 3783 2 3785 2 3787 2 3789 2 3791 2 3793 2 3795 2 3797 2 3799 2 3801 2 3803 2 3805 2

3736

550

948

3737

3738

554

3738

554

950

3739

3740

558

3740

558

952

3741

3742

562

3742

562

954

3743

3744

566

3744

566

956

3745

3746

570

3746

570

958

3747

3748

574

3748

574

960

3749

3750

578

3750

578

962

3751

3752

582

3752

582

964

3753

3754

586

3754

586

966

3755

3756

590

3756

590

968

3757

3758

594

3758

594

970

3759

3760

598

3760

598

972

3761

3762

602

3762

602

974

3763

3764

606

3764

606

976

3765

3766

610

3766

610

978

3767

3768

614

3768

614

980

3769

3770

618

3770

618

982

3771

3772

622

3772

622

984

3773

3774

626

3774

626

986

3775

3776

630

3776

630

988

3777

3778

634

3778

634

990

3779

3780

638

3780

638

992

3781

3782

642

3782

642

994

3783

3784

646

3784

646

996

3785

3786

650

3786

650

998

3787

3788

654

3788

654

1000

3789

3790

658

3790

658

1002

3791

3792

662

3792

662

1004

3793

3794

666

3794

666

1006

3795

3796

670

3796

670

1008

3797

3798

674

3798

674

1010

3799

3800

678

3800

678

1012

3801

3802

682

3802

682

1014

3803

3804

686

31

11

10

32

2495

35

OptiStruct 13.0 Reference Guide 1459 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

34 2150 38 2151 42 2152 46 2153 50 2154 54 2155 58 2156 62 2157 66 2158 70 2159 74 2160 78 2161 82 2162 86 2163 90 2164 94 2165 98 2166 102 2167 106 2168 110 2169 114 2170 118 2171 122 2172 126 2173 130 2174 134 2175 138 2176 142 2177 146 2178 150 2179 154 2180 158 2181 162 2182 166 2183 170

3478 2 3480 2 3482 2 3484 2 3486 2 3488 2 3490 2 3492 2 3494 2 3496 2 3498 2 3500 2 3502 2 3504 2 3506 2 3508 2 3510 2 3512 2 3514 2 3516 2 3518 2 3520 2 3522 2 3524 2 3526 2 3528 2 3530 2 3532 2 3534 2 3536 2 3538 2 3540 2 3542 2 3544 2 3546

2495

35

34

3478

2497

39

2497

39

38

3480

2499

43

2499

43

42

3482

2501

47

2501

47

46

3484

2503

51

2503

51

50

3486

2505

55

2505

55

54

3488

2507

59

2507

59

58

3490

2509

63

2509

63

62

3492

2511

67

2511

67

66

3494

2513

71

2513

71

70

3496

2515

75

2515

75

74

3498

2517

79

2517

79

78

3500

2519

83

2519

83

82

3502

2521

87

2521

87

86

3504

2523

91

2523

91

90

3506

2525

95

2525

95

94

3508

2527

99

2527

99

98

3510

2529

103

2529

103

102

3512

2531

107

2531

107

106

3514

2533

111

2533

111

110

3516

2535

115

2535

115

114

3518

2537

119

2537

119

118

3520

2539

123

2539

123

122

3522

2541

127

2541

127

126

3524

2543

131

2543

131

130

3526

2545

135

2545

135

134

3528

2547

139

2547

139

138

3530

2549

143

2549

143

142

3532

2551

147

2551

147

146

3534

2553

151

2553

151

150

3536

2555

155

2555

155

154

3538

2557

159

2557

159

158

3540

2559

163

2559

163

162

3542

2561

167

2561

167

166

3544

2563

171

1460 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

2184 174 2185 178 2186 182 2187 186 2188 190 2189 194 2190 198 2271 522 2272 526 2273 530 2274 534 2275 538 2276 542 2277 546 2278 550 2279 554 2280 558 2281 562 2282 566 2283 570 2284 574 2285 578 2286 582 2287 586 2288 590 2289 594 2290 598 2291 602 2292 606 2293 610 2294 614 2295 618 2296 622 2297 626 2298

Altair Engineering

2 3548 2 3550 2 3552 2 3554 2 3556 2 3558 2 3560 2 3722 2 3724 2 3726 2 3728 2 3730 2 3732 2 3734 2 3736 2 3738 2 3740 2 3742 2 3744 2 3746 2 3748 2 3750 2 3752 2 3754 2 3756 2 3758 2 3760 2 3762 2 3764 2 3766 2 3768 2 3770 2 3772 2 3774 2

2563

171

170

3546

2565

175

2565

175

174

3548

2567

179

2567

179

178

3550

2569

183

2569

183

182

3552

2571

187

2571

187

186

3554

2573

191

2573

191

190

3556

2575

195

2575

195

194

3558

2577

199

2577

199

198

3560

2739

523

2739

523

522

3722

2741

527

2741

527

526

3724

2743

531

2743

531

530

3726

2745

535

2745

535

534

3728

2747

539

2747

539

538

3730

2749

543

2749

543

542

3732

2751

547

2751

547

546

3734

2753

551

2753

551

550

3736

2755

555

2755

555

554

3738

2757

559

2757

559

558

3740

2759

563

2759

563

562

3742

2761

567

2761

567

566

3744

2763

571

2763

571

570

3746

2765

575

2765

575

574

3748

2767

579

2767

579

578

3750

2769

583

2769

583

582

3752

2771

587

2771

587

586

3754

2773

591

2773

591

590

3756

2775

595

2775

595

594

3758

2777

599

2777

599

598

3760

2779

603

2779

603

602

3762

2781

607

2781

607

606

3764

2783

611

2783

611

610

3766

2785

615

2785

615

614

3768

2787

619

2787

619

618

3770

2789

623

2789

623

622

3772

2791

627

2791

627

626

3774

2793

631

OptiStruct 13.0 Reference Guide 1461 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

630 2299 634 2300 638 2301 642 2302 646 2303 650 2304 654 2305 658 2306 662 2307 666 2308 670 2309 674 2310 678 2311 682 2312 686 2313 3479 2314 3481 2315 3483 2316 3485 2317 3487 2318 3489 2319 3491 2320 3493 2321 3495 2322 3497 2323 3499 2324 3501 2325 3503 2326 3505 2327 3507 2328 3509 2329 3511 2330 3513 2331 3515 2332 3517

3776 2 3778 2 3780 2 3782 2 3784 2 3786 2 3788 2 3790 2 3792 2 3794 2 3796 2 3798 2 3800 2 3802 2 3804 2 3807 2 3809 2 3811 2 3813 2 3815 2 3817 2 3819 2 3821 2 3823 2 3825 2 3827 2 3829 2 3831 2 3833 2 3835 2 3837 2 3839 2 3841 2 3843 2 3845

2793

631

630

3776

2795

635

2795

635

634

3778

2797

639

2797

639

638

3780

2799

643

2799

643

642

3782

2801

647

2801

647

646

3784

2803

651

2803

651

650

3786

2805

655

2805

655

654

3788

2807

659

2807

659

658

3790

2809

663

2809

663

662

3792

2811

667

2811

667

666

3794

2813

671

2813

671

670

3796

2815

675

2815

675

674

3798

2817

679

2817

679

678

3800

2819

683

2819

683

682

3802

2821

687

26

32

24

25

3806

3478

3806

3478

3479

3807

3808

3480

3808

3480

3481

3809

3810

3482

3810

3482

3483

3811

3812

3484

3812

3484

3485

3813

3814

3486

3814

3486

3487

3815

3816

3488

3816

3488

3489

3817

3818

3490

3818

3490

3491

3819

3820

3492

3820

3492

3493

3821

3822

3494

3822

3494

3495

3823

3824

3496

3824

3496

3497

3825

3826

3498

3826

3498

3499

3827

3828

3500

3828

3500

3501

3829

3830

3502

3830

3502

3503

3831

3832

3504

3832

3504

3505

3833

3834

3506

3834

3506

3507

3835

3836

3508

3836

3508

3509

3837

3838

3510

3838

3510

3511

3839

3840

3512

3840

3512

3513

3841

3842

3514

3842

3514

3515

3843

3844

3516

1462 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

2333 3519 2334 3521 2335 3523 2336 3525 2337 3527 2338 3529 2339 3531 2340 3533 2341 3535 2342 3537 2343 3539 2344 3541 2345 3543 2346 3545 2347 3547 2348 3549 2349 3551 2350 3553 2351 3555 2352 3557 2353 3559 2354 3561 2435 3723 2436 3725 2437 3727 2438 3729 2439 3731 2440 3733 2441 3735 2442 3737 2443 3739 2444 3741 2445 3743 2446 3745 2447

Altair Engineering

2 3847 2 3849 2 3851 2 3853 2 3855 2 3857 2 3859 2 3861 2 3863 2 3865 2 3867 2 3869 2 3871 2 3873 2 3875 2 3877 2 3879 2 3881 2 3883 2 3885 2 3887 2 3889 2 4051 2 4053 2 4055 2 4057 2 4059 2 4061 2 4063 2 4065 2 4067 2 4069 2 4071 2 4073 2

3844

3516

3517

3845

3846

3518

3846

3518

3519

3847

3848

3520

3848

3520

3521

3849

3850

3522

3850

3522

3523

3851

3852

3524

3852

3524

3525

3853

3854

3526

3854

3526

3527

3855

3856

3528

3856

3528

3529

3857

3858

3530

3858

3530

3531

3859

3860

3532

3860

3532

3533

3861

3862

3534

3862

3534

3535

3863

3864

3536

3864

3536

3537

3865

3866

3538

3866

3538

3539

3867

3868

3540

3868

3540

3541

3869

3870

3542

3870

3542

3543

3871

3872

3544

3872

3544

3545

3873

3874

3546

3874

3546

3547

3875

3876

3548

3876

3548

3549

3877

3878

3550

3878

3550

3551

3879

3880

3552

3880

3552

3553

3881

3882

3554

3882

3554

3555

3883

3884

3556

3884

3556

3557

3885

3886

3558

3886

3558

3559

3887

3888

3560

3888

3560

3561

3889

4050

3722

4050

3722

3723

4051

4052

3724

4052

3724

3725

4053

4054

3726

4054

3726

3727

4055

4056

3728

4056

3728

3729

4057

4058

3730

4058

3730

3731

4059

4060

3732

4060

3732

3733

4061

4062

3734

4062

3734

3735

4063

4064

3736

4064

3736

3737

4065

4066

3738

4066

3738

3739

4067

4068

3740

4068

3740

3741

4069

4070

3742

4070

3742

3743

4071

4072

3744

4072

3744

3745

4073

4074

3746

OptiStruct 13.0 Reference Guide 1463 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

3747 2448 3749 2449 3751 2450 3753 2451 3755 2452 3757 2453 3759 2454 3761 2455 3763 2456 3765 2457 3767 2458 3769 2459 3771 2460 3773 2461 3775 2462 3777 2463 3779 2464 3781 2465 3783 2466 3785 2467 3787 2468 3789 2469 3791 2470 3793 2471 3795 2472 3797 2473 3799 2474 3801 2475 3803 2476 3805 2477 3478 2478 3480 2479 3482 2480 3484 2481 3486

4075 2 4077 2 4079 2 4081 2 4083 2 4085 2 4087 2 4089 2 4091 2 4093 2 4095 2 4097 2 4099 2 4101 2 4103 2 4105 2 4107 2 4109 2 4111 2 4113 2 4115 2 4117 2 4119 2 4121 2 4123 2 4125 2 4127 2 4129 2 4131 2 4133 2 3806 2 3808 2 3810 2 3812 2 3814

4074

3746

3747

4075

4076

3748

4076

3748

3749

4077

4078

3750

4078

3750

3751

4079

4080

3752

4080

3752

3753

4081

4082

3754

4082

3754

3755

4083

4084

3756

4084

3756

3757

4085

4086

3758

4086

3758

3759

4087

4088

3760

4088

3760

3761

4089

4090

3762

4090

3762

3763

4091

4092

3764

4092

3764

3765

4093

4094

3766

4094

3766

3767

4095

4096

3768

4096

3768

3769

4097

4098

3770

4098

3770

3771

4099

4100

3772

4100

3772

3773

4101

4102

3774

4102

3774

3775

4103

4104

3776

4104

3776

3777

4105

4106

3778

4106

3778

3779

4107

4108

3780

4108

3780

3781

4109

4110

3782

4110

3782

3783

4111

4112

3784

4112

3784

3785

4113

4114

3786

4114

3786

3787

4115

4116

3788

4116

3788

3789

4117

4118

3790

4118

3790

3791

4119

4120

3792

4120

3792

3793

4121

4122

3794

4122

3794

3795

4123

4124

3796

4124

3796

3797

4125

4126

3798

4126

3798

3799

4127

4128

3800

4128

3800

3801

4129

4130

3802

4130

3802

3803

4131

4132

3804

27

31

32

26

2987

2495

2987

2495

3478

3806

2989

2497

2989

2497

3480

3808

2991

2499

2991

2499

3482

3810

2993

2501

2993

2501

3484

3812

2995

2503

1464 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

2482 3488 2483 3490 2484 3492 2485 3494 2486 3496 2487 3498 2488 3500 2489 3502 2490 3504 2491 3506 2492 3508 2493 3510 2494 3512 2495 3514 2496 3516 2497 3518 2498 3520 2499 3522 2500 3524 2501 3526 2502 3528 2503 3530 2504 3532 2505 3534 2506 3536 2507 3538 2508 3540 2509 3542 2510 3544 2511 3546 2512 3548 2513 3550 2514 3552 2515 3554 2516

Altair Engineering

2 3816 2 3818 2 3820 2 3822 2 3824 2 3826 2 3828 2 3830 2 3832 2 3834 2 3836 2 3838 2 3840 2 3842 2 3844 2 3846 2 3848 2 3850 2 3852 2 3854 2 3856 2 3858 2 3860 2 3862 2 3864 2 3866 2 3868 2 3870 2 3872 2 3874 2 3876 2 3878 2 3880 2 3882 2

2995

2503

3486

3814

2997

2505

2997

2505

3488

3816

2999

2507

2999

2507

3490

3818

3001

2509

3001

2509

3492

3820

3003

2511

3003

2511

3494

3822

3005

2513

3005

2513

3496

3824

3007

2515

3007

2515

3498

3826

3009

2517

3009

2517

3500

3828

3011

2519

3011

2519

3502

3830

3013

2521

3013

2521

3504

3832

3015

2523

3015

2523

3506

3834

3017

2525

3017

2525

3508

3836

3019

2527

3019

2527

3510

3838

3021

2529

3021

2529

3512

3840

3023

2531

3023

2531

3514

3842

3025

2533

3025

2533

3516

3844

3027

2535

3027

2535

3518

3846

3029

2537

3029

2537

3520

3848

3031

2539

3031

2539

3522

3850

3033

2541

3033

2541

3524

3852

3035

2543

3035

2543

3526

3854

3037

2545

3037

2545

3528

3856

3039

2547

3039

2547

3530

3858

3041

2549

3041

2549

3532

3860

3043

2551

3043

2551

3534

3862

3045

2553

3045

2553

3536

3864

3047

2555

3047

2555

3538

3866

3049

2557

3049

2557

3540

3868

3051

2559

3051

2559

3542

3870

3053

2561

3053

2561

3544

3872

3055

2563

3055

2563

3546

3874

3057

2565

3057

2565

3548

3876

3059

2567

3059

2567

3550

3878

3061

2569

3061

2569

3552

3880

3063

2571

3063

2571

3554

3882

3065

2573

OptiStruct 13.0 Reference Guide 1465 Proprietary Information of Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

3556 2517 3558 2518 3560 2599 3722 2600 3724 2601 3726 2602 3728 2603 3730 2604 3732 2605 3734 2606 3736 2607 3738 2608 3740 2609 3742 2610 3744 2611 3746 2612 3748 2613 3750 2614 3752 2615 3754 2616 3756 2617 3758 2618 3760 2619 3762 2620 3764 2621 3766 2622 3768 2623 3770 2624 3772 2625 3774 2626 3776 2627 3778 2628 3780 2629 3782 2630 3784

3884 2 3886 2 3888 2 4050 2 4052 2 4054 2 4056 2 4058 2 4060 2 4062 2 4064 2 4066 2 4068 2 4070 2 4072 2 4074 2 4076 2 4078 2 4080 2 4082 2 4084 2 4086 2 4088 2 4090 2 4092 2 4094 2 4096 2 4098 2 4100 2 4102 2 4104 2 4106 2 4108 2 4110 2 4112

3065

2573

3556

3884

3067

2575

3067

2575

3558

3886

3069

2577

3069

2577

3560

3888

3231

2739

3231

2739

3722

4050

3233

2741

3233

2741

3724

4052

3235

2743

3235

2743

3726

4054

3237

2745

3237

2745

3728

4056

3239

2747

3239

2747

3730

4058

3241

2749

3241

2749

3732

4060

3243

2751

3243

2751

3734

4062

3245

2753

3245

2753

3736

4064

3247

2755

3247

2755

3738

4066

3249

2757

3249

2757

3740

4068

3251

2759

3251

2759

3742

4070

3253

2761

3253

2761

3744

4072

3255

2763

3255

2763

3746

4074

3257

2765

3257

2765

3748

4076

3259

2767

3259

2767

3750

4078

3261

2769

3261

2769

3752

4080

3263

2771

3263

2771

3754

4082

3265

2773

3265

2773

3756

4084

3267

2775

3267

2775

3758

4086

3269

2777

3269

2777

3760

4088

3271

2779

3271

2779

3762

4090

3273

2781

3273

2781

3764

4092

3275

2783

3275

2783

3766

4094

3277

2785

3277

2785

3768

4096

3279

2787

3279

2787

3770

4098

3281

2789

3281

2789

3772

4100

3283

2791

3283

2791

3774

4102

3285

2793

3285

2793

3776

4104

3287

2795

3287

2795

3778

4106

3289

2797

3289

2797

3780

4108

3291

2799

3291

2799

3782

4110

3293

2801

1466 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA 2631 2 3293 2801 3784 4112 3295 2803 + 3786 4114 CHEXA 2632 2 3295 2803 3786 4114 3297 2805 + 3788 4116 CHEXA 2633 2 3297 2805 3788 4116 3299 2807 + 3790 4118 CHEXA 2634 2 3299 2807 3790 4118 3301 2809 + 3792 4120 CHEXA 2635 2 3301 2809 3792 4120 3303 2811 + 3794 4122 CHEXA 2636 2 3303 2811 3794 4122 3305 2813 + 3796 4124 CHEXA 2637 2 3305 2813 3796 4124 3307 2815 + 3798 4126 CHEXA 2638 2 3307 2815 3798 4126 3309 2817 + 3800 4128 CHEXA 2639 2 3309 2817 3800 4128 3311 2819 + 3802 4130 CHEXA 2640 2 3311 2819 3802 4130 3313 2821 + 3804 4132 $ $HMMOVE 2 $ 17THRU 58 139THRU 222 303THRU 386 $ 467THRU 550 631THRU 714 795THRU 878 $ 959THRU 1042 1123THRU 1206 1287THRU 1370 $ 1451THRU 1534 1615THRU 1698 1779THRU 1862 $ 1943THRU 2026 2107THRU 2190 2271THRU 2354 $ 2435THRU 2518 2599THRU 2640 $ $$ $$------------------------------------------------------------------------------$ $$ HyperMesh name and color information for generic components $ $$------------------------------------------------------------------------------$ $HMNAME COMP 2"Air" 2 "Air" 5 $HWCOLOR COMP 2 5 $ $HMNAME COMP 5"Piston" $HWCOLOR COMP 5 8 $ $HMNAME COMP 6"absorber" $HWCOLOR COMP 6 3 $ $ $HMDPRP $ 17THRU 58 139THRU 222 303THRU 386 $ 467THRU 550 631THRU 714 795THRU 878 $ 959THRU 1042 1123THRU 1206 1287THRU 1370 $ 1451THRU 1534 1615THRU 1698 1779THRU 1862 $ 1943THRU 2026 2107THRU 2190 2271THRU 2354 $ 2435THRU 2518 2599THRU 2640 5627 5629 6116 $ 6122 6125 6520THRU 6521 6523 6528 6954 7220 $ 7647 7652 7945 7948 7955 $ $ $$ $$ PSHELL Data $$ $ $ $ $ $ $ $ $HMNAME PROP $HWCOLOR PROP PSHELL 1 $$

Altair Engineering

20.1

1"tube" 4 1 52 2

2

0.0

OptiStruct 13.0 Reference Guide 1467 Proprietary Information of Altair Engineering

$$ PSOLID Data $$ $HMNAME PROP 2"Air" 5 $HWCOLOR PROP 2 4 PSOLID 2 1 PFLUID $$ $$ MAT1 Data $$ $HMNAME MAT 2"alum" "MAT1" $HWCOLOR MAT 2 3 MAT1 21.0+7 0.3 0.000254 $$ $$ MAT10 Data $HMNAME MAT 1"Air" "MAT10" $HWCOLOR MAT 1 3 MAT10 1 1.21-7 13000.0 $$ $$------------------------------------------------------------------------------$ $$ HyperMesh Commands for loadcollectors name and color information $ $$------------------------------------------------------------------------------$ $HMNAME LOADCOL 2"spc" $HWCOLOR LOADCOL 2 6 $$ $HMNAME LOADCOL 8"Force" $HWCOLOR LOADCOL 8 7 $$ $HMNAME LOADCOL 12"SPC" $HWCOLOR LOADCOL 12 5 $$ $$ $$ FREQi cards $$ $HMNAME LOADCOL 3"Freq" $HWCOLOR LOADCOL 3 6 $FREQ1 3 0.0 5.0 600 FREQ 3480. $ $$ $$ RLOAD1 cards $$ $HMNAME LOADCOL 6"Rload" $HWCOLOR LOADCOL 6 6 RLOAD1 6 8 7 0 VELO $$ $$ $$ TABLED1 cards $$ $HMNAME LOADCOL 7"Table" $HWCOLOR LOADCOL 7 6 TABLED1 7 LINEAR LINEAR + 0.0 1.0 3000.0 1.0ENDT $$ $HMNAME LOADCOL 10"reactance" $HWCOLOR LOADCOL 10 5 TABLED1 10 LINEAR LINEAR + 0.0 0.00154 3000.0 0.00154ENDT $$ $HMNAME LOADCOL 11"Impedance" $HWCOLOR LOADCOL 11 5 TABLED1 11 LINEAR LINEAR + 0.0 0.0 3000.0 0.0ENDT $$ $$ $$ DLOAD cards $$ $HMNAME LOADCOL 9"Dload" $HWCOLOR LOADCOL 9 6 DLOAD 91.0 1.0 6 $$

1468 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

$$ EIGRL cards $$ $HMNAME LOADCOL 4"EigrlTube" $HWCOLOR LOADCOL 4 6 EIGRL 4 5 MASS $HMNAME LOADCOL 5"EigrlAir" $HWCOLOR LOADCOL 5 6 EIGRL 5 30 MASS $$ $$ SPC Data $$ SPC1 12123456 6776 thru 6800 spcd 86776 3 1.0 spcd 86777 3 1.0 spcd 86778 3 1.0 spcd 86779 3 1.0 spcd 86780 3 1.0 spcd 86781 3 1.0 spcd 86782 3 1.0 spcd 86783 3 1.0 spcd 86784 3 1.0 spcd 86785 3 1.0 spcd 86786 3 1.0 spcd 86788 3 1.0 spcd 86789 3 1.0 spcd 86790 3 1.0 spcd 86791 3 1.0 spcd 86792 3 1.0 spcd 86793 3 1.0 spcd 86794 3 1.0 spcd 86795 3 1.0 spcd 86796 3 1.0 spcd 86797 3 1.0 spcd 86798 3 1.0 spcd 86799 3 1.0 spcd 86800 3 1.0 $ $ DAREA Data $ $$ $$ DAREA Data $$ DAREA 8 6798 3-15.0 $$ $$ CAABSF 7957 5 689 688 687 686 CAABSF 7960 5 1017 689 686 1016 CAABSF 7964 5 1345 1344 688 689 CAABSF 7969 5 1509 1345 689 1017 CAABSF 7972 5 2165 2164 2163 2162 CAABSF 7977 5 688 2165 2162 687 CAABSF 7978 5 4133 3805 3804 4132 CAABSF 7980 5 2493 2492 2164 2165 CAABSF 7984 5 1344 2493 2165 688 CAABSF 7985 5 2821 687 2162 2820 CAABSF 7988 5 2820 2162 2163 2985 CAABSF 7990 5 3313 2821 2820 3312 CAABSF 7994 5 3312 2820 2985 3477 CAABSF 7996 5 3805 1016 686 3804 CAABSF 7998 5 3804 686 687 2821 CAABSF 8003 5 4132 3804 2821 3313 PAABSF 5 11 10 ENDDATA $$ $$------------------------------------------------------------------------------$$ $$ Data Definition for AutoDV $$ $$------------------------------------------------------------------------------$$ $$ $$-----------------------------------------------------------------------------$$

Altair Engineering

OptiStruct 13.0 Reference Guide 1469 Proprietary Information of Altair Engineering

$$ Design Variables Card for Control Perturbations $$ $$-----------------------------------------------------------------------------$$ $ $------------------------------------------------------------------------------$ $ Domain Element Definitions $ $------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$$ $$ Nodeset Definitions $$ $$------------------------------------------------------------------------------$$ $$ Design domain node sets $$ $$------------------------------------------------------------------------------$$ $$ Control Perturbation $$ $$------------------------------------------------------------------------------$$ $$ $$ $$ CONTROL PERTURBATION Data $$

ALTDOCTAG "0mjpRI@DXd^3_0ASnbi`;l;q6A23R@9_67hgW8R?OiZ] Eq:PeN``A;WXh3ITgJeq5NZRd5jSHQK3X@:`a12;n4qD_I^RYMo" ADI0.1.0 2011-02-11T20:16:20 0of1 OSQA ENDDOCTAG

Comments 1.

PAABSF is referenced by a CAABSF entry only.

2.

If only one grid point is specified on the CAABSF entry, then the impedance Z(f) = ZR + iZi is the total impedance at the point. If two grids are specified, then the impedance is the impedance per unit length. If three or four points are specified, then the impedance is the impedance per unit area. ZR(f) = TZREID(f) + B and Zi(f) = TZIMID(f) – K/(ω).

3.

The resistance represents a damper quantity B. The reactance represents a quantity of the type (ωM – K/ω). The impedance is defined as: Z = p/u where, p is the pressure and u is the velocity.

4.

The impedance scale factor S is used in computing element stiffness and damping terms as:

5.

To create a non-reflecting boundary, set the values of the TABLEDi entry referenced by the TZREID field (Resistance-real part of Impedance) to be equal to for all frequencies. This will allow the acoustic wave to propagate normally through the boundary, without reflection. This condition is called the Sommerfeld boundary condition. Where,

6.

is the density of the fluid and,

is the speed of sound in the fluid.

This card is represented as a property in HyperMesh.

1470 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PACABS Bulk Data Entry PACABS – Frequency-Dependant Structural Acoustic Absorber Property Description Defines the properties of the structural acoustic absorber element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PAC ABS

PID

SYNTH

TID1

TID2

TID3

TESTAR

C UTFR

B

K

M

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PAC ABS

4

YES

3

4

5

1.

200.

Field

Contents

PID

Property identification number.

(9)

(10)

(Integer > 0) SYNTH

Request the calculation of B, K, and M from the specified tables TIDi. Default = “YES” (Character = “YES” or “NO”)

TID1

Identification of the TABLEDi entry that defines the resistance. (Integer > 0 or Blank)

TID2

Identification of the TABLEDi entry that defines the reactance.

Altair Engineering

OptiStruct 13.0 Reference Guide 1471 Proprietary Information of Altair Engineering

Field

Contents (Integer > 0 or Blank)

TID3

Identification of the TABLEDi entry that defines the weighting function. (Integer > 0 or Blank)

TESTAR Area of the test specimen. Default = 1.0 (Real > 0.0) CUTFR

Cutoff frequency for tables referenced above. (Real > 0.0)

B, K, M

Equivalent damping, stiffness and mass values per unit area. K and M (Real > 0.0), B (Real)

Input File - chacab.fem $$------------------------------------------------------------------------------$ $$ $ $$ NASTRAN Input Deck Generated by HyperMesh Version : 8.0SR1 $ $$ Generated using HyperMesh-Nastran Template Version : 8.0sr1 $$ $ $$ Template: general $ $$ $ $$------------------------------------------------------------------------------$ $$------------------------------------------------------------------------------$ $$ Executive Control Cards $ $$------------------------------------------------------------------------------$ SOL 111 CEND $$------------------------------------------------------------------------------$ $$ Case Control Cards $ $$------------------------------------------------------------------------------$ SET 1 = 1734 DISPLACEMENT = 1 $ $HMNAME LOADSTEP 1"Load2" SUBCASE 1 LABEL= Load2 SPC = 4 FREQUENCY = 5 DLOAD = 2 $$------------------------------------------------------------------------------$ $$ Bulk Data Cards $ $$------------------------------------------------------------------------------$ BEGIN BULK $CHEXA $+

1056 1683

2 1672

1650

1661

1662

1651

1671

1472 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

1682+

Altair Engineering

CHACAB 1056 100 1650 1645 1657 + 1671 1672 PACABS,100,YES,1,2,3,1.5,10.0,2.0 PARAM,G,0.001 PARAM,COUPMASS,-1 PARAM,POST,-1 $ACMODL DIFF 0.1 $$ EIGRL,20,,,300 EIGRL,21,,,300 $$ GRID Data $$ GRID 1 2.0 2.0 0.0 GRID 2 2.0 1.5 0.0 GRID 3 2.0 1.0 0.0 GRID 4 2.0 0.5 0.0 GRID 5 2.0 0.0 0.0 GRID 6 2.0 -0.5 0.0 GRID 7 2.0 -1.0 0.0 GRID 8 2.0 -1.5 0.0 GRID 9 2.0 -2.0 0.0 GRID 10 1.5 2.0 0.0 GRID 11 1.5 1.5 0.0 GRID 12 1.5 1.0 0.0 GRID 13 1.5 0.5 0.0 GRID 14 1.5 0.0 0.0 GRID 15 1.5 -0.5 0.0 GRID 16 1.5 -1.0 0.0 GRID 17 1.5 -1.5 0.0 GRID 18 1.5 -2.0 0.0 GRID 19 1.0 2.0 0.0 GRID 20 1.0 1.5 0.0 GRID 21 1.0 1.0 0.0 GRID 22 1.0 0.5 0.0 GRID 23 1.0 0.0 0.0 GRID 24 1.0 -0.5 0.0 GRID 25 1.0 -1.0 0.0 GRID 26 1.0 -1.5 0.0 GRID 27 1.0 -2.0 0.0 GRID 28 0.5 2.0 0.0 GRID 29 0.5 1.5 0.0 GRID 30 0.5 1.0 0.0 GRID 31 0.5 0.5 0.0 GRID 32 0.5 0.0 0.0 GRID 33 0.5 -0.5 0.0 GRID 34 0.5 -1.0 0.0 GRID 35 0.5 -1.5 0.0 GRID 36 0.5 -2.0 0.0 GRID 37 0.0 2.0 0.0 GRID 38 0.0 1.5 0.0 GRID 39 0.0 1.0 0.0 GRID 40 0.0 0.5 0.0 GRID 41 0.0 0.0 0.0 GRID 42 0.0 -0.5 0.0 GRID 43 0.0 -1.0 0.0 GRID 44 0.0 -1.5 0.0 GRID 45 0.0 -2.0 0.0 GRID 46 -0.5 2.0 0.0 GRID 47 -0.5 1.5 0.0 GRID 48 -0.5 1.0 0.0 GRID 49 -0.5 0.5 0.0 GRID 50 -0.5 0.0 0.0 GRID 51 -0.5 -0.5 0.0 GRID 52 -0.5 -1.0 0.0 GRID 53 -0.5 -1.5 0.0 GRID 54 -0.5 -2.0 0.0 GRID 55 -1.0 2.0 0.0 GRID 56 -1.0 1.5 0.0 GRID 57 -1.0 1.0 0.0

Altair Engineering

1658

1676

1675+

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1473 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 727 728 729 730 731

-1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 2.5 2.5 2.0 2.0 1.5 1.5 1.0 1.0 0.5 0.5 0.0 0.0 -0.5 -0.5 -1.0 -1.0 -1.5 -1.5 -2.0 -2.0 -2.5 -2.5 2.5 2.5 2.0 2.0 2.5

0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.0 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 2.5 -2.5 2.5 -2.5 2.5 -2.5 2.5 -2.5 2.5 -2.5 2.5 -2.5 2.5 -2.5 2.5 -2.5 2.5 -2.5 2.5 -2.5 2.5 -2.5 2.5 2.0 2.0 2.5 1.5

0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 1.0 1.0 1.0 1.0 1.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1474 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

732 733 734 735 736 737 738 739 740 741 742 743 744 745 746 747 748 749 750 751 752 753 754 755 756 757 758 759 760 761 762 763 764 765 766 767 768 769 770 771 772 773 774 775 776 777 778 779 780 781 782 783 784 785 786 787 788 789 790 791 792 793 794 795 796 797 798 799 800

Altair Engineering

2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5

1.5 1.0 1.0 1.0 1.0 1.0 0.5 1.0 0.5 1.0 -4.2E-191.0 -6.5E-201.0 -0.5 1.0 -0.5 1.0 -1.0 1.0 -1.0 1.0 -1.5 1.0 -1.5 1.0 -2.0 1.0 -2.0 1.0 -2.5 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -9.8E-211.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -1.5E-211.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -2.3E-221.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -3.5E-231.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -5.3E-241.0 -0.5 1.0 -1.0 1.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1475 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

801 802 803 804 805 806 807 808 809 810 811 812 813 814 815 816 817 818 819 820 821 822 823 824 825 826 827 828 829 830 831 832 833 834 835 836 837 838 839 840 841 842 843 844 845 846 847 848 849 850 851 852 853 854 855 856 857 858 859 860 861 862 863 864 865 866 867 868 869

-0.5 -0.5 -0.5 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 2.5 2.5 2.0 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0

-1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -8.1E-251.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -9.3E-181.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -2.0E-181.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.0 1.0 2.5 1.0 1.5 1.0 1.0 1.0 0.5 1.0 -1.0E-181.0 -0.5 1.0 -1.0 1.0 -1.5 1.0 -2.0 1.0 -2.5 1.0 2.5 2.0 2.0 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.5 2.0 1.0 2.0 1.0 2.0 0.5 2.0 0.5 2.0 -6.0E-192.0 -1.2E-192.0 -0.5 2.0 -0.5 2.0 -1.0 2.0 -1.0 2.0 -1.5 2.0 -1.5 2.0 -2.0 2.0 -2.0 2.0 -2.5 2.0 -2.5 2.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1476 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

870 871 872 873 874 875 876 877 878 879 880 881 882 883 884 885 886 887 888 889 890 891 892 893 894 895 896 897 898 899 900 901 902 903 904 905 906 907 908 909 910 911 912 913 914 915 916 917 918 919 920 921 922 923 924 925 926 927 928 929 930 931 932 933 934 935 936 937 938

Altair Engineering

1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -0.5 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.5 -1.5 -1.5

2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -2.1E-202.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -3.8E-212.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -6.7E-222.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -1.2E-222.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -2.0E-232.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -1.4E-182.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1477 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

939 940 941 942 943 944 945 946 947 948 949 950 951 952 953 954 955 956 957 958 959 960 961 962 963 964 965 966 967 968 969 970 971 972 973 974 975 976 977 978 979 980 981 982 983 984 985 986 987 988 989 990 991 992 993 994 995 996 997 998 999 1000 1001 1002 1003 1004 1005 1006 1007

-1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 2.5 2.5 2.0 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 2.5 2.0 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.0 1.0 1.0 1.0 1.0 1.0

1.0 2.0 0.5 2.0 -1.3E-172.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -4.1E-182.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.0 2.0 2.5 2.0 1.5 2.0 1.0 2.0 0.5 2.0 -2.5E-182.0 -0.5 2.0 -1.0 2.0 -1.5 2.0 -2.0 2.0 -2.5 2.0 2.5 3.0 2.0 3.0 2.0 3.0 2.5 3.0 1.5 3.0 1.5 3.0 1.0 3.0 1.0 3.0 0.5 3.0 0.5 3.0 -6.7E-193.0 -1.5E-193.0 -0.5 3.0 -0.5 3.0 -1.0 3.0 -1.0 3.0 -1.5 3.0 -1.5 3.0 -2.0 3.0 -2.0 3.0 -2.5 3.0 -2.5 3.0 2.0 3.0 2.5 3.0 1.5 3.0 1.0 3.0 0.5 3.0 -3.1E-203.0 -0.5 3.0 -1.0 3.0 -1.5 3.0 -2.0 3.0 -2.5 3.0 2.0 3.0 2.5 3.0 1.5 3.0 1.0 3.0 0.5 3.0 -6.2E-213.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1478 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1008 1009 1010 1011 1012 1013 1014 1015 1016 1017 1018 1019 1020 1021 1022 1023 1024 1025 1026 1027 1028 1029 1030 1031 1032 1033 1034 1035 1036 1037 1038 1039 1040 1041 1042 1043 1044 1045 1046 1047 1048 1049 1050 1051 1052 1053 1054 1055 1056 1057 1058 1059 1060 1061 1062 1063 1064 1065 1066 1067 1068 1069 1070 1071 1072 1073 1074 1075 1076

Altair Engineering

1.0 -0.5 3.0 1.0 -1.0 3.0 1.0 -1.5 3.0 1.0 -2.0 3.0 1.0 -2.5 3.0 0.5 2.0 3.0 0.5 2.5 3.0 0.5 1.5 3.0 0.5 1.0 3.0 0.5 0.5 3.0 0.5 -1.2E-213.0 0.5 -0.5 3.0 0.5 -1.0 3.0 0.5 -1.5 3.0 0.5 -2.0 3.0 0.5 -2.5 3.0 1.50E-322.0 3.0 3.80E-332.5 3.0 2.67E-331.5 3.0 4.07E-341.0 3.0 6.20E-350.5 3.0 6.35E-32-2.3E-223.0 1.29E-31-0.5 3.0 -4.0E-32-1.0 3.0 -5.5E-32-1.5 3.0 -3.2E-32-2.0 3.0 -4.8E-33-2.5 3.0 -0.5 2.0 3.0 -0.5 2.5 3.0 -0.5 1.5 3.0 -0.5 1.0 3.0 -0.5 0.5 3.0 -0.5 -2.2E-193.0 -0.5 -0.5 3.0 -0.5 -1.0 3.0 -0.5 -1.5 3.0 -0.5 -2.0 3.0 -0.5 -2.5 3.0 -1.0 2.0 3.0 -1.0 2.5 3.0 -1.0 1.5 3.0 -1.0 1.0 3.0 -1.0 0.5 3.0 -1.0 -2.6E-183.0 -1.0 -0.5 3.0 -1.0 -1.0 3.0 -1.0 -1.5 3.0 -1.0 -2.0 3.0 -1.0 -2.5 3.0 -1.5 2.0 3.0 -1.5 2.5 3.0 -1.5 1.5 3.0 -1.5 1.0 3.0 -1.5 0.5 3.0 -1.5 -1.5E-173.0 -1.5 -0.5 3.0 -1.5 -1.0 3.0 -1.5 -1.5 3.0 -1.5 -2.0 3.0 -1.5 -2.5 3.0 -2.0 2.0 3.0 -2.0 2.5 3.0 -2.0 1.5 3.0 -2.0 1.0 3.0 -2.0 0.5 3.0 -2.0 -5.3E-183.0 -2.0 -0.5 3.0 -2.0 -1.0 3.0 -2.0 -1.5 3.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1479 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1077 1078 1079 1080 1081 1082 1083 1084 1085 1086 1087 1088 1089 1090 1091 1092 1093 1094 1095 1096 1097 1098 1099 1100 1101 1102 1103 1104 1105 1106 1107 1108 1109 1110 1111 1112 1113 1114 1115 1116 1117 1118 1119 1120 1121 1122 1123 1124 1125 1126 1127 1128 1129 1130 1131 1132 1133 1134 1135 1136 1137 1138 1139 1140 1141 1142 1143 1144 1145

-2.0 -2.0 3.0 -2.0 -2.5 3.0 -2.5 2.0 3.0 -2.5 2.5 3.0 -2.5 1.5 3.0 -2.5 1.0 3.0 -2.5 0.5 3.0 -2.5 -3.3E-183.0 -2.5 -0.5 3.0 -2.5 -1.0 3.0 -2.5 -1.5 3.0 -2.5 -2.0 3.0 -2.5 -2.5 3.0 2.5 2.5 4.0 2.5 2.0 4.0 2.0 2.0 4.0 2.0 2.5 4.0 2.5 1.5 4.0 2.0 1.5 4.0 2.5 1.0 4.0 2.0 1.0 4.0 2.5 0.5 4.0 2.0 0.5 4.0 2.5 -1.0E-164.0 2.0 -1.8E-164.0 2.5 -0.5 4.0 2.0 -0.5 4.0 2.5 -1.0 4.0 2.0 -1.0 4.0 2.5 -1.5 4.0 2.0 -1.5 4.0 2.5 -2.0 4.0 2.0 -2.0 4.0 2.5 -2.5 4.0 2.0 -2.5 4.0 1.5 2.0 4.0 1.5 2.5 4.0 1.5 1.5 4.0 1.5 1.0 4.0 1.5 0.5 4.0 1.5 -3.1E-164.0 1.5 -0.5 4.0 1.5 -1.0 4.0 1.5 -1.5 4.0 1.5 -2.0 4.0 1.5 -2.5 4.0 1.0 2.0 4.0 1.0 2.5 4.0 1.0 1.5 4.0 1.0 1.0 4.0 1.0 0.5 4.0 1.0 -3.6E-164.0 1.0 -0.5 4.0 1.0 -1.0 4.0 1.0 -1.5 4.0 1.0 -2.0 4.0 1.0 -2.5 4.0 0.5 2.0 4.0 0.5 2.5 4.0 0.5 1.5 4.0 0.5 1.0 4.0 0.5 0.5 4.0 0.5 -2.8E-164.0 0.5 -0.5 4.0 0.5 -1.0 4.0 0.5 -1.5 4.0 0.5 -2.0 4.0 0.5 -2.5 4.0 -1.7E-162.0 4.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1480 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1146 1147 1148 1149 1150 1151 1152 1153 1154 1155 1156 1157 1158 1159 1160 1161 1162 1163 1164 1165 1166 1167 1168 1169 1170 1171 1172 1173 1174 1175 1176 1177 1178 1179 1180 1181 1182 1183 1184 1185 1186 1187 1188 1189 1190 1191 1192 1193 1194 1195 1196 1197 1198 1199 1200 1201 1202 1203 1204 1205 1206 1207 1208 1209 1210 1211 1212 1213 1214

Altair Engineering

-2.3E-162.5 4.0 -2.7E-171.5 4.0 -3.0E-171.0 4.0 -7.0E-170.5 4.0 2.16E-17-1.4E-164.0 1.65E-16-0.5 4.0 3.53E-16-1.0 4.0 2.86E-16-1.5 4.0 -5.5E-17-2.0 4.0 -2.5E-16-2.5 4.0 -0.5 2.0 4.0 -0.5 2.5 4.0 -0.5 1.5 4.0 -0.5 1.0 4.0 -0.5 0.5 4.0 -0.5 -2.5E-174.0 -0.5 -0.5 4.0 -0.5 -1.0 4.0 -0.5 -1.5 4.0 -0.5 -2.0 4.0 -0.5 -2.5 4.0 -1.0 2.0 4.0 -1.0 2.5 4.0 -1.0 1.5 4.0 -1.0 1.0 4.0 -1.0 0.5 4.0 -1.0 9.63E-174.0 -1.0 -0.5 4.0 -1.0 -1.0 4.0 -1.0 -1.5 4.0 -1.0 -2.0 4.0 -1.0 -2.5 4.0 -1.5 2.0 4.0 -1.5 2.5 4.0 -1.5 1.5 4.0 -1.5 1.0 4.0 -1.5 0.5 4.0 -1.5 2.14E-164.0 -1.5 -0.5 4.0 -1.5 -1.0 4.0 -1.5 -1.5 4.0 -1.5 -2.0 4.0 -1.5 -2.5 4.0 -2.0 2.0 4.0 -2.0 2.5 4.0 -2.0 1.5 4.0 -2.0 1.0 4.0 -2.0 0.5 4.0 -2.0 1.84E-164.0 -2.0 -0.5 4.0 -2.0 -1.0 4.0 -2.0 -1.5 4.0 -2.0 -2.0 4.0 -2.0 -2.5 4.0 -2.5 2.0 4.0 -2.5 2.5 4.0 -2.5 1.5 4.0 -2.5 1.0 4.0 -2.5 0.5 4.0 -2.5 1.10E-164.0 -2.5 -0.5 4.0 -2.5 -1.0 4.0 -2.5 -1.5 4.0 -2.5 -2.0 4.0 -2.5 -2.5 4.0 2.5 2.5 5.0 2.5 2.0 5.0 2.0 2.0 5.0 2.0 2.5 5.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1481 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1215 1216 1217 1218 1219 1220 1221 1222 1223 1224 1225 1226 1227 1228 1229 1230 1231 1232 1233 1234 1235 1236 1237 1238 1239 1240 1241 1242 1243 1244 1245 1246 1247 1248 1249 1250 1251 1252 1253 1254 1255 1256 1257 1258 1259 1260 1261 1262 1263 1264 1265 1266 1267 1268 1269 1270 1271 1272 1273 1274 1275 1276 1277 1278 1279 1280 1281 1282 1283

2.5 1.5 5.0 2.0 1.5 5.0 2.5 1.0 5.0 2.0 1.0 5.0 2.5 0.5 5.0 2.0 0.5 5.0 2.5 -1.8E-165.0 2.0 -2.4E-165.0 2.5 -0.5 5.0 2.0 -0.5 5.0 2.5 -1.0 5.0 2.0 -1.0 5.0 2.5 -1.5 5.0 2.0 -1.5 5.0 2.5 -2.0 5.0 2.0 -2.0 5.0 2.5 -2.5 5.0 2.0 -2.5 5.0 1.5 2.0 5.0 1.5 2.5 5.0 1.5 1.5 5.0 1.5 1.0 5.0 1.5 0.5 5.0 1.5 -2.8E-165.0 1.5 -0.5 5.0 1.5 -1.0 5.0 1.5 -1.5 5.0 1.5 -2.0 5.0 1.5 -2.5 5.0 1.0 2.0 5.0 1.0 2.5 5.0 1.0 1.5 5.0 1.0 1.0 5.0 1.0 0.5 5.0 1.0 -3.0E-165.0 1.0 -0.5 5.0 1.0 -1.0 5.0 1.0 -1.5 5.0 1.0 -2.0 5.0 1.0 -2.5 5.0 0.5 2.0 5.0 0.5 2.5 5.0 0.5 1.5 5.0 0.5 1.0 5.0 0.5 0.5 5.0 0.5 -2.4E-165.0 0.5 -0.5 5.0 0.5 -1.0 5.0 0.5 -1.5 5.0 0.5 -2.0 5.0 0.5 -2.5 5.0 -2.4E-162.0 5.0 -2.4E-162.5 5.0 -1.4E-161.5 5.0 -1.1E-161.0 5.0 -6.8E-170.5 5.0 -2.1E-17-1.4E-165.0 1.13E-16-0.5 5.0 2.64E-16-1.0 5.0 2.07E-16-1.5 5.0 -8.9E-18-2.0 5.0 -1.0E-16-2.5 5.0 -0.5 2.0 5.0 -0.5 2.5 5.0 -0.5 1.5 5.0 -0.5 1.0 5.0 -0.5 0.5 5.0 -0.5 -2.9E-175.0 -0.5 -0.5 5.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

1482 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1284 1285 1286 1287 1288 1289 1290 1291 1292 1293 1294 1295 1296 1297 1298 1299 1300 1301 1302 1303 1304 1305 1306 1307 1308 1309 1310 1311 1312 1313 1314 1315 1316 1317 1318 1319 1320 1321 1322 1323 1324 1325 1326 1327 1328 1329 1330 1331 1332 1333 1334 1335 1336 1337 1338 1339 1340 1341 1342 1343 1344 1345 1346 1347 1348 1349 1350 1351 1352

Altair Engineering

-0.5 -0.5 -0.5 -0.5 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.0 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -1.5 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.0 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 -2.5 2.0 2.0 2.0 2.0 2.0 2.0 2.0 2.0 2.0 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.0 1.0 1.0

-1.0 5.0 -1.5 5.0 -2.0 5.0 -2.5 5.0 2.0 5.0 2.5 5.0 1.5 5.0 1.0 5.0 0.5 5.0 8.84E-175.0 -0.5 5.0 -1.0 5.0 -1.5 5.0 -2.0 5.0 -2.5 5.0 2.0 5.0 2.5 5.0 1.5 5.0 1.0 5.0 0.5 5.0 1.34E-165.0 -0.5 5.0 -1.0 5.0 -1.5 5.0 -2.0 5.0 -2.5 5.0 2.0 5.0 2.5 5.0 1.5 5.0 1.0 5.0 0.5 5.0 1.09E-165.0 -0.5 5.0 -1.0 5.0 -1.5 5.0 -2.0 5.0 -2.5 5.0 2.0 5.0 2.5 5.0 1.5 5.0 1.0 5.0 0.5 5.0 5.75E-175.0 -0.5 5.0 -1.0 5.0 -1.5 5.0 -2.0 5.0 -2.5 5.0 2.0 0.0 1.5 0.0 1.0 0.0 0.5 0.0 -2.2E-180.0 -0.5 0.0 -1.0 0.0 -1.5 0.0 -2.0 0.0 2.0 0.0 1.5 0.0 1.0 0.0 0.5 0.0 -1.9E-180.0 -0.5 0.0 -1.0 0.0 -1.5 0.0 -2.0 0.0 2.0 0.0 1.5 0.0 1.0 0.0

-1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1 -1

OptiStruct 13.0 Reference Guide 1483 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1353 1354 1355 1356 1357 1358 1359 1360 1361 1362 1363 1364 1365 1366 1367 1368 1369 1370 1371 1372 1373 1374 1375 1376 1377 1378 1379 1380 1381 1382 1383 1384 1385 1386 1387 1388 1389 1390 1391 1392 1393 1394 1395 1396 1397 1398 1399 1400 1401 1402 1403 1404 1405 1406 1407 1408 1409 1410 1411 1412 1413 1414 1415 1416 1417 1418 1419 1420 1421

1.0 0.5 0.0 1.0 -1.9E-180.0 1.0 -0.5 0.0 1.0 -1.0 0.0 1.0 -1.5 0.0 1.0 -2.0 0.0 0.5 2.0 0.0 0.5 1.5 0.0 0.5 1.0 0.0 0.5 0.5 0.0 0.5 -1.9E-180.0 0.5 -0.5 0.0 0.5 -1.0 0.0 0.5 -1.5 0.0 0.5 -2.0 0.0 -2.8E-182.0 0.0 -2.8E-181.5 0.0 -2.5E-181.0 0.0 -2.8E-180.5 0.0 -3.1E-18-1.7E-180.0 -2.8E-18-0.5 0.0 -3.1E-18-1.0 0.0 -1.9E-18-1.5 0.0 -2.8E-18-2.0 0.0 -0.5 2.0 0.0 -0.5 1.5 0.0 -0.5 1.0 0.0 -0.5 0.5 0.0 -0.5 -1.7E-180.0 -0.5 -0.5 0.0 -0.5 -1.0 0.0 -0.5 -1.5 0.0 -0.5 -2.0 0.0 -1.0 2.0 0.0 -1.0 1.5 0.0 -1.0 1.0 0.0 -1.0 0.5 0.0 -1.0 -1.9E-180.0 -1.0 -0.5 0.0 -1.0 -1.0 0.0 -1.0 -1.5 0.0 -1.0 -2.0 0.0 -1.5 2.0 0.0 -1.5 1.5 0.0 -1.5 1.0 0.0 -1.5 0.5 0.0 -1.5 -1.7E-180.0 -1.5 -0.5 0.0 -1.5 -1.0 0.0 -1.5 -1.5 0.0 -1.5 -2.0 0.0 -2.0 2.0 0.0 -2.0 1.5 0.0 -2.0 1.0 0.0 -2.0 0.5 0.0 -2.0 -2.2E-180.0 -2.0 -0.5 0.0 -2.0 -1.0 0.0 -2.0 -1.5 0.0 -2.0 -2.0 0.0 2.4964642.0 0.004472 2.4964641.5 0.004472 2.4964641.0 0.004472 2.4964640.5 0.004472 2.496464-2.6E-180.004472 2.496464-0.5 0.004472 2.496464-1.0 0.004472 2.496464-1.5 0.004472 2.496464-2.0 0.004472

1484 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1422 1423 1424 1425 1426 1427 1428 1429 1430 1431 1432 1433 1434 1435 1436 1437 1438 1439 1440 1441 1442 1443 1444 1445 1446 1447 1448 1449 1450 1451 1452 1453 1454 1455 1456 1457 1458 1459 1460 1461 1462 1463 1464 1465 1466 1467 1468 1469 1470 1471 1472 1473 1474 1475 1476 1477 1478 1479 1480 1481 1482 1483 1484 1485 1486 1487 1488 1489 1493

Altair Engineering

-2.496462.0 0.004472 -2.496461.5 0.004472 -2.496461.0 0.004472 -2.496460.5 0.004472 -2.49646-2.6E-180.004472 -2.49646-0.5 0.004472 -2.49646-1.0 0.004472 -2.49646-1.5 0.004472 -2.49646-2.0 0.004472 2.4961522.4961520.005963 2.496152-2.496150.005963 2.0 2.4964640.004472 2.0 -2.496460.004472 1.5 2.4964640.004472 1.5 -2.496460.004472 1.0 2.4964640.004472 1.0 -2.496460.004472 0.5 2.4964640.004472 0.5 -2.496460.004472 -2.6E-182.4964640.004472 -2.6E-18-2.496460.004472 -0.5 2.4964640.004472 -0.5 -2.496460.004472 -1.0 2.4964640.004472 -1.0 -2.496460.004472 -1.5 2.4964640.004472 -1.5 -2.496460.004472 -2.0 2.4964640.004472 -2.0 -2.496460.004472 -2.496152.4961520.005963 -2.49615-2.496150.005963 -2.49615-2.496154.994037 -2.49646-2.0 4.995528 -2.49646-1.5 4.995528 -2.49646-1.0 4.995528 -2.49646-0.5 4.995528 -2.496465.58E-174.995528 -2.496460.5 4.995528 -2.496461.0 4.995528 -2.496461.5 4.995528 -2.496152.4961524.994037 -2.496462.0 4.995528 -2.0 -2.496464.995528 -2.0 -2.0 5.0 -2.0 -1.5 5.0 -2.0 -1.0 5.0 -2.0 -0.5 5.0 -2.0 1.05E-165.0 -2.0 0.5 5.0 -2.0 1.0 5.0 -2.0 1.5 5.0 -2.0 2.4964644.995528 -2.0 2.0 5.0 -1.5 -2.496464.995528 -1.5 -2.0 5.0 -1.5 -1.5 5.0 -1.5 -1.0 5.0 -1.5 -0.5 5.0 -1.5 1.32E-165.0 -1.5 0.5 5.0 -1.5 1.0 5.0 -1.5 1.5 5.0 -1.5 2.4964644.995528 -1.5 2.0 5.0 -1.0 -2.496464.995528 -1.0 -2.0 5.0 -1.0 -1.5 5.0 -1.0 -1.0 5.0 -1.0 1.0 5.0

OptiStruct 13.0 Reference Guide 1485 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1494 1495 1496 1497 1498 1499 1500 1504 1505 1506 1507 1508 1509 1510 1511 1515 1516 1517 1518 1519 1520 1521 1522 1526 1527 1528 1529 1530 1531 1532 1533 1534 1535 1536 1537 1538 1539 1540 1541 1542 1543 1544 1545 1546 1547 1548 1549 1550 1551 1552 1553 1554 1555 1556 1557 1558 1559 1560 1561 1562 1563 1564 1565 1566 1567 1568 1569 1570 1571

-1.0 1.5 5.0 -1.0 2.4964644.995528 -1.0 2.0 5.0 -0.5 -2.496464.995528 -0.5 -2.0 5.0 -0.5 -1.5 5.0 -0.5 -1.0 5.0 -0.5 1.0 5.0 -0.5 1.5 5.0 -0.5 2.4964644.995528 -0.5 2.0 5.0 -1.0E-16-2.496464.995528 -1.1E-17-2.0 5.0 2.04E-16-1.5 5.0 2.61E-16-1.0 5.0 -1.2E-161.0 5.0 -1.4E-161.5 5.0 -2.4E-162.4964644.995528 -2.4E-162.0 5.0 0.5 -2.496464.995528 0.5 -2.0 5.0 0.5 -1.5 5.0 0.5 -1.0 5.0 0.5 1.0 5.0 0.5 1.5 5.0 0.5 2.4964644.995528 0.5 2.0 5.0 1.0 -2.496464.995528 1.0 -2.0 5.0 1.0 -1.5 5.0 1.0 -1.0 5.0 1.0 -0.5 5.0 1.0 -3.0E-165.0 1.0 0.5 5.0 1.0 1.0 5.0 1.0 1.5 5.0 1.0 2.4964644.995528 1.0 2.0 5.0 1.5 -2.496464.995528 1.5 -2.0 5.0 1.5 -1.5 5.0 1.5 -1.0 5.0 1.5 -0.5 5.0 1.5 -2.8E-165.0 1.5 0.5 5.0 1.5 1.0 5.0 1.5 1.5 5.0 1.5 2.4964644.995528 1.5 2.0 5.0 2.0 -2.496464.995528 2.496152-2.496154.994037 2.0 -2.0 5.0 2.496464-2.0 4.995528 2.0 -1.5 5.0 2.496464-1.5 4.995528 2.0 -1.0 5.0 2.496464-1.0 4.995528 2.0 -0.5 5.0 2.496464-0.5 4.995528 2.0 -2.4E-165.0 2.496464-1.8E-164.995528 2.0 0.5 5.0 2.4964640.5 4.995528 2.0 1.0 5.0 2.4964641.0 4.995528 2.0 1.5 5.0 2.4964641.5 4.995528 2.0 2.4964644.995528 2.0 2.0 5.0

1486 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1572 1573 1574 1575 1576 1577 1578 1579 1580 1581 1582 1583 1584 1585 1586 1587 1588 1589 1590 1591 1592 1593 1594 1595 1596 1597 1598 1599 1600 1601 1602 1603 1604 1605 1606 1607 1608 1609 1610 1611 1612 1613 1614 1615 1616 1617 1618 1619 1620 1621 1622 1623 1624 1625 1626 1627 1628 1629 1630 1631 1632 1633 1634 1635 1636 1637 1638 1639 1640

Altair Engineering

2.4964642.0 4.995528 2.4961522.4961524.994037 -2.49776-2.497764.0 -2.5 -2.0 4.0 -2.5 -1.5 4.0 -2.5 -1.0 4.0 -2.5 -0.5 4.0 -2.5 1.07E-164.0 -2.5 0.5 4.0 -2.5 1.0 4.0 -2.5 1.5 4.0 -2.497762.4977644.0 -2.5 2.0 4.0 -2.0 -2.5 4.0 -2.0 2.5 4.0 -1.5 -2.5 4.0 -1.5 2.5 4.0 -1.0 -2.5 4.0 -1.0 2.5 4.0 -0.5 -2.5 4.0 -0.5 2.5 4.0 -2.5E-16-2.5 4.0 -2.3E-162.5 4.0 0.5 -2.5 4.0 0.5 2.5 4.0 1.0 -2.5 4.0 1.0 2.5 4.0 1.5 -2.5 4.0 1.5 2.5 4.0 2.0 -2.5 4.0 2.497764-2.497764.0 2.5 -2.0 4.0 2.5 -1.5 4.0 2.5 -1.0 4.0 2.5 -0.5 4.0 2.5 -1.0E-164.0 2.5 0.5 4.0 2.5 1.0 4.0 2.5 1.5 4.0 2.0 2.5 4.0 2.5 2.0 4.0 2.4977642.4977644.0 -2.49776-2.497763.0 -2.5 -2.0 3.0 -2.5 -1.5 3.0 -2.5 -1.0 3.0 -2.5 -0.5 3.0 -2.5 -5.4E-183.0 -2.5 0.5 3.0 -2.5 1.0 3.0 -2.5 1.5 3.0 -2.497762.4977643.0 -2.5 2.0 3.0 -2.0 -2.5 3.0 -2.0 2.5 3.0 -1.5 -2.5 3.0 -1.5 2.5 3.0 -1.0 -2.5 3.0 -1.0 2.5 3.0 -0.5 -2.5 3.0 -0.5 2.5 3.0 -2.9E-18-2.5 3.0 -3.1E-182.5 3.0 0.5 -2.5 3.0 0.5 2.5 3.0 1.0 -2.5 3.0 1.0 2.5 3.0 1.5 -2.5 3.0 1.5 2.5 3.0

OptiStruct 13.0 Reference Guide 1487 Proprietary Information of Altair Engineering

GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID

1641 1642 1643 1644 1645 1646 1647 1648 1649 1650 1651 1652 1653 1654 1655 1656 1657 1658 1659 1660 1661 1662 1663 1664 1665 1666 1667 1668 1669 1670 1671 1672 1673 1674 1675 1676 1677 1678 1679 1680 1681 1682 1683 1684 1685 1686 1687 1688 1689 1690 1691 1692 1693 1694 1695 1696 1697 1698 1699 1700 1701 1702 1703 1704 1705 1706 1707 1708 1709

2.0 -2.5 3.0 2.497764-2.497763.0 2.5 -2.0 3.0 2.5 -1.5 3.0 2.5 -1.0 3.0 2.5 -0.5 3.0 2.5 -3.4E-183.0 2.5 0.5 3.0 2.5 1.0 3.0 2.5 1.5 3.0 2.0 2.5 3.0 2.5 2.0 3.0 2.4977642.4977643.0 -2.49776-2.497762.0 -2.5 -2.0 2.0 -2.5 -1.5 2.0 -2.5 -1.0 2.0 -2.5 -0.5 2.0 -2.5 -5.0E-182.0 -2.5 0.5 2.0 -2.5 1.0 2.0 -2.5 1.5 2.0 -2.497762.4977642.0 -2.5 2.0 2.0 -2.0 -2.5 2.0 -2.0 2.5 2.0 -1.5 -2.5 2.0 -1.5 2.5 2.0 -1.0 -2.5 2.0 -1.0 2.5 2.0 -0.5 -2.5 2.0 -0.5 2.5 2.0 -2.5E-18-2.5 2.0 -2.5E-182.5 2.0 0.5 -2.5 2.0 0.5 2.5 2.0 1.0 -2.5 2.0 1.0 2.5 2.0 1.5 -2.5 2.0 1.5 2.5 2.0 2.0 -2.5 2.0 2.497764-2.497762.0 2.5 -2.0 2.0 2.5 -1.5 2.0 2.5 -1.0 2.0 2.5 -0.5 2.0 2.5 -3.1E-182.0 2.5 0.5 2.0 2.5 1.0 2.0 2.5 1.5 2.0 2.0 2.5 2.0 2.5 2.0 2.0 2.4977642.4977642.0 -2.49776-2.497761.0 -2.5 -2.0 1.0 -2.5 -1.5 1.0 -2.5 -1.0 1.0 -2.5 -0.5 1.0 -2.5 -3.5E-181.0 -2.5 0.5 1.0 -2.5 1.0 1.0 -2.5 1.5 1.0 -2.497762.4977641.0 -2.5 2.0 1.0 -2.0 -2.5 1.0 -2.0 2.5 1.0 -1.5 -2.5 1.0 -1.5 2.5 1.0 -1.0 -2.5 1.0

1488 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

GRID 1710 -1.0 2.5 1.0 GRID 1711 -0.5 -2.5 1.0 GRID 1712 -0.5 2.5 1.0 GRID 1713 -2.5E-18-2.5 1.0 GRID 1714 -2.5E-182.5 1.0 GRID 1715 0.5 -2.5 1.0 GRID 1716 0.5 2.5 1.0 GRID 1717 1.0 -2.5 1.0 GRID 1718 1.0 2.5 1.0 GRID 1719 1.5 -2.5 1.0 GRID 1720 1.5 2.5 1.0 GRID 1721 2.0 -2.5 1.0 GRID 1722 2.497764-2.497761.0 GRID 1723 2.5 -2.0 1.0 GRID 1724 2.5 -1.5 1.0 GRID 1725 2.5 -1.0 1.0 GRID 1726 2.5 -0.5 1.0 GRID 1727 2.5 -2.9E-181.0 GRID 1728 2.5 0.5 1.0 GRID 1729 2.5 1.0 1.0 GRID 1730 2.5 1.5 1.0 GRID 1731 2.0 2.5 1.0 GRID 1732 2.5 2.0 1.0 GRID 1733 2.4977642.4977641.0 GRID 1734 -0.25 3.33E-165.0 $$ $$ SPOINT Data $$ $$ $$------------------------------------------------------------------------------$ $$ Group Definitions $ $$------------------------------------------------------------------------------$ $$ $$ RBE2 Elements - Multiple dependent nodes $$ RBE2 1553 1734 123456 1478 1479 1480 1481 1482+ + 1489 1493 1500 1504 1511 1515 1522 1526+ + 1533 1534 1535 1536 1537 $ $HMMOVE 6 $ 1553 $ $ CQUAD4 Elements $ CQUAD4 1101 4 1332 1341 1342 1333 CQUAD4 1102 4 1333 1342 1343 1334 CQUAD4 1103 4 1334 1343 1344 1335 CQUAD4 1104 4 1335 1344 1345 1336 CQUAD4 1105 4 1336 1345 1346 1337 CQUAD4 1106 4 1337 1346 1347 1338 CQUAD4 1107 4 1338 1347 1348 1339 CQUAD4 1108 4 1339 1348 1349 1340 CQUAD4 1109 4 1341 1350 1351 1342 CQUAD4 1110 4 1342 1351 1352 1343 CQUAD4 1111 4 1343 1352 1353 1344 CQUAD4 1112 4 1344 1353 1354 1345 CQUAD4 1113 4 1345 1354 1355 1346 CQUAD4 1114 4 1346 1355 1356 1347 CQUAD4 1115 4 1347 1356 1357 1348 CQUAD4 1116 4 1348 1357 1358 1349 CQUAD4 1117 4 1350 1359 1360 1351 CQUAD4 1118 4 1351 1360 1361 1352 CQUAD4 1119 4 1352 1361 1362 1353 CQUAD4 1120 4 1353 1362 1363 1354 CQUAD4 1121 4 1354 1363 1364 1355 CQUAD4 1122 4 1355 1364 1365 1356 CQUAD4 1123 4 1356 1365 1366 1357 CQUAD4 1124 4 1357 1366 1367 1358 CQUAD4 1125 4 1359 1368 1369 1360

Altair Engineering

OptiStruct 13.0 Reference Guide 1489 Proprietary Information of Altair Engineering

CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4

1126 1127 1128 1129 1130 1131 1132 1133 1134 1135 1136 1137 1138 1139 1140 1141 1142 1143 1144 1145 1146 1147 1148 1149 1150 1151 1152 1153 1154 1155 1156 1157 1158 1159 1160 1161 1162 1163 1164 1165 1166 1167 1168 1169 1170 1171 1172 1173 1174 1175 1176 1177 1178 1179 1180 1181 1182 1183 1184 1185 1186 1187 1188 1189 1190 1191 1192 1193 1194

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

1360 1361 1362 1363 1364 1365 1366 1368 1369 1370 1371 1372 1373 1374 1375 1377 1378 1379 1380 1381 1382 1383 1384 1386 1387 1388 1389 1390 1391 1392 1393 1395 1396 1397 1398 1399 1400 1401 1402 1413 1414 1415 1416 1417 1418 1419 1420 1404 1405 1406 1407 1408 1409 1410 1411 1431 1433 1421 1340 1435 1349 1437 1358 1439 1367 1441 1376 1443 1385

1369 1370 1371 1372 1373 1374 1375 1377 1378 1379 1380 1381 1382 1383 1384 1386 1387 1388 1389 1390 1391 1392 1393 1395 1396 1397 1398 1399 1400 1401 1402 1404 1405 1406 1407 1408 1409 1410 1411 1332 1333 1334 1335 1336 1337 1338 1339 1422 1423 1424 1425 1426 1427 1428 1429 1433 1435 1340 1349 1437 1358 1439 1367 1441 1376 1443 1385 1445 1394

1370 1371 1372 1373 1374 1375 1376 1378 1379 1380 1381 1382 1383 1384 1385 1387 1388 1389 1390 1391 1392 1393 1394 1396 1397 1398 1399 1400 1401 1402 1403 1405 1406 1407 1408 1409 1410 1411 1412 1333 1334 1335 1336 1337 1338 1339 1340 1423 1424 1425 1426 1427 1428 1429 1430 1332 1341 1434 1436 1350 1438 1359 1440 1368 1442 1377 1444 1386 1446

1361 1362 1363 1364 1365 1366 1367 1369 1370 1371 1372 1373 1374 1375 1376 1378 1379 1380 1381 1382 1383 1384 1385 1387 1388 1389 1390 1391 1392 1393 1394 1396 1397 1398 1399 1400 1401 1402 1403 1414 1415 1416 1417 1418 1419 1420 1421 1405 1406 1407 1408 1409 1410 1411 1412 1413 1332 1432 1434 1341 1436 1350 1438 1359 1440 1368 1442 1377 1444

1490 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4

1195 1196 1197 1198 1199 1200 1201 1202 1203 1204 1205 1206 1207 1208 1209 1210 1211 1212 1213 1214 1215 1216 1217 1218 1219 1220 1221 1222 1223 1224 1225 1226 1227 1228 1229 1230 1231 1232 1233 1234 1235 1236 1237 1238 1239 1240 1241 1242 1243 1244 1245 1246 1247 1248 1249 1250 1251 1252 1253 1254 1255 1256 1257 1258 1259 1260 1261 1262 1263

Altair Engineering

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

1445 1394 1447 1403 1449 1412 1431 1413 1414 1433 1415 1416 1417 1418 1419 1420 1421 1432 1434 1436 1435 1438 1437 1440 1439 1442 1441 1444 1443 1446 1445 1448 1447 1450 1449 1452 1451 1422 1423 1424 1425 1426 1427 1428 1429 1430 1732 1733 1730 1731 1729 1728 1727 1726 1725 1724 1723 1722 1721 1719 1720 1717 1718 1715 1716 1713 1714 1711 1712

1447 1403 1449 1412 1451 1430 1733 1732 1730 1731 1729 1728 1727 1726 1725 1724 1723 1722 1721 1719 1720 1717 1718 1715 1716 1713 1714 1711 1712 1709 1710 1707 1708 1705 1706 1694 1703 1704 1702 1701 1700 1699 1698 1697 1696 1695 1692 1693 1690 1691 1689 1688 1687 1686 1685 1684 1683 1682 1681 1679 1680 1677 1678 1675 1676 1673 1674 1671 1672

1395 1448 1404 1450 1422 1452 1731 1733 1732 1720 1730 1729 1728 1727 1726 1725 1724 1723 1722 1721 1718 1719 1716 1717 1714 1715 1712 1713 1710 1711 1708 1709 1706 1707 1703 1705 1704 1702 1701 1700 1699 1698 1697 1696 1695 1694 1693 1691 1692 1680 1690 1689 1688 1687 1686 1685 1684 1683 1682 1681 1678 1679 1676 1677 1674 1675 1672 1673 1670

1386 1446 1395 1448 1404 1450 1433 1431 1413 1435 1414 1415 1416 1417 1418 1419 1420 1421 1432 1434 1437 1436 1439 1438 1441 1440 1443 1442 1445 1444 1447 1446 1449 1448 1451 1450 1422 1423 1424 1425 1426 1427 1428 1429 1430 1452 1733 1731 1732 1720 1730 1729 1728 1727 1726 1725 1724 1723 1722 1721 1718 1719 1716 1717 1714 1715 1712 1713 1710

OptiStruct 13.0 Reference Guide 1491 Proprietary Information of Altair Engineering

CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4

1264 1265 1266 1267 1268 1269 1270 1271 1272 1273 1274 1275 1276 1277 1278 1279 1280 1281 1282 1283 1284 1285 1286 1287 1288 1289 1290 1291 1292 1293 1294 1295 1296 1297 1298 1299 1300 1301 1302 1303 1304 1305 1306 1307 1308 1309 1310 1311 1312 1313 1314 1315 1316 1317 1318 1319 1320 1321 1322 1323 1324 1325 1326 1327 1328 1329 1330 1331 1332

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

1709 1710 1707 1708 1705 1706 1694 1703 1704 1702 1701 1700 1699 1698 1697 1696 1695 1692 1693 1690 1691 1689 1688 1687 1686 1685 1684 1683 1682 1681 1679 1680 1677 1678 1675 1676 1673 1674 1671 1672 1669 1670 1667 1668 1665 1666 1654 1663 1664 1662 1661 1660 1659 1658 1657 1656 1655 1652 1653 1650 1651 1649 1648 1647 1646 1645 1644 1643 1642

1669 1670 1667 1668 1665 1666 1654 1663 1664 1662 1661 1660 1659 1658 1657 1656 1655 1652 1653 1650 1651 1649 1648 1647 1646 1645 1644 1643 1642 1641 1639 1640 1637 1638 1635 1636 1633 1634 1631 1632 1629 1630 1627 1628 1625 1626 1614 1623 1624 1622 1621 1620 1619 1618 1617 1616 1615 1612 1613 1610 1611 1609 1608 1607 1606 1605 1604 1603 1602

1671 1668 1669 1666 1667 1663 1665 1664 1662 1661 1660 1659 1658 1657 1656 1655 1654 1653 1651 1652 1640 1650 1649 1648 1647 1646 1645 1644 1643 1642 1641 1638 1639 1636 1637 1634 1635 1632 1633 1630 1631 1628 1629 1626 1627 1623 1625 1624 1622 1621 1620 1619 1618 1617 1616 1615 1614 1613 1611 1612 1600 1610 1609 1608 1607 1606 1605 1604 1603

1711 1708 1709 1706 1707 1703 1705 1704 1702 1701 1700 1699 1698 1697 1696 1695 1694 1693 1691 1692 1680 1690 1689 1688 1687 1686 1685 1684 1683 1682 1681 1678 1679 1676 1677 1674 1675 1672 1673 1670 1671 1668 1669 1666 1667 1663 1665 1664 1662 1661 1660 1659 1658 1657 1656 1655 1654 1653 1651 1652 1640 1650 1649 1648 1647 1646 1645 1644 1643

1492 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4

1333 1334 1335 1336 1337 1338 1339 1340 1341 1342 1343 1344 1345 1346 1347 1348 1349 1350 1351 1352 1353 1354 1355 1356 1357 1358 1359 1360 1361 1362 1363 1364 1365 1366 1367 1368 1369 1370 1371 1372 1373 1374 1375 1376 1377 1378 1379 1380 1381 1382 1383 1384 1385 1386 1387 1388 1389 1390 1391 1392 1393 1394 1395 1396 1397 1398 1399 1400 1401

Altair Engineering

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

1641 1639 1640 1637 1638 1635 1636 1633 1634 1631 1632 1629 1630 1627 1628 1625 1626 1614 1623 1624 1622 1621 1620 1619 1618 1617 1616 1615 1612 1613 1610 1572 1611 1569 1609 1567 1608 1565 1607 1563 1606 1561 1605 1559 1604 1557 1603 1555 1602 1601 1553 1599 1571 1568 1600 1566 1564 1562 1560 1558 1556 1554 1552 1597 1551 1549 1598 1548 1547

1601 1599 1600 1597 1598 1595 1596 1593 1594 1591 1592 1589 1590 1587 1588 1585 1586 1574 1583 1584 1582 1581 1580 1579 1578 1577 1576 1575 1572 1573 1569 1571 1570 1568 1567 1566 1565 1564 1563 1562 1561 1560 1559 1558 1557 1556 1555 1554 1553 1552 1552 1541 1551 1549 1550 1548 1547 1546 1545 1544 1543 1542 1541 1530 1540 1538 1539 1537 1536

1602 1601 1598 1599 1596 1597 1594 1595 1592 1593 1590 1591 1588 1589 1586 1587 1583 1585 1584 1582 1581 1580 1579 1578 1577 1576 1575 1574 1573 1570 1572 1570 1550 1571 1569 1568 1567 1566 1565 1564 1563 1562 1561 1560 1559 1558 1557 1556 1555 1553 1554 1552 1550 1551 1539 1549 1548 1547 1546 1545 1544 1543 1542 1541 1539 1540 1528 1538 1537

1642 1641 1638 1639 1636 1637 1634 1635 1632 1633 1630 1631 1628 1629 1626 1627 1623 1625 1624 1622 1621 1620 1619 1618 1617 1616 1615 1614 1613 1611 1612 1573 1600 1572 1610 1569 1609 1567 1608 1565 1607 1563 1606 1561 1605 1559 1604 1557 1603 1602 1555 1601 1570 1571 1598 1568 1566 1564 1562 1560 1558 1556 1554 1599 1550 1551 1596 1549 1548

OptiStruct 13.0 Reference Guide 1493 Proprietary Information of Altair Engineering

CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4

1402 1403 1404 1405 1406 1407 1408 1409 1410 1411 1412 1417 1418 1419 1420 1421 1422 1423 1424 1429 1430 1431 1432 1433 1434 1435 1436 1441 1442 1443 1444 1445 1446 1447 1448 1453 1454 1455 1456 1457 1458 1459 1460 1465 1466 1467 1468 1469 1470 1471 1472 1473 1474 1475 1476 1477 1478 1479 1480 1481 1482 1483 1484 1485 1486 1487 1488 1489 1490

4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

1546 1545 1544 1543 1542 1541 1595 1540 1538 1596 1537 1532 1531 1530 1593 1529 1527 1594 1526 1521 1520 1519 1591 1518 1516 1592 1515 1510 1509 1508 1589 1507 1505 1590 1504 1499 1498 1497 1587 1496 1494 1588 1493 1488 1487 1486 1585 1485 1483 1586 1482 1481 1480 1479 1478 1477 1476 1475 1574 1583 1474 1584 1472 1582 1471 1581 1470 1580 1469

1535 1534 1533 1532 1531 1530 1519 1529 1527 1528 1526 1521 1520 1519 1508 1518 1516 1517 1515 1510 1509 1508 1497 1507 1505 1506 1504 1499 1498 1497 1486 1496 1494 1495 1493 1488 1487 1486 1475 1485 1483 1484 1482 1477 1476 1475 1464 1474 1472 1473 1471 1470 1469 1468 1467 1466 1465 1464 1453 1462 1463 1463 1461 1461 1460 1460 1459 1459 1458

1536 1535 1534 1533 1532 1531 1530 1528 1529 1517 1527 1522 1521 1520 1519 1517 1518 1506 1516 1511 1510 1509 1508 1506 1507 1495 1505 1500 1499 1498 1497 1495 1496 1484 1494 1489 1488 1487 1486 1484 1485 1473 1483 1478 1477 1476 1475 1473 1474 1462 1472 1471 1470 1469 1468 1467 1466 1465 1464 1463 1462 1461 1463 1460 1461 1459 1460 1458 1459

1547 1546 1545 1544 1543 1542 1597 1539 1540 1594 1538 1533 1532 1531 1595 1528 1529 1592 1527 1522 1521 1520 1593 1517 1518 1590 1516 1511 1510 1509 1591 1506 1507 1588 1505 1500 1499 1498 1589 1495 1496 1586 1494 1489 1488 1487 1587 1484 1485 1583 1483 1482 1481 1480 1479 1478 1477 1476 1585 1584 1473 1582 1474 1581 1472 1580 1471 1579 1470

1494 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CQUAD4 1491 4 1579 CQUAD4 1492 4 1468 CQUAD4 1493 4 1578 CQUAD4 1494 4 1467 CQUAD4 1495 4 1577 CQUAD4 1496 4 1466 CQUAD4 1497 4 1576 CQUAD4 1498 4 1465 CQUAD4 1499 4 1575 CQUAD4 1500 4 1464 $ $ CHEXA Elements: First Order $ CHEXA 601 1 100 + 729 728 CHEXA 602 1 82 + 732 731 CHEXA 603 1 83 + 734 733 CHEXA 604 1 84 + 736 735 CHEXA 605 1 85 + 738 737 CHEXA 606 1 86 + 740 739 CHEXA 607 1 87 + 742 741 CHEXA 608 1 88 + 744 743 CHEXA 609 1 89 + 746 745 CHEXA 610 1 90 + 748 747 CHEXA 611 1 102 + 749 729 CHEXA 612 1 1 + 751 732 CHEXA 613 1 2 + 752 734 CHEXA 614 1 3 + 753 736 CHEXA 615 1 4 + 754 738 CHEXA 616 1 5 + 755 740 CHEXA 617 1 6 + 756 742 CHEXA 618 1 7 + 757 744 CHEXA 619 1 8 + 758 746 CHEXA 620 1 9 + 759 748 CHEXA 621 1 104 + 760 749 CHEXA 622 1 10 + 762 751 CHEXA 623 1 11 + 763 752 CHEXA 624 1 12 + 764 753 CHEXA 625 1 13 + 765 754 CHEXA 626 1 14 + 766 755 CHEXA 627 1 15 + 767 756 CHEXA 628 1 16 + 768 757

Altair Engineering

1458 1457 1457 1456 1456 1455 1455 1454 1454 1453

1457 1458 1456 1457 1455 1456 1454 1455 1453 1454

1578 1469 1577 1468 1576 1467 1575 1466 1574 1465

102

1

82

727

730+

1

2

83

728

729+

2

3

84

731

732+

3

4

85

733

734+

4

5

86

735

736+

5

6

87

737

738+

6

7

88

739

740+

7

8

89

741

742+

8

9

90

743

744+

9

103

101

745

746+

104

10

1

730

750+

10

11

2

729

749+

11

12

3

732

751+

12

13

4

734

752+

13

14

5

736

753+

14

15

6

738

754+

15

16

7

740

755+

16

17

8

742

756+

17

18

9

744

757+

18

105

103

746

758+

106

19

10

750

761+

19

20

11

749

760+

20

21

12

751

762+

21

22

13

752

763+

22

23

14

753

764+

23

24

15

754

765+

24

25

16

755

766+

25

26

17

756

767+

OptiStruct 13.0 Reference Guide 1495 Proprietary Information of Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

629 769 630 770 631 771 632 773 633 774 634 775 635 776 636 777 637 778 638 779 639 780 640 781 641 782 642 784 643 785 644 786 645 787 646 788 647 789 648 790 649 791 650 792 651 793 652 795 653 796 654 797 655 798 656 799 657 800 658 801 659 802 660 803 661 804 662 806 663

1 758 1 759 1 760 1 762 1 763 1 764 1 765 1 766 1 767 1 768 1 769 1 770 1 771 1 773 1 774 1 775 1 776 1 777 1 778 1 779 1 780 1 781 1 782 1 784 1 785 1 786 1 787 1 788 1 789 1 790 1 791 1 792 1 793 1 795 1

17

26

27

18

757

768+

18

27

107

105

758

769+

106

108

28

19

761

772+

19

28

29

20

760

771+

20

29

30

21

762

773+

21

30

31

22

763

774+

22

31

32

23

764

775+

23

32

33

24

765

776+

24

33

34

25

766

777+

25

34

35

26

767

778+

26

35

36

27

768

779+

27

36

109

107

769

780+

108

110

37

28

772

783+

28

37

38

29

771

782+

29

38

39

30

773

784+

30

39

40

31

774

785+

31

40

41

32

775

786+

32

41

42

33

776

787+

33

42

43

34

777

788+

34

43

44

35

778

789+

35

44

45

36

779

790+

36

45

111

109

780

791+

110

112

46

37

783

794+

37

46

47

38

782

793+

38

47

48

39

784

795+

39

48

49

40

785

796+

40

49

50

41

786

797+

41

50

51

42

787

798+

42

51

52

43

788

799+

43

52

53

44

789

800+

44

53

54

45

790

801+

45

54

113

111

791

802+

112

114

55

46

794

805+

46

55

56

47

793

804+

47

56

57

48

795

806+

1496 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

807 664 808 665 809 666 810 667 811 668 812 669 813 670 814 671 815 672 817 673 818 674 819 675 820 676 821 677 822 678 823 679 824 680 825 681 826 682 828 683 829 684 830 685 831 686 832 687 833 688 834 689 835 690 836 691 837 692 839 693 840 694 841 695 842 696 843 697 844

Altair Engineering

796 1 797 1 798 1 799 1 800 1 801 1 802 1 803 1 804 1 806 1 807 1 808 1 809 1 810 1 811 1 812 1 813 1 814 1 815 1 817 1 818 1 819 1 820 1 821 1 822 1 823 1 824 1 825 1 826 1 828 1 829 1 830 1 831 1 832 1 833

48

57

58

49

796

807+

49

58

59

50

797

808+

50

59

60

51

798

809+

51

60

61

52

799

810+

52

61

62

53

800

811+

53

62

63

54

801

812+

54

63

115

113

802

813+

114

116

64

55

805

816+

55

64

65

56

804

815+

56

65

66

57

806

817+

57

66

67

58

807

818+

58

67

68

59

808

819+

59

68

69

60

809

820+

60

69

70

61

810

821+

61

70

71

62

811

822+

62

71

72

63

812

823+

63

72

117

115

813

824+

116

118

73

64

816

827+

64

73

74

65

815

826+

65

74

75

66

817

828+

66

75

76

67

818

829+

67

76

77

68

819

830+

68

77

78

69

820

831+

69

78

79

70

821

832+

70

79

80

71

822

833+

71

80

81

72

823

834+

72

81

119

117

824

835+

118

120

91

73

827

838+

73

91

92

74

826

837+

74

92

93

75

828

839+

75

93

94

76

829

840+

76

94

95

77

830

841+

77

95

96

78

831

842+

78

96

97

79

832

843+

OptiStruct 13.0 Reference Guide 1497 Proprietary Information of Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

698 845 699 846 700 847 701 850 702 853 703 855 704 857 705 859 706 861 707 863 708 865 709 867 710 869 711 870 712 872 713 873 714 874 715 875 716 876 717 877 718 878 719 879 720 880 721 881 722 883 723 884 724 885 725 886 726 887 727 888 728 889 729 890 730 891 731 892 732

1 834 1 835 1 836 1 849 1 852 1 854 1 856 1 858 1 860 1 862 1 864 1 866 1 868 1 850 1 853 1 855 1 857 1 859 1 861 1 863 1 865 1 867 1 869 1 870 1 872 1 873 1 874 1 875 1 876 1 877 1 878 1 879 1 880 1 881 1

79

97

98

80

833

844+

80

98

99

81

834

845+

81

99

121

119

835

846+

727

730

729

728

848

851+

728

729

732

731

849

850+

731

732

734

733

852

853+

733

734

736

735

854

855+

735

736

738

737

856

857+

737

738

740

739

858

859+

739

740

742

741

860

861+

741

742

744

743

862

863+

743

744

746

745

864

865+

745

746

748

747

866

867+

730

750

749

729

851

871+

729

749

751

732

850

870+

732

751

752

734

853

872+

734

752

753

736

855

873+

736

753

754

738

857

874+

738

754

755

740

859

875+

740

755

756

742

861

876+

742

756

757

744

863

877+

744

757

758

746

865

878+

746

758

759

748

867

879+

750

761

760

749

871

882+

749

760

762

751

870

881+

751

762

763

752

872

883+

752

763

764

753

873

884+

753

764

765

754

874

885+

754

765

766

755

875

886+

755

766

767

756

876

887+

756

767

768

757

877

888+

757

768

769

758

878

889+

758

769

770

759

879

890+

761

772

771

760

882

893+

760

771

773

762

881

892+

1498 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

894 733 895 734 896 735 897 736 898 737 899 738 900 739 901 740 902 741 903 742 905 743 906 744 907 745 908 746 909 747 910 748 911 749 912 750 913 751 914 752 916 753 917 754 918 755 919 756 920 757 921 758 922 759 923 760 924 761 925 762 927 763 928 764 929 765 930 766 931

Altair Engineering

883 1 884 1 885 1 886 1 887 1 888 1 889 1 890 1 891 1 892 1 894 1 895 1 896 1 897 1 898 1 899 1 900 1 901 1 902 1 903 1 905 1 906 1 907 1 908 1 909 1 910 1 911 1 912 1 913 1 914 1 916 1 917 1 918 1 919 1 920

762

773

774

763

883

894+

763

774

775

764

884

895+

764

775

776

765

885

896+

765

776

777

766

886

897+

766

777

778

767

887

898+

767

778

779

768

888

899+

768

779

780

769

889

900+

769

780

781

770

890

901+

772

783

782

771

893

904+

771

782

784

773

892

903+

773

784

785

774

894

905+

774

785

786

775

895

906+

775

786

787

776

896

907+

776

787

788

777

897

908+

777

788

789

778

898

909+

778

789

790

779

899

910+

779

790

791

780

900

911+

780

791

792

781

901

912+

783

794

793

782

904

915+

782

793

795

784

903

914+

784

795

796

785

905

916+

785

796

797

786

906

917+

786

797

798

787

907

918+

787

798

799

788

908

919+

788

799

800

789

909

920+

789

800

801

790

910

921+

790

801

802

791

911

922+

791

802

803

792

912

923+

794

805

804

793

915

926+

793

804

806

795

914

925+

795

806

807

796

916

927+

796

807

808

797

917

928+

797

808

809

798

918

929+

798

809

810

799

919

930+

OptiStruct 13.0 Reference Guide 1499 Proprietary Information of Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

767 932 768 933 769 934 770 935 771 936 772 938 773 939 774 940 775 941 776 942 777 943 778 944 779 945 780 946 781 947 782 949 783 950 784 951 785 952 786 953 787 954 788 955 789 956 790 957 791 958 792 960 793 961 794 962 795 963 796 964 797 965 798 966 799 967 800 968 801

1 921 1 922 1 923 1 924 1 925 1 927 1 928 1 929 1 930 1 931 1 932 1 933 1 934 1 935 1 936 1 938 1 939 1 940 1 941 1 942 1 943 1 944 1 945 1 946 1 947 1 949 1 950 1 951 1 952 1 953 1 954 1 955 1 956 1 957 1

799

810

811

800

920

931+

800

811

812

801

921

932+

801

812

813

802

922

933+

802

813

814

803

923

934+

805

816

815

804

926

937+

804

815

817

806

925

936+

806

817

818

807

927

938+

807

818

819

808

928

939+

808

819

820

809

929

940+

809

820

821

810

930

941+

810

821

822

811

931

942+

811

822

823

812

932

943+

812

823

824

813

933

944+

813

824

825

814

934

945+

816

827

826

815

937

948+

815

826

828

817

936

947+

817

828

829

818

938

949+

818

829

830

819

939

950+

819

830

831

820

940

951+

820

831

832

821

941

952+

821

832

833

822

942

953+

822

833

834

823

943

954+

823

834

835

824

944

955+

824

835

836

825

945

956+

827

838

837

826

948

959+

826

837

839

828

947

958+

828

839

840

829

949

960+

829

840

841

830

950

961+

830

841

842

831

951

962+

831

842

843

832

952

963+

832

843

844

833

953

964+

833

844

845

834

954

965+

834

845

846

835

955

966+

835

846

847

836

956

967+

848

851

850

849

969

972+

1500 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

971 802 974 803 976 804 978 805 980 806 982 807 984 808 986 809 988 810 990 811 991 812 993 813 994 814 995 815 996 816 997 817 998 818 999 819 1000 820 1001 821 1002 822 1004 823 1005 824 1006 825 1007 826 1008 827 1009 828 1010 829 1011 830 1012 831 1013 832 1015 833 1016 834 1017 835 1018

Altair Engineering

970 1 973 1 975 1 977 1 979 1 981 1 983 1 985 1 987 1 989 1 971 1 974 1 976 1 978 1 980 1 982 1 984 1 986 1 988 1 990 1 991 1 993 1 994 1 995 1 996 1 997 1 998 1 999 1 1000 1 1001 1 1002 1 1004 1 1005 1 1006 1 1007

849

850

853

852

970

971+

852

853

855

854

973

974+

854

855

857

856

975

976+

856

857

859

858

977

978+

858

859

861

860

979

980+

860

861

863

862

981

982+

862

863

865

864

983

984+

864

865

867

866

985

986+

866

867

869

868

987

988+

851

871

870

850

972

992+

850

870

872

853

971

991+

853

872

873

855

974

993+

855

873

874

857

976

994+

857

874

875

859

978

995+

859

875

876

861

980

996+

861

876

877

863

982

997+

863

877

878

865

984

998+

865

878

879

867

986

999+

867

879

880

869

988

1000+

871

882

881

870

992

1003+

870

881

883

872

991

1002+

872

883

884

873

993

1004+

873

884

885

874

994

1005+

874

885

886

875

995

1006+

875

886

887

876

996

1007+

876

887

888

877

997

1008+

877

888

889

878

998

1009+

878

889

890

879

999

1010+

879

890

891

880

1000

1011+

882

893

892

881

1003

1014+

881

892

894

883

1002

1013+

883

894

895

884

1004

1015+

884

895

896

885

1005

1016+

885

896

897

886

1006

1017+

OptiStruct 13.0 Reference Guide 1501 Proprietary Information of Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

836 1019 837 1020 838 1021 839 1022 840 1023 841 1024 842 1026 843 1027 844 1028 845 1029 846 1030 847 1031 848 1032 849 1033 850 1034 851 1035 852 1037 853 1038 854 1039 855 1040 856 1041 857 1042 858 1043 859 1044 860 1045 861 1046 862 1048 863 1049 864 1050 865 1051 866 1052 867 1053 868 1054 869 1055 870

1 1008 1 1009 1 1010 1 1011 1 1012 1 1013 1 1015 1 1016 1 1017 1 1018 1 1019 1 1020 1 1021 1 1022 1 1023 1 1024 1 1026 1 1027 1 1028 1 1029 1 1030 1 1031 1 1032 1 1033 1 1034 1 1035 1 1037 1 1038 1 1039 1 1040 1 1041 1 1042 1 1043 1 1044 1

886

897

898

887

1007

1018+

887

898

899

888

1008

1019+

888

899

900

889

1009

1020+

889

900

901

890

1010

1021+

890

901

902

891

1011

1022+

893

904

903

892

1014

1025+

892

903

905

894

1013

1024+

894

905

906

895

1015

1026+

895

906

907

896

1016

1027+

896

907

908

897

1017

1028+

897

908

909

898

1018

1029+

898

909

910

899

1019

1030+

899

910

911

900

1020

1031+

900

911

912

901

1021

1032+

901

912

913

902

1022

1033+

904

915

914

903

1025

1036+

903

914

916

905

1024

1035+

905

916

917

906

1026

1037+

906

917

918

907

1027

1038+

907

918

919

908

1028

1039+

908

919

920

909

1029

1040+

909

920

921

910

1030

1041+

910

921

922

911

1031

1042+

911

922

923

912

1032

1043+

912

923

924

913

1033

1044+

915

926

925

914

1036

1047+

914

925

927

916

1035

1046+

916

927

928

917

1037

1048+

917

928

929

918

1038

1049+

918

929

930

919

1039

1050+

919

930

931

920

1040

1051+

920

931

932

921

1041

1052+

921

932

933

922

1042

1053+

922

933

934

923

1043

1054+

923

934

935

924

1044

1055+

1502 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1056 871 1057 872 1059 873 1060 874 1061 875 1062 876 1063 877 1064 878 1065 879 1066 880 1067 881 1068 882 1070 883 1071 884 1072 885 1073 886 1074 887 1075 888 1076 889 1077 890 1078 891 1079 892 1081 893 1082 894 1083 895 1084 896 1085 897 1086 898 1087 899 1088 900 1089 901 1092 902 1095 903 1097 904 1099

Altair Engineering

1045 1 1046 1 1048 1 1049 1 1050 1 1051 1 1052 1 1053 1 1054 1 1055 1 1056 1 1057 1 1059 1 1060 1 1061 1 1062 1 1063 1 1064 1 1065 1 1066 1 1067 1 1068 1 1070 1 1071 1 1072 1 1073 1 1074 1 1075 1 1076 1 1077 1 1078 1 1091 1 1094 1 1096 1 1098

926

937

936

925

1047

1058+

925

936

938

927

1046

1057+

927

938

939

928

1048

1059+

928

939

940

929

1049

1060+

929

940

941

930

1050

1061+

930

941

942

931

1051

1062+

931

942

943

932

1052

1063+

932

943

944

933

1053

1064+

933

944

945

934

1054

1065+

934

945

946

935

1055

1066+

937

948

947

936

1058

1069+

936

947

949

938

1057

1068+

938

949

950

939

1059

1070+

939

950

951

940

1060

1071+

940

951

952

941

1061

1072+

941

952

953

942

1062

1073+

942

953

954

943

1063

1074+

943

954

955

944

1064

1075+

944

955

956

945

1065

1076+

945

956

957

946

1066

1077+

948

959

958

947

1069

1080+

947

958

960

949

1068

1079+

949

960

961

950

1070

1081+

950

961

962

951

1071

1082+

951

962

963

952

1072

1083+

952

963

964

953

1073

1084+

953

964

965

954

1074

1085+

954

965

966

955

1075

1086+

955

966

967

956

1076

1087+

956

967

968

957

1077

1088+

969

972

971

970

1090

1093+

970

971

974

973

1091

1092+

973

974

976

975

1094

1095+

975

976

978

977

1096

1097+

OptiStruct 13.0 Reference Guide 1503 Proprietary Information of Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

905 1101 906 1103 907 1105 908 1107 909 1109 910 1111 911 1112 912 1114 913 1115 914 1116 915 1117 916 1118 917 1119 918 1120 919 1121 920 1122 921 1123 922 1125 923 1126 924 1127 925 1128 926 1129 927 1130 928 1131 929 1132 930 1133 931 1134 932 1136 933 1137 934 1138 935 1139 936 1140 937 1141 938 1142 939

1 1100 1 1102 1 1104 1 1106 1 1108 1 1110 1 1092 1 1095 1 1097 1 1099 1 1101 1 1103 1 1105 1 1107 1 1109 1 1111 1 1112 1 1114 1 1115 1 1116 1 1117 1 1118 1 1119 1 1120 1 1121 1 1122 1 1123 1 1125 1 1126 1 1127 1 1128 1 1129 1 1130 1 1131 1

977

978

980

979

1098

1099+

979

980

982

981

1100

1101+

981

982

984

983

1102

1103+

983

984

986

985

1104

1105+

985

986

988

987

1106

1107+

987

988

990

989

1108

1109+

972

992

991

971

1093

1113+

971

991

993

974

1092

1112+

974

993

994

976

1095

1114+

976

994

995

978

1097

1115+

978

995

996

980

1099

1116+

980

996

997

982

1101

1117+

982

997

998

984

1103

1118+

984

998

999

986

1105

1119+

986

999

1000

988

1107

1120+

988

1000

1001

990

1109

1121+

992

1003

1002

991

1113

1124+

991

1002

1004

993

1112

1123+

993

1004

1005

994

1114

1125+

994

1005

1006

995

1115

1126+

995

1006

1007

996

1116

1127+

996

1007

1008

997

1117

1128+

997

1008

1009

998

1118

1129+

998

1009

1010

999

1119

1130+

999

1010

1011

1000

1120

1131+

1000

1011

1012

1001

1121

1132+

1003

1014

1013

1002

1124

1135+

1002

1013

1015

1004

1123

1134+

1004

1015

1016

1005

1125

1136+

1005

1016

1017

1006

1126

1137+

1006

1017

1018

1007

1127

1138+

1007

1018

1019

1008

1128

1139+

1008

1019

1020

1009

1129

1140+

1009

1020

1021

1010

1130

1141+

1010

1021

1022

1011

1131

1142+

1504 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1143 940 1144 941 1145 942 1147 943 1148 944 1149 945 1150 946 1151 947 1152 948 1153 949 1154 950 1155 951 1156 952 1158 953 1159 954 1160 955 1161 956 1162 957 1163 958 1164 959 1165 960 1166 961 1167 962 1169 963 1170 964 1171 965 1172 966 1173 967 1174 968 1175 969 1176 970 1177 971 1178 972 1180 973 1181

Altair Engineering

1132 1 1133 1 1134 1 1136 1 1137 1 1138 1 1139 1 1140 1 1141 1 1142 1 1143 1 1144 1 1145 1 1147 1 1148 1 1149 1 1150 1 1151 1 1152 1 1153 1 1154 1 1155 1 1156 1 1158 1 1159 1 1160 1 1161 1 1162 1 1163 1 1164 1 1165 1 1166 1 1167 1 1169 1 1170

1011

1022

1023

1012

1132

1143+

1014

1025

1024

1013

1135

1146+

1013

1024

1026

1015

1134

1145+

1015

1026

1027

1016

1136

1147+

1016

1027

1028

1017

1137

1148+

1017

1028

1029

1018

1138

1149+

1018

1029

1030

1019

1139

1150+

1019

1030

1031

1020

1140

1151+

1020

1031

1032

1021

1141

1152+

1021

1032

1033

1022

1142

1153+

1022

1033

1034

1023

1143

1154+

1025

1036

1035

1024

1146

1157+

1024

1035

1037

1026

1145

1156+

1026

1037

1038

1027

1147

1158+

1027

1038

1039

1028

1148

1159+

1028

1039

1040

1029

1149

1160+

1029

1040

1041

1030

1150

1161+

1030

1041

1042

1031

1151

1162+

1031

1042

1043

1032

1152

1163+

1032

1043

1044

1033

1153

1164+

1033

1044

1045

1034

1154

1165+

1036

1047

1046

1035

1157

1168+

1035

1046

1048

1037

1156

1167+

1037

1048

1049

1038

1158

1169+

1038

1049

1050

1039

1159

1170+

1039

1050

1051

1040

1160

1171+

1040

1051

1052

1041

1161

1172+

1041

1052

1053

1042

1162

1173+

1042

1053

1054

1043

1163

1174+

1043

1054

1055

1044

1164

1175+

1044

1055

1056

1045

1165

1176+

1047

1058

1057

1046

1168

1179+

1046

1057

1059

1048

1167

1178+

1048

1059

1060

1049

1169

1180+

OptiStruct 13.0 Reference Guide 1505 Proprietary Information of Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA

974 1182 975 1183 976 1184 977 1185 978 1186 979 1187 980 1188 981 1189 982 1191 983 1192 984 1193 985 1194 986 1195 987 1196 988 1197 989 1198 990 1199 991 1200 992 1202 993 1203 994 1204 995 1205 996 1206 997 1207 998 1208 999 1209 1000 1210 1001 1213 1002 1216 1003 1218 1004 1220 1005 1222 1006 1224 1007 1226 1008

1 1171 1 1172 1 1173 1 1174 1 1175 1 1176 1 1177 1 1178 1 1180 1 1181 1 1182 1 1183 1 1184 1 1185 1 1186 1 1187 1 1188 1 1189 1 1191 1 1192 1 1193 1 1194 1 1195 1 1196 1 1197 1 1198 1 1199 1 1212 1 1215 1 1217 1 1219 1 1221 1 1223 1 1225 1

1049

1060

1061

1050

1170

1181+

1050

1061

1062

1051

1171

1182+

1051

1062

1063

1052

1172

1183+

1052

1063

1064

1053

1173

1184+

1053

1064

1065

1054

1174

1185+

1054

1065

1066

1055

1175

1186+

1055

1066

1067

1056

1176

1187+

1058

1069

1068

1057

1179

1190+

1057

1068

1070

1059

1178

1189+

1059

1070

1071

1060

1180

1191+

1060

1071

1072

1061

1181

1192+

1061

1072

1073

1062

1182

1193+

1062

1073

1074

1063

1183

1194+

1063

1074

1075

1064

1184

1195+

1064

1075

1076

1065

1185

1196+

1065

1076

1077

1066

1186

1197+

1066

1077

1078

1067

1187

1198+

1069

1080

1079

1068

1190

1201+

1068

1079

1081

1070

1189

1200+

1070

1081

1082

1071

1191

1202+

1071

1082

1083

1072

1192

1203+

1072

1083

1084

1073

1193

1204+

1073

1084

1085

1074

1194

1205+

1074

1085

1086

1075

1195

1206+

1075

1086

1087

1076

1196

1207+

1076

1087

1088

1077

1197

1208+

1077

1088

1089

1078

1198

1209+

1090

1093

1092

1091

1211

1214+

1091

1092

1095

1094

1212

1213+

1094

1095

1097

1096

1215

1216+

1096

1097

1099

1098

1217

1218+

1098

1099

1101

1100

1219

1220+

1100

1101

1103

1102

1221

1222+

1102

1103

1105

1104

1223

1224+

1104

1105

1107

1106

1225

1226+

1506 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

+ CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1228 1009 1230 1010 1232 1011 1233 1012 1235 1013 1236 1014 1237 1015 1238 1016 1239 1017 1240 1018 1241 1019 1242 1020 1243 1021 1244 1022 1246 1023 1247 1024 1248 1025 1249 1026 1250 1027 1251 1028 1252 1029 1253 1030 1254 1031 1255 1032 1257 1033 1258 1034 1259 1035 1260 1036 1261 1037 1262 1038 1263 1039 1264 1040 1265 1041 1266 1042 1268

Altair Engineering

1227 1 1229 1 1231 1 1213 1 1216 1 1218 1 1220 1 1222 1 1224 1 1226 1 1228 1 1230 1 1232 1 1233 1 1235 1 1236 1 1237 1 1238 1 1239 1 1240 1 1241 1 1242 1 1243 1 1244 1 1246 1 1247 1 1248 1 1249 1 1250 1 1251 1 1252 1 1253 1 1254 1 1255 1 1257

1106

1107

1109

1108

1227

1228+

1108

1109

1111

1110

1229

1230+

1093

1113

1112

1092

1214

1234+

1092

1112

1114

1095

1213

1233+

1095

1114

1115

1097

1216

1235+

1097

1115

1116

1099

1218

1236+

1099

1116

1117

1101

1220

1237+

1101

1117

1118

1103

1222

1238+

1103

1118

1119

1105

1224

1239+

1105

1119

1120

1107

1226

1240+

1107

1120

1121

1109

1228

1241+

1109

1121

1122

1111

1230

1242+

1113

1124

1123

1112

1234

1245+

1112

1123

1125

1114

1233

1244+

1114

1125

1126

1115

1235

1246+

1115

1126

1127

1116

1236

1247+

1116

1127

1128

1117

1237

1248+

1117

1128

1129

1118

1238

1249+

1118

1129

1130

1119

1239

1250+

1119

1130

1131

1120

1240

1251+

1120

1131

1132

1121

1241

1252+

1121

1132

1133

1122

1242

1253+

1124

1135

1134

1123

1245

1256+

1123

1134

1136

1125

1244

1255+

1125

1136

1137

1126

1246

1257+

1126

1137

1138

1127

1247

1258+

1127

1138

1139

1128

1248

1259+

1128

1139

1140

1129

1249

1260+

1129

1140

1141

1130

1250

1261+

1130

1141

1142

1131

1251

1262+

1131

1142

1143

1132

1252

1263+

1132

1143

1144

1133

1253

1264+

1135

1146

1145

1134

1256

1267+

1134

1145

1147

1136

1255

1266+

OptiStruct 13.0 Reference Guide 1507 Proprietary Information of Altair Engineering

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1043 1269 1044 1270 1045 1271 1046 1272 1047 1273 1048 1274 1049 1275 1050 1276 1051 1277 1052 1279 1053 1280 1054 1281 1055 1282

1 1258 1 1259 1 1260 1 1261 1 1262 1 1263 1 1264 1 1265 1 1266 1 1268 1 1269 1 1270 1 1271

1136

1147

1148

1137

1257

1268+

1137

1148

1149

1138

1258

1269+

1138

1149

1150

1139

1259

1270+

1139

1150

1151

1140

1260

1271+

1140

1151

1152

1141

1261

1272+

1141

1152

1153

1142

1262

1273+

1142

1153

1154

1143

1263

1274+

1143

1154

1155

1144

1264

1275+

1146

1157

1156

1145

1267

1278+

1145

1156

1158

1147

1266

1277+

1147

1158

1159

1148

1268

1279+

1148

1159

1160

1149

1269

1280+

1149

1160

1161

1150

1270

1281+

CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA + CHEXA +

1057 1284 1058 1285 1059 1286 1060 1287 1061 1288 1062 1290 1063 1291 1064 1292 1065 1293 1066 1294 1067 1295 1068 1296 1069 1297 1070 1298 1071 1299 1072 1301 1073 1302 1074 1303 1075 1304 1076 1305 1077 1306

1 1273 1 1274 1 1275 1 1276 1 1277 1 1279 1 1280 1 1281 1 1282 1 1283 1 1284 1 1285 1 1286 1 1287 1 1288 1 1290 1 1291 1 1292 1 1293 1 1294 1 1295

1151

1162

1163

1152

1272

1283+

1152

1163

1164

1153

1273

1284+

1153

1164

1165

1154

1274

1285+

1154

1165

1166

1155

1275

1286+

1157

1168

1167

1156

1278

1289+

1156

1167

1169

1158

1277

1288+

1158

1169

1170

1159

1279

1290+

1159

1170

1171

1160

1280

1291+

1160

1171

1172

1161

1281

1292+

1161

1172

1173

1162

1282

1293+

1162

1173

1174

1163

1283

1294+

1163

1174

1175

1164

1284

1295+

1164

1175

1176

1165

1285

1296+

1165

1176

1177

1166

1286

1297+

1168

1179

1178

1167

1289

1300+

1167

1178

1180

1169

1288

1299+

1169

1180

1181

1170

1290

1301+

1170

1181

1182

1171

1291

1302+

1171

1182

1183

1172

1292

1303+

1172

1183

1184

1173

1293

1304+

1173

1184

1185

1174

1294

1305+

1508 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

CHEXA 1078 1 1174 1185 1186 1175 1295 1306+ + 1307 1296 CHEXA 1079 1 1175 1186 1187 1176 1296 1307+ + 1308 1297 CHEXA 1080 1 1176 1187 1188 1177 1297 1308+ + 1309 1298 CHEXA 1081 1 1179 1190 1189 1178 1300 1311+ + 1310 1299 CHEXA 1082 1 1178 1189 1191 1180 1299 1310+ + 1312 1301 CHEXA 1083 1 1180 1191 1192 1181 1301 1312+ + 1313 1302 CHEXA 1084 1 1181 1192 1193 1182 1302 1313+ + 1314 1303 CHEXA 1085 1 1182 1193 1194 1183 1303 1314+ + 1315 1304 CHEXA 1086 1 1183 1194 1195 1184 1304 1315+ + 1316 1305 CHEXA 1087 1 1184 1195 1196 1185 1305 1316+ + 1317 1306 CHEXA 1088 1 1185 1196 1197 1186 1306 1317+ + 1318 1307 CHEXA 1089 1 1186 1197 1198 1187 1307 1318+ + 1319 1308 CHEXA 1090 1 1187 1198 1199 1188 1308 1319+ + 1320 1309 CHEXA 1091 1 1190 1201 1200 1189 1311 1322+ + 1321 1310 CHEXA 1092 1 1189 1200 1202 1191 1310 1321+ + 1323 1312 CHEXA 1093 1 1191 1202 1203 1192 1312 1323+ + 1324 1313 CHEXA 1094 1 1192 1203 1204 1193 1313 1324+ + 1325 1314 CHEXA 1095 1 1193 1204 1205 1194 1314 1325+ + 1326 1315 CHEXA 1096 1 1194 1205 1206 1195 1315 1326+ + 1327 1316 CHEXA 1097 1 1195 1206 1207 1196 1316 1327+ + 1328 1317 CHEXA 1098 1 1196 1207 1208 1197 1317 1328+ + 1329 1318 CHEXA 1099 1 1197 1208 1209 1198 1318 1329+ + 1330 1319 CHEXA 1100 1 1198 1209 1210 1199 1319 1330+ + 1331 1320 $$ $$------------------------------------------------------------------------------$ $$ HyperMesh name information for generic property collectors $ $$------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$ $$ Property Definition for 1-D Elements $ $$------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$ $$ HyperMesh name and color information for generic components $ $$------------------------------------------------------------------------------$ $HMNAME COMP 6"auto1" $HWCOLOR COMP 6 3 $ $$ $$------------------------------------------------------------------------------$ $$ Property Definition for Surface and Volume Elements $ $$------------------------------------------------------------------------------$ $$ $$ PSHELL Data $ $HMNAME COMP 4"shells"

Altair Engineering

OptiStruct 13.0 Reference Guide 1509 Proprietary Information of Altair Engineering

$HWCOLOR COMP 4 7 PSHELL 4 20.2 2 2 $$ $$ PSOLID Data $ $HMNAME COMP 1"solids" $HWCOLOR COMP 1 26 PSOLID 1 1 PFLUID PSOLID 2 2 $$ $$------------------------------------------------------------------------------$ $$ Material Definition Cards $ $$------------------------------------------------------------------------------$ $$-------------------------------------------------------------$$ HYPERMESH TAGS $$-------------------------------------------------------------$$BEGIN TAGS $$END TAGS $$ $$ MAT1 Data $ $HMNAME MAT 2"MAT1" $HWCOLOR MAT 2 18 MAT1 2200000.0 0.3 0.9e-5 $$ $$ $$ MAT10 Data $HMNAME MAT 1"MAT10_1" $HWCOLOR MAT 1 3 MAT10 11.0 0.01 $$ $$ $$------------------------------------------------------------------------------$ $$ HyperMesh name information for generic materials $ $$------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$ $$ Material Definition Cards $ $$------------------------------------------------------------------------------$ $$ $$------------------------------------------------------------------------------$ $$ Loads and Boundary Conditions $ $$------------------------------------------------------------------------------$ $$ $$HyperMesh name and color information for generic loadcollectors $$ $HMNAME LOADCOL 4"SPC" $HWCOLOR LOADCOL 4 3 $ $HMNAME LOADCOL 6"spcd" $HWCOLOR LOADCOL 6 4 $ $$ $$ $$ $$ $$ FREQ1 cards $$ $HMNAME LOADCOL 5"freq" $HWCOLOR LOADCOL 5 4 FREQ1 50.1 10.0 5 $$ $$ $$ $$ $$ $$ RLOAD2 cards $$ $HMNAME LOADCOL 2"rload2"

1510 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

$HWCOLOR LOADCOL RLOAD2 2 6 $$ $HMNAME LOADCOL $HWCOLOR LOADCOL RLOAD2 3 3 $$ $$ $$ $$ TABLED1 cards $$ $HMNAME LOADCOL $HWCOLOR LOADCOL TABLED1 1 LINEAR + 0.0 0.0 $$ TABLED1 2 LINEAR + 0.0 0.0 $$ TABLED1 3 LINEAR + 0.0 5.0 $$ DLOAD cards $$ $HMNAME LOADCOL $HWCOLOR LOADCOL DLOAD 111.0 $$ $$ $$ $$ $$ $$ $$ $$ SPC Data $$ SPC 4 1431 SPC 4 1432 SPC 4 1451 SPC 4 1452 SPC 4 1734 $$ $$ SPCD Data $$ SPCD 6 1734 $ $ DAREA Data $ $$ $$ DAREA Data $$ DAREA 3 1734 ENDDATA

2

5 1

0

ACCE

1

0

LOAD

1.0

3

3"darea" 3 5

1"tab" 1 41 LINEAR 1000.0 1.0ENDT LINEAR 1000.0

1.0ENDT

LINEAR 1000.0

5.0ENDT

11"DLOAD11" 11 3 1.0 2

1234560.0 1234560.0 1234560.0 1234560.0 3 0.0

3

3.0

3-10.0

ALTDOCTAG "HqTD_ARNMI\S\pMpN13G;5oANN]l[enE7fmSbTJro20LOpNriZFOQfUk] _`5hfS5ATf6pT7RXMjA3e@k_r^K?GP;?OeEbD0" ADI0.1.0 2011-05-13T19:57:45 0of1 OSQA ENDDOCTAG

Altair Engineering

OptiStruct 13.0 Reference Guide 1511 Proprietary Information of Altair Engineering

Comments 1.

PACABS is referenced by a CHACAB entry only.

2.

If SYNTH = “YES”, then TID1 and TID2 must be supplied (TID3 is optional) and the equivalent structural model will be derived from tables TIDi. If TID3 is blank, then the weighting function defaults to 1.0.

3.

If SYNTH=”NO”, then the equivalent structural model will be derived from B, K and M.

4.

This card is represented as a property in HyperMesh.

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PANEL Bulk Data Entry PANEL – Panel Definition for Panel Participation Output Description Defines up to four sets of grid points or elements as panels for panel participation output for a frequency response analysis of a coupled fluid-structural model. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PANEL

NAME1

SID1

NAME2

SID2

NAME3

SID3

NAME4

SID4

Field

Contents

NAME#

Panel label.

(10)

No default (Character string) SID#

Set identification number for a set of grids or elements. No default (Integer > 0)

Comments 1.

If a set of elements is defined, the panel will consist of all grid points connected to these elements.

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OptiStruct 13.0 Reference Guide 1513 Proprietary Information of Altair Engineering

PANELG Bulk Data Entry PANELG – Generic Panel Definition Description Defines a set of grid points and/or elements as generic panel. Format (1)

(2)

(3)

(4)

(5)

(6)

PANELG

ID

NAME

TYPE

ESID

GSID

Field

Contents

ID

Unique panel identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) NAME

Panel label. No default (Character string)

TYPE

Panel type. Default = blank (PFP, ERP, SOUND, or blank, See comment 1)

ESID

Set identification number for a set of elements. No default (Integer > 0 or blank)

GSID

Set identification number for a set of grids. No default (Integer > 0 or blank)

Comments 1.

The panel type indicates the context in which the panel should be used. PFP indicates that the panel should be considered for panel participation output (similar to PANEL). ERP indicates that the panel should be considered for equivalent radiated power output

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Altair Engineering

(similar to ERPPNL). SOUND indicates that the panel should be considered for radiated sound output. Blank indicates that the panel should be considered in any context involving panels. 2.

Panels of type ERP/SOUND (or blank) may be defined as a set of elements, a set of grid points, or both. If a set of elements is defined, the panel will consist of all grid points connected to these elements. If both sets are defined, the panel will consist of the intersection of those sets.

3.

Panels of type PFP must be defined as a set of grid points exclusively.

4.

The element set can also consist of solid elements. In such cases, grids on the wetted surface are automatically detected to define the panel.

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PARAM Bulk Data Entry PARAM – Solution Control Parameter Description Defines values for parameters used during analysis and optimization. Format (1)

(2)

(3)

PARAM

N

V

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

PARAM

C OUPMASS

YES

Field

Contents

N

Name of Parameter.

V

Value of Parameter.

(4)

(5)

(6)

(7)

(8)

(9)

(10)

The available parameters and their values are listed below (click the parameter name for parameter descriptions).

Parameter

Description

Values

ACMODL12

Used to restore the ACMODL formulation used in version 12.0 and earlier for the Fluid-Structure Interface.

YES, NO Default = NO

AGGPCH

To support output of the fluid-structure coupling matrix to the Punch (.pch) file as a matrix defined

YES, NO

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Parameter

Description

Values

using DMIG data entry.

Default = NO

AKUSMOD

Use external fluid-structure coupling matrix generated by AKUSMOD.

YES, NO Default = NO

ALPHA1

Adds Rayleigh damping to viscous damping for structural mesh.

Default = 0.0

ALPHA2

Adds Rayleigh damping to viscous damping for structural mesh.

Default = 0.0

ALPHA1FL

Adds Rayleigh damping to viscous damping for fluid mesh.

Default = 0.0

ALPHA2FL

Adds Rayleigh damping to viscous damping for fluid mesh.

Default = 0.0

AMLS

Use external AMLS eigenvalue solver.

YES, NO Default = NO

AMLSMAXR

Used to determine singularities in the stiffness matrix for AMLS eigenvalue solver. Default = 1.0e-8

AMLSMEM

Defines the amount of memory in Gigabytes to be used by the external AMLS eigenvalue solver.

No default

AMLSNCPU

Identify number of cpu's to be used by AMLS eigenvalue solver.

1, 2, 4 Default = no. of cpu’s used by the solver

AMLSUCON

Constrain unconnected grids for AMLS eigenvalue solver.

1, 0 Default = 0

AMSESLM

Indicate if the AMSES numerical mode for enforced motion based modal dynamic analysis with large mass method will be activated or not.

Default = NO

ASCOUP

Generates the fluid-structure coupling (area) matrix for use in the solution.

Default = YES

AUTOMSET

Automatically convert dependent degrees-of-



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Parameter

Description

Values

freedom of rigid elements to independent degreesof-freedom.

Default = YES

AUTOSPC

Automatically constrain degrees-of-freedom with no stiffness.

YES, NO Default = YES

AUTOSPRT

Activate inertia relief and auto-support degree-offreedom generation.

1, 0 Default = 1

BUSHRLMT

Issues a WARNING when the stiffness value for rotational components on the PBUSH entry exceeds the specified limit (BUSHRLMT).

0.0> Default = 1.0E+09

BUSHSTIF

Specifies a value to replace large stiffness values (>1.0E+07) input in field K of the PBUSH data entry.

0.0> No default

BUSHTLMT

Issues a WARNING when the stiffness value for translational components on the PBUSH entry exceeds the specified limit (BUSHTLMT).

0.0> Default = 1E+07

CB2

Scale factor for direct input damping matrices.

Real Default = 1.0

CHECKEL

Activate element quality checking.

NO, YES, FULL Default = YES

CHECKMAT

Activate material property checking.

YES, NO, FULL Default = YES

CHKGPDIR

Activate gap direction alignment checking.

YES, NO, WARN, FULL, REVERSE Default = YES

CK2

Scale factor for direct input stiffness matrices.

Real Default = 1.0

CK3

Specifies factors for the stiffness matrix produced by GENEL cards.

Real Default = 1.0

CM2

Scale factor for direct input mass matrices.

Real Default = 1.0

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Parameter

Description

Values

CMFTINIT

Defines lower threshold for *.HM.comp.cmf and *.HM.ent.cmf HyperMesh command files.

0.0 < REAL < 1.0 Default = 0.0

CMFTSTEP

Defines step or interval value for *.HM.comp.cmf and *.HM.ent.cmf HyperMesh command.

0.0 < REAL < 1.0 Default = 0.1

CMSALOD

Controls the inclusion of mass contribution from the mass matrix stored in the PUNCH DMIG or the H3D DMIG files for the generation of RFORCE and Gravity Loads.

Default = YES

CMSDIRM

Allows flexible body generation when directional masses are defined in the input file.

YES, NO Default = NO

CMSOFST

Consider shell offsets for flexbody generation.

Default - NO

COEFFC

Friction coefficient on curvatures for one-step stamping simulation.

Real > 0.0

COMP2SHL

Results of homogenization of composite properties.

CONTFEL

Activates Contact-friendly elements. This is recommended when second order solids/gaskets are used with contact analysis in OptiStruct.

Default = NO

COUPMASS

Use coupled mass matrix approach for eigenvalue analysis.

-1, 0, 1, YES, NO Default = NO

CP2

Scale factor for direct input load matrices.

Real Default = 1.0

CSTEVAL

Use wall time based cost evaluation for Lanczos steps.

Default = YES

CSTOL

Specifies how many decimal digits may be lost to cancellation in one operation during the eigensolution process.

Real Default = 3.5

DFREQ

Used to determine duplicate frequencies.

Real

Altair Engineering

YES, NO, BULK Default = NO

OptiStruct 13.0 Reference Guide 1519 Proprietary Information of Altair Engineering

Parameter

Description

Values

Default = 10-5 DISIFMCK

Skip indefinite mass matrix check.

Default = NO

DISJOINT

Used to allow AMLS to handle disconnected parts. This can also be accomplished with PARAM,AMLSUCON.

Integer Default = NONE

DUPTOL

Level of accuracy used in determining duplicate grids.

Default = 0

EFFMAS

Output modal participation factors and effective mass for normal modes analyses.

YES, NO, Integer Default = NO

EHD

Prints the inverse of the stiffness matrix created by static reduction to FORTRAN unit 3

Default = NO

ELASRLMT

Issues a WARNING when the stiffness value for rotational components on the CELAS2/4 or PELAS entry exceeds the specified limit (ELASRLMT).

0.0> Default = 1.0E + 09

ELASSTIF

Specifies a value to replace large stiffness values (>1.0E+07) input in field K of the PELAS data entry.

0.0> No default

ELASTLMT

Issues a WARNING when the stiffness value for translational components on the CELAS2/4 or PELAS entry exceeds the specified limit (ELASTLMT).

0.0> Default = 1E+07

ENFMOTN

Switch between relative and absolute displacement output in Modal Frequency Response Analysis with enforced motion.

Default = ABS

ERPC

The speed of sound used in the ERP calculation

Real > 0.0 Default = 1.0

ERPREFDB

The reference value in decibels (dB) used in ERP calculations.

Real > 0.0 Default = 1.0

ERPRHO

The fluid density used in ERP calculations.

Real > 0.0 Default = 1.0

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Parameter

Description

Values

ERPRLF

The Radiation Loss Factor used in ERP calculation.

Real > 0.0 Default = 1.0

EXCEXB

Controls the output of the AVL/EXCITE .exb file directly from OptiStruct.

Default = BOTH

EXCOUT

Outputs of condensed superelement information for AVL/EXCITE.

Default = 0

EXPERTNL

Activates nonlinear expert system to aid in the convergence of small displacement nonlinear problems.

YES, NO Default = NO

EXTOUT

Output reduced matrices to .pch or .dmg file.

No default

FASTFR

Controls the activation of a faster, alternative method (FASTFR) for Modal Frequency Response Analysis.

Default = AUTO

FFRS

Used to invoke the external FastFRS (Fast Frequency Response Solver).

Default = NO

FFRSLFREQ

Defines a frequency cut-off value in Hertz used to partition the structural system into low frequency and high frequency parts.

Real Default = 1.0

FFRSMEM

Defines the amount of memory in Gigabytes to be used by the external FastFRS modal equation solver. Default = 2.0 (GB)

FFRSNCPU

Defines the number of cpu’s to be used by the external FastFRS solver.

Default = number of cpu's used by OptiStruct.

FLEXH3D

Generate flexh3d files for flexible bodies in an MBD analysis.

Default = AUTO

FLIPOK

Allows tetrahedral elements to invert during shape optimization.

NO, YES Default = NO

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Parameter

Description

Values

FRIC

Define multiplier for K2PP reference.

Default = 1.0

FZERO

Identify the maximum frequency of a rigid body mode.

Default = 0.1

G

Specifies the uniform structural damping coefficient for dynamic analyses.

Default = 0.0

GE_MOD

Modifies specified GE values.

or NO_GE> No default

GFL

Specifies the uniform fluid damping coefficient for dynamic analyses.

Default = 0.0

GMAR

Controls the accuracy of the external AMLS eigenvalue solution.

Default = 1.1

GMAR1

Controls the accuracy of the external AMLS eigenvalue solution.

Default = 1.7

GPSLOC

Controls where the grid point stresses are calculated Z1, Z2 and MID for output to the .mnf file. Default = Z1

GRDPNT

Obsolete NASTRAN parameter that will give information about the mass properties of the structure.

Default = -1

GRIDFORM

This parameter controls the output format of the .grid file.

Default = SHORT

GYROAVG

Used to select the frequency response analysis formulation type for rotor dynamics analysis.

Default = 0

HASHASSM

Enable hash-table based assembly.

Default = NO

HFREQ

Specifies the upper bound of the frequency range of interest for modal combination.

Default = None

HFREQFL

Excludes modes with frequencies greater than



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Parameter

Description

Values

HFREQFL in Coupled Modal Frequency Response Analysis (Acoustic Analysis).

(Hertz)

I64SLV

Enforces the activation of internal long (64-bit) integer sparse direct solver.

Default = NO

INREL

Controls the calculation of inertia relief.

0, -1, -2 Default = 0, for static subcases Default = -2, for modal frequency response subcases

ITAPE

Writes the ‘Tape Label’ at the beginning of the OUTPUT2 results file.

-1, 0 Default = -1

INTRFACE

Generates the .interface file to verify if proper connection has been established between the Fluid and Structure meshes at the interface.

YES, NO Default = YES

K4CUTOFF

Sets cut-off value if the low rank representation for the structural damping matrix is selected.

Default = 0.1

KDAMP

Enter viscous modal damping into the stiffness matrix as structural damping.

1, -1 Default = 1

KGRGD

Include contributions from rigid elements in the geometric stiffness matrix.

YES, NO Default = NO

LFREQ

Can be used to remove the Rigid Body Modes from the Modal Space.

Default = None

LFREQFL

Excludes modes with frequencies lower than LFREQFL in Coupled Modal Frequency Response Analysis (Acoustic Analysis).

(Hertz)

LGDISP

Activates Large Displacement Nonlinear Analysis.

Default = 0

LMSOUT

Output the condensed Flex Body Modes, full Diagonal YES, NO, STRESS Mass Matrix, and modal stresses to the .op2 file. Default = NO

Altair Engineering

Default = None

Default = None

OptiStruct 13.0 Reference Guide 1523 Proprietary Information of Altair Engineering

Parameter

Description

Values

LOWRANK

Indicates to FastFRS which solution strategy to use to handle the modal structural damping matrix.

Default = 0

MASSDMIG

For static condensation with ASET of a static loadcase, the reduced stiffness matrix [k] and load vector {p} are created.

Default = NO

MAXDAMP

Identify the maximum number of residual vectors to be calculated.

Default = 400

MBDH3D

Choose the type of the results output to the .h3d file for MBD analyses.

NODAL, MODAL, BOTH, NONE Default = BOTH

MBDREC

Create a small and large flexible body files during Component Mode Synthesis (CMS).

MEMTRIM

Activate/deactivate the memory-trim feature when using AMLS eigensolver.

Default = YES

MFILTER

Defines a threshold for the mode tracking matrix to check eigenvector correspondence.



MODETRAK

Track mode numbers by comparing eigenvectors between iterations.

-1, 0, 1, YES, NO Default = NO

NEGMASS

Allows run to proceed with negative diagonal mass terms.

Default = 0

NLAFILE

Controls the output of animation files (A-File) in geometric nonlinear analysis.

Default = NO

NLFAT

Forces OptiStruct to run models in which fatigue solutions reference nonlinear quasi-static analysis (NLSTAT) subcases.

Default = NO

YES, NO Default = NO

This is not recommended; refer to the complete PARAM, NLFAT documentation for details. NLRFILE

Controls the output of restart files (R-File) in geometric nonlinear analysis.

1524 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Default = NO

Altair Engineering

Parameter

Description

NLRUN

Controls the run of geometric nonlinear analysis after bulk to block conversion. Default = YES

NPRBAR

Controls the number of the output INFORMATION #741 for RBAR element.

Default = 3

NPRBE2

Controls the number of the output INFORMATION #741 for RBE2 element.

Default = 3

NPRGDE

Controls the number of the output INFORMATION #742.

Default = 3

NUMEG

Specifies the anticipated number of modes to be calculated in order to estimate disk space usage.

1000

OGEOM

Output model data to the OUTPUT2 results file.

Default = YES

OMACHPR

Select newer version of certain OUTPUT2 datablocks.

Default = NO

OMID

Output stress and strain results for shell and membrane elements with reference to the material coordinate system.

Default = NO

OP2GM34

Controls the output of GEOM3 and GEOM4 data blocks to the .op2 file.

Default = TRUE

PLIGEXT

Print the applied load vector in DMIG form to the .pligext file.

Default = NO

POST

Generate an OUTPUT2 results file.

0, -1, -2, -5 Default = 0

POSTEXT

Output the modal complex stiffness matrix and modal YES, NO viscous damping matrix to the OUTPUT2 results file. Default = NO

PRESUBNL

Forces OptiStruct to run models in which Linear Buckling Analysis or Preloaded Analysis is defined, in conjunction with nonlinear materials (MATS1, MATHE, or MGASK) or Large Displacement Nonlinear

Altair Engineering

Values

YES, NO Default = NO

OptiStruct 13.0 Reference Guide 1525 Proprietary Information of Altair Engineering

Parameter

Description

Values

Analysis. This is not recommended. Refer to the complete PARAM, PRESUBNL documentation for details. PRGPST

Output AutoSPC information to the .out file.

Default = YES

PRINFACC

Controls the output of inertial relief rigid body forces and accelerations.



RBE2FREE

Used to convert ERROR 725 into WARNING 825 when singular RBE2 elements are present in the model.

Default = NO

RBE3FREE

Used to convert ERROR 772 into WARNING 824 when free spiders on RBE3 elements are present in the model. These free spiders may contain singular degrees of freedom.

Default = NO

RBMEIG

Defines the cut-off eigenvalue for determining rigid body modes calculated by AMLS.

Default = 0.1

REANAL

Reanalyze the final iteration of a topology optimization without penalization.

0.0 < REAL < 1.0 No default

RECOVER

Allows you to request full-structure mode shape output instead of the modes of the condensed system generated during Component Mode Synthesis (CMS) within the specified range of frequencies.

Default for LB = 0.0, and UB must be specified

RENUMOK

Allows you to correctly renumber the reversed (but acceptable) sequence of element grids without having to run (import and re-export) the model through HyperMesh.

Default = NO

RFIOUT

This parameter controls the output of modal super element for use in the RecurDyn multibody dynamics software from FunctionBay.

Default = NO

RHOCP

The scale factor used to calculate ERP in decibels (dB).

Real > 0.0 Default = 1.0

RSPLICOR

RSPLINE end rotation correction.

0, 1, REAL > 1.0 Default = 0

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Parameter

Description

Values

SEP1XOVR

The old and new location of moved shell grid points are printed if SEP1XOVR = 16.

0, 16 Default = 0

SEPLOT

Output display model to .seplot file, from a CMS run.

Default = YES

SH4NRP

Controls the full projection of 4-node shell elements in NLGEOM implicit analysis.

0, 1, 2 Default = 0 in NLGEOM subcases Default = 1 in IMPDYN subcases

SHELOS11

Allows you to revert to the first order shell element formulation (for CQUAD4 and CTRIA3) used in version Default = NO 11.0.240 and earlier.

SHL2MEM

A shell property (defined by the PSHELL bulk data entry) is automatically converted into a membrane property if the membrane thickness (field T) of the PSHELL bulk data entry is less than the value specified using PARAM, SHL2MEM.

0.0> No default

SHPBCKOR

Defines the type and order of approximation used in plate bending geometric stiffness for linear shell elements (CQUAD4, CTRIA3).

1, 2 Default = 1

SIMPACK

Requests generation of the SIMPACK .fbi file containing flexible body information for SIMPACK analysis.

0, 1, 2, 3, 4, 5 Default =0

SMDISP

Controls if small displacement formulation or large displacement formulation is used.

0, 1 Default = 0

SNAPTHRU

Controls the output of the force-deflection curve in geometric nonlinear analysis.

Default = NO

SORTCON

Controls the output of violated constraints to the .out file from an optimization.

Default = 20

SPLC

Specifies the speed of sound used in the wave number and the complex particle velocity vector calculations.

Real > 0.0 Default = 1.0

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OptiStruct 13.0 Reference Guide 1527 Proprietary Information of Altair Engineering

Parameter

Description

Values

SPLFAC

Specifies the scale factor (q ) used to calculate the Sound Pressure Level in Radiated Sound Analysis.

Real > 0.0 Default = 1.0

SPLREFDB

Specifies the reference sound pressure value used to calculate the Sound Pressure Level (SPL) in decibels (dB).

Real > 0.0 Default = 1.0

SPLRHO

Specifies the density of the acoustic medium in the calculation of the complex acoustic sound pressure and the complex particle velocity vector.

Real > 0.0 Default = 1.0

SRCOMPS

Outputs the strength ratios for composite elements that have failure indices requested.

Default = NO

SS2GCR

Controls the accuracy of the external AMLS eigenvalue solution.

Default = 5.0

STRTHR

Specifies the von Mises stress threshold value above which the stress results are output for a model. Default = 0.0

THCNTPEN

Controls the penalty factor used in thermal contact analysis.

AUTO, LOW, HIGH Default = AUTO

TOLRSC

Connecting grid points of the shell element are moved onto the solid face.

Default = 0.05

TRAKMETH

Used to select the criterion employed for mode tracking.

Default = 0

TRAKMTX

Controls output of the mode tracking matrix during optimization.

Default = 0

TPS

Activate fast transient response analysis (only shell stress results output).

Default = YES

UCORD

Specifies the coordinate system in which the mass moment of inertia is output. It also can be used to control the point about which the mass moment of inertia is calculated.



Allows you to prevent the inclusion of the Virtual



VMOPT

1528 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Default = -1

Altair Engineering

Parameter

Description

Values

Mass Matrix in the Regular Mass Matrix for Modal Dynamic Subcases. In such cases, the virtual mass is added after the eigen solution and modes are modified based on the virtual mass matrix.

Default = 0

W3

Convert structural damping to equivalent viscous damping for transient analysis.

Default = 0.0

W4

Convert structural damping to equivalent viscous damping for transient analysis.

Default = 0.0

WR3

Used to include or exclude frequency dependent damping in rotor dynamics analysis.

Default = 0.0

WR4

Used to include or exclude frequency dependent damping in rotor dynamics analysis.

Default = 0.0

WTMASS

Convert weights to masses using this multiplier.

REAL > 0.0 Default = 1.0

Comments 1.

This card is represented as a control card in HyperMesh.

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OptiStruct 13.0 Reference Guide 1529 Proprietary Information of Altair Engineering

PARAM, ACMODL12 Parameter ACMODL

Values

Description

Default = NO

PARAM, ACMODL12, YES can be used to restore the ACMODL formulation used in version 12.0 and earlier for the Fluid-Structure Interface. Note In OptiStruct 13.0 the new and improved ACMODL formulation will couple the fluid grids at the interface to only a single layer of structural grids. This parameter can be used to restore the formulation used prior to 13.0. The old formulation coupled the fluid face to every structural grid in the search box.

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PARAM, AGGPCH Parameter AGGPCH

Values

Description

Default = NO

If YES, OptiStruct will output the Fluid-Structure coupling matrix to the Punch file (.pch) as a matrix defined using the DMIG data entry, with the name AGGAX. This DMIG can be used in a subsequent OptiStruct run using the A2GG Solution Control Command. If NO, the Fluid-Structure coupling matrix will not be output to the Punch file (.pch).

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PARAM, AKUSMOD Parameter AKUSMOD

Values

Description

Default = NO

If YES, this indicates that OptiStruct should use a fluidstructure coupling matrix generated by AKUSMOD. In this case, the ACMODL data is ignored. By default it is presumed that the AKUSMOD coupling matrix is to be found in the same directory as the solver input file and is given the file name “ftn.70“. However an alternate file name and location may be assigned via the ASSIGN,AKUSMOD command.

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PARAM, ALPHA1 Parameter ALPHA1

Values

Description

Default = 0.0

PARAM, ALPHA1 is used in frequency response, transient response and modal complex eigenvalue analyses. If PARAM, ALPHA1 and/or PARAM, ALPHA2 are not equal to zero, then Rayleigh damping is added to the viscous damping. ALPHA1 is the scale factor applied to the mass matrix and ALPHA2 to the structural stiffness matrix as in:

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PARAM, ALPHA2 Parameter ALPHA2

Values

Description

Default = 0.0

PARAM, ALPHA2 is used in frequency response, transient response and modal complex eigenvalue analyses. If PARAM, ALPHA1 and/or PARAM, ALPHA2 are not equal to zero, then Rayleigh damping is added to the viscous damping. ALPHA1 is the scale factor applied to the mass matrix and ALPHA2 to the structural stiffness matrix as in:

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PARAM, ALPHA1FL Parameter ALPHA1FL

Values

Description

Default = 0.0

PARAM, ALPHA1FL is used in frequency and transient response analysis. If PARAM, ALPHA1FL and/or PARAM, ALPHA2FL are not equal to zero, then Rayleigh damping is added to the viscous damping. ALPHA1FL is the scale factor applied to the mass matrix and ALPHA2FL to the fluid stiffness matrix as in:

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OptiStruct 13.0 Reference Guide 1535 Proprietary Information of Altair Engineering

PARAM, ALPHA2FL Parameter ALPHA2FL

Values

Description

Default = 0.0

PARAM, ALPHA2FL is used in frequency and transient response analysis. If PARAM, ALPHA1FL and/or PARAM, ALPHA2FL are not equal to zero, then Rayleigh damping is added to the viscous damping. ALPHA1FL is the scale factor applied to the mass matrix and ALPHA2FL to the fluid stiffness matrix as in:

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PARAM, AMLS Parameter

Values

Description

AMLS

YES, NO Default = NO

This parameter is used to invoke the external AMLS eigenvalue solver. This solver is faster than the Lanczos solver for large eigenvalue problems. Note that AMLS must be installed on the system and the environment variable AMLS_EXE must point to the AMLS executable for this setting to work. If YES, then the external AMLS eigenvalue solver is used. If NO, then the internal Lanczos eigenvlaue solver is used. Refer to the User’s Guide section, Using the AMLS (Automatic Multi-Level Sub-structuring) Eigensolver for more details.

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PARAM, AMLSMAXR Parameter

Values

Description

AMLSMAXR

PARAM, AMLSMAXR is used to determine singularities in Default = 1.0e-8 the stiffness matrix. If the value of AMLSMAXR is exceeded in the process of factoring a stiffness matrix, this indicates a singularity in K. If the mass of this degree-of-freedom is zero, there is a "massless mechanism"; an SPC is applied and a message is written to the .out file. If there is mass, then this is a mechanism which is treated as a rigid body mode and a message is written to the .out file. Refer to the User’s Guide section, Using the AMLS (Automatic Multi-Level Sub-structuring) Eigensolver for more details.

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PARAM, AMLSMEM Parameter

Values

AMLSMEM



Description

This parameter is used to define the amount of memory in Gigabytes to be used by the external AMLS eigenvalue Default = solver. This parameter is only valid for AMLS versions 5 Memory used by and higher. OptiStruct for a Note particular run. 1.

If this parameter is not set, AMLS will use the amount of memory that OptiStruct is using for the run.

2.

OptiStruct and AMLS can be run with different allocations of memory. For example, OptiStruct can be run with 10.0 Gigabytes and AMLS with 20.0 Gigabytes in the same run.

3.

If the environment variable AMLS_MEM is set, it will override the value set using PARAM,AMLSMEM.

4.

This parameter can be used only if PARAM, AMLS is set to YES.

Refer to the User’s Guide section, Using the AMLS (Automatic Multi-Level Sub-structuring) Eigensolver for more details.

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PARAM, AMLSNCPU Parameter

Values

Description

AMLSNCPU

1, 2, 4 Default = no. of cpu’s used by the solver

This parameter is used to define the number of cpu’s to be used by the external AMLS eigenvalue solver. This parameter will set the environment variable OMP_NUM_THREADS. The default value is the current value of OMP_NUM_THREADS. Note that this value can be set through the command line arguments –nproc or – ncpu. OptiStruct and AMLS can be run with different allocations of processors. For example, OptiStruct can be run with 1 processor and AMLS with 4 processors in the same run. Only valid when PARAM, AMLS is set to YES. Refer to the User’s Guide section, Using the AMLS (Automatic Multi-Level Sub-structuring) Eigensolver for more details.

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PARAM, AMLSUCON Parameter AMLSUCON

Values

Description

0, 1 Default = 0

This parameter is used to indicate whether or not unconnected grids are to be constrained for AMLS run. If 0, then unconnected grids are not constrained. If 1, then unconnected grids are to be constrained. Refer to the User’s Guide section, Using the AMLS (Automatic Multi-Level Sub-structuring) Eigensolver for more details.

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PARAM, AMSESLM Parameter AMSESLM

Values

Description

Default = NO

YES: The EIGRA (AMSES) numerical method for enforced motion based modal dynamic analysis with large mass method will be activated. NO: The EIGRA (AMSES) numerical method for enforced motion based modal dynamic analysis with large mass method will not be activated.

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PARAM, ASCOUP Parameter ASCOUP

Values

Description

Default = YES

If YES, the fluid-structure coupling (area) matrix will be calculated and used in the solution. If NO, the fluid-structure (area) matrix is not calculated. Note: PARAM,AGGPCH,YES should be used to output the matrix to the Punch (.pch) file. PARAM,ASCOUP,NO is required when the fluidstructure coupling (area) matrix is read in from the Punch (.pch) file.

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PARAM, AUTOMSET Parameter AUTOMSET

Values

Description

Default = YES Defaults 1. The default is NO when the parameter is not present in the deck. 2. The default is YES when PARAM, AUTOMSET is input without specifying a value.

If YES, the dependent degrees-of-freedom of rigid elements may be converted to independent degreesof-freedom when conversion is necessary for the model to run. If NO, the above conversion will not be performed. The model may not run when multiple constraint equations reference the same dependent degree-offreedom more than once. Note: 1.

This parameter can be used if the dependent degree-of-freedom (DOF) of a rigid element is SPC’ed, part of the ASET, or if it is a dependent DOF of another constraint equation (MPC equation or another rigid element).

2.

PARAM, AUTOMSET, YES can be used in models with SPC’ed dependent rigid element grids, only if multiple SPC sets are present in multiple subcases.

3.

AUTOMSET cannot be used to convert the dependent degrees of freedom (DOF’s) of a rigid element constrained by global SPC’s to independent DOF’s. In such situations, it is recommended to create another subcase with a different SPC set.

4.

AUTOMSET cannot be used if Direct Matrix Input (DMIG) generation is performed using the Static Condensation method (Component Mode Synthesis (CMSMETH entry) is not used).

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PARAM, AUTOSPC Parameter

Values

Description

AUTOSPC

YES, NO Default = YES

If YES, the global stiffness matrix is checked for degrees-of-freedom with no stiffness. If found, these degrees-of-freedom are automatically constrained. If NO, the degrees of freedom with no stiffness are not automatically constrained.

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PARAM, AUTOSPRT Parameter

Values

Description

AUTOSPRT

Default = 1

This parameter applies to residual vector calculation in inertia relief analysis. If 1, rigid body modes from the eigenvalue analysis (PARAM,FZERO defines cut-off for determination of rigid body modes) are used to automatically generate SUPORT dofs. If 0, SUPORT dofs are automatically generated using the 6 geometric rigid body modes.

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PARAM, BUSHRLMT Parameter BUSHRLMT

Values

Description

This parameter is used to issue a WARNING when the 0.0> stiffness value for rotational components on the PBUSH entry exceeds the specified limit (BUSHRLMT). Default = 1.0E + 09 Note: This check is overridden when PARAM, BUSHSTIF is used to control the maximum stiffness value.

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PARAM, BUSHSTIF Description This parameter can accept two arguments. If only one argument is specified, the same value is used for the second argument. Format PARAM, BUSHSTIF, , Parameter BUSHSTIFT

Values

Description

This parameter controls the value of field “K” in the 0.0> PBUSH property entries. No default

BUSHSTIFR

BUSHSTIFT: This value applies to translational stiffness fields on the property entry (first three values).

BUSHSTIFR: 0.0> This value applies to rotational stiffness values on the Default = property entry. Note: 1.

Any value on the field “K” on the PBUSH entry which exceeds BUSHSTIFT or BUSHSTIFR, respectively will be replaced by BUSHSTIFT or BUSHSTIFR.

2.

Either BUSHSTIFT or BUSHSTIFR (or both) can be set to 0.0. This will disable stiffness control for the corresponding translational or rotational stiffnesses.

3.

Defaults: a. If BUSHSTIFT is input without specifying a value, then OptiStruct will error out (no default). The default for BUSHSTIFR is BUSHSTIFT. b. If PARAM, BUSHSTIF is not included in the deck, the stiffness value (Field K) is not replaced regardless of its value (no stiffness control).

4.

This parameter applies, in a similar fashion, to the PBUSH1D Rod-type Spring-and-Damper Property as well (using BUSHSTIFT).

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PARAM, BUSHTLMT Parameter BUSHTLMT

Values

Description

This parameter is used to issue a WARNING when the 0.0> stiffness value for translational components on the PBUSH entry exceeds the specified limit (BUSHTLMT). Default = 1E+07 Note: This check is overridden when PARAM, BUSHSTIF is used to control the maximum stiffness value.

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PARAM, CB2 Parameter

Values

Description

CB2

Real Default = 1.0

CB2 specified factors for the direct input damping matrix. The total damping matrix is:

where

is selected via the subcase information

command B2GG, and comes from CDAMP1, CDAMP2, CDAMP3, CDAMP4, or CVISC element bulk data entries.

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PARAM, CHECKEL Parameter CHECKEL

Values

Description

NO, YES, FULL Default = YES

If NO, element quality checks are not performed, but mathematical validity checks are performed. If YES, the geometric quality of each element is checked. Any violation of the error limits is counted as a fatal error and the run will stop. Any violation of warning limits is non-fatal. Error or warning messages are printed for elements violating the limits along with the offending property values. The amount of output is limited to the first 3 occurrences for each individual case, plus a summary table of all errors. If FULL, the same checks are performed as for YES, but the error or warning messages are printed for all of the elements violating the error or warning limits. See Element Quality Check for an overview of the element quality checking performed by the solver. The ELEMQUAL bulk data entry may be used to control the values for warning and error limits for each quality check, but validity limits cannot be altered by the user.

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PARAM, CHECKMAT Parameter CHECKMAT

Values

Description

YES, NO, FULL Default = YES

If YES, the material properties for all referenced material definitions are checked for adherence to the default material requirements as described on the Material Property Check page. The amount of output is limited. If NO, mathematical requirement checks only are performed for all referenced material definitions. If FULL, material property checks are performed as when the value is YES, but all violations are output.

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PARAM, CHKGPDIR Parameter CHKGPDIR

Values

Description

YES, NO, WARN, FULL, REVERSE Default = YES

If YES, all gap elements of non-zero length (distance between GA-GB) that have a prescribed coordinate system CID are checked for misalignment of gap prescribed axis (x-axis of CID) with the vector GA->GB (angles larger than 30 degrees produce errors). The amount of output is limited to the first ten occurrences. Note that this check applies correctly to the most typical situations where in there is an initial opening between bodies A and B, and the gap element is used to enforce non-penetration condition (for other cases, see the REVERSE option below). If NO, no gap CID direction checks are performed. If WARN, only warnings are issued. If FULL, the error or warning messages are printed for all gap elements violating this check. If REVERSE, orientations of vector GA->GB generally opposite to the prescribed x-axis of CID system are also accepted (this can be used in cases when gap is used to model rope behavior or when there is initial penetration, rather than gap, between bodies A and B). The tolerance levels are the same as for YES, except that they are measured from either 0 or 180 degrees reference angle. For more details, refer to the CGAP description. PARAM, CHKGPDIR is superseded by the CKGAPDIR parameter on the GAPPRM bulk data entry if present.

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PARAM, CK2 Parameter CK2

Values

Description

Real Default = 1.0

CK2 specifies factors for the direct input stiffness matrix. The total stiffness matrix is:

where

is selected via the subcase information

command K2GG, and is generated from structural element entries in the bulk data section.

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PARAM, CK3 Parameter CK3

Values

Description

Real Default = 1.0

CK3 specifies factors for the stiffness matrix produced by GENEL cards. The total stiffness matrix is:

where

is the stiffness generated by all GENEL cards

and is the combination of the stiffness generated from structural element entries in the bulk data section and the stiffness generated by the subcase information command K2GG and scaled by PARAM,CK2.

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PARAM, CM2 Parameter CM2

Values

Description

Real Default = 1.0

CM2 specifies factors for the direct input mass matrix. The total mass matrix is:

where

is selected via the subcase information

command M2GG, and is generated from the mass element entries in the bulk data section.

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PARAM, CMFTINIT Parameter CMFTINIT

Values

Description

0.0 < REAL < 1.0 PARAM, CMFTINIT defines the lower threshold value used Default = 0.0 for the HyperMesh command files *.HM.comp.cmf and *.HM.ent.cmf. These command files are used to organize elements, which formed a topology or free-size design space, into components (.comp.cmf) or sets (.ent.cmf), based on their optimized densities/thicknesses.

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PARAM, CMFTSTEP Parameter CMFTSTEP

Values

Description

0.0 < REAL < 1.0 Default = 0.1

PARAM, CMFTSTEP defines the step or interval value used for the HyperMesh command files *.HM.comp.cmf and *.HM.ent.cmf. These command files are used to organize elements, which formed a topology or free-size design space, into components (.comp.cmf) or sets (.ent.cmf), based on their optimized densities/thicknesses.

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PARAM, CMSALOD Parameter CMSALOD

Values

Description

Default = YES

PARAM, CMSALOD controls the generation of RFORCE and Gravity loads from the mass matrix stored in the PUNCH DMIG or H3DDMIG file. If YES, the RFORCE and Gravity loads include the contribution from the mass matrix stored in the PUNCH DMIG or H3DDMIG file. If NO, the DMIG mass contribution is ignored when generating the RFORCE and Gravity loads. Refer to Direct Matrix Input and DMIG.

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PARAM, CMSDIRM Parameter CMSDIRM

Values

Description

YES, NO Default = NO

PARAM, CMSDIRM allows flexible body generation when directional masses are defined in the input file. If YES, the existence of directional mass will be allowed for flexbody generation runs. A warning will be issued for the ignored or approximated CMASS1, CMASS2, and CONM1. If NO, the run will be terminated with an ERROR if the input file contains directional mass definitions and flexible body generation is requested. See the User’s Guide entry on Flexible Body Generation.

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PARAM, CMSOFST Parameter CMSOFST

Values

Description

Default = NO

PARAM, CMSOFST applies to Component Mode Synthesis (CMS) runs for flexbody generation. While element offsets are valid for DMIG generation, that is performing CMS with METHOD = CBN or GUYAN, they are undesirable for flexbody generation, that is performing CMS with METHOD = CC or CB, as it may introduce approximation error into the generated flexh3d file, and so in general, you will not solve these problems. However, the approximation error for plates offset by half of their thickness, such that the grids can be aligned on one side of the plate surface, is tolerable. Setting this parameter to YES will allow problems with this kind of offset to be solved.

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PARAM, COEFFC Parameter

Values

Description

COEFFC

Real > 0.0

Value of the friction coefficient on curvatures for onestep stamping simulation.

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PARAM, COMP2SHL Parameter

Values

Description

COMP2SHL

YES, NO, BULK Default = NO

If YES or blank, results of homogenization of composite properties (equivalent shell and material, PSHELL and MAT2) will be printed in a descriptive form in the “.out” file. If NO, echo of composite homogenization will not be printed. If BULK, then results of composite homogenization (equivalent PSHELL and MAT2) will be printed in a version corresponding to bulk data input in large field (long) format. This version can be cut and pasted directly into an OptiStruct input deck. Note: The equivalent shell and materials represent composite properties as they are defined in the input deck. In optimization runs involving composites, OptiStruct internally adjusts and changes the composite properties. Such changes are not reflected in the equivalent shell results printed by this command.

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PARAM, CONTFEL Parameter

Values

Description

CONTFEL

Default = NO

If YES, Contact-friendly elements are activated. PARAM, CONTFEL, YES is recommended when second order solids/gaskets are used with contact analysis in OptiStruct. If NO, Contact-friendly elements are not activated.

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PARAM, COUPMASS Parameter

Values

Description

COUPMASS

-1, 0, 1, YES, NO Default = NO

If -1, 0 or NO, the lumped mass matrix approach is used for eigenvalue analysis. If 1 or YES, the coupled mass matrix approach is used for eigenvalue analysis.

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PARAM, CP2 Parameter

Values

Description

CP2

Real Default = 1.0

CP2 specifies factors for the direct input load matrix. The total load matrix is:

where

is selected via the subcase information

command P2G, and is generated from the static load entries in the bulk data section.

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PARAM, CSTEVAL Parameter

Values

Description

CSTEVAL

YES, NO Default = YES

This parameter controls whether to use wall time based cost evaluation to provide the optimal performance in running Lanczos steps. The wall time based cost evaluation is a function of system performance, hence it could be influenced by the system load. Although it rarely happens, this influence could result in a different number of Lanczos steps, which could cause the resulting eigenvalues having a round off difference. In most cases, this small difference in solution is completely negligible for analysis. However, it can produce visible differences in optimization runs or in any solution that is sensitive to the small difference of the obtained eigenvalues and eigenvectors. If Yes, the wall time based cost evaluation is performed. If NO, the wall time based cost evaluation is not performed.

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PARAM, CSTOL Parameter

Values

Description

CSTOL

Default = 3.5

PARAM, CSTOL relates to the FastFRS interface. If the low rank representation is not selected, then a cancellation tolerance must be provided. The CSTOL value specifies how many decimal digits may be lost to cancellation in one operation during the eigensolution process. Since double precision arithmetic maintains nearly 16 digits of precision, the recommended limit of 3.5 on the number of digits lost leaves more than 12 digits, which is quite conservative for maintaining adequate accuracy for engineering purposes. You may choose to increase this value to speed computation, at the risk of introducing inaccuracy from uncorrected cancellation error. Setting it to 16 turns off the capability to address cancellation error in the eigensolution, and this has consistently been found to give very satisfactory results when the number of modes is under three thousand. Refer to the User’s Guide section, FastFRS Usage (Fast Frequency Response Solver) for more details.

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PARAM, DFREQ Parameter

Values

Description

DFREQ

Real Default = 10-5

DFREQ specified the threshold for the elimination of duplicate frequencies on all FREQi bulk data entries. and

are considered duplicated if

where and are the maximum and minimum excitation frequencies of the combined FREQi entries.

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PARAM, DISIFMCK Parameter

Values

Description

DISIFMCK

Default = NO

For vibrational eigenvalue analysis, the mass matrix must be positive semi-definite. However, if this is simply caused by numerical ill-conditioning, then PARAM,DISIFMCK may be used to skip the indefinite mass matrix check. YES

Skip indefinite mass matrix checking.

NO

Perform indefinite mass matrix checking.

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PARAM, DISJOINT Parameter

Values

Description

DISJOINT

DISJOINT is used to allow AMLS to handle disconnected Default = NONE parts. This can also be accomplished with PARAM,AMLSUCON. PARAM, DISJOINT should be set to one larger than the number of disconnected parts as determined by AMLS. PARAM, DISJOINT causes the environment variable AMLS_NPART to be set to the value of PARAM, DISJOINT. AMLS will read the value of AMLS_NPART and handle the disconnected structure. PARAM, DISJOINT can be set to a real value for compatibility, but it is recommended to use an integer value.

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PARAM, DUPTOL Parameter

Values

Description

DUPTOL

PARAM, DUPTOL controls how many decimal places Default = 0 can differ when comparing X, Y, and Z coordinates on GRID and CORDxx cards with identical ID. Obsolete, use SYSSETTINGS,DUPTOL command.

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PARAM, EFFMAS Param eter

Values

Description

EFFMA S

Default = NO

When EFFMAS < 0 or NO, the modal participation factors, modal participation factor ratio, and modal effective mass are not output for normal modes analysis. When EFFMAS > 0 or YES, the modal participation factors, modal participation factor ratio, and modal effective mass will be computed and output to the .out and .pch files for normal modes analysis. They are computed as follows:

Modal Participation Factor = The Modal Participation Factor is a measure of how close each mode is to a rigid body mode. The Modal Participation Factor Ratio is the Modal Participation Factor for each rotational and translational direction divided by the maximum Modal Participation Factor of all the modes for that direction. So, each of the six directions will have a value of 1.0 for the mode that has the maximum Modal Participation Factor and the other modes will have a value less than 1.0.

Modal Effective Mass = The Modal Effective Mass is a measure of how much mass is associated with each mode. whe re

Altair Engineering

is the matrix of eigenvectors. [m]

is the system mass matrix.

[V]

is the objective function matrix. Six rigid body modes are used as objective function in normal modes analysis to obtain [PF] and [EFFMAS].

[M]

is the diagonal modal mass matrix.

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PARAM, EHD Parameter

Values

Description

EHD

Default = NO

This parameter is used to print the inverse of the stiffness matrix created by static reduction to FORTRAN unit 3. The inverse reduced stiffness matrix is written in NASTRAN MATPRN format. To perform static reduction there must be ASET data and PARAM,EXTOUT,DMIGPCH in the input data. After the stiffness matrix is reduced to the ASET DOF, its inverse is calculated and written using NASTRAN MATPRN format to FORTRAN unit 3. PARAM,EXTOUT,DMIGPCH must also be specified when this parameter is used in order to trigger the static reduction.

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PARAM, ELASRLMT Parameter ELASRLMT

Values

Description

0.0> Default = 1.0E + 09

This parameter is used to issue a WARNING when the stiffness value for rotational components on the CELAS2/4 or PELAS entry exceeds the specified limit (ELASRLMT). Note: This check is overridden when PARAM, ELASSTIF is used to control the maximum stiffness value.

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PARAM, ELASSTIF Description This parameter can accept two arguments. If only one argument is specified, the same value is used for the second argument. Format PARAM, ELASSTIF, , Parameter ELASSTIFT

ELASSTIFR

Values

Description

This parameter controls the value of field “K” in the 0.0> PELAS scalar elastic property entry and the CELAS2/ CELAS4 scalar spring property and connection entries. No default ELASSTIFT: This value applies to translational stiffness fields on the PELAS scalar elastic property entry and the CELAS2/ CELAS4 scalar spring property and connection entries. ELASSTIFR: This value applies to rotational stiffness values on the PELAS scalar elastic property entry and the CELAS2/ 0.0> CELAS4 scalar spring property and connection entries. Default =

Note: 1.

Any value on the field “K” on the PELAS or CELAS2/ CELAS4 entry which exceeds ELASSTIFT or ELASSTIFR, respectively will be replaced by ELASSTIFT or ELASSTIFR.

2.

Either ELASSTIFT or ELASSTIFR (or both) can be set to 0.0. This will disable stiffness control for the corresponding translational or rotational stiffnesses.

3.

Defaults: a. If ELASSTIFT is input without specifying a value, then OptiStruct will error out (no default). The default for ELASSTIFR is ELASSTIFT. b. If PARAM, BUSHSTIF is not included in the deck, the elastic property value (Field K) is not replaced regardless of its value (no stiffness control).

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PARAM, ELASTLMT Parameter ELASTLMT

Values

Description

0.0> Default = 1E+07

This parameter is used to issue a WARNING when the stiffness value for translational components on the CELAS2/4 or PELAS entry exceeds the specified limit (ELASTLMT). Note: This check is overridden when PARAM, ELASSTIF is used to control the maximum stiffness value.

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PARAM, ENFMOTN Parameter

Values

Description

ENFMOTN

Default = ABS

If ABS, TOTAL or blank, the displacements/velocities/ accelerations output during Modal Frequency Response Analysis and Modal Transient Response Analysis are the total/absolute displacements/velocities/accelerations that include the specified enforced motion. Stresses/ forces will be calculated (if requested) based on the total displacements/velocities/accelerations. If REL, the displacements/velocities/accelerations output during Modal Frequency Response Analysis and Modal Transient Response Analysis are relative to the enforced motion specified in the model. Stresses/forces will be calculated (if requested) based on the relative displacements/velocities/accelerations.

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PARAM, ERPC Parameter

Values

Description

ERPC

Real > 0.0 Default = 1.0

The speed of sound used in the ERP calculation:

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PARAM, ERPREFDB Parameter

Values

Description

ERPREFDB

Real > 0.0 Default = 1.0

This parameter can be used to specify the reference power value used to calculate Equivalent Radiated Power (ERP) in decibels (dB). Note: The Equivalent Radiated Power (ERP) in decibels can be calculated using the following equation:

Where, ERPdB is the Equivalent Radiated Power in decibels. RHOCP is the value of the scale factor specified using the parameter PARAM, RHOCP. ERPREFDB is the reference power value specified using this parameter.

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PARAM, ERPRHO Parameter

Values

Description

ERPRHO

Real > 0.0 Default = 1.0

The fluid density used in ERP calculations:

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PARAM, ERPRLF Parameter

Values

Description

ERPRLF

Real > 0.0 Default = 1.0

The Radiation Loss Factor used in the ERP calculation:

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PARAM, EXCEXB Parameter EXCEXB

Values

Description

This parameter controls the output of the AVL/EXCITE .exb file directly from OptiStruct. Defaults If this parameter If YES, the AVL/EXCITE .exb file is output. is included in the If BOTH, the AVL/EXCITE .exb file and the old files input file, but, no (.doft, .geom, _mff.out4, _x2oa.out4, and .out4) value is provided, are output. then the default value is YES. If NO, the AVL EXCITE interface output files are not If this parameter output. is not included in Note: PARAM, EXCEXB, YES/BOTH should be used in the input file (and conjunction with PARAM, EXCOUT. OptiStruct will PARAM, EXCOUT error out if PARAM, EXCEXB, YES/BOTH is is present), then specified without PARAM, EXCOUT in the model. the default value is BOTH.

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PARAM, EXCOUT Parameter

Values

Description

EXCOUT

Default = 0

Output of condensed superelement information for AVL/ EXCITE. -1

No output.

0

All output.

1

DOF, geometry, and elements tables (GEOM1, GEOM2, EQEXIN, and USET), as well as the reduced mass and stiffness matrices (MAA and KMAA).

3

1 + eigenvectors of the full system (GOA transpose).

4

3 + unreduced mass matrix (MFF).

5

1 + eigenvectors of condensed system (PHA) and the grid point stress table (OGS1).

6

4 + eigenvectors of condensed system (PHA) and the grid point stress table (OGS1).

1.

When PARAM,EXCOUT,1 is defined, only the ASET dofs are output when the MODEL card is not present. Otherwise, the entire model is output when the MODEL card is not present.

2.

PARAM, EXCEXB, BOTH is automatically activated if PARAM, EXCOUT is present in the input deck.

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PARAM, EXPERTNL Parameter

Values

Description

EXPERTNL

YES, NO, CNTSTB, AUTO

YES activates a nonlinear "expert system" that aids in the convergence of small displacement nonlinear problems (NLSTAT). This version is designed to facilitate obtaining converged, high accuracy solutions without much concern for computational time. The system monitors the convergence of nonlinear processes and, if needed, implements measures designed to improve convergence for poorly converging cases. These measures include: performing additional iterations, under-relaxation, automatic adjustment of the load increment, as well as backing off to the last convergent solution and retrying. This may lead to a large number of nonlinear iterations for poorly converging problems.

Default = AUTO

CNTSTB additionally introduces temporary stabilization on contact interfaces (CONTACT or GAP(G) elements) that may improve nonlinear convergence, especially in cases where individual parts lack full support and are supported only by contact. The stabilization is applied only during incremental loading and is not present in the final solution for the respective nonlinear subcase. AUTO activates a “light” version of the expert system, which is designed to facilitate converging nonlinear process in reasonably close to minimum number of iterations. In particular, this version may adjust the time step, including increasing the time step beyond that prescribed on the NLPARM card. This parameter does not apply to geometric nonlinear solution sequences (NLGEOM, IMPDYN or EXPDYN).

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PARAM, EXTOUT Parameter

Values

Description

EXTOUT

DMIGPCH, DMIGBIN No default

EXTOUT controls the output of reduced matrices to external data files for use in subsequent analyses. If DMIGPCH, the matrices are written to an ASCII .pch file. If DMIGBIN, the matrices are written to a binary .dmg file. See the User's Guide section The Direct Matrix Approach for more detailed information.

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PARAM, FASTFR Parameter

Values

Description

FASTFR

If, AUTO (Default), the faster method is automatically Default = AUTO chosen by the program for Modal Frequency Response Analysis. If the FASTFR method is not activated, the standard method is used (see comments). If YES, and if FASTFR is allowed (see comments), it activates an alternative method to run Modal Frequency Response Analysis that enhances the performance. If NO, the FASTFR method is deselected and the program is run using the standard solution method. Comments: The FASTFR method will be ignored for Modal Frequency Response Analysis, if: 1.

Multiple modal spaces exist in the model.

2.

Single Program, Multiple Data (SPMD) parallelization has been requested.

3.

Viscous degrees of freedom are significantly large.

The FASTFR method will be allowed, if Shared Memory Parallelism (SMP) parallelization has been requested by specifying the number of processors using the –nproc run option.

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PARAM, FFRS Parameter

Values

Description

FFRS

Default = NO

This parameter is used to invoke the external FastFRS (Fast Frequency Response Solver). This solver is very efficient for a certain class of large modal frequency response problems, such as those common in automotive NVH analysis. Note that FastFRS must be installed on the system and the environment variable FASTFRS_EXE must point to the FastFRS executable for this setting to work. If YES, then the external FastFRS solver is used. If NO, then the internal solver is used. Refer to the User’s Guide section, FastFRS Usage (Fast Frequency Response Solver) for more details.

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PARAM, FFRSLFREQ Parameter

Values

Description

FFRSLFREQ

Default = 1.0

PARAM, FFRSLFREQ relates to the FastFRS interface. It defines a frequency cut-off value in Hertz used to partition the structural system into low frequency and high frequency parts, to improve matrix condition numbers and solution accuracy at a very small computational cost. If the value is defined as 0.0, then FastFRS will set FFRSLFREQ to 1.0. Refer to the User’s Guide section, FastFRS Usage (Fast Frequency Response Solver) for more details.

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PARAM, FFRSMEM Parameter

Values

Description

FFRSMEM



This parameter is used to define the amount of memory in Gigabytes to be used by the external FastFRS modal equation solver. This parameter is only valid for FastFRS versions 2 and higher.

Default = Memory used by OptiStruct for a particular run.

Note: 1.

If this parameter is not set, FastFRS will use the amount of memory that OptiStruct is using for the run.

2.

If the environment variable FFRS_MEM is set, it will override the value set using PARAM, FFRSMEM.

3.

OptiStruct and FastFRS can be run with different allocations of memory. For example, OptiStruct can be run with 10.0 Gigabytes and FastFRS with 20.0 Gigabytes in the same run.

4.

This parameter is only valid when PARAM, FFRS is set to YES.

Refer to the User’s Guide section, FastFRS Usage (Fast Frequency Response Solver) for more details.

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PARAM, FFRSNCPU Parameter FFRSNCPU

Values

Description

Default = number of cpu's used by OptiStruct.

PARAM, FFRSNCPU relates to the FastFRS interface. This parameter is used to define the number of cpu’s to be used by the external FastFRS solver. This parameter will set the environment variable OMP_NUM_THREADS. The default value is the current value of OMP_NUM_THREADS. Note 1.

If FFRSNCPU is not set, but AMLSNCPU is set, the FastFRS will use the number of cpu’s specified by AMLSNCPU.

2.

OptiStruct and FastFRS can be run with different allocations of processors. For example, OptiStruct can be run with one processor and FastFRS with four processors in the same run.

3.

This parameter is only valid when PARAM, FFRS or the run option –ffrs is set to YES.

Refer to the User’s Guide section, FastFRS Usage (Fast Frequency Response Solver) for more details.

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PARAM, FLEXH3D Parameter

Values

Description

FLEXH3D

AUTO, YES, NO Default = AUTO

This parameter controls the generation of flexh3d files for flexible bodies in an MBD analysis. If AUTO, flexh3d files are generated only for those flexible bodies for which no previously generated flexh3d file exists. Previously generated flexh3d files are checked for validity; if the file is valid for the corresponding flex-body definition, the run will continue using the existing flexh3d file. If the file is found to be invalid (has a different mass or the wrong number of grids), an error termination will occur. If YES, flexh3d files are generated for all flexible bodies, overwriting existing files (if present). If NO, flexh3d files are not generated. The run makes use of previously generated files. An error termination will occur if no such files exist.

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PARAM, FLIPOK Parameter

Values

Description

FLIPOK

NO, YES Default = NO

If YES, severely distorted and possibly inverted elements will be accepted by the solver. This is limited to first order tetra (CTETRA) and tria (CTRIA3) elements. If NO, severely distorted elements will not be accepted by the solver, and the solution will be terminated with an error to avoid inaccurate results.

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PARAM, FRIC Parameter

Values

Description

FRIC

Default = 1.0

PARAM, FRIC defines a multiplier for matrices (DMIG) referenced by K2PP.

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PARAM, FZERO Parameter

Values

Description

FZERO

Default = 0.1

This parameter defines the maximum frequency for a rigid body mode for the Lanczos eigensolver. That is all eigenmodes with frequency at or below this cutoff will be regarded as rigid body modes in the inertia relief analysis. Note: To set the rigid body mode cutoff eigenvalue for the AMSES and AMLS eigensolvers, use PARAM, RBMEIG.

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PARAM, G Parameter

Values

Description

G

Default = 0.0

G specifies the uniform structural damping coefficient in the formulation of dynamics problems. To obtain the value for the parameter G, multiply the critical damping ratio, C/C0 by 2.0. Note: To achieve identical displacements in Modal frequency response or Modal transient analyses when the SDAMPING bulk data entry is used instead of PARAM, G, the steps described here can be followed: 1.

The TYPE field in the TABDMP1 bulk data entry should be set to CRIT. This TABDMP1 bulk data entry is referenced by the SDAMPING subcase information entry.

2.

Set the damping value (field gi) in the TABDMP1 bulk data entry equal to half of the value of PARAM, G (that is set the constant value to C/C0).

3.

Set PARAM, KDAMP,-1.

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PARAM, GE_MOD Parameter

Values

Description

GE_MOD

No default

The real value of GE_MOD overrides the value of GE specified in all MATx material data, sets the table ID for GE on the MATTx material data to zero, and overrides the value of GE specified on the PCOMP, PCOMPP, and PCOMPG data. GE_MOD can be set to 0.0 to remove all material-based structural damping from the model. The damping from PARAM, G will also be applied when GE_MOD is present. The GE_MOD setting of NO_GE is used to remove all structural damping from the model. When NO_GE is specified, the value of GE will be set to zero on all MATx material data and the GE values specified in the CELAS2, PELAS, PELAST, PBUSH, PBUSHT, PCOMP, PCOMPP, and PCOMPG data will also be set to zero. In addition, the table ID for GE on MATTx material data will be set to zero. PARAM, G can be used to set the value to a constant value for the entire structure.

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PARAM, GFL Parameter

Values

Description

GFL

Default = 0.0

GFL specifies the uniform fluid damping coefficient in the formulation of dynamics problems. To obtain the value for the parameter GFL, multiply the critical damping ration, C/C0, by 2.0. In coupled fluid-structure models, PARAM, G is applied to structural portion and PARAM, GFL to the fluid portion.

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PARAM, GMAR Parameter

Values

Description

GMAR

Default = 1.1

PARAM, GMAR is used to control the accuracy of the AMLS solution. Refer to the User’s Guide section, Using the AMLS (Automatic Multi-Level Sub-structuring) Eigensolver for more details.

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PARAM, GMAR1 Parameter

Values

Description

GMAR1

Default = 1.7

PARAM, GMAR1 is used to control the accuracy of the AMLS solution. Refer to the User’s Guide section, Using the AMLS (Automatic Multi-Level Sub-structuring) Eigensolver for more details.

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PARAM, GPSLOC Parameter GPSLOC

Values

Description

Z1, Z2 and MID Used to control the where grid point stresses are calculated for output to the .mnf file. Default = Z1 The highest stresses are at the bottom (Z1) or top (Z2) surface of the shell. For pure bending, they have the same magnitude. GPSLOC is used to specify the location of the calculation of the grid point stresses. They can be calculated at the bottom surface (Z1), top surface (Z2), or at the midplane (MID).

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PARAM, GRDPNT Parameter GRDPNT

Values

Description



If = -1, no output from grid point weight generator.

Default = -1

If = 0, the center of gravity coordinates are relative to the origin of the basic coordinate system and are expressed in the coordinate system CID. If > 0, the center of gravity coordinates are relative to GID and are expressed in the coordinate system CID. Note: 1.

The coordinate system CID is defined by PARAM, UCORD.

2.

If PARAM, UCORD is not specified, CID = -1, or CID given is not found, all values are calculated relative to the basic coordinate system.

3.

If PARAM, GRDPNT is not specified in the input deck, then the center of gravity and moment of inertia are not output regardless of the value of PARAM, UCORD.

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PARAM, GRIDFORM Parameter

Values

Description

GRODFORM

< LONG, SHORT > Default = SHORT

This parameter controls the output format of the .grid file. If LONG, the Large Field Fixed Format is used to output the .grid file. If SHORT (Default), the Fixed Format is used to output the .grid file.

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PARAM, GYROAVG Parameter GYROAVG

Values

Description

Default = 0

This parameter is used to select the frequency response analysis formulation type for rotor dynamics analysis. PARAM, GYROAVG, 0 If this formulation is selected, the frequencydependent rotor dynamics terms are calculated for each frequency. A frequency-dependent looping option is activated, however, the run time is higher compared to PARAM, GYROAVG, -1 as the calculation process has to be repeated for each frequency in the specified range. PARAM, GYROAVG, -1 If this formulation is selected, frequency-dependent looping does not occur and an average frequency method is used to calculate the rotor dynamic terms. The run time is lower compared to PARAM, GYROAVG, 0 as this option avoids intensive calculations for each frequency. PARAM, WR3 and PARAM, WR4 must be specified for this formulation to include rotor damping. Refer to the User’s Guide section, Rotor Dynamics for more details.

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PARAM, HASHASSM Parameter

Values

Description

HASHASSM

YES, NO Default = NO

This parameter is used to enable the hash-table based assembly method. The hash-table based assembly method reduces the memory requirement of the assembly module by about a factor of 3 for linear static analyses, by about a factor of 5 for eigenvalue analyses, and by about a factor of 7 for frequency response analyses involving material damping. The reduction in the overall memory requirement is problem-dependant. For problems where modules other than the assembly module are dictating the overall memory requirement, using this alternative assembly method will not result in a reduction in the overall memory requirement. Using the hash-table based assembly method while possibly reducing memory requirements may result in longer run times. If YES, hash-table based assembly method is used. If NO, hash-table based assembly method is not used.

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PARAM, HFREQ Parameter

Values

Description

HFREQ

Real> (Hertz)

Modes with frequencies higher than HFREQ are not used in Modal Frequency Response and Modal Transient Analysis.

Default = None Defaults

HFREQ is used in Response Spectrum Analysis to specify the upper bound of the frequency range of interest for modal combination.

If PARAM, HFREQ is input Note: without 1. The Residual Vector (RESVEC) calculation still specifying a includes the modes above HFREQ so that they are value, then the normalized correctly. solution runs into an error 2. Modes that are eliminated by PARAM, HFREQ will display:

a) an “S” next to the mode number if the mode is eliminated by MODESELECT in one subcase and PARAM, HFREQ in another subcase, or b) an “H” next to the mode number if the mode is eliminated only by PARAM, HFREQ.

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PARAM, HFREQFL Parameter

Values

Description

HFREQFL

Real> (Hertz)

Modes with frequencies greater than HFREQFL are not used in Coupled Modal Frequency Response Analysis. HFREQFL can be used to remove Rigid Body Modes from the Modal Space.

Default = None Defaults If PARAM, HFREQFL is input without specifying a value, then the solution runs into an error

Altair Engineering

Note: Modes that are eliminated by PARAM, HFREQFL will display an “H” next to the mode number.

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PARAM, I64SLV Parameter

Values

Description

I64SLV

YES, NO Default = NO

This parameter is used to enforce the activation of internal long (64-bit) integer sparse direct solver. With automatic memory allocation mode, the solver automatically decides whether or not to switch the 64-bit integer solver on. However, even if the 64-bit integer solver is not the preferred choice in certain scenarios, this parameter can still be used to enforce activation. YES: the long (64-bit) integer sparse direct solver is used. NO: the short (32-bit) integer sparse direct solver is used.

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PARAM, INREL Parameter

Values

Description

INREL

< 0, -1, -2 >

INREL controls the calculation of inertia relief.

Default = 0, for static subcases

-2 requests inertia relief analysis without the need for a SUPORT/SUPORT1 entry.

Default = -2, for modal frequency response subcases

-1 requests that inertia relief be performed. SUPORT or SUPORT1 cards are required in the bulk data section to restrain rigid body motion. The total number of degrees-of-freedom specified on SUPORT and SUPORT1 cards must be less than or equal to six. 0 requests that constrained analysis be performed. SUPORT and SUPORT1 cards are treated like SPC in this case.

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PARAM, ITAPE Parameter

Values

Description

ITAPE

-1, 0 Default = -1

If ITAPE = -1, then the ‘Tape Label’ is written at the beginning of the OUTPUT2 results file.

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PARAM, INTRFACE Parameter

Values

Description

INTRFACE

YES, NO Default = YES

If YES, OptiStruct generates the .interface file which contains data about the Fluid-Structure Coupling. The .interface file can then be loaded into HyperMesh to verify if the Fluid and Structure meshes are properly connected at the interface. The parameters that determine the Fluid-Structure coupling are set in the ACMODL Data. If NO, the .interface file is not generated.

Comments 1.

When the fluid domain is represented by an MFLUID card, and PARAM, INTRFACE, YES is specified, OptiStruct generates the .wetel file which contains data about the wet elements resulting from MFLUID cards. The .wetel file can then be loaded into HyperMesh to visualize the locations of submerged/damp elements in the model.

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PARAM, K4CUTOFF Parameter

Values

Description

K4CUTOFF

Default = 0.1

PARAM, K4CUTOFF relates to the FastFRS interface. If the low rank representation for the structural damping matrix is selected, a cut-off value must be set. The value is set using K4CUTOFF. Refer to the User’s Guide section, FastFRS Usage (Fast Frequency Response Solver) for more details.

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PARAM, KDAMP Parameter

Values

Description

KDAMP

< 1, -1 > Default = 1

If KDAMP is set to –1, modal damping is entered into the complex stiffness matrix as material damping. If KDAMP is set to 1, modal damping is entered into the complex stiffness matrix as viscous damping. Note: To achieve identical displacements in Modal frequency response or Modal transient analyses when the SDAMPING subcase information entry is used instead of PARAM, G, the steps described here can be followed:

Altair Engineering

1.

The TYPE field in the TABDMP1 bulk data entry should be set to CRIT. This TABDMP1 bulk data entry is referenced by the SDAMPING subcase information entry.

2.

Set the damping value (field gi) in the TABDMP1 bulk data entry equal to half of the value of PARAM, G (that is set the constant value to C/C0).

3.

Set PARAM, KDAMP,-1 (See description above).

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PARAM, KGRGD Parameter

Values

Description

KGRGD

YES, NO Default = NO

If YES, the rigid elements contribution to the geometric stiffness matrix is included. This may result in missing buckling modes that are found in other codes. If NO, the rigid elements contribution to the geometric stiffness matrix is omitted. This is the default.

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PARAM, LFREQ Parameter

Values

Description

LFREQ

(Hertz)

Modes with frequencies less than LFREQ are not used in Modal Frequency Response and Modal Transient Analysis. LFREQ can be used to remove Rigid Body Modes from the Modal Space.

Default = None Defaults If PARAM, LFREQ is input without specifying a value, then the solution runs into an error.

LFREQ is used in Response Spectrum Analysis to specify the lower bound of the frequency range of interest for modal combination. Note: 1.

The Residual Vector (RESVEC) calculation still includes the modes below LFREQ so that they are normalized correctly.

2.

Modes that are eliminated by PARAM, LFREQ will display: a) an “S” next to the mode number, if the mode is eliminated by MODESELECT in one subcase and PARAM, LFREQ in another subcase, or b) an “L” next to the mode number, if the mode is eliminated only by PARAM, LFREQ.

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PARAM, LFREQFL Parameter

Values

Description

LFREQFL

Real> (Hertz)

Modes with frequencies less than LFREQFL are not used in Coupled Modal Frequency Response Analysis. LFREQFL can be used to remove Rigid Body Modes from the Modal Space.

Default = None Defaults If PARAM, LFREQFL is input without specifying a value, then the solution runs into an error

Note: Modes that are eliminated by PARAM, LFREQFL will display an “L” next to the mode number.

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PARAM, LGDISP Parameter

Values

Description

LGDISP

Default = 0

If LGDISP = 1, Large displacement nonlinear static analysis is activated. The corresponding nonlinear solution parameters should be specified in the NLPARM bulk data entry. If LGDISP = 0 or -1, Large displacement nonlinear static analysis is deactivated (Small displacement nonlinear static analysis is the default). The corresponding nonlinear solution parameters should be specified in the NLPARM bulk data entry.

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PARAM, LMSOUT Parameter

Values

Description

LMSOUT

body modes, full diagonal mass matrix, and modal stresses Default = NO to the .op2 file. If YES, the condensed flex body modes and the full diagonal mass matrix are output to the .op2 file. If STRESS, the modal stresses are also output to the .op2 file. If NO, the condensed flex body modes, full diagonal mass matrix and the modal stresses are not output to the .op2 file.

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PARAM, LOWRANK Parameter

Values

Description

LOWRANK

PARAM, LOWRANK relates to the FastFRS interface. Default = 0 It indicates to FastFRS which solution strategy to use to handle the modal structural damping matrix. If the value is 0, then FastFRS computes a full eigensolution using the data found in either the optimization FSPSD data block or the diagonal stiffness and structural damping data blocks. If the value is -1, a low rank representation of the matrix found in structural damping is used. A special case of this option occurs when acoustic fluid is present in the model and the matrices found in the fluid mass matrix, fluid stiffness matrix, and fluid viscous damping matrix data blocks are all diagonal. FastFRS takes advantage of this special case when the value of LOWRANK is set to 1 by treating the matrix found in the structural damping data block and the fluid matrices as low rank representations. Note that for optimization problems, the mass and stiffness matrices are full and a low rank representation cannot be used. Refer to the User’s Guide section, FastFRS Usage (Fast Frequency Response Solver) for more details.

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PARAM, MASSDMIG Parameter

Values

Description

MASSDMIG

YES, NO Default = NO

For static condensation with ASET of a static loadcase, the reduced stiffness matrix [k] and load vector {p} are created. If the reduced mass matrix is also desired, then set PARAM, MASSDMIG to YES.

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PARAM, MAXDAMP Parameter MAXDAMP

Values

Description

Default = 400

Identifies the maximum number of viscous residual vectors that are to be calculated. If MAXDAMP is exceeded, a WARNING message is issued and no viscous residual vectors are calculated. Solution times can be greatly extended due to the calculation of large numbers of viscous residual vectors, if this is not intended by the user.

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PARAM, MBDH3D Parameter

Values

Description

MBDH3D

NODAL, MODAL, BOTH, NONE Default = BOTH

This parameter controls the type of results output to the .h3d results format for MBD analyses. If NODAL, nodal based results are output to the .h3d results file. If MODAL, modal based results are output to the _mbd.h3d results file. If BOTH, nodal results are output to the .h3d results file and modal results are output to the _mbd.h3d file. If NONE, MBD results are not output to either the .h3d or _mbd.h3d results file. Note: If the HyperMesh output format is requested, nodal based results will be output to the .res file, regardless of this parameter setting.

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PARAM, MBDREC Parameter

Values

Description

MBDREC

YES, NO Default = NO

PARAM, MBDREC creates two flexible body files during Component Mode Synthesis (CMS). A small *.h3d is generated that contains the minimum amount of information required for MBD simulation in MotionSolve. A larger file *_recov.h3d will also be generated that contains the information from the small file as well as recovery information for displacement, velocity, acceleration, stress, and strain. The large file is used along with the MotionSolve calculated result (.mrf) file specified with the ASSIGN, MBDINP data in an OptiStruct transient analysis to recover displacement, velocity, acceleration, stress, and strain results of the flex body. These results can be output in the .op2 and .h3d files. See the User’s Guide entry on Flexible Body Generation.

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PARAM, MEMTRIM Parameter MEMTRIM

Values

Description

YES, NO This parameter is used to activate/deactivate the memory Default = YES trim feature for AMLS runs. AMLS is an external program that requires its own memory and disk space to perform eigenvalue analysis. Without memory trim, the total memory requirement (T) to perform eigenvalue analysis using AMLS was the sum of the memory required by OptiStruct (O), the memory exclusively allocated for AMLS (A), and other miscellaneous memory requirements; for example, MIO library requirement, (M). Thus: T = O + A + M. With memory trim enabled, the total memory requirement is reduced to: T = max(O,A) + M. If YES, memory trim is active. If NO, memory trim is inactive.

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PARAM, MFILTER Parameter

Values

Description

MFILTER



This parameter defines a threshold for the mode tracking matrix to check eigenvector correspondence.

Defaults:

If an entry of the mode tracking matrix is greater than the specified threshold, the eigenvectors of previous and current iterations (corresponding to the row number and column number of the entry) are assumed to have correspondence.

-If this parameter is included in the input file, but, no value is provided, then running the program will result in an error. In such cases a real value between 0.0 and 1.0 must be specified. - If this parameter is not included in the input file, then:

If PARAM, TRAKMETH is set to 0, the mass matrix based cross-orthogonality criterion (CORC) is used to check for eigenvector correspondence, and PARAM, MFILTER is set to 0.7. If PARAM, TRAKMETH is set to 1, the modal assurance criterion square root (MACSR) is used, and PARAM, MFILTER is set to 0.7. If PARAM, TRAKMETH is set to 2, the modal assurance criterion (MAC) is used and PARAM, MFILTER is set to be 0.5.

The value of PARAM, MFILTER is equal to 0.7 if PARAM, TRAKMETH is set to 0 or 1. The value of PARAM, MFILTER is equal to 0.5 if PARAM, TRAKMETH is set to 2.

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PARAM, MODETRAK Parameter

Values

Description

MODETRAK

-1, 0, 1, YES, NO Default = NO

If -1, 0 or NO, mode tracking is not used. Mode numbers are determined by frequency. If 1 or YES, mode tracking is used. Mode numbers are tracked by comparing eigenvectors between iterations. Concerning mode tracking, the following symbols are used in the output format:

*

Indicates that the tracked mode was not found in the modes retrieved for that iteration. If this mode is not a part of the objective, optimization will continue and mode will be tracked if found in later iterations, otherwise optimization will stop. If optimization is halted for this reason, increase the number of modes or range of modes being retrieved.

~

Indicates that the tracked mode was found but does not correlate well with the original mode. Optimization will continue.

Note: In topology optimization, mode shapes can change greatly due to the reorganization of material within the design domain. For some models, mode tracking may be of limited effectiveness. Also, the values of optimized modes may increase substantially during the optimization process. You are advised to provide a wide range or large number of modes in the EIGRL card to protect against optimized modes being lost. Note: This parameter is ignored if a MODTRAK subcase information entry is present in the input.

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PARAM, NEGMASS Parameter NEGMASS

Values

Description

0, 1 Default = 0

This parameter is used to check for negative diagonal mass. If 0, an error termination will occur if negative diagonal mass is discovered. If 1, negative diagonal mass or inertia from CONM2 is allowed.

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PARAM, NLAFILE Parameter NLAFILE

Values

Description

Default = NO

This parameter controls the output of animation files (A-File) in geometric nonlinear analysis. If YES, the animation files are retained after geometric nonlinear analysis; If NO, the animation files are removed after geometric nonlinear analysis.

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PARAM, NLFAT Parameter NLFAT

Values

Description

Default = NO Defaults: 1. If this parameter does not exist in the deck, the default behavior is NO. 2. If this parameter exists in the deck, however, no value (YES/ NO) is specified, then the default behavior is NO.

PARAM, NLFAT, YES, forces OptiStruct to run models in which fatigue solutions (using the FATLOAD entry) reference nonlinear quasi-static analysis (NLSTAT) subcases. PARAM, NLFAT, NO, does not allow NLSTAT subcases to be referenced by the FATLOAD data entry and the solution errors out if such models are run. Note: PARAM, NLFAT, YES can be introduced to force OptiStruct to run fatigue analysis based on a nonlinear subcase (ANALYSIS=NLSTAT). Nonlinear analysis results are not recommended for use in a fatigue analysis because nonlinear stresses and strains cannot be scaled and superimposed, however, acceptable results may be generated in the following cases: During a nonlinear run (ANALYSIS=NLSTAT), acceptable results may be generated if a model uses elasto-plastic material and NEUBER correction is turned OFF (Plasticity field on FATPARM bulk data entry). This statement is based on the assumption that nonlinear analysis is run until shakedown is achieved. If strain results from the nonlinear analysis are used prior to shakedown, the fatigue results will most likely be incorrect since the magnitude of plastic strain may not be close to the steady state strain value. Additionally, acceptable results may be generated if contact based nonlinearity exists in the model (ANALYSIS=NLSTAT) and the contact area is not expected to change appreciably as the load increases (for example, surfaces that match from the beginning). In both cases, the Scale and Offset fields on the FATLOAD entry should be left blank as the stresses and strains cannot be scaled and superimposed. Regardless of the model type, fatigue results based on nonlinear results using PARAM, NLFAT, YES should always be interpreted with caution.

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PARAM, NLRFILE Parameter NLRFILE

Values

Description

Default = NO

This parameter controls the output of restart files (R-File) in geometric nonlinear analysis. If YES, the restart files are retained after geometric nonlinear analysis; If NO, the restart files are removed after geometric nonlinear analysis.

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PARAM, NLRUN Parameter NLRUN

Values

Description

Default = YES

The parameter controls if geometric nonlinear analysis subcases run automatically after these subcases in bulk format are converted into block format. If YES, geometric nonlinear analysis subcases run automatically after conversion. If NO, geometric nonlinear analysis subcases do not run automatically after conversion.

Altair Engineering

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PARAM, NPRBAR Parameter NPRBAR

Values

Description

Default = 3

Controls the number of the output INFORMATION #741 for RBAR elements. Example of INFORMATION #741, *** INFORMATION # 741 No need to constrain the rotational dof of this dependent grid. RBAR element id = 20436260 independent grid id = 20374048 dependent grid id = 20367448 This is because there isn't any stiffness and load on the rotational dof of the dependent grid.

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Altair Engineering

PARAM, NPRBE2 Parameter NPRBE2

Values

Description

Default = 3

Controls the number of the output INFORMATION #741 for RBE2 elements. Example of INFORMATION #741, *** INFORMATION # 741 No need to constrain the rotational dof of this dependent grid. RBE2 element id = 20436260 independent grid id = 20374048 dependent grid id = 20367448 This is because there isn't any stiffness and load on the rotational dof of the dependent grid.

Altair Engineering

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PARAM, NPRGDE Parameter NPRGDE

Values

Description

Default = 3

Controls the number of the output INFORMATION #742. Example of INFORMATION #742, *** INFORMATION # 742 The dependent rotational dof of this rigid element is removed. RBE2 element id = 20436262 independent grid id = 20374050 a dependent grid id = 20367345 This is because there is no need to constrain the rotational dof of any of the dependent grids.

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Altair Engineering

PARAM, NUMEG Parameter NUMEG

Values 1000

Altair Engineering

Description When ND on the EIGRL/EIGRA data is blank, the disk space estimate in the .out file for modal frequency response and the transient analysis is based on the number of modes specified by PARAM,NUMEG. When Lanczos is used, the disk space estimate is based on this value plus the number of the potential residual vectors. When AMLS/AMSES is used, the disk space estimate is based only on the value of PARAM,NUMEG. In this case, it is assumed that PARAM,NUMEG includes the number of potential residual vectors.

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PARAM, OGEOM Parameter

Values

Description

OGEOM

Default = YES

PARAM, OGEOM controls the output of model (geometry) data to the .op2 file. This functionality is also controlled by the MODEL/NOMODEL option on the OUTPUT, OP2 I/O option, but this parameter setting will override the OUTPUT, OP2 setting. PARAM, OGEOM, YES will output model data to the .op2 file. PARAM, OGEOM, NO will not output model data to the .op2 file.

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Altair Engineering

PARAM, OMACHPR Parameter

Values

Description

OMACHPR

Default = NO

PARAM, OMACHPR controls the Nastran version for some OP2 datablocks. YES means that the new Nastran version should be used. NO means that the old Nastran version should be used.

Altair Engineering

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PARAM, OMID Parameter

Values

Description

OMID

Default = YES

Controls the coordinate system used by shell and membrane elements for stress and strain results. This affects the recovery of optimization responses as well as results output to the HM, PUNCH, and OPTI output formats. Stress and strain results are always output to OUTPUT2 and H3D output formats with reference to the elemental system. YES indicates that shell and membrane stresses/strains are with reference to the material coordinate system, as defined by the MID/THETA field of the element card. NO indicates that shell and membrane stresses/strains are with reference to the elemental coordinate system, regardless of what is defined on the MID/THETA field of the element card.

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Altair Engineering

PARAM, OP2GM34 Parameter

Values

Description

OP2GM34

PARAM, OP2GM34 controls the output of GEOM3 and Default = TRUE GEOM4 data blocks to the .op2 file if PARAM, POST, -1 is specified. PARAM, OP2GM34, TRUE will output GEOM3 and GEOM4 data blocks to the .op2 file if PARAM, POST, -1 is specified. PARAM, OP2GM34, FALSE will not output GEOM3 and GEOM4 data blocks to the .op2 file.

Altair Engineering

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PARAM, PLIGEXT Parameter

Values

Description

PLIGEXT

Default = NO

This parameter is used to print the applied load vector in DMIG form to the .pligext file. The DMIG NAME is PLIGEXT. To generate the .pligext file the oload(opti)=all command must also be requested.

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PARAM, POST Parameter

Values

Description

POST

Default = 0

Adding PARAM, POST to the bulk data section of the input deck will activate the creation of the .op2 file. PARAM, POST, -1 will create the .op2 file with displacement results output in the analysis system and PARAM, ITAPE set to -1. PARAM, POST, -2 will create the .op2 file with displacement results output in the basic coordinate system and PARAM, ITAPE set to 0. The GEOM3, GPDT and GPL data blocks are also included in the .op2 file when PARAM, POST, -2 is used. PARAM, POST, -5 will write the stiffness and mass matrices to the .k.op2 and the .m.op2 files, respectively, in addition to creating the .op2 file with displacement results output in the analysis system and PARAM, ITAPE set to -1.

Altair Engineering

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PARAM, POSTEXT Parameter

Values

Description

POSTEXT

YES, NO Default = NO

If PARAM,POSTEXT,YES, the modal complex stiffness matrix (KHH) and, if it exists, the modal viscous damping matrix (BHH) are written to the .op2 file when frequency response analysis is performed. The modal complex stiffness matrix is:

Where G is the PARAM,G structural damping value and [Kge] is the structural damping matrix based on the structural damping values on the MATi data. The modal viscous damping matrix is:

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PARAM, PRESUBNL Parameter PRESUBNL

Values

Description

YES, NO Default = NO Defaults: If this parameter does not exist in the deck, the default behavior is NO. If this parameter exists in the deck, however, no value (YES/ NO) is specified, then the default behavior is NO.

Altair Engineering

PARAM, PRESUBNL, YES forces OptiStruct to run models, in which Linear Buckling Analysis or Preloaded Analysis is defined, in conjunction with nonlinear materials (MATS1, MATHE, or MGASK) or large displacement nonlinear analysis. PARAM, PRESUBNL, NO does not allow Linear Buckling Analysis or Preloaded Analysis with nonlinear materials or large displacement nonlinear analysis to be defined and the solution errors out if such models are run. Note: Linear Buckling Analysis or Preloaded Analysis is not recommended in models with nonlinear materials or large displacement nonlinear analysis. It is the user’s responsibility to interpret such results with caution.

OptiStruct 13.0 Reference Guide 1643 Proprietary Information of Altair Engineering

PARAM, PRGPST Parameter PRGPST

Values

Description

< YES, NO, ALL, PRGPST controls the printing of AUTOSPC information NONE,< number of to the .out file. DOFs> > PARAM, PRGPST, YES Default = YES

A maximum of 100 degrees of freedom (DOF) of AUTOSPC data will be printed in the .out file. PARAM, PRGPST, NO No AUTOSPC data will be printed. PARAM, PRGPST, NONE Works exactly like PARAM, PRGPST, NO - No AUTOSPC data will be printed. PARAM, PRGPST, ALL All AUTOSPC data will be printed in the .out file. PARAM, PRGPST, A maximum of degrees of freedom (DOF) of AUTOSPC data will be printed in the .out file.

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PARAM, PRINFACC Parameter PRINFACC

Values

Description If 1, the inertia relief rigid body forces and accelerations are printed to the .out file.

Defaults 1. The default is 0, when the parameter is not present in the deck.

If 0, the inertia relief rigid body forces and accelerations are NOT printed to the .out file.

2. The default is 1, when PARAM, PRINFACC is input without specifying a value.

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PARAM, RBE2FREE Parameter

Values

Description

RBE2FREE



Modeling errors can result in the creation of RBE2 elements with rigid body rotations. This parameter can be used to convert ERROR 725 into WARNING 825 when singular RBE2 elements, with rotational rigid body modes in all three directions, are present in the model.

Default = NO

YES If PARAM, RBE2FREE, YES is specified, ERROR 725 is converted into WARNING 825. For AMSES/AMLS SUBCASEs the free rotational degrees of freedom are AUTOSPC’ed. For static analysis and Lanczos eigenvalue analysis, the run may fail due to singularities and ERROR 153 or 155 will be issued. NO If PARAM, RBE2FREE, NO is specified, ERROR 725 is not converted into WARNING 825 and models containing singular RBE2 elements will error out. Note: To solve a problem with Lanczos or static analysis, AMSES can used first to determine which RBE2 degrees of freedom are AUTOSPC’ed. Single point constraints (SPC) can be added to manually constrain such degrees of freedom in subsequent static analysis or Lanczos eigenvalue analysis.

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Altair Engineering

PARAM, RBE3FREE Parameter

Values

Description

RBE3FREE



Modeling errors can result in the creation of RBE3 elements with free spiders. This parameter can be used to convert ERROR 772 into WARNING 824 when free spiders on RBE3 elements are present in the model. These free spiders may contain singular degrees of freedom.

Default = NO

YES If PARAM, RBE3FREE, YES is specified, ERROR 772 is converted into WARNING 824. For AMSES/AMLS runs the free spiders will be AUTOSPC’ed if they are singular. This will cause invalid results as the RBE3 will be constrained to ground. Check the AUTOSPC output to make sure the free spiders are not AUTOSPC’ed. If the free spiders are singular, Lanczos eigenvalue solutions and static analysis runs will fail with ERROR’s 155 or 153. NO If PARAM, RBE3FREE, NO is specified, ERROR 772 is not converted into WARNING. Models containing RBE3 elements with free spiders will error out.

Altair Engineering

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PARAM, RBMEIG Parameter

Values

Description

RBMEIG

Default = 1.0

PARAM, RBMEIG defines the cutoff eigenvalue for determination of rigid body modes calculated by the AMLS and AMSES eigensolvers.

Default

Note: The default 1. PARAM, RBMEIG functions in a similar manner to cutoff PARAM, FZERO, which is used in models solved by the eigenvalue Lanczos eigensolver. (AMSES and AMLS) is 1.0, if 2. The default cutoff eigenvalue of 1.0 is equivalent to a this parameter natural frequency of 0.16 Hz. is not present in the deck. 3. For the Lanczos eigensolver, use PARAM,FZERO to set the cutoff frequency for rigid body modes.

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Altair Engineering

PARAM, REANAL Parameter REANAL

Values

Description

0.0 < Real < 1.0 No default

This parameter is for restart runs of topology optimizations only. Inclusion of this parameter on a restart run will cause the last iteration to be reanalyzed without penalization. If the value given is less than the value of MINDENS (default = 0.01) used in the optimization, all elements will be assigned the densities they had during the final iteration of the optimization. As there is no penalization, stiffness will now be proportional to density. If the value given is greater than the value of MINDENS, those elements whose density is less than the given value will have density equal to MINDENS, all others will have a density of 1.0.

Altair Engineering

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PARAM, RECOVER Param eter

Value s

RECOVE R

Description

: They represent the Lower Bound (LB) and the Upper Bound (UB) of the frequencies between which the full-structure mode shapes are requested instead of the modes of the condensed system generated during Component Mode Synthesis (CMS). LB (real > 0.0, optional): Mode shapes of the full-structure, at frequencies greater than “LB”, will be output to the .op2 file. UB (real > 0.0, mandatory): Mode shapes of the full-structure, at frequencies lower than “UB”, will be output to the .op2 file. Note: 1.

The following example implementations are incorrect and will result in an ERROR: PARAM, RECOVER, 30.0, 20.0 (as UB < LB) PARAM, RECOVER, ,0.0 (as UB 0)

Defaults 1.

The mode shapes of the condensed system (only) generated during CMS are output when this parameter is not present in the deck.

2.

If PARAM, RECOVER is input without specifying a value, the program results in an ERROR.

3.

LB is optional and the default for LB is 0.0, if it is left blank.

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PARAM, RENUMOK Parameter RENUMOK

Values

Description

Default = NO

If YES or BLANK, when the solid element grids are listed in the order that would make the element inside out, they are automatically re-ordered. In this way, running (importing and exporting) the model through HyperMesh to get the corrected element grid sequence can be avoided. If NO, when the element grids are input in reverse order, they are not re-sequenced to the correct order. OptiStruct will error out if such element grid ordering exists. Note: 1.

If the element grids are input in a random order, then PARAM, RENUMOK will not be able to correct the sequence. OptiStruct will error out in such cases.

2. If PARAM, RENUMOK is not specified (default), then the default is NO. This is different from specifying PARAM, RENUMOK and leaving the value field blank, which implies YES. 3. If PARAM,RENUMOK is used and the .fem file is used for the model information file in HyperView, then corner stresses for the solid elements will be wrong when the .h3d or .op2 files are used for the results file. So, if PARAM,RENUMOK is used, HyperView should use the .op2 or .h3d file for the model information file.

Altair Engineering

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PARAM, RFIOUT Parameter RFIOUT

Values

Description

Default = NO

This parameter controls the output of modal super element for use in the RecurDyn multibody dynamics software from FunctionBay. This information is written to the .rfi file. This should be used with CMSMETH CBN and ASET DOF for the connection points. If YES, the modal super element is output to the .rfi file. If NO, the .rfi file is not created. Note: This .rfi file can be created only by OptiStruct executables running on 64-bit Windows machines. This file cannot be created while using OptiStruct on Linux or Mac OS X machines.

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PARAM, RHOCP Parameter

Values

Description

RHOCP

Real > 0.0 Default = 1.0

The scale factor used to calculate ERP in decibels (dB). The calculation is:

Altair Engineering

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PARAM, RSPLICOR Parameter RSPLICOR

Values

Description

0, 1, REAL > 1.0 Default = 0

RSPLINE end rotation correction. 0: No correction 1: two RSPLINE ends have rotation correction >1: Defines cut-off angle. Two RSPLINE ends have rotation correction. If two consecutive RSPLINE sections have an angle larger then the cut-off angle, rotation correction is applied to the shared RESPLINE node.

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Altair Engineering

PARAM, SEP1XOVR Parameter SEP1XOVR

Values

Description

0, 16 Default = 0

The old and new location of moved shell grid points are printed if SEP1XOVR = 16. When the RSSCON shell-tosolid element connector is used. By default, the moved shell grid points are not printed, SEP1XOVR = 0. See the description of PARAM,TOLRSC for more details.

Altair Engineering

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PARAM, SEPLOT Parameter SEPLOT

Values

Description

Default = YES Defaults:

PARAM, SEPLOT can be used during CMS analysis (only with the CBN method) to create a .seplot file that contains the ASET grid data as well as the GRID and PLOTEL data defined using the MODEL I/O Option. The data is written to the .seplot file in OptiStruct.

The value of this parameter is YES, YES: The .seplot file is created. if it is included in the input file, but NO: The .seplot file is not created. no value is provided. The value of this parameter is NO, if it is not included in input file.

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PARAM, SH4NRP Parameter SH4NRP

Values

Description

0, 1, 2

This parameter controls the full projection of 4-node shell elements in NLGEOM implicit analysis.

Default = 0 in NLGEOM subcase Default = 1 in IMPDYN subcase

If 0, the full projection for warped QEPH shell elements will be deactivated. This option may improve the implicit nonlinear analysis with QEPH warped shell elements if the rigid rotation of warped elements is small enough. If 1, the full projection for warped elements will be applied only for internal force calculation; the option gives accurate results if it converges successfully, but convergence issue could be encountered with very warped elements. If 2, the full projection for warped QEPH shell elements will be activated for the stiffness matrix to stay consistent with the internal force calculation. This option can improve the convergence of implicit nonlinear analysis with QEPH warped shell elements at the cost of some additional calculations. In the case of finite rigid rotations with warped shell elements, PARAM, SH4NRP, 1 gives accurate results. If convergence difficulties are encountered, PARAM, SH4NRP, 2 should be used. If PARAM SMDISP 1 is present, SH4NRP is always set as 0 internally.

Altair Engineering

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PARAM, SHELOS11 Parameter SHELOS11

Values

Description

YES, NO Default = NO

YES can be used to restore the formulation used in version 11.0.240 and earlier for first-order shell elements (CQUAD4 and CTRIA3). Note: In Release 12.0 the first order shell elements have been improved to: Eliminate inaccuracies in transverse shear and inter-laminar stress calculation that could occur for cases with membrane-bending coupling, especially composites. Improve robustness and stability of buckling formulation by changing the default order for plate buckling to first order. The behavior of shells from earlier releases can be recovered using this parameter.

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PARAM, SHL2MEM Parameter

Values

Description

SHL2MEM

0.0>

A shell property (defined by the PSHELL bulk data entry) is automatically converted into a membrane property if the membrane thickness (field T) of the PSHELL bulk data entry is less than or equal to the value specified using PARAM, SHL2MEM. This is done by setting MID2 and MID3 to blank for the PSHELL.

No default (see note 6)

Note: 1. With regard to determining the conversion from a PSHELL shell to membrane property, the nodal thicknesses defined using the Ti fields of the CTRIA3/6 or the CQUAD4/8 bulk data entries are ignored. 2. If the value of the field T in the referenced PSHELL entry is less than or equal to the value of PARAM,SHL2MEM then the shell property is converted to a membrane property regardless of the Ti field values. 3. PARAM, SHL2MEM should be used with caution in optimization runs, as this parameter will also apply to design properties. If the shell thickness on such design properties (in PSHELL) is lower than the value specified with PARAM, SHL2MEM, they will automatically be converted to membrane properties (regardless of the value of their corresponding design variables). 4. If PARAM, SHL2MEM is used in optimization runs with the shell thickness (T) of the PSHELL design property equal to zero or blank, then the shell property is automatically converted into a membrane property. 5. PARAM, SHL2MEM is intended for use with ‘skin’ elements, which are useful for stress calculation on the surface of solid (3D) elements. 6. Defaults: If PARAM,SHL2MEM is input without specifying a value, then the code will error out (no default). If PARAM,SHL2MEM is not used, the conversion from shell property to a membrane property will not occur.

Altair Engineering

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PARAM, SHPBCKOR Parameter SHPBCKOR

Values

Description

1, 2 Default = 1

PARAM,SHPBCKOR defines the type and order of approximation used in plate bending geometric stiffness for linear shell elements (CQUAD4 and CTRIA3). 1: First order approximation, expressed using displacement degrees of freedom in the geometric stiffness matrix. It is more numerically stable and includes both bending and transverse shear contributions. Being first order, this option may over-estimate buckling loads, especially when the mesh is coarse relative to the buckling wavelength (only a few elements per wave length). 2: Second order approximation, expressed using rotational degrees of freedom in the geometric stiffness matrix. This option ignores contributions of transverse shear to buckling. Note: Second order approximation is appropriate and provides better accuracy for buckling of thin shells, which is dominated by bending. For thick shells or for composites with soft cores (where transverse shear contributions are significant), it is advisable to use PARAM,SHPBCKOR,1, which captures both bending and transverse shear effects. Since PARAM,SHPBCKOR,1 is more numerically stable, it can also help if there are difficulties in the eigensolver.

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PARAM, SIMPACK Parameter SIMPACK

Values

Description

0, 1, 2, 3, 4 Default = 0

Requests generation of the SIMPACK .fbi file containing flexible body information for SIMPACK analysis. PARAM,SIMPACK,1 Writes CMS Matrices [k] and [m] to the SIMPACK .fbi file. Writes modes and eigenvectors of the SE to the SIMPACK .fbi file. PARAM,SIMPACK,2 This option writes out all the information specified in PARAM, SIMPACK,1 (above) and additionally writes model information to the SIMPACK .fbi file. See Comment 2 about MODEL data. PARAM,SIMPACK,3 This option writes out all the information specified in PARAM, SIMPACK, 2 (above) to the SIMPACK .fbi file and additionally includes the following: Writes the Interior point recovery GRID SET to the SIMPACK .fbi file. Writes the Interior point recovery matrix to the to the SIMPACK .fbi file. PARAM,SIMPACK,4 This option writes out all the information specified in PARAM, SIMPACK, 3 (above) to the SIMPACK .fbi file and additionally includes the following: Writes rotational forces to the SIMPACK .fbi file.

Comments 1.

Refer to the SIMPACK section of “Coupling OptiStruct with Third Party Software” in the User’s Guide for more information.

2.

If PARAM, SIMPACK, 2 is specified, the MODEL I/O Options Entry does not have any effect on the output. The entire model is written to the SIMPACK .fbi file.

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PARAM, SMDISP Parameter SMDISP

Values

Description

< 0, 1 > Default = 0

This parameter is used to specify that small displacement formulation or large displacement formulation is used. It affects Geometric Nonlinear Implicit Static Analysis (ANALYSIS = NLGEOM) and Geometric Nonlinear Implicit Dynamic Analysis (ANALYSIS = IMPDYN). When large displacement effects are negligible, “PARAM, SMDISP, 1” could be used to improve the convergence and performance. If 0, use large displacement formulation. If 1, use small displacement formulation.

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PARAM, SNAPTHRU Parameter SNAPTHRU

Values

Description

YES, NO Default = NO

PARAM, SNAPTHRU controls the output of the forcedeflection curve in geometric nonlinear analysis. If YES, the converter will generate rigid bodies internally and output the time history for rigid body forces in the Time-History (TH) file. This is valid only when grids are defined on XHIST bulk data entry with TYPE = GRID and ENTRY=DEF simultaneously. The force-deflection curve can be cross plotted with the grid displacements and corresponding rigid body forces in HyperGraph. If NO, output of the force-deflection curve is not requested and the internal rigid bodies are not generated.

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PARAM, SORTCON Parameter

Values

Description

SORTCON

Default = 20

This parameter controls the output of violated constraints to the .out file (and to screen). By default, the 20 most violated constraints are printed in a separate table and sorted by percentage violation. This behavior can be modified with PARAM, SORTCON, N; where N is the number of constraints to be printed. (N = 0 disables this feature).

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PARAM, SPLC Parameter SPLC

Values

Description

Real > 0.0 Default = 1.0

This parameter is used to specify the speed of sound used in the wave number and the complex particle velocity vector calculations, as shown below (see the Radiated Sound Analysis section in the User’s Guide for further information): Wave Number The wave number k is defined as follows:

2 f c

k

Where, c is the speed of sound defined by PARAM, SPLC.

f is the frequency of the sound wave in the medium. Complex Particle Velocity Vector The complex particle velocity vector is defined for each frequency as follows:

uuur ( pv) j ( f )

ˆ pj ( f ) X j c

1

i krj

Where,

pj ( f )

is the complex acoustic pressure due to source grid

j at the microphone location.

ˆ X j

is the unit vector from the source grid j to the microphone grid

ˆ X j

r Xj r Xj

r Xj rj

(see Figure 1)

is the density of the acoustic medium defined by PARAM, SPLRHO.

c is the speed of sound defined by PARAM, SPLC. k is the wave number defined above under Wave Number.

rj

Altair Engineering

is the distance from the acoustic source grid j on the

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Parameter

Values

Description panel to the microphone grid (see Figure 1).

i is the square root of -1 Note: 1.

This parameter is used to specify the speed of sound used in Radiated Sound Analysis. The same value is used in the Equivalent Radiated Power (ERP) calculations (See PARAM, ERPC).

2.

If both PARAM, SPLC and PARAM, ERPC are specified in the same input deck, then the last instance dominates.

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PARAM, SPLFAC Parameter SPLFAC

Values

Description

Real > 0.0 Default = 1.0

This parameter specifies the scale factor (q ) used to calculate the Sound Pressure Level in Radiated Sound Analysis. The equation used for the calculation is: Sound Pressure Total Complex Acoustic Sound Pressure requested by SPL is: np

ptotal f j 1

f q V flux f rj

j

ie

ikr j

Where,

f is the frequency of the sound wave in the medium. is the density of the acoustic medium defined by PARAM, SPLRHO.

rj

is the distance from the acoustic source grid j on the panel to the microphone location grid (see Figure 1).

V flux f

j

is the velocity flux of the source grid j .

k is the wave number as defined in Wave Number. i is the square root of -1 np is the number of source grids (see Figure 1). q is the value of the scale factor specified using the parameter PARAM, SPLFAC.

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PARAM, SPLREFDB Parameter SPLREFDB

Values

Description

Real > 0.0 Default = 1.0

This parameter can be used to specify the reference sound pressure value used to calculate the Sound Pressure Level (SPL) in decibels (dB). Note: The Sound Pressure Level (SPL) in decibels can be calculated using the following equation:

SPLdB

20.0 * log10 (

SPL SPLREFDB

)

Where,

SPLdB

is the Sound Pressure Level in decibels.

SPL

is the magnitude of the acoustic sound pressure specified in the Radiated Sound Analysis section of the User’s Guide.

SPLREFDB is the reference sound pressure value specified using this parameter.

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PARAM, SPLRHO Parameter SPLRHO

Values

Description

Real > 0.0 Default = 1.0

This parameter is used to specify the density of the acoustic medium in the calculation of the complex acoustic sound pressure and the complex particle velocity vector, as shown below (see the Radiated Sound Analysis section of the User’s Guide for further information): Sound Pressure Level Total Complex Acoustic Sound Pressure requested by SPL is: np

ptotal f j 1

f q V flux f rj

j

ie

ikr j

Where,

f is the frequency of the sound wave in the medium. is the density of the acoustic medium defined by PARAM, SPLRHO.

rj

is the distance from the acoustic source grid j on the panel to the microphone location grid (see Figure 1).

V flux f

j

is the velocity flux of the source grid j .

k is the wave number as defined in Wave Number. i is the square root of -1 np is the number of source grids (see Figure 1). q is the value of the scale factor specified using the parameter PARAM, SPLFAC. Complex Particle Velocity Vector The complex particle velocity vector is defined for each frequency as follows:

uuur ( pv) j ( f )

ˆ pj ( f ) X j c

1

i krj

Where,

pj ( f )

Altair Engineering

is the complex acoustic pressure due to source

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Parameter

Values

Description grid j at the microphone location.

ˆ X j

is the unit vector from the source grid j to the microphone grid

r Xj r Xj

ˆ X j

r Xj rj

(see Figure 1)

is the density of the acoustic medium defined by PARAM, SPLRHO.

c is the speed of sound defined by PARAM, SPLC. k is the wave number defined above under Wave Number.

rj

is the distance from the acoustic source grid j on the panel to the microphone grid (see Figure 1).

i is the square root of -1 Note: 1.

This parameter is used to specify the acoustic medium density used in Radiated Sound Analysis. The same value is used in the Equivalent Radiated Power (ERP) calculations (See PARAM, ERPRHO).

2.

If both PARAM, SPLRHO and PARAM, ERPRHO are specified in the same input deck, then the last instance dominates.

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PARAM, SRCOMPS Parameter SRCOMPS

Values

Description

Default = NO

If YES, the strength ratios are output for composite elements that have failure indices requested. (The Output formats currently supported are: H3D, HM, OP2, PCH and OPT) If NO or blank, the strength ratio will not be output. Note: The Strength Ratios that are output as a result of PARAM, SRCOMPS, YES depend on the Failure Theory specified by the user. The following equations show the relationship between the Failure Index and the Strength Ratio for different Failure Theories. Hill Failure Theory:

Strength Ratio

1 Failure Index

Hoffman Failure Theory: There is no direct relationship between the Strength Ratio and Failure Index. (refer to the Composite Laminates section of the User’s Guide for more information). Tsai-Wu Failure Theory: There is no direct relationship between the Strength Ratio and Failure Index. (refer to the Composite Laminates section of the User’s Guide for more information). Maximum Stress (Strain) Failure Theory:

Strength Ratio

1 Failure Index

For the Transverse Shear Failure Theory:

Strength Ratio

Altair Engineering

1 Failure Index

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PARAM, SS2GCR Parameter

Values

Description

SS2GCR

Default = 5.0

PARAM, SS2GCR is used to control the accuracy of the AMLS solution. Refer to the User’s Guide section, Using the AMLS (Automatic Multi-Level Sub-structuring) Eigensolver for more details.

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PARAM, STRTHR Parameter

Values

Description

STRTHR Default = 0.0

This parameter can be used to specify the von Mises stress threshold above which the stress results are output for a model. Note 1.

PARAM, STRTHR applies to all static subcases defined within a model. The stress results for a particular element are not output ONLY if its von Mises stress value falls below STRTHR for ALL static subcases. For example, if the von Mises stress results for elements ID=1 and ID=2 fall below the threshold for subcase 1, but are above the threshold for subcase 2; then the stress results for both elements (ID=1 and ID=2) are output for both subcases.

Altair Engineering

2.

PARAM, STRTHR applies to stress results output in all active formats.

3.

PARAM, STRTHR is supported for static analysis only.

4.

If PARAM, STRTHR is defined in a model, then 1D element stresses are not output, regardless of their stress level or the specified threshold.

OptiStruct 13.0 Reference Guide 1673 Proprietary Information of Altair Engineering

PARAM, THCNTPEN Parameter THCNTPEN

Values

Description

AUTO, LOW, HIGH Default = AUTO

PARAM, THCNTPEN controls the penalty factor used in thermal contact analysis. AUTO: Determines the value of conductivity for each contact/ gap element based on the conductivity of surrounding elements. LOW: Imposes a lower penalty factor that reduces the conductivity of each contact/gap element compared to the conductivities of the surrounding elements. It can be used when the program runs into convergence difficulties. HIGH: Imposes a higher penalty factor that increases the conductivity of each contact/gap element compared to the conductivities of the surrounding elements. It can be used to enforce stronger conduction. Note: 1.

Theoretically, while higher conductivity values enforce a perfect conductor, excessively high values may result in poor conditioning of the conductivity matrix. In such cases, it may be beneficial to reduce the value of conductivity, or use conductivity based contact clearance and pressure.

2.

This parameter influences the KC field of the PCONTHT bulk data entry and the KAHT field of the PGAPHT bulk data entry.

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PARAM, TOLRSC Parameter TOLRSC

Values

Description

Real Default = 0.05

When the RSSCON shell-to-solid element connector is used, the connecting grid points of the shell element are moved onto the solid face if the grid points are close enough. The tolerable distance of the shell grid point to the solid edge or face is where h is the height of the solid edge. Rigid body invariance is satisfied with double-precision accuracy if the shell grid points are adjusted.

Altair Engineering

OptiStruct 13.0 Reference Guide 1675 Proprietary Information of Altair Engineering

PARAM, TRAKMETH Parameter

Values

Description

TRAKMETH



TRAKMETH is a parameter that can be used to select the criterion employed for mode tracking.

Default = 0 Defaults: -The value of this parameter is 0 if it is not included in input file. -If this parameter is included in the input file, but no value is provided, then running the program will result in an error.

There are three tracking criteria available for selection in the current implementation: Mass cross-orthogonality check (CORC) Modal assurance criterion (MAC) Modal assurance criterion square root (MACSR). If TRAKMETH = 0 The Mass cross-orthogonality check (CORC) criterion is used for mode tracking. This performs a mass orthogonality check of the current and previous eigenvectors after reanalysis. CORC is implemented as follows:

If TRAKMETH = 1 The Modal assurance criterion square root (MACSR) criterion is used for mode tracking. This criterion essentially calculates the dot product of the two unit vectors associated with the current and previous eigenvectors. MACSR is implemented as follows:

If TRAKMETH = 2 The standard modal assurance criterion (MAC) is used for mode tracking. MAC is implemented as follows:

Where, is the current eigenvector. is the previous eigenvector. is the mass matrix.

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PARAM, TRAKMTX Parameter

Values

Description

TRAKMTX

Default = 0

TRAKMTX is a parameter that controls the output of the mode tracking matrix during optimization.

If TRAKMTX = 1 The mode tracking matrix will be printed to the output file -The value of this at each iteration. parameter is 0 if If TRAKMTX = 0 it is not included The mode tracking matrix will not be printed to the in input file. output file. -If this parameter is included in the Note: input file, but no Each element of the mode tracking matrix stores the value is provided, correlation value of two eigenvectors which is calculated then running the using certain mode tracking criteria (see PARAM, program will result TRAKMETH). Defaults:

in an error.

Example The following is an example of the mode tracking matrix. For this example, assume that: 1.

The first 5 modes are being tracked.

2.

10 modes are calculated for each analysis

3.

PARAM, MFILTER is set to 0.7.

Mode Tracking Matrix

Based on the above matrix, mode 1 (of the previous iteration) will get tracked to mode 1 (of current iteration). Mode 2 will get tracked to mode 2. Mode 3 will get tracked to mode 4. Mode 4 will get tracked to mode 3. And mode 5 could not be tracked to any of the 10 modes in the current iteration (out of bounds).

Altair Engineering

OptiStruct 13.0 Reference Guide 1677 Proprietary Information of Altair Engineering

PARAM, TPS Parameter

Values

Description

TPS

Default = YES

PARAM, TPS may be used with transient response analysis. When only shell stress results are required from a transient response analysis, significant speed improvements in run time can be obtained with the use of this parameter. YES: fast transient response analysis is activated – only shell stress results output may be requested in this case. that is, no displacement results are output. NO: normal transient response analysis is performed.

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PARAM, UCORD Parameter UCORD

Values

Description



If = -1, the mass moment of inertia is calculated about the center of gravity and is output in the basic coordinate system.

Default = -1

If = 0, the mass moment of inertia is calculated about the origin of the basic coordinate system. The output values are expressed in the basic coordinate system. the center of gravity coordinates are expressed in the coordinate system CID. The mass moment of inertia is calculated about the center of gravity and expressed in the coordinate system CID. Note:

Altair Engineering

1.

If PARAM, UCORD is not specified, CID = -1, or CID given is not found, all values in PARAM, GRDPNT are calculated relative to the basic coordinate system.

2.

If PARAM, GRDPNT is not specified in the input deck, then the center of gravity and moment of inertia are not output regardless of the value of PARAM, UCORD.

OptiStruct 13.0 Reference Guide 1679 Proprietary Information of Altair Engineering

PARAM, VMOPT Parameter VMOPT

Values

Description

Default = 0

If PARAM,VMOPT is set to 0 or 1, then the virtual mass of the fluid is included in the mass matrix for all calculations. This can increase the calculation time because of the dense mass matrix on the damp surface of the structure. If “PARAM,VMOPT,2” is specified, the eigenvalue solution is performed without adding the mass contribution from MFLUID, so that dry modes are calculated. A second eigenvalue analysis is performed to get the damp modes, which are used in modal dynamic solution. This solution is much faster with only a slight loss of accuracy. Note: Dry mode output in the .out file is available only when PARAM,VMOPT,2 is specified.

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PARAM, W3 Parameter

Values

Description

W3

Default = 0.0

Used in transient analyses to convert structural damping to equivalent viscous damping. The damping matrix [B] for transient analysis is assembled from:

where: is the contribution from damping elements (CDAMP#, CVSIC) and B2GG. is the overall structural damping coefficient (PARAM, G). is the frequency of interest in radians per unit time (PARAM, W3) for the conversion of overall structural damping into equivalent viscous damping.

[K]

is the global stiffness matrix. is the element structural damping coefficient (GE on the MAT# entry). is the frequency of interest in radians per unit time (PARAM, W4) for the conversion of element structural damping into equivalent viscous damping. is the element stiffness matrix.

Altair Engineering

OptiStruct 13.0 Reference Guide 1681 Proprietary Information of Altair Engineering

PARAM, W4 Parameter

Values

Description

W4

Default = 0.0

Used in transient analyses to convert structural damping to equivalent viscous damping. The damping matrix [B] for transient analysis is assembled from:

where: is the contribution from damping elements (CDAMP#, CVSIC) and B2GG. is the overall structural damping coefficient (PARAM, G). is the frequency of interest in radians per unit time (PARAM, W3) for the conversion of overall structural damping into equivalent viscous damping.

[K]

is the global stiffness matrix. is the element structural damping coefficient (GE on the MAT# entry). is the frequency of interest in radians per unit time (PARAM, W4) for the conversion of element structural damping into equivalent viscous damping. is the element stiffness matrix.

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PARAM, WR3 Parameter WR3

Values

Description

Default = 0.0

This parameter is used to include or exclude frequency dependent damping in rotor dynamics analysis. PARAM, WR3, If any real value except 0.0 (default) is specified, then it is included in the rotor dynamics equation as the “average” excitation frequency. PARAM, WR3, should be specified to activate frequency dependent damping if PARAM, GYROAVG is set to -1. PARAM, WR3, 0 If 0.0 is specified, then frequency dependent damping terms are not included in rotor dynamics analysis. Refer to the User’s Guide section, Rotor Dynamics for more details.

Altair Engineering

OptiStruct 13.0 Reference Guide 1683 Proprietary Information of Altair Engineering

PARAM, WR4 Parameter WR4

Values

Description

Default = 0.0

This parameter is used to include or exclude frequency dependent damping in rotor dynamics analysis. PARAM, WR4, If any real value except 0.0 (default) is specified, then it is included in the rotor dynamics equation as the “average” excitation frequency. PARAM, WR4, should be specified to activate frequency dependent damping if PARAM, GYROAVG is set to -1. PARAM, WR4, 0 If 0.0 is specified, then frequency dependent damping terms are not included in rotor dynamics analysis. Refer to the User’s Guide section, Rotor Dynamics for more details.

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PARAM, WTMASS Parameter

Values

Description

WTMASS

Real > 0.0 Default = 1.0

The WTMASS (Weight-To-MASS) parameter is used as a multiplier for the terms of the structural mass matrix. Note PARAM, WTMASS cannot be applied to superelements (.h3d or .pch) that are read into the model. If the unit of mass is incorrect on the MAT# entries and PARAM, WTMASS is required to update the structural mass matrix; then this should be done in the creation run.

Altair Engineering

OptiStruct 13.0 Reference Guide 1685 Proprietary Information of Altair Engineering

PAXI Bulk Data Entry PAXI – Axisymmetric Element Property Description Defines the properties of axisymmetric elements. Referenced by CTAXI entry. Format (1)

(2)

(3)

(4)

PAXI

PID

MID

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

PAXI

2

203

(4)

(5)

(6)

(7)

(8)

(9)

Field

Contents

PID

Unique axisymmetric element property identification number.

(10)

No default (Integer > 0) MID

Identification number of a MAT1 or MAT3 entry. No default (Integer > 0)

Comments 1.

All axisymmetric element property entries must have unique ID numbers.

2.

This card is represented as a property in HyperMesh.

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PBAR Bulk Data Entry PBAR – Simple Beam Property Description The PBAR bulk data entry defines the properties of a simple beam (bar), which is used to create bar elements via the CBAR entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PBAR

PID

MID

A

I1

I2

J

NSM

C1

C2

D1

D2

E1

E2

F1

K1

K2

I12

(9)

(10)

F2

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

PBAR

39

6

2.9

8.4

5.97

1.1

2.0

4.0

Field

Contents

PID

Unique simple beam property identification number.

(8)

(9)

(10)

No default (Integer > 0) MID

Material identification number. See comment 1. No default (Integer > 0)

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OptiStruct 13.0 Reference Guide 1687 Proprietary Information of Altair Engineering

Field

Contents

A

Area of bar cross-section. No default (Real > 0.0)

I1

Area moment inertia in plane 1 about the neutral axis. No default (Real > 0.0)

I2

Area moment inertia in plane 2 about the neutral axis. No default (Real > 0.0)

I12

Area product of inertia. Default = 0.0 (Real) (

J

)

Torsional constant. Default = 0.0 (Real > 0.0)

NSM

Nonstructural mass per unit length. Default = 0.0 (Real)

K1, K2

Area factor for shear. Default = 0.0 (Real)

Ci, Di, Ei, Fi

Stress recovery coefficients. Default = 0.0 (Real)

Comments 1.

For structural problems, MID may reference only a MAT1 material entry. For heat transfer problems, MID may reference only a MAT4 material entry.

2.

The transverse shear stiffness in planes 1 and 2 are (K1)AG and (K2)AG, respectively. The default values for K1 and K2 are infinite; in other words, the transverse shear used for K1 and K2, the transverse shear flexibilities are set to 0.0 (K1 and K2 are interpreted as infinite).

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3.

The stress recovery coefficients C1 and C2, and so on, are the y and z coordinates in the BAR element coordinate system of a point at which stresses are computed. Stresses are computed at both ends of the BAR.

Fig 1: C oordinate System for Bar Element (PBAR).

4.

The moments of inertia are defined as follows:

5.

This card is represented as a property in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1689 Proprietary Information of Altair Engineering

PBARL Bulk Data Entry PBARL – Simple Beam Property Description Defines the properties of a simple beam (bar) by cross-sectional dimensions, which is used to create bar elements via the CBAR entry. Format (1)

(2)

(3)

(4)

(5)

(6)

PBARL

PID

MID

GROUP

TYPE/ NAME

ND

DIM1

DIM2

DIM3

DIM4

DIM5

DIM9

…

NSM

(7)

(8)

(9)

(10)

DIM6

DIM7

DIM8

Example

(1)

(2)

(3)

PBARL

12

7

10.

6.

(4)

(5)

(6)

(7)

(8)

(9)

(10)

BOX

.5

.5

Field

Contents

PID

Unique simple beam property identification number. No default (Integer > 0)

MID

Material identification number. See comment 1. No default (Integer > 0)

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Field

Contents

GROUP

Indicates if an arbitrary beam section definition is to be used. Refer to Arbitrary Beam Section Definition in the User’s Guide. If the value of this field is HYPRBEAM, the following field is NAME; otherwise it is TYPE. Default = blank (blank or HYPRBEAM)

TYPE

Cross-section type. When GROUP field is blank, this field is TYPE. No default ("BAR", "BOX", "BOX1", "CHAN", "CHAN1", "CHAN2", "CROSS", "H", "HAT", "I", "I1", "ROD", "T", "T1", "T2", "TUBE", "Z")

NAME

Name of arbitrary beam section definition. Refer to Arbitrary Beam Section Definition in the User’s Guide. When the value of GROUP is HYPRBEAM, this field is NAME. No default (Character string)

ND

Number of dimensions used to specify the Cross-section shape. This is required when the value of the GROUP field is HYPRBEAM. ND represents the total number of dimensions used to define an Arbitrary Beam Section. Default = blank

DIMi

Cross-sectional dimensions. No default (Real > 0.0)

NSM

Nonstructural mass per unit length. NSM is specified after the last DIMi. Default 0.0 (Real)

Comments 1.

For structural problems, MID may reference only a MAT1 material entry. For heat transfer problems, MID may reference only a MAT4 material entry.

2.

The cross-sectional properties, shear flexibility factors, and stress recovery points (C, D, E, and F) are computed using the TYPE and DIMi as shown below. The origin of the element coordinate system is centered at the shear center of the cross-section oriented as shown. The PBARL does not account for offsets between the neutral axis and the shear center. Therefore, the CHAN cross-sections may produce incorrect results. The PBEAML entry is recommended.

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OptiStruct 13.0 Reference Guide 1691 Proprietary Information of Altair Engineering

Type = BAR

Type = BOX

Type = BOX1

Type = CHAN

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Type = CHAN1

Type = CHAN2

Type = CROSS

Type = H

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Type = HAT

Type = I

Type = I1

Type = ROD

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Type = T

Type = T2

Altair Engineering

Type = T1

Type = TUBE

OptiStruct 13.0 Reference Guide 1695 Proprietary Information of Altair Engineering

Type = Z 3.

This card is represented as a property in HyperMesh.

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PBARX Bulk Data Entry PBARX – Optional BAR Property Extension for Geometric Nonlinear Analysis Description Defines additional BAR properties for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

PBARX

PID

ISMSTR

ISTRAIN

DM

DB

(7)

(8)

(9)

(10)

Field

Contents

PID

Property identification number of the associated PBAR or PBARL card. See comment 1. No default (Integer > 0)

ISMSTR

Flag for small strain formulation. Default = 2 (Integer = 1, 2) 1 - Small strain from time =0 2 - Full geometric nonlinearity

ISTRAIN

Flag for shear in beam formulation. Default = ON (ON or OFF)

DM

Beam membrane damping. Default = 0.0 (Real > 0)

DB

Beam bending damping. Default = 0.01 (Real > 0)

Comments 1.

The property identification number must be that of an existing PBAR bulk data entry. Only one PBARX property extension can be associated with a particular PBAR.

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OptiStruct 13.0 Reference Guide 1697 Proprietary Information of Altair Engineering

2.

PBARX is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

If the small strain option is activated (ISMSTR = 1), the strain and stress are engineering strain and stress; otherwise they are true strain and stress.

4.

This card is represented as an extension to a PBAR property in HyperMesh.

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PBEAM Bulk Data Entry PBEAM – Beam Property Description The PBEAM bulk data entry defines the properties of beam elements defined via the CBEAM entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PBEAM

PID

MID

A(A)

I1(A)

I2(A)

I12(A)

J(A)

NSM(A)

C 1(A)

C 2(A)

D1(A)

D2(A)

E1(A)

E2(A)

F1(A)

F2(A)

(10)

The following two continuation lines may be repeated up to ten times. They are used to define stations along the beam element. SO

X/XB

A

I1

I2

I12

J

NSM

C1

C2

D1

D2

E1

E2

F1

F2

NSIA

NSIB

N1A

N2A

N1B

N2B

The last two continuation lines are: K1

K2

M1A

M2A

Altair Engineering

M1B

M2B

OptiStruct 13.0 Reference Guide 1699 Proprietary Information of Altair Engineering

Fig 1: Beam Element C oordinate System (for PBEAM entry)

Example 1

This example represents a straight beam with stress recovery, only at end A. (1)

(2)

(3)

(4)

(5)

(6)

PBEAM

9

7

9.5

18.073

98.792

0.0

2.0

0.0

-2.0

NO

1.0

(7)

(8)

(9)

(10)

0.813

2.1

0.5

Example 2

This example represents a tapered beam with an intermediate section defined halfway along its length and stress recovery at both end A and end B.

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Note that the blank line after YES is entered for Stress Output (SO) at end B. (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PBEAM

9

7

9.5

18.073

98.792

0.813

0.0

2.0

0.0

-2.0

NO

0.5

6.5

5.385

35.542

0.563

YES

1.0

3.5

0.698

7.292

0.313

(9)

(10)

2.1

0.5

Field

Contents

PID

Property identification number. No default (Integer > 0)

MID

Material identification number. See comment 1. No default (Integer > 0)

A(A)

Area of beam cross-section at end A. No default (Real > 0.0)

I1(A)

Area moment inertia in plane 1 about the neutral axis at end A. No default (Real > 0.0)

I2(A)

Area moment inertia in plane 2 about the neutral axis at end A. No default (Real > 0.0)

I12(A)

Area product inertia at end A (

).

Default = 0.0 (Real)

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OptiStruct 13.0 Reference Guide 1701 Proprietary Information of Altair Engineering

Field

Contents

J(A)

Torsional stiffness parameter at end A. Default = 0.0 (Real > 0.0)

NSM(A)

Nonstructural mass per unit length at end A. Default = 0.0 (Real)

Ci(A), Di(A), Ei(A), Fi(A)

The y and z locations in element coordinates for stress data recovery at end A. (i=1 is y and i=2 is z) Default = 0.0 for all entries (Real)

SO

Stress output request option for intermediate stations and end B. See comments 5 through 8. If set to NO, the following continuation line (containing fields C1 through F2) must be omitted for that intermediate station, and no stresses are recovered for that intermediate station. If set to YESA, the following continuation line (containing fields C1 through F2) must be omitted for that intermediate station, and stresses, for that intermediate station, are recovered at the stress recovery locations identified for end A. If set to YES, the following continuation line (containing fields C1 through F2) must contain the same stress recovery locations as the first continuation line (containing fields C1(A) through F2(A)) or must be entirely blank. Default = YES (YES, YESA, or NO)

X/XB

Fractional distance of the intermediate station from end A. Default = 1.0 (Real > 0.0)

A

Area of beam cross-section for intermediate stations. Default = A(A) (Real > 0.0)

I1

Area moment inertia in plane 1 about the neutral axis for intermediate stations. Default = I1(A) (Real > 0.0)

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Field

Contents

I2

Area moment inertia in plane 2 about the neutral axis for intermediate stations. Default = I2(A) (Real > 0.0)

I12

Area product inertia for intermediate stations (

).

Default = I12(A) (Real) J

Torsional stiffness parameter for intermediate stations. Default = J(A) (Real > 0.0)

NSM

Nonstructural mass per unit length for intermediate stations. Default = NSM(A) (Real)

Ci, Di, Ei, Fi

The y and z locations in element coordinates for stress data recovery for intermediate stations. (i=1 is y and i=2 is z). See comments 5 through 8. Default = 0.0 for all entries. (Real)

K1,K2

Shear stiffness factor K in K*A*G for plane 1 and plane 2. Default = 1.0 for both (Real)

NSIA

Nonstructural mass moment of inertia per unit length about nonstructural mass center of gravity at end A. Default = 0.0 (Real)

NSIB

Nonstructural mass moment of inertia per unit length about nonstructural mass center of gravity at end B. Default = NSIA (Real)

M1A, M2A

(y,z) coordinates of center of gravity of nonstructural mass at end A. Default = 0.0, 0.0 (Real)

M1B, M2B

(y,z) coordinates of center of gravity of nonstructural mass at end B. Default = M1A, M2A (Real)

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OptiStruct 13.0 Reference Guide 1703 Proprietary Information of Altair Engineering

Field

Contents

N1A, N2A

(y,z) coordinates of neutral axis at end A. Default = 0.0, 0.0 (Real)

N1B, N2B

(y,z) coordinates of neutral axis at end B. Default = N1A, N2A (Real)

Comments 1.

For structural problems, MID may reference only a MAT1 material entry. For heat transfer problems, MID may reference only a MAT4 material entry.

2.

Blank fields for K1 and K2 are defaulted to 1.0. If a value of 0.0 is used for K1 and K2, the transverse shear flexibilities are set to 0.0.

3.

One value for X/XB must be 1.0.

4.

The moments of inertia are defined as follows:

5.

Stress recovery is only allowed at end A and end B. Stress recovery at intermediate stations is not supported.

6.

If no stress data at end A is to be recovered, but a stress recovery location is defined for end B, then the first continuation entry, which contains the fields C1(A) through F2(A), may be omitted.

7.

If the continuation line containing values C1 through F2 is entirely blank for end B, then the stress recovery locations defined for end A are used. However, if any entry is defined on this line, then all blank entries will default to 0.0 and not the corresponding entry for end A.

8.

Stress recovery locations must be the same for end A and end B.

9.

OSDIAG, 166, 1 may be input in the I/O options section of the input deck to bypass error terminations caused by PBEAM definitions which violate the rules outlined in comments 5 and 8. In such instances, the following occurs: Warning messages regarding the violations are echoed to the .out file. Stress is not recovered at intermediate stations. Recovery locations defined for end A are also used for end B.

10. For tapered beams, a single prismatic beam is created with properties obtained by weighted averaging of all station properties.

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11. The cross-sectional properties have to be specified fully for end A. For end B, blank fields mean that the properties are the same as for end A. For intermediate stations, blank fields result in a linear interpolation between the property value at end A and end B being used. 12. The NSM specified at end A is the default value for NSM at end B. The default for all other stations is a linear interpolation between end A and end B. So, for a constant NSM over the length of the beam, only NSM at end A is required. The mass of the element is calculated as: Mass = density * beam_area * beam_length + NSM * beam_length If the NSM value is different in different stations, it is averaged over all the stations and the average is used in the element calculation. 13. This card is represented as a property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1705 Proprietary Information of Altair Engineering

PBEAML Bulk Data Entry PBEAML – Beam Property Description Defines the properties of a beam element by cross-sectional dimensions that are used to create beam elements via the CBEAM entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PBEAML

PID

MID

GROUP

TYPE/ NAME

ND

DIM1(A)

DIM2(A)

…

NSM(A)

…

NSM(1)

…

SO(B)

(10)

SO(1)

X(1)/XB

DIM1(1)

DIM2(1)

X(B)/XB

DIM1(B)

DIM2(B)

…

NSM(B)

* The format of this bulk data entry is somewhat unusual as the field locations can vary depending on the number of dimensions used to define the cross-section.

Example

(1)

(2)

(3)

(4)

PBEAML

99

21

12.

14.8

2.5

7.

1.2

2.6

5.6.

2.3

(5)

(6)

(7)

(8)

(9)

NO

0.4

6.

0.6

6.

7.8

(10)

T

26.

YES

YES

1706 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Field

Contents

PID

Property identification number. No default (Integer > 0)

MID

Material identification number. See comment 1. No default (Integer > 0)

GROUP

Indicates if an arbitrary beam section definition is to be used. Refer to Arbitrary Beam Section Definition in the User’s Guide. If the value of this field is HYPRBEAM, the following field is NAME; otherwise it is TYPE. Default = blank (blank or HYPRBEAM)

TYPE

Cross-section shape. When GROUP field is blank, this field is TYPE. No default ("BAR", "BOX", "BOX1", "CHAN", "CHAN1", "CHAN2", "CROSS", "H", "HAT", "I", "I1", "L", "ROD", "T", "T1", "T2", "TUBE", "Z")

NAME

Name of arbitrary beam section definition. Refer to Arbitrary Beam Section Definition in the User’s Guide. When the value of GROUP is HYPRBEAM, this field is NAME. No default (Character string)

ND

Number of dimensions used to specify the Cross-section shape. This is required when the value of the GROUP field is HYPRBEAM. ND represents the total number of dimensions used to define an Arbitrary Beam Section. Default = blank

DIMi(A)

Cross-section dimensions at end A. No default (Real > 0.0)

NSM(A)

Nonstructural mass per unit length at end A. Default = 0.0 (Real)

SO(#)

Stress output request option for intermediate station #. Stress output is not supported for intermediate stations so this field must be set to NO.

X(#)/XB

Distance from end A to intermediate station # in the element coordinate

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OptiStruct 13.0 Reference Guide 1707 Proprietary Information of Altair Engineering

Field

Contents system, divided by the length of the element. Default = 1.0 (Real > 0.0)

DIMi(#)

Cross-section dimensions at intermediate station #. (Real > 0.0)

NSM(#)

Nonstructural mass per unit length at intermediate station #. Default = 0.0 (Real)

SO(B)

Stress output request option for end B. Default = YES (YES or NO)

X(B)/XB

Distance form end A to end B in the element coordinate system, divided by the length of the element. This must be 1.0

DIMi(B)

Cross-section dimensions at end B (Real > 0.0)

NSM(B)

Nonstructural mass per unit length at end B. Default = 0.0 (Real)

Comments 1.

For structural problems, MID may reference only a MAT1 material entry. For heat transfer problems, MID may reference only a MAT4 material entry.

2.

Up to eleven stations are allowed (end A and B, and nine intermediate stations #).

3.

The cross-sectional properties, shear flexibility factors, and stress recovery points (C, D, E, and F) are computed using the TYPE and DIMi as shown below. The element coordinate system is located at the shear center.

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Type = BAR

Type = BOX

Type = BOX1

Type = CHAN

Altair Engineering

OptiStruct 13.0 Reference Guide 1709 Proprietary Information of Altair Engineering

Type = CHAN1

Type = CHAN2

Type = CROSS

Type = H

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Type = HAT

Type = I

Type = I1

Type = L

Altair Engineering

OptiStruct 13.0 Reference Guide 1711 Proprietary Information of Altair Engineering

Type = ROD

Type = T

Type = T1

Type = T2

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Type = TUBE

Type = Z

4.

For PBEAML entries with more than one section, an equivalent PBEAM entry is derived. An echo request will cause a printout of the derived PBEAM.

5.

Stress recovery is only allowed at end A and end B. Stress recovery at intermediate stations is not supported.

6.

For tapered beams, a single prismatic beam is created with dimensions obtained by weighted averaging of all station dimensions.

7.

DIMi and NSM have to be specified fully on station A. On station B, blank means that the dimensions are the same as at A. On other stations, it is a linear interpolation between A and B.

8.

The NSM specified at end A is the default value for NSM at end B. The default for all other stations is a linear interpolation between end A and end B. So, for a constant NSM over the length of the beam, only NSM at end A is required. The mass of the element is calculated as: Mass = density * beam_area * beam_length + NSM * beam_length If the NSM value is different in different stations, it is averaged over all the stations and the average is used in the element calculation.

9.

This card is represented as a property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1713 Proprietary Information of Altair Engineering

PBEAMX Bulk Data Entry PBEAMX – Optional BEAM Property Extension for Geometric Nonlinear Analysis Description Defines additional BEAM properties for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

PBEAMX

PID

ISMSTR

ISTRAIN

DM

DB

(7)

(8)

(9)

(10)

Field

Contents

PID

Property identification number of the associated PBEAM, PBEAML. See comment 1. No default (Integer > 0)

ISMSTR

Flag for small strain formulation. Default = 2 (Integer = 1, 2) 1 - Small strain from time =0 2 - Full geometric non-linearity

ISTRAIN

Flag for shear in beam formulation. Default = ON (ON or OFF)

DM

Beam membrane damping. Default = 0.0 (Real > 0.0)

DB

Beam bending damping. Default = 0.01 (Real > 0.0)

Comments 1.

The property identification number must be that of an existing PBEAM bulk data entry. Only one PBEAMX property extension can be associated with a particular PBEAM.

1714 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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2.

PBEAMX is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

If the small strain option is activated (ISMSTR = 1), the strain and stress are engineering strain and stress; otherwise they are true strain and stress.

4.

This card is represented as an extension to a PSOLID property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1715 Proprietary Information of Altair Engineering

PBUSH Bulk Data Entry PBUSH – Generalized Spring-Damper-Mass Property Description Defines the nominal property values for a generalized spring-damper-mass structural element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PBUSH

PID

K

K1

K2

K3

K4

K5

K6

B

B1

B2

B3

B4

B5

B6

GE

GE1

GE2

GE3

GE4

GE5

GE6

M

M1

M2

M3

M4

M5

M6

(10)

Example 1

(1)

(2)

(3)

(4)

(5)

(6)

PBUSH

35

K

4.35

2.4

RIGID

GE

0.02

(5)

(6)

(7)

(8)

(9)

(10)

3.1

Example 2

(1)

(2)

(3)

(4)

PBUSH

35

B

4.35

M

1.2

(7)

(8)

(9)

(10)

7.1

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Field

Contents

PID

Property identification number. No default (Integer > 0)

K

Flag indicating that the next 1 to 6 fields are stiffness values. No default (Character)

Ki

Nominal stiffness values in directions 1 through 6. See comments 3, 6, and 8. Default = 0.0 (Real or RIGID)

B

Flag indicating that the next 1 to 6 fields are force-per-velocity damping. No default (Character)

Bi

Nominal damping coefficients in directions 1 through 6 in units of force per unit velocity. Default = 0.0 (Real)

GE

Flag indicating that the next 1 to 6 fields are the structural damping constants. No default (Character)

GEi

Nominal structural damping constants in directions 1 through 6. See comments 3, 5, and 6. Default = 0.0 (Real)

M

Flag indicating that the next 1 to 6 fields are directional masses.

Mi

Nominal mass values in directions 1 through 6. See comment 7. Default = 0.0 (Real)

Comments 1.

All generalized spring-damper-mass property entries must have unique ID numbers.

2.

The K, B, GE, and M lines may be specified in any order.

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OptiStruct 13.0 Reference Guide 1717 Proprietary Information of Altair Engineering

3.

Ki, Bi, GEi, or Mi may be made frequency dependent for both direct and modal frequency response by use of the PBUSHT entry. The nominal values are used for all analysis types except frequency response. For modal frequency response, the normal modes are computed using the nominal Ki values. The frequency-dependent values are used at every excitation frequency.

4.

To obtain the damping coefficient GE, multiply the critical damping ratio C/C0 by 2.0.

5.

If PARAM, W4 is not specified, GEi is ignored in transient analysis.

6.

For upward compatibility, if ONLY GE1 is specified on a PBUSH entry and GEi, i = 2 to 6 are blank on that PBUSH entry, then a single structural damping is assumed and applied to all Ki of that PBUSH. If a PBUSH entry has a GEi, i = 2 to 6 specified, then the GEi fields are considered variable for that PBUSH entry.

7.

The Mi fields do not contribute to mass and inertia properties. Their contributions to gravity and/or centrifugal loading are also not included.

8.

The keyword RIGID may be used in place of a stiffness value for Ki entries. When RIGID is defined, a very high relative stiffness (relative to the surrounding structure) is selected for that degree-of-freedom simulating a rigid connection.

9.

This card is represented as a property in HyperMesh.

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PBUSH1D Bulk Data Entry PBUSH1D – Rod-type Spring-and-Damper Property Description Defines the linear and nonlinear properties for a one-dimensional spring-and-damper structural element. Format (1)

(2)

(3)

(4)

(5)

PBUSH1D

PID

K

B

M

SPRING

TYPE

IDT

(6)

(7)

(8)

(9)

(10)

Example 1

(1)

(2)

(3)

(4)

PBUSH1D

35

4.35

0.5

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Example 2

(1)

(2)

(3)

PBUSH1D

35

4.35

SPRING

TABLE

(5)

(6)

(7)

(8)

(9)

(10)

43

Field

Contents

PID

Property identification number. No default (Integer > 0)

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OptiStruct 13.0 Reference Guide 1719 Proprietary Information of Altair Engineering

Field

Contents

K

Stiffness. Default = 0.0 (Real > 0)

B

Viscous damping. Default = 0.0 (Real > 0)

M

Total mass. Default = 0.0 (Real > 0)

SPRING String indicating that a function defining the spring characteristics follows. TYPE

Type of input definition. Default = TABLE (Character = TABLE)

IDT

Identification number of a TABLEDi table entry. No default (Integer > 0)

Comments 1.

Either the stiffness K, or the damping B, or the mass M must be specified. B and M are ignored in static subcases.

2.

The SPRING continuation line is used in nonlinear analysis solution sequences only. The table input supersedes the stiffness K.

3.

PBUSH1D may only be referenced by CBUSH1D elements.

4.

In all linear subcases, as well as small displacement nonlinear quasi-static (ANALYSIS=NLSTAT) subcases, PBUSH1D and CBUSH1D are converted internally to the equivalent PBUSH (with PBUSHT, if necessary) and CBUSH.

5.

This card is represented as a property in HyperMesh.

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PBUSHT Bulk Data Entry PBUSHT – Generalized Spring and Damper Property Description Defines property values for a generalized spring and damper structural element. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PBUSHT

PID

TYPE

TID1

TID2

TID3

TID4

TID5

TID6

TYPE

TID1

TID2

TID3

TID4

TID5

TID6

TYPE

TID1

TID2

TID3

TID4

TID5

TID6

TYPE

TID1

TID2

...

...

Field

Contents

PID

Property identification number. Must match with a PID of a PBUSH Bulk Data Entry.

(10)

No default (Integer > 0) TYPE

Identifies what the following six fields reference. If TYPE is K, then the following six fields are stiffness vs. frequency table references for dofs 1 through 6, respectively. If TYPE is B, then the following six fields are viscous damping vs. frequency table references for dofs 1 through 6, respectively. If TYPE is GE, then the following six fields are structural damping vs. frequency table references for dofs 1 through 6, respectively.

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OptiStruct 13.0 Reference Guide 1721 Proprietary Information of Altair Engineering

Field

Contents If TYPE is M, then the following six fields are directional mass vs. frequency table references for dofs 1 through 6, respectively. If TYPE is KN, then the following six fields are force vs. deflection table references for dofs 1 through 6, respectively. See comment 4. No default (K, B, GE, M, or KN)

TID#

Identification number of a TABLED# entry. The type of the referenced table is defined by the TYPE keyword given on the same line. The six references on each line represent the 6 degrees-of-freedom in sequence from 1 through 6. Default = 0 (Integer > 0)

Comments 1.

The K, B, GE, and M fields are associated with the same entries on the PBUSH entry

2.

PBUSHT may only be referenced by CBUSH elements in the residual structure which do not attach to any omitted degrees-of-freedom.

3.

The TYPEs can be defined in any order, but may only appear once per PBUSH definition.

4.

TYPE=K, B, GE and M are allowed for frequency response analysis only, while TYPE=KN is allowed only for nonlinear analysis.

5.

For upward computability, if ONLY the dof1 field for the GE line (line where TYPE=GE) is specified on ALL PBUSHT entries and the other dofs for the GE line are blank on ALL PBUSH entries, then a single structural damping table for each PBUSHT applied to all defined dofs on the K line for each PBUSH is assumed. If ANY PBUSHT entry has a dof field other than dof1 for the GE line specified, then the GE fields are considered variable on ALL PBUSH and PBUSHT entries.

6.

This card is represented as a property in HyperMesh.

1722 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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PCNTX2 Bulk Data Entry PCNTX2 – Extended CONTACT Property type 2 for Geometric Nonlinear Analysis Description Defines properties TYPE2 tied CONTACT interface for geometric nonlinear analysis. Format (1)

(2)

PC NTX2

PID

IGNROE

(3)

(4)

(5)

(6)

FSPOT

LEVEL

ISRC H

IDELG

(7)

(8)

(9)

(10)

(7)

(8)

(9)

(10)

MAXND

MAXTD

(8)

(9)

If FSPOT = 20, 21, or 22, two continuation lines (1)

(2)

(3)

(4)

(5)

(6)

RUPT

IFILT

SRTID

SNTID

STTID

FSTR

FSTRATE

FDIST

ALPHA

If FSPOT = 25, one continuation line (1)

(2)

(3)

(4)

STFAC

VISC

(5)

(6)

(7)

(10)

Example

(1)

(2)

PC ONT

34

PC NTX2

34

Altair Engineering

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

OptiStruct 13.0 Reference Guide 1723 Proprietary Information of Altair Engineering

Field

Contents

PID

Property identification number of the associated PCONT. No default (Integer > 0)

IGNORE

Flag to ignore slave nodes if no master segment found for TIE contact (See comment 7). Default as defined by CONTPRM (Integer = 0, 1, or 2) 0 - No deletion of slave nodes; 1 - Slave nodes with no master segment found are deleted from the interface; 2 - Slave nodes with no master segment found are deleted from the interface, if SRCHDIS is blank, then it would be new calculated internally.

FSPOT

Flag for spotweld formulation. (Integer). Default = 5. 1 - Formulation is optimized for spotweld or rivets. 2 - Same formulation as standard formulation. Required when using hierarchy levels. Not compatible with nodal time step (TSTYP= GRID, TSC = CST). 4 - Rotational degrees of freedom are not transmitted (if shells are used). 5 - Standard formulation. 20, 21, 22 - formulation with failure. Not compatible with nodal time step GRID(CST) on XSTEP card. The stress is computed for each slave node according to the "equivalent" surface around the node. The equivalent surface is defined accordingly: 20 - Surface computed using shell and brick faces attached to the node. 21 - Surface computed using only the shell attached to the node. 22 - Surface computed using only the brick faces attached to the node. 25 - Penalty formulation. 30 - Formulation with cubic curvature of master segment. Not compatible with nodal time step GRID(CST) on XSTEP card.

LEVEL

Hierarchy level of the interface. No default (Integer > 0)

ISRCH

Search formulation flag for the closest master segment. Default = 2 (Integer) 1 - Old formulation (only used for previous version) 2 - New improved formulation

1724 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Field

Contents

IDELG

Flag for node deletion. 0 - No deletion. 1 - The kinematic condition is suppressed on slave node, if the master element is deleted. (The slave node is removed from the interface).

RUPT

Failure model (only available with FSPOT = 20, 21, 22) (Integer). See comment 7. 0 - Failure when MAXND or MAXTD are reached; 1 - See comment 10.

IFILT

Filter flag (See comment 13) Default = 0 (Integer = 0, 1) 0 - No filtering 1 - Filtering (alpha filter)

SRTID

Identification number of TABLEDi entry defining stress factor vs stress rate (See comment 9). No default (Integer > 0)

SNTID

Identification number of TABLEDi entry defining maximum normal stress vs normal relative displacement(ND). This function must be defined. (See comment 9) No default (Integer > 0)

STTID

Identification number of TABLEDi entry defining maximum tangential stress vs tangential relative displacement (TD). This function must be defined. (See comment 9) No default (Integer > 0)

MAXND

Maximum normal relative displacement. Default = 1.0E20 (Real)

MAXTD

Maximum tangential relative displacement. Default = 1.0E20 (Real)

FSTR

Stress scale factor (See comment 9)

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OptiStruct 13.0 Reference Guide 1725 Proprietary Information of Altair Engineering

Field

Contents Default = 1.00 (Real)

FSTRATE

Stress rate scale factor (See comment 9) Default = 1.00 (Real)

FDIST

Distance scale factor (See comment 9) Default = 1.00 (Real)

ALPHA

Stress filter alpha value Default = 1.00 (Real)

STFAC

Interface stiffness scale factor. (Only used with FSPOT = 25) Default = 1.00 (Real)

VISC

(Optional) Critical damping coefficient on interface stiffness (Only used with FSPOT = 25) Default = 0.05 (Real)

Comments 1. The property identification number must be that of an existing PCONT bulk data entry. Only one PCNTX2 property extension can be associated with a particular PCONT. 2. PCNTX2 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases. 3. If FRIC is not explicitly defined on the PCONTX/PCNTX# entries, the MU1 value on the CONTACT or PCONT entry is used for FRIC in the /INTER entries for Geometric Nonlinear Analysis. Otherwise, FRIC on PCONTX/PCNTX# overwrites the MU1 value on CONTACT/ PCONT. 4. PCNXT2 is only valid for tied contact on TIE card. 5. Interface type 2 is a kinematic condition, no other kinematic condition should be set on any nodes of the slave surface. 6. The default value for SRCHDIS is the average of the mater segments. 7. If IGNORE = 1 or 2, the slave nodes without a master segment found during the searching are deleted from the interface; If INGORE = 1 and SRCHDIS is blank, then the default value of the distance for searching closest master segment is the average size of the master segments; If IGNORE = 2 and SRCHDIS is blank, then the distance for searching closest master segment is computed as follows for each slave node:

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d1 = 0.6 * (T s + T m) d2 = 0.05 * T md SRCHDIS = max(d1 , d2) where, T s - Thickness of the element connected to the slave node, for solids T s = 0.0 T m - Thickness of master segment, for solids T m = Element volume / Segment area T md - Master segment diagonal 8. Master nodes of an interface type 2 may be slave nodes of another interface type 2 if the hierarchy level of the first interface is lower than the hierarchy level of the second interface. Hierarchy levels are only available with FSPOT=2. 9. For failure (FSPOT = 20, 21, 22), it could model glue connection. In this case, the force in slave node will be scaled by reduced force coefficient f N (f T ), which is computed as;

The reduced force is compared to the maximum value: If

, then ƒN = 1, which means the force will not be reduced.

If reduced.

, then

, which means the force will be then

Here the maximum value will be defined by you with:

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OptiStruct 13.0 Reference Guide 1727 Proprietary Information of Altair Engineering

Where: : maximum normal stress value defined by SNTID : normal stress : maximum tangential stress value defined by STTID : tangential stress FSTR: the input constant stress factor SRTID: the input variable coefficient SNTID and STTID: the input stress-displacement tables. Once the rupture criterion (defined by Rupt) is reached, the contact will be deleted. 10. If RUPT = 1, the failure criterion is as follows:

11. If FSPOT = 30, slave mass/inertia/stiffness distribution to the master node is based on the Kirschoff model: bi-cubic form functions are used instead of linear (standard formulation). It allows a softer contact behavior since the element shape curvature is taken into account in the force/moment transmission. 12. If IDELG = 1, then when a 4-node shell, a 3-node shell or a solid element is deleted, it is also removed from the master side of the interface (kinematic condition is suppressed on relative slave nodes). 13. If IFILT is set to 1, the normal and tangential stresses are filtered with an alpha filter, as follows:

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14. FSPOT = 25 (penalty formulation) will keep the penalty formulation during the whole run. The slave node (of this contact) could also be the slave node of another kinematic option, like rigid body. The penalty stiffness is constant, calculated as the mean nodal stiffness of master and slave side. The stiffness factor, STFAC, may be used to modify it, if needed. The penalty stiffness will be multiplied by STFAC. A critical viscous damping coefficient (VISC) allows damping to be applied to the interface stiffness.

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OptiStruct 13.0 Reference Guide 1729 Proprietary Information of Altair Engineering

PCNTX5 Bulk Data Entry PCNTX5 – Extended CONTACT Property type 5 for Geometric Nonlinear Analysis Description Defines properties type 5 of a CONTACT interface for geometric nonlinear analysis. Format (1)

(2)

(3)

PC NTX5

PID

STFAC

(4)

FRIC

IBC

(5)

(6)

GAP

TSTART

IRM

INAC TI

IFRIC

IFILT

FFAC

FRIC DAT

C1

C2

C3

(7)

(8)

IBAG

IDEL

C5

C6

(9)

(10)

TEND

C4

Example

(1)

(2)

PC ONT

34

PC NTX5

34

(3)

(4)

(5)

(6)

(7)

(8)

Field

Contents

PID

Property identification number of the associated PCONT.

(9)

(10)

No default (Integer > 0) IBAG

Airbag vent holes closure flag in case of contact. Default = 0 (Integer)

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Field

Contents 0 - No closure 1 - Closure

IDEL

Flag for node and segment deletion. (See comment 5) Default as defined by CONTPRM (Integer = 0, …, 2) 0 - No deletion. 1 - When all the elements (shells, solids) associated to one segment are deleted, the segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface. 2 - When a shell or a solid element is deleted, the corresponding segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface.

STFAC

Interface stiffness scale factor. Default = 0.2 (Real > 0)

FRIC

Coulomb friction. Default as defined by CONTPRM (Real > 0)

GAP

Gap for impact activation (See comment 4). Default as defined by CONTPRM (Real > 0)

TSTART

Start time Default = 0.0 (Real > 0)

TEND

Time for temporary deactivation. Default = 1030 (Real > 0)

IBC

Flag for deactivation of boundary conditions at impact applied to the slave grid set. Default as defined by CONTPRM (Character = X, Y, Z, XY, XZ, YZ, XYZ)

IRM

Renumbering flag for segments of the master surface (Integer = 0, 1, 2). 0 - If segment is connected to a solid element its normal is reversed if entering the solid element (the segment is renumbered). 1 - Normal is always reversed (segment 1234 is read 2143).

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OptiStruct 13.0 Reference Guide 1731 Proprietary Information of Altair Engineering

Field

Contents 2 - Normal is never reversed (segment connected to a solid element are not renumbered).

INACTI

Flag for handling of initial penetrations (See comment 6). Default as defined by CONTPRM (Integer = 0, 3, 4) 0 - No action. 3 - Change slave node coordinates to avoid small initial penetrations. 4 - Change master node coordinates to avoid small initial penetrations. Invalid entries are ignored.

IFRIC

Friction formulation flag (See comment 7). Default as defined by CONTPRM (Character = COUL, GEN, DARM, REN) COUL - Static Coulomb friction law. GEN - Generalized viscous friction law. DARM - Darmstad friction law. REN - Renard friction law.

IFILT

Friction filtering flag (See comment 8). Default as defined by CONTPRM (Character = NO, SIMP, PER, CUTF) NO - No filter is used. SIMP - Simple numerical filter. PER - Standard -3dB filter with filtering period. CUTF - Standard -3dB filter with cutting frequency.

FFAC

Friction filtering factor. Default as defined by CONTPRM (Real = 0.0 < FFAC < 1.0)

FRICDAT

FRICDAT flag indicates that additional information for IFRIC will follow. Only available when IFRIC = GEN, DARM or REN.

C1, C2, C3, Coefficients to define variable friction coefficient in IFRIC = GEN, DARM, C4, C5, C6 REN. Default as defined by CONTPRM (Real > 0) Comments 1.

The property identification number must be that of an existing PCONT bulk data entry. Only one PCNTX5 property extension can be associated with a particular PCONT.

2.

PCNTX5 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM or IMPDYN. It is ignored for all other subcases.

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3.

If FRIC is not explicitly defined on the PCONTX/PCNTX# entries, the MU1 value on the CONTACT or PCONT entry is used for FRIC in the /INTER entries for Geometric Nonlinear Analysis. Otherwise, FRIC on PCONTX/PCNTX# overwrites the MU1 value on CONTACT/ PCONT.

4.

In implicit analysis, different contact formulations are used for contact where slave and master set do not overlap and where they overlap (self-contact). In the case of self-contact, the gap cannot be zero and a constant gap is used. For small initial gaps, the convergence will be more stable and faster if GAP is larger than the initial gap. In implicit analysis, sometimes a stiffness with scaling factor reduction (for example, STFAC = 0.01) or reduction in impacted thickness (if rigid one) might reduce unbalanced forces and improve convergence, particularly in shell structures under bending where the effective stiffness is much lower than membrane stiffness; but it should be noted that too low of a value could also lead to divergence.

5. Flag IDEL = 1 has a CPU cost higher than IDEL = 2. 6. INACTI = 3, 4 are only recommended for small initial penetrations and should be used with caution because: the coordinate change is irreversible. it may create other initial penetrations if several surface layers are defined in the interfaces. it may create initial energy if the node belongs to a spring element. 7.

IFRIC defines the friction model. IFRIC = COUL – Coulomb friction with F T < FRIC * F N. For IFRIC > 0 the friction coefficient is set by a function (µ = µ (p, V)), where p is the pressure of the normal force on the master segment and V is the tangential velocity of the slave node. The following formulations are available: IFRIC = 1 - Generalized viscous friction law µ = FRIC + C1 * p + C2 * V + C3 * p * v + C4 * p2 + C5 * v2 IFRIC = 2 - Darmstad law µ = C1 * e(C 2V ) * p2 + C3 * e(C 4V ) * p + C5 * e(C 6V ) IFRIC = 3 - Renard law

0 < V < C5

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C5 < V < C6

C6 < V

where:

The first critical velocity Vcr1 second critical velocity Vcr2 (C5 < C6). The static friction coefficient C1 and the dynamic friction coefficient C2, must be lower than the maximum friction C3 (C1 < C3 and C2 < C3). The minimum friction coefficient C4, must be lower than the static friction coefficient C1 and the dynamic friction coefficient C2 (C4 < C1 and C4 < C2). 8.

IFILT defines the method for computing the friction filtering coefficient. If IFILT the tangential friction forces are smoothed using a filter:

NO,

F T = α * F'T + (1 - α) * F'T-1 where, F T - Tangential force F'T - Tangential force at time t F'T-1 - Tangential force at time t-1 α - filtering coefficient IFILT = SIMP – α = FFAC IFILT = PER – α = 2 IFILT = CUTF – α = 2 9.

dt/FFAC, where dt/T = FFAC, T is the filtering period * FFAC * dt, where FFAC is the cutting frequency

This card is represented as an extension to a PCONT property in HyperMesh.

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PCNTX7 Bulk Data Entry PCNTX7 – Extended CONTACT Property type 7 for Geometric Nonlinear Analysis Description Defines properties type 7 of a CONTACT interface for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

PC NTX7

PID

ISTF

ITHE

IGAP

GAPFAC

GAPMAX

FPENMAX

STMIN

STMAX

MESHSIZ E

DTMIN

IREMGAP

STFAC

FRIC

GAP

TSTART

TEND

INAC TI

VISS

IFORM

SENSID

IBC

(5)

IFRIC

IFILT

FFAC

C URVDA T

G1

G2

FRIC DAT

C1

C2

C3

ADMDAT

NRADM

PADM

ANGLAD M

THEDAT

RTHE

FRAD

DRAD

FHEATS

(6)

(7)

(8)

(9)

IBAG

IDEL

IC URV

IADM

VISF

BMULT

C4

C5

C6

TINT

ITHEF

(10)

FHEATM

Example

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(1)

(2)

PC ONT

34

PC NTX7

34

(3)

(4)

(5)

(6)

(7)

Field

Contents

PID

Property identification number of the associated PCONT.

(8)

(9)

(10)

No default (Integer > 0) ISTF

Flag for stiffness definition (See comment 5). Default as defined by CONTPRM (Integer = 0, …, 5) 0 - The stiffness is computed according to the master side characteristics. 1 - STIF1 is used as interface stiffness. 2, 3, 4 and 5 - The interface stiffness is computed from both master and slave characteristics.

ITHE

Heat contact flag (Integer). Default = 0. 0 - No heat transfer. 1 - Heat transfer activated.

IGAP

Flag for gap definition. Default as defined by CONTPRM (Character = CONST, VAR, VAR2, VAR3) CONST - Gap is constant and equal to GAP (See comment 6). VAR, VAR2, VAR3 - Gap is variable (in space, not in time) according to the characteristics of the impacting surfaces and nodes (See comment 7).

IBAG

Airbag vent holes closure flag in case of contact. Default = 0 (Integer). 0 - No closure. 1 - Closure.

IDEL

Flag for node and segment deletion. Default as defined by CONTPRM (Integer = 0, …, 2)

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Field

Contents 0 - No deletion. 1 - When all the elements (shells, solids) associated to one segment are deleted, the segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface. 2 - When a shell or a solid element is deleted, the corresponding segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface.

ICURV

Gap envelope with curvature (See comment 8). Integer 0, ..., 3. 0 - No curvature. 1 - Spherical curvature. 2 - Cylindrical curvature. 3 - Automatic bicubic surface.

IADM

Computing local curvature flag for adaptive meshing (See comments 9 and 10). Default = 0 (Integer 0, 1, 2). 0 - Not activated. 1 - Interface update according mesh size. 2 - Interface update according mesh size, penetration and angle.

GAPFAC

Gap scale factor (used only when IGAP = VAR2 and VAR3). Default as defined by CONTPRM (Real > 0)

GAPMAX

Maximum gap (used only when IGAP = VAR2 and VAR3). Default as defined by CONTPRM (Real > 0)

FPENMAX

Maximum fraction of initial penetration (See comment 13). (Real)

STMIN

Minimum stiffness (Only with ISTF > 1). Default as defined by CONTPRM (Real > 0)

STMAX

Maximum stiffness (Only with ISTF > 1).

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Field

Contents Default as defined by CONTPRM (Real > 0)

MESHSIZE

Percentage of mesh size (used only when IGAP = VAR3). Default = 0.4 (Real, 0.0 < MESHSIZE < 1.0)

DTMIN

Limiting nodal time step (see comment 19)

IREMGAP

Flag to deactivate slave nodes if element size < gap value, in case of self-impact contact (See comment 20). Default = 1 (Integer) 1 - No slave node deactivation 2 - Deactivate slave nodes.

STFAC

Interface stiffness scale factor. Default as defined by CONTPRM (Real > 0)

FRIC

Coulomb friction. Default as defined by CONTPRM (Real > 0)

GAP

Gap for impact activation (See comments 4 and 6). Default as defined by CONTPRM (Real > 0)

TSTART

Start time Default = 0.0 (Real > 0)

TEND

Time for temporary deactivation. Default = 1030 (Real > 0)

IBC

Flag for deactivation of boundary conditions at impact applied to the slave grid set. Default as defined by CONTPRM (Character = X, Y, Z, XY, XZ, YZ, XYZ)

INACTI

Flag for handling of initial penetrations (See comment 13). Default as defined by CONTPRM (Integer = 0, 1, 2, 3, 5, or 6) 0 1 2 3

-

No action. Deactivation of stiffness on nodes. Deactivation of stiffness on elements. Change slave node coordinates to avoid small initial penetrations.

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Field

Contents 5 - GAP is variable with time and initial gap is adjusted as follows: gap0 = gap - P0 6 - Gap is variable with time but initial gap is slightly de-penetrated as follows: gap0 = gap - P0 – 0.05*(gap - P0) Invalid entries are ignored.

VISS

Critical damping coefficient on interface stiffness. Default as defined by CONTPRM (Real > 0)

VISF

Critical damping coefficient on interface friction. Default as defined by CONTPRM (Real > 0)

BMULT

Sorting factor. Can be used to speed up the sorting algorithm. Is machine-dependent. Default as defined by CONTPRM (Real > 0)

IFRIC

Friction formulation flag (See comment 14). Default as defined by CONTPRM (Character = COUL, GEN, DARM, or REN) COUL - Static Coulomb friction law. GEN - Generalized viscous friction law. DARM - Darmstad friction law. REN - Renard friction law.

IFILT

Friction filtering flag (See comment 15). Default as defined by CONTPRM (Character = NO, SIMP, PER, or CUTF) NO - No filter is used. SIMP - Simple numerical filter. PER - Standard -3dB filter with filtering period. CUTF - Standard -3dB filter with cutting frequency.

FFAC

Friction filtering factor. Default as defined by CONTPRM (Real = 0.0 < FFAC < 1.0)

IFORM

Type of friction penalty formulation (See comment 16). Default as defined by CONTPRM (Character = VISC, STIFF) VISC - Viscous (total) formulation.

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Field

Contents STIFF - Stiffness (incremental) formulation.

SENSID

Sensor identifier to Activate/Deactivate the interface (See comment 21) No default (Integer) If a sensor identifier is defined, the activation/deactivation of the interface is based on SENSID instead of TSTART or TSTOP.

CURVDAT

CURVDAT flag indicates that additional information about ICURV will follow. Only available when ICURV = 1 or 2.

G1

First grid identifier (used only when ICURV = 1 or 2) (Integer)

G2

Second grid identifier (used only when ICURV = 2, ignored when ICURV = 1) (Integer)

FRICDAT

FRICDAT flag indicates that additional information for IFRIC will follow. Only available when IFRIC = GEN, DARM or REN.

C1, C2, C3, Coefficients to define variable friction coefficient in IFRIC = GEN, DARM, C4, C5, C6 REN. Default as defined by CONTPRM (Real > 0) ADMDAT

ADMDAT flag indicates that additional information about IADM will follow. Only available when IADM = 2.

NRADM

Number of elements through a 90 degree radius 3 (used only when IADM = 2) (Integer)

PADM

Criteria on the percentage of penetration (used only when IADM = 2). Default = 1.0 (Real)

ANGLADM

Angle criteria (used only when IADM = 2) (Real)

THEDAT

THEDAT flag indicates that additional information about ITHE will follow. Only available when ITHE = 1.

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Field

Contents

RTHE

Heat conduction coefficient (used only when ITHE = 1, see comment 18) (Real).

TINT

Interface temperature (used only when ITHE = 1) (Real)

ITHEF

Heat contact formulation flag (used only when ITHE = 1, Integer). 0 - Exchange between constant temperature in the interface and shells (slave side). 1 - Heat exchange between pieces in contact.

FRAD

Radiation factor (used only when ITHE = 1) No default (Real)

DRAD

Maximum distance for radiation computation (used only when ITHE = 1) No default (Real)

FHEATS

Frictional heating factor of the slave (used only when ITHE = 1, see comment 25) No default (Real)

FHEATM

Frictional heating factor of the master (used only when ITHE = 1, see comment 25) No default (Real)

Comments 1.

The property identification number must be that of an existing PCONT bulk data entry. Only one PCNTX7 property extension can be associated with a particular PCONT.

2.

PCNTX7 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

If FRIC is not explicitly defined on the PCONTX/PCNTX# entries, the MU1 value on the CONTACT or PCONT entry is used for FRIC in the /INTER entries for Geometric Nonlinear Analysis. Otherwise, FRIC on PCONTX/PCNTX# overwrites the MU1 value on CONTACT/ PCONT.

4.

In implicit analysis, different contact formulations are used for contact where slave and master set do not overlap and where they overlap (self-contact). In the case of self-contact, the gap cannot be zero and a constant gap is used. For small initial gaps, the convergence will be more stable and faster if GAP is larger than the

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initial gap. In implicit analysis, sometimes a stiffness with scaling factor reduction (for example, STFAC = 0.01) or reduction in impacted thickness (if rigid one) might reduce unbalanced forces and improve convergence, particularly in shell structures under bending where the effective stiffness is much lower than membrane stiffness; but it should be noted that too low of a value could also lead to divergence. 5. and/or the slave segment stiffness Ks. The master stiffness is computed from Km = STFAC * B * S * S/V for solids, Km = 0.5 * STFAC * E * t for shells. The slave stiffness is an equivalent nodal stiffness computed as Ks = STFAC * B * V-3 for solids, Ks = 0.5 * STFAC * E * t for shells. In these equations, B is the Bulk Modulus, S is the segment area, and V is the volume of a solid. There is no limitation to the value of stiffness factor (but a value larger than 1.0 can reduce the initial time step). The interface stiffness is then K = max (STMIN, min (STMAX, K1)) with: ISTF = 0, K1 = Km ISTF = 2, K1 = 0.5 * (Km + Ks) ISTF = 3, K1 = max (Km, Ks) ISTF = 4, K1 = min (Km, Ks) ISTF = 5, K1 = Km * Ks / (Km + Ks) 6. The default for the constant gap (IGAP = CONST) is the minimum of: t, average thickness of the master shell elements; l/10, l – average side length of the master solid elements; lmin/2, lmin – smallest side length of all master segments (shell or solid). 7.

If IGAP = VAR, the variable gap is computed as gs + gm; If IGAP = VAR2, the variable gap is computed as max(GAP, min(GAPFAC * (gs+gm), GAPMAX); If IGAP = VAR3, the variable gap is computed as max(GAP, min(GAPFAC * (gs+gm), MESHSIZE * (gsl+gml), GAPMAX). with: gm - master element gap, with: gm = t/2, t: thickness of the master element for shell elements. gm = 0 for solid elements. gs - slave node gap: gs = 0 if the slave node is not connected to any element or is only connected to solid

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or spring elements. gs = t/2, t - largest thickness of the shell elements connected to the slave node. element. gml - length of the smaller edge of element. gsl - length of the smaller edge of elements connected to the slave nodes. If the slave node is connected to multiple shells and/or beams or trusses, the largest computed slave gap is used. The variable gap is always at least equal to GAP. 8.

If ICURV = 1, a spherical curvature is defined for the gap with node_ID1 (center of the sphere). If ICURV = 2, a cylindrical curvature is defined for the gap with node_ID1 and node_ID2 (on the axis of the cylinder). If ICURV = 3, the master surface shape is obtained with a bicubic interpolation, respecting continuity of the coordinates and the normal from one segment to the other. In case of a large change in curvature, this formulation might become unstable (will be improved in future version).

9.

In case of adaptive meshing and IADM =1: If the contact occurs in a zone (master side) whose radius of curvature is lower than the element size (slave side), the element on the slave side will be divided (if not yet at maximum level).

10. In case of adaptive meshing and IADM =2:

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If the contact occurs in a zone (master side) whose radius of curvature is lower than NRadm times the element size (slave side), the element on the slave side will be divided (if not yet at maximum level). If the contact occurs in a zone (master side) where the angles between the normals are greater than Angladm and the percentage of penetration is greater than Padm, the element on the slave side will be divided (if not yet at maximum level).

11. The coefficients NRADM, PADM, and ANGLADM are used only adaptive meshing and IADM = 2. 12. If GAPMAX is equal to zero, there is no maximum value for the gap. 13. INACTI = 3, is only recommended for small initial penetrations and should be used with caution because: the coordinate change is irreversible. it may create other initial penetrations if several surface layers are defined in the interfaces. it may create initial energy if the node belongs to a spring element. INACTI = 5 is recommended for airbag simulation deployment. INACTI = 6 is recommended instead of INACTI = 5, in order to avoid high frequency effects into the interfaces.

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If FPENMAX is not equal to zero, nodes stiffness is deactivated if penetration > FPENMAX*GAP, regardless of the value of INACTI. 14. IFRIC defines the friction model. IFRIC = COUL – Coulomb friction with F T < FRIC * F N. For IFRIC > 0 the friction coefficient is set by a function ( = (p, V)), where p is the pressure of the normal force on the master segment and V is the tangential velocity of the slave node. The following formulations are available: IFRIC = 1 - Generalized viscous friction law = FRIC + C1 * p + C2 * V + C3 * p * v + C4 * p2 + C5 * v2 IFRIC = 2 - Darmstad law = C1 * e(C 2V) * p2 + C3 * e(C 4V) * p + C5 * e(C 6V) IFRIC = 3 - Renard law

0 < V < C5

C5 < V < C6

C6 < V

where:

The first critical velocity Vcr1 second critical velocity Vcr2 (C5 < C6). The static friction coefficient C1 and the dynamic friction coefficient C2, must be lower than the maximum friction C3 (C1 < C3) and C2 < C3).

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The minimum friction coefficient C4, must be lower than the static friction coefficient C1 and the dynamic friction coefficient C2 (C4 < C1 and C4 < C2). 15. the tangential friction forces are smoothed using a filter: F T = α * F'T + (1 - α) * F'T-1 where, F T - Tangential force F'T - Tangential force at time t F'T-1 - Tangential force at time t-1 α - filtering coefficient IFILT = SIMP – α = FFAC IFILT = PER – α = 2 dt/FFAC, where dt/T = FFAC, T is the filtering period IFILT = CUTF – α = 2

* FFAC * dt, where FFAC is the cutting frequency

16. IFORM selects two types of contact friction penalty formulation. The viscous (total) formulation (IFORM = VISC) computes an adhesive force as: F adh

T

F T = min (µF N, F adh) The stiffness (incremental) formulation (IFORM = STIFF) computes an adhesive force as: F adh = F Told + F T F T = K * VT * dt F Tnew = min (µF N, F adh) 17. Exchange between shell and constant temperature contact TINT. 18. RTHE is the inverse of thermal resistance (units: [W/(m2·K)]). 19. Slave segment contact is deactivated when the segment kinematic time step calculated for this contact is lower than DTMIN. 20. With IREMGAP = 2, this allows the element size < gap values:

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In case of self-impact contact, when curvilinear distance (from a node of the master segment to a slave node) is < gap*sqrt(2) (in initial configuration), then this slave node will not be taken into account by this master segment, and it will not be deleted from the contact for the other master segments. 21. When SENSID is defined for activation/deactivation of the interface, TSTART and TSTOP are not taken into account. 22. If FRAD is not equal to zero, and d, the distance from the slave node to the master segment, is in the range: Gap < d < DRAD, then radiation is calculated. The radiant heat transfer conductance is calculated as:

Where, 2

is the Stefan Boltzman constant,

1

is the emissivity of the slave surface, and

is the emissivity of the master surface.

23. If FRAD is not equals to zero, then the default value of DRAD is calculated as the maximum of: upper value of the gap (at time 0) among all nodes; smallest side length of slave element. 24. A very high value of DRAD is not recommended as it may reduce the performance of the solver 25. Frictional energy is converted into heat when heat transfer is activated (ITHE > 0) on the interface. Options FHEATS and FHEATM are used to control this option. When FHEATS and FHEATM = 0, the conversion of the frictional sliding energy to heat is not activated. Non-zero values of FHEATS and FHEATM define the fraction of this energy which is converted into heat and transferred to the slave and master respectively. The frictional heat QFric is defined as follows:

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If IFORM = 2 (a stiffness formulation):

Slave:

Master:

(ITHEF=1)

If IFORM = 1 (a penalty formulation): Slave: Master:

(ITHEF=1)

26. This card is represented as an extension to a PCONT property in HyperMesh.

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PCNTX11 Bulk Data Entry PCNTX11 – Extended Contact (CONTX11) Property type 11 for Geometric Nonlinear Analysis Description Defines properties type 11 of a CONTACT interface for geometric nonlinear analysis. Format (1)

(2)

PC NTX11

PID

(3)

(4)

(5)

(6)

ISTF

(7)

(9)

IGAP

(10)

IDEL

STMIN

STMAX

MESHSIZE

DTMIN

STFAC

FRIC

GAP

TSTART

TEND

STF1

INAC TI

VISS

VISF

IBC

(8)

BMULT

Example

(1)

(2)

PC ONT

34

PC NTX11

34

(3)

(4)

(5)

(6)

(7)

(8)

Field

Contents

PID

Property identification number of the associated PCONT.

(9)

(10)

No default (Integer > 0) ISTF

Flag for stiffness definition (See comment 6). Default as defined by CONTPRM (Integer = 0, …, 5) 0 - STFAC is a stiffness scale factor and the stiffness is computed according to the master side characteristics. 1 - STIF1 is used as interface stiffness. 2, 3, 4 and 5 - STFAC is a stiffness scale factor and the interface

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Field

Contents stiffness is computed from both master and slave characteristics.

IGAP

Flag for gap definition. Default as defined by CONTPRM (Character = CONST, VAR, VAR3) CONST - Gap is a constant and equal to GAP (See comment 7). VAR - Gap is a variable (in space, not in time) according to the characteristics of the impacted master line and the impacting slave nodes (See comment 8). VAR3 - Gap is a variable according to the characteristics of the impacted master line and impacting slave node + gap is taken into account the size of the elements.

IDEL

Flag for node and segment deletion. Default as defined by CONTPRM (Integer = 0, …, 2) 0 - No deletion. 1 - When all the elements (shells and solids) associated to one segment are deleted, the segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface. 2 - When a shell or a solid element is deleted, the corresponding segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface.

STMIN

Minimum stiffness (Only with ISTF > 1). Default as defined by CONTPRM (Real > 0)

STMAX

Maximum stiffness (Only with ISTF > 1). Default as defined by CONTPRM (Real > 0)

MESHSIZE

Percentage of mesh size (Used only when IGAP = VAR3). Default = 0.4 (Real, 0.0 < MESHSIZE < 1.0)

DTMIN

Limiting nodal time step (see comment 10) No default (Real > 0)

STFAC Default as defined by CONTPRM (Real > 0)

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Field

Contents

FRIC

Coulomb friction. Default as defined by CONTPRM (Real > 0)

GAP

Gap for impact activation (See comments 7 and 8). Default as defined by CONTPRM (Real > 0)

TSTART

Start time. Default = 0.0 (Real > 0)

TEND

Time for temporary deactivation. Default = 1030 (Real > 0)

STIF1

Interface stiffness (Only with ISTF = 1). Default = 0.0 (Real > 0)

IBC

Flag for deactivation of boundary conditions at impact applied to the slave grid set. Default as defined by CONTPRM (Character = X, Y, Z, XY, XZ, YZ, XYZ)

INACTI

Flag for handling of initial penetrations (See comment 8). Default as defined by CONTPRM (Integer = 0, 1, 2, 3, 5, or 6) 0 1 2 3 5

-

No action. Deactivation of stiffness on nodes. Deactivation of stiffness on elements. Change slave node coordinates to avoid small initial penetrations. GAP is a variable with time and initial gap is adjusted as follows: gap0 = gap - P0

6 - Gap is variable with time but initial gap is slightly de-penetrated as follows: gap0 = gap - P0 – 0.05*(gap - P0) Invalid entries are ignored. VISS

Critical damping coefficient on interface stiffness. Default as defined by CONTPRM (Real > 0)

VISF

Critical damping coefficient on interface friction. Default as defined by CONTPRM (Real > 0)

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Field

Contents

BMULT

Sorting factor. Can be used to speed up the sorting algorithm and is machine-dependent. Default as defined by CONTPRM (Real > 0)

Comments 1. The property identification number must be that of an existing PCONT bulk data entry. Only one PCNTX11 property extension can be associated with a particular PCONT. 2. PCNTX11 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases. 3. If FRIC is not explicitly defined on the PCONTX/PCNTX# entries, the MU1 value on the CONTACT or PCONT entry is used for FRIC in the /INTER entries for Geometric Nonlinear Analysis. Otherwise, FRIC on PCONTX/PCNTX# overwrites the MU1 value on CONTACT/ PCONT. 4. PCNTX11 defines the properties of contact interface type CONTX11, it describes the edge to edge or line to line interface. This interface simulates impact between lines, a line can be a beam or truss element or a shell edge or spring elements. The interface properties are: impacts occur between a master and a slave line; a slave line can impact on one or more master lines; a line can belong to the master and the slave side. This allows self impact; this interface can be used in addition to the interface type 7 PCNTX7 to solve the edge to edge limitation of interface type 7. 5. and/or the slave segment stiffness Ks. The master stiffness is computed from Km = STFAC * B * S * S/V for solids, Km = 0.5 * STFAC * E * t for shells. The slave stiffness is an equivalent nodal stiffness computed as Ks = STFAC * B * V-3 for solids, Ks = 0.5 * STFAC * E * t for shells. In these equations, B is the Bulk Modulus, S is the segment area, and V is the volume of a solid. There is no limitation to the value of stiffness factor (but a value larger than 1.0 can reduce the initial time step). The interface stiffness is then, K = max (STMIN, min (STMAX, K1)) with: ISTF = 0, K1 = Km ISTF = 2, K1 = 0.5 * (Km + Ks) ISTF = 3, K1 = max (Km, Ks) ISTF = 4, K1 = min (Km, Ks)

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ISTF = 5, K1 = Km * Ks / (Km + Ks) 6. The default for the constant gap (IGAP = CONST) is equal to GAP. 7. If IGAP = VAR, the variable gap is computed as: gm + gs with: gm - master element gap with gm = t/2, t: thickness of the master element for shell elements. gm = L/10, L - length of the smallest side of a solid element. element. gm = 0 for spring elements. gs - slave element gap is computed as the same way. If the slave node is connected to multiple shells and/or beams or trusses, the largest computed slave gap is used. The variable gap is always at least equal to GAP. 8. INACTI = 3, is only recommended for small initial penetrations and should be used with caution because: the coordinate change is irreversible. it may create other initial penetrations, if several surface layers are defined in the interfaces. it may create initial energy, if the node belongs to a spring element. INACTI = 5 is recommended for airbag simulation deployment. INACTI = 6 is recommended instead of INACTI = 5, in order to avoid high frequency effects into the interfaces.

9. The sorting factor BUMULT is used to speed up the sorting algorithm, it is machine dependent.

Altair Engineering

OptiStruct 13.0 Reference Guide 1753 Proprietary Information of Altair Engineering

10. Slave segment is deactivated from the contact when the segment kinematic time step calculated for this contact becomes smaller than DTMIN.

1754 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PCNTX20 Bulk Data Entry PCNTX20 – Extended CONTACT Property type 20 for Geometric Nonlinear Analysis Description Defines properties type 20 of a CONTACT interface for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

PC NTX20

PID

ISYM

IEDGE

GRNDID

(7)

(8)

(9)

(10)

EDGEAngle

IGAP

IBAG

IDEL

FPENMAX

STFAC

FRIC

GAP

IBC

TSATAT

TEND

INAC TI

VISS

VISF

C4

C5

IFRIC

IFILT

FFAC

IFORM

FRIC DAT

C1

C2

C3

C6

Example

(1)

(2)

PC ONT

34

PC NTX20

34

(3)

(4)

(5)

(6)

(7)

(8)

Field

Contents

PID

Property identification number of the associated PCONT.

(9)

(10)

No default (Integer > 0)

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OptiStruct 13.0 Reference Guide 1755 Proprietary Information of Altair Engineering

Field

Contents

ISYM

Flag for symmetric contact. Default as defined by CONTPRM (Character = SYM or UNSYM) SYM – Symmetric contact. UNSYM – Master-slave contact. If SSID defines a grid set, the contact is always a master-slave contact.

IEDGE

Flag for edge generation from slave and master surfaces. Default as defined by CONTPRM (Character = NO, ALL, BORD, FEAT) NO – No edge generation. All – All segment edges are included. BORD – External border of slave and master surface is used. FEAT – External border as well as features defined by FANG are used.

GRNDID

Optional nodes group identifier (Integer).

EdgeAngle

Edges angle (used only if IEDGE = FEAT) Default = 91 (Real). If angle between two edges is smaller than EdgeAngle, the edge is considered.

IGAP

Flag for gap definition. Default as defined by CONTPRM (Character = CONST or VAR) CONST - Gap is constant and equal to GAP (See comment 6). VAR - Gap is variable (in space, not in time) according to the characteristics of the impacting surfaces and nodes (See comment 7).

IBAG

Airbag vent holes closure flag in case of contact. Default = 0 (Integer). 0 - No closure. 1 - Closure.

IDEL

Flag for node and segment deletion. Default as defined by CONTPRM (Integer = 0, …, 2) 0 - No deletion. 1 - When all the elements (shells and solids) associated to one segment are deleted, the segment is removed from the master side of the

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Field

Contents interface. Additionally, non-connected nodes are removed from the slave side of the interface. 2 - When a shell or a solid element is deleted, the corresponding segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface.

FPENMAX

Maximum initial penetration factor (0 < FPENMAX < 1) (See comment 8). Default = 1.0 (Real)

STFAC

Interface stiffness scale factor. Default as defined by CONTPRM (Real > 0)

FRIC

Coulomb friction. Default as defined by CONTPRM (Real > 0)

GAP

Gap for impact activation (See comments 4 and 6). Default as defined by CONTPRM (Real > 0)

TSTART

Start time. Default = 0.0 (Real > 0)

TEND

Time for temporary deactivation. Default = 1030 (Real > 0)

IBC

Flag for deactivation of boundary conditions at impact applied to the slave grid set. Default as defined by CONTPRM (Character = X, Y, Z, XY, XZ, YZ, XYZ)

INACTI

Flag for handling of initial penetrations (See comment 9). Default as defined by CONTPRM (Integer = 0, 1, 2, 3, or 5) 0 - No action. 1 - Deactivation of stiffness on nodes. 2 - Deactivation of stiffness on elements. 3 - Change slave node coordinates to avoid small initial penetrations. 5 - Gap is variable with time but initial gap is slightly de-penetrated as follows: gap0 = gap - P0 – 0.05 * (gap - P0) Valid in explicit analysis: 0, 1, 2, 3 and 5.

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Field

Contents Invalid entries are ignored.

VISS

Critical damping coefficient on interface stiffness. Default as defined by CONTPRM (Real > 0)

VISF

Critical damping coefficient on interface friction. Default as defined by CONTPRM (Real > 0)

IFRIC

Friction formulation flag (See comment 10). Default as defined by CONTPRM (Character = COUL, GEN, DARM, REN) COUL - Static Coulomb friction law. GEN - Generalized viscous friction law. DARM - Darmstad friction law. REN - Renard friction law.

IFILT

Friction filtering flag (See comment 11). Default as defined by CONTPRM (Character = NO, SIMP, PER, CUTF) NO - No filter is used. SIMP - Simple numerical filter. PER - Standard -3dB filter with filtering period. CUTF - Standard -3dB filter with cutting frequency.

FFAC

Friction filtering factor. Default as defined by CONTPRM (Real = 0.0 < FFAC < 1.0)

IFORM

Type of friction penalty formulation (See comment 12). Default as defined by CONTPRM (Character = VISC, STIFF) VISC - Viscous (total) formulation. STIFF - Stiffness (incremental) formulation.

FRICDAT

FRICDAT flag indicates that additional information for IFRIC will follow. Only available when IFRIC = GEN, DARM or REN.

C1, C2, C3, Coefficients to define variable friction coefficient in IFRIC = GEN, DARM, C4, C5, C6 REN. Default as defined by CONTPRM (Real > 0) Comments 1.

The property identification number must be that of an existing PCONT bulk data entry. Only one PCNTX20 property extension can be associated with a particular PCONT.

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Altair Engineering

2.

PCNTX20 is only applied in geometric nonlinear explicit dynamic analysis subcase which is defined by ANALYSIS = EXPDYN, but not supported in NLGEOM or IMPDYN subcases. It is ignored for all other subcases.

3.

If FRIC is not explicitly defined on the PCONTX/PCNTX# entries, the MU1 value on the CONTACT or PCONT entry is used for FRIC in the /INTER entries for Geometric Nonlinear Analysis. Otherwise, FRIC on PCONTX/PCNTX# overwrites the MU1 value on CONTACT/ PCONT.

4.

In implicit analysis, different contact formulations are used for contact where slave and master set do not overlap and where they overlap (self-contact). In the case of self-contact, the gap cannot be zero and a constant gap is used. For small initial gaps, the convergence will be more stable and faster if GAP is larger than the initial gap. In implicit analysis, sometimes a stiffness with scaling factor reduction (for example, STFAC = 0.01) or reduction in impacted thickness (if rigid one) might reduce unbalanced forces and improve convergence, particularly in shell structures under bending where the effective stiffness is much lower than membrane stiffness; but it should be noted that too low of a value could also lead to divergence.

5. and/or the slave segment stiffness Ks. The master stiffness is computed from Km = STFAC * B * S * S/V for solids, Km = 0.5 * STFAC * E * t for shells. The slave stiffness is an equivalent nodal stiffness computed as Ks = STFAC * B * V-3 for solids, Ks = 0.5 * STFAC * E * t for shells. In these equations, B is the Bulk Modulus, S is the segment area, and V is the volume of a solid. There is no limitation to the value of stiffness factor (but a value larger than 1.0 can reduce the initial time step). The interface stiffness is then K = max (STMIN, min (STMAX, K1)) with: ISTF = 0, K1 = Km ISTF = 2, K1 = 0.5 * (Km + Ks) ISTF = 3, K1 = max (Km, Ks) ISTF = 4, K1 = min (Km, Ks) ISTF = 5, K1 = Km * Ks / (Km + Ks) 6. The default for the constant gap (IGAP = CONST) is the minimum of: t, average thickness of the master shell elements; l/10, l – average side length of the master solid elements; lmin/2, lmin – smallest side length of all master segments (shell or solid). 7. The variable gap (IGAP = VAR) is computed as: gs + gm with:

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OptiStruct 13.0 Reference Guide 1759 Proprietary Information of Altair Engineering

gm - master element gap with gm = t/2, t: thickness of the master element for shell elements. gm = 0 for solid elements. gs - slave node gap: gs = 0 if the slave node is not connected to any element or is only connected to solid or spring elements. gs = t/2, t - largest thickness of the shell elements connected to the slave node. element. If the slave node is connected to multiple shells and/or beams or trusses, the largest computed slave gap is used. 8. Maximum penetration value is set as a fraction of the actual gap (including variable gap): Penmax = FPENMAX * gap If the initial penetration of a slave node is greater than the calculated maximum value (Penmax), the node will be deactivated from the interface (node stiffness deactivation). 9. INACTI = 3, is only recommended for small initial penetrations and should be used with caution because: the coordinate change is irreversible. it may create other initial penetrations if several surface layers are defined in the interfaces. it may create initial energy if the node belongs to a spring element. INACTI = 5 works as follows:

10. IFRIC defines the friction model. IFRIC = COUL – Coulomb friction with F T < FRIC * F N. For IFRIC > 0, the friction coefficient is set by a function (

p, V

1760 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

)

Altair Engineering

where, p is the pressure of the normal force on the master segment and V is the tangential velocity of the slave node. The following formulations are available: IFRIC = 1 - Generalized viscous friction law µ = FRIC + C1 * p + C2 * V + C3 * p * v + C4 * p2 + C5 * v2 IFRIC = 2 - Darmstad law µ = C1 * e(C 2V ) * p2 + C3 * e(C 4V ) * p + C5 * e(C 6V ) IFRIC = 3 - Renard law

0 < V < C5

C5 < V < C6

C6 < V

where:

The first critical velocity Vcr1 second critical velocity Vcr2 (C5 < C6). The static friction coefficient C1 and the dynamic friction coefficient C2, must be lower than the maximum friction C3 (C1 < C3 and C2 < C3). The minimum friction coefficient C4, must be lower than the static friction coefficient C1 and the dynamic friction coefficient C2 (C4 < C1 and C4 < C2). 11. IFILT defines the method for computing the friction filtering coefficient. If IFILT the tangential friction forces are smoothed using a filter:

NO,

F T = α * F'T + (1 - α) * F'T-1

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OptiStruct 13.0 Reference Guide 1761 Proprietary Information of Altair Engineering

where, F T - Tangential force F'T - Tangential force at time t F'T-1 - Tangential force at time t-1 α - filtering coefficient IFILT = SIMP – α = FFAC IFILT = PER – α = 2

dt/FFAC, where dt/T = FFAC, T is the filtering period

IFILT = CUTF – α = 2

* FFAC * dt, where FFAC is the cutting frequency

12. IFORM selects two types of contact friction penalty formulation. The viscous (total) formulation (IFORM = VISC) computes an adhesive force as: F adh

T

F T = min (µF N, F adh) The stiffness (incremental) formulation (IFORM = STIFF) computes an adhesive force as: F adh = F Told + ∆F T ∆F T = K * VT * dt F Tnew = min (µF N, F adh) 13. This card is represented as an extension to a PCONT property in HyperMesh.

1762 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PCNTX24 Bulk Data Entry PCNTX24 – Extended CONTACT Property type 24 for Geometric Nonlinear Analysis Description Defines properties type 24 of a CONTACT interface for geometric nonlinear analysis. Format (1)

(2)

PC NTX24

PID

(3)

(4)

(5)

(6)

(7)

(8)

GAPMAXs

GAPMAXm

(9)

(10)

ISTF

STMIN

STMAX

STFAC

FRIC

IGAP0

IBC

IFRIC

IFILT

FFAC

FRIC DAT

C1

C2

IPEN0

IPENMAX

TSTART

TEND

INAC TI

VISS

IPENMIN

SENSID

C3

C4

C5

C6

Example

(1)

(2)

PC ONT

34

PC NTX24

34

Altair Engineering

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

OptiStruct 13.0 Reference Guide 1763 Proprietary Information of Altair Engineering

Field

Contents

PID

Property identification number of the corresponding PCONT entry. No default (Integer > 0)

ISTF

Flag for stiffness definition (See comment 5). Default as defined by CONTPRM (Integer = 0, …, 5) 0 - The stiffness is computed according to the master side characteristics. 2, 3, 4 and 5 - The interface stiffness is computed from both master and slave characteristics.

GAPMAXs

Slave maximum gaps. No default (Real)

GAPMAXm

Master maximum gaps. No default (Real)

STMIN

Minimum stiffness (Only with ISTF > 1). Default as defined by CONTPRM (Real > 0)

STMAX

Maximum stiffness (Only with ISTF > 1). Default as defined by CONTPRM (Real > 0)

IGAP0

Gap modification flag for slave shell nodes on the free edges. (Integer) 0 - No change 1 - Set gap to zero for the slave shell nodes

IPEN0

Initial penetration detection flag (See comment 14) (Integer) 0 - default method (excluding auto-impact in each part) 1 - method 1 (including auto-impact in each part)

IPENMAX

Maximum initial penetration: Penetration higher than this value will not be taken into account. (Real)

IPENMIN

Minimum initial penetration: Penetration higher than this value will be

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Field

Contents taken into account. (Real)

STFAC

Interface stiffness scale factor. Default as defined by CONTPRM (Real > 0)

FRIC

Coulomb friction. Default as defined by CONTPRM (Real > 0)

TSTART

Start time Default = 0.0 (Real > 0)

TEND

Time for temporary deactivation. Default = 1030 (Real > 0)

IBC

Flag for deactivation of boundary conditions at impact applied to the slave grid set. Default as defined by CONTPRM (Character = X, Y, Z, XY, XZ, YZ, XYZ)

INACTI

Flag for handling of initial penetrations (See comment 8). Default as defined by CONTPRM (Integer = 0, 1, -1, 5) 0 - only tiny initial penetrations (1.0e-08) will be taken into account. 1 - all initial penetrations will be ignored. -1 - all initial penetrations will be taken into account. 5 - GAP is variable with time and initial gap is adjusted as follows: gap0 = gap - P0 , where P0 is the initial penetration

VISS

Critical damping coefficient on interface stiffness. Default as defined by CONTPRM (Real > 0)

IFRIC

Friction formulation flag (See comment 9). Default as defined by CONTPRM (Character = COUL, GEN, DARM, REN) COUL - Static Coulomb friction law. GEN - Generalized viscous friction law. DARM - Darmstad friction law. REN - Renard friction law.

IFILT

Friction filtering flag (See comment 10).

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OptiStruct 13.0 Reference Guide 1765 Proprietary Information of Altair Engineering

Field

Contents Default as defined by CONTPRM (Character = NO, SIMP, PER, CUTF) NO - No filter is used. SIMP - Simple numerical filter. PER - Standard -3dB filter with filtering period. CUTF - Standard -3dB filter with cutting frequency.

FFAC

Friction filtering factor. Default as defined by CONTPRM

SENSID

Sensor identifier to Activate/Deactivate the interface (See comment 12) No default (Integer) If a sensor identifier is defined, the activation/deactivation of interface is based on the sensor and not on Tstart or Tstop.

FRICDAT

FRICDAT flag indicates that additional information for IFRIC will follow. Only available when IFRIC = GEN, DARM or REN.

C1, C2, C3, Coefficients to define variable friction coefficient in IFRIC = GEN, DARM, C4, C5, C6 REN. Default as defined by CONTPRM (Real > 0) Comments 1.

The property identification number must be that of an existing PCONT bulk data entry. Only one PCNTX24 property extension can be associated with a particular PCONT.

2.

PCNTX24 is only supported for geometric nonlinear explicit dynamic analysis subcase defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

If FRIC is not explicitly defined on the PCONTX/PCNTX# entries, the MU1 value on the CONTACT or PCONT entry is used for FRIC in the /INTER entries for Geometric Nonlinear Analysis. Otherwise, FRIC on PCONTX/PCNTX# overwrites the MU1 value on CONTACT/ PCONT.

4.

In implicit analysis, different contact formulations are used for contact where slave and master set do not overlap and where they overlap (self-contact). In the case of self-contact, the gap cannot be zero and a constant gap is used. For small initial gaps, the convergence will be more stable and faster if GAP is larger than the initial gap. In implicit analysis, sometimes a stiffness with scaling factor reduction (for example, STFAC = 0.01) or reduction in impacted thickness (if rigid one) might reduce unbalanced forces and improve convergence, particularly in shell structures under bending where the effective stiffness is much lower than membrane stiffness; but it should be noted that too low of a value could also lead to divergence.

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5. and/or the slave segment stiffness Ks. The master stiffness is computed from Km = STFAC * B * S * S/V for solids, Km = 0.5 * STFAC * E * t for shells. The slave stiffness is an equivalent nodal stiffness computed as Ks = STFAC * B * V-3 for solids, Ks = 0.5 * STFAC * E * t for shells. In these equations, B is the Bulk Modulus, S is the segment area, and V is the volume of a solid. There is no limitation to the value of stiffness factor (but a value larger than 1.0 can reduce the initial time step). The interface stiffness is then K = max (STMIN, min (STMAX, K1)) with: ISTF = 0, K1 = Km ISTF = 2, K1 = 0.5 * (Km + Ks) ISTF = 3, K1 = max (Km, Ks) ISTF = 4, K1 = min (Km, Ks) ISTF = 5, K1 = Km * Ks / (Km + Ks) 6.

The gap is computed automatically (similar with IGAP = VAR on PCNTX7) for each impact as gs + gm; with: gm - master element gap, with: gm = t/2, t: thickness of the master element for shell elements. gm = 0 for solid elements. gs - slave node gap: gs = 0 if the slave node is not connected to any element or is only connected to solid or spring elements. gs = t/2, t - largest thickness of the shell elements connected to the slave node. element. gm and gs are limited separately by GAPMAXm and GAPMAXs before the gap computation.

7.

The coefficients C1 - C6 are used to define a variable friction coefficient

.

8.

INACTI = 0 ignores the initial penetrations, but the contacts are not deleted, new contact will be well detected once the penetrations are disappeared. INACTI = 5 is similar to the one of interface type 7, but once the initial penetration is gone, the new contact will be detected using not-adjusted gap (P0 is reset to zero).

9.

IFRIC defines the friction model. IFRIC = COUL – Coulomb friction with F T < FRIC * F N.

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OptiStruct 13.0 Reference Guide 1767 Proprietary Information of Altair Engineering

p, V

For IFRIC > 0 the friction coefficient is set by a function (

)

where, p is the pressure of the normal force on the master segment and V is the tangential velocity of the slave node. The following formulations are available: IFRIC = GEN - Generalized viscous friction law FRIC + C1 * p + C2 * V + C3 * p * v + C4 * p2 + C5 * v2 IFRIC = DARM - Darmstad law = C1 * e(C 2V) * p2 + C3 * e(C 4V) * p + C5 * e(C 6V) IFRIC = REN - Renard law

0 < V < C5

C5 < V < C6

C6 < V

where:

The first critical velocity Vcr1 second critical velocity Vcr2 (C5 < C6). The static friction coefficient C1 and the dynamic friction coefficient C2, must be lower than the maximum friction C3 (C1 < C3 and C2 < C3). The minimum friction coefficient C4, must be lower than the static friction coefficient C1 and the dynamic friction coefficient C2 (C4 < C1 and C4 < C2). 10. IFILT defines the method for computing the friction filtering coefficient. If IFILT the tangential friction forces are smoothed using a filter:

1768 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

NO,

Altair Engineering

F T = α * F'T + (1 - α) * F'T-1 where, F T - Tangential force F'T - Tangential force at time t F'T-1 - Tangential force at time t-1 α - filtering coefficient IFILT = SIMP – α = FFAC IFILT = PER – α = 2

dt/FFAC, where dt/T = FFAC, T is the filtering period

IFILT = CUTF – α = 2

* FFAC * dt, where FFAC is the cutting frequency

11. IFORM selects two types of contact friction penalty formulation. The viscous (total) formulation (IFORM = VISC) computes an adhesive force as: F adh

T

F T = min (µF N, F adh) The stiffness (incremental) formulation (IFORM = STIFF) computes an adhesive force as: F adh = F Told + ∆F T ∆F T = K * VT * dt F Tnew = min (µF N, F adh) 12. When SENSID is defined for activation/deactivation of the interface, TSTART and TSTOP are not taken into account. 13. When the contact type is the symmetric surface to surface, the output normal contact forces in TH file are correctly calculated if the two surfaces are well separated. 14. IPEN0 = 0 excludes the initial auto-impacts in the same part (shell and solid elements only). IPEN0 = 1 takes into account the initial auto-impacts in the same part, but in some complex situations, wrong initial penetrations might be given. 15. For implicit test: Interface type24 is now only available with SMP. The default of ISTF will be set to 4. The default INACTI will be set to -1 . 16. This card is represented as an extension to a PCONT property in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1769 Proprietary Information of Altair Engineering

PCOMP Bulk Data Entry PCOMP – Composite Laminate Property Description Defines the structure and properties of an n-ply composite laminate material. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PC OMP

PID

Z0

NSM

SB

FT

TREF

GE

LAM

MID1

T1

THETA1

SOUT1

MID2

T2

THETA2

SOUT2

MID3

T3

THETA3

SOUT3

etc.

DS

Example

(1)

(2)

(3)

PC OMP

100

-0.5

120

0.2

120

0.2

(4)

(5)

(6)

(7)

1.E5

STRN

100.

0.0

YES

120

0.6

0.0

YES

(8)

(9)

0.0

NO

(10)

1.0

Field

Contents

PID

Unique composite property identification number. No default (Integer > 0)

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Field

Contents

Z0

Real number or character input (Top/Bottom) Real Number - It represents the distance from the shell element reference plane to the bottom surface of the shell (Default = -0.5 * Thick, Thick being the composite total thickness (Real or blank)). Character Input - See comment 17

NSM

Nonstructural mass per unit area. No default (Real)

SB

Allowable inter-laminar shear stress (shear stress in the bonding material). Disregarded if blank or 0.0. No default (Real > 0.0)

FT

Failure theory code. If blank, no failure calculations are performed. The following failure theory codes are supported: HILL for Hill theory, HOFF for Hoffman theory, TSAI for Tsai-Wu theory, STRN for Maximum Strain Theory. See comments 13 through 15. Default = no failure calculations are performed (HILL, HOFF, TSAI, or STRN)

TREF

Reference (stress free) temperature. See comment 1. Default = 0.0 (Real)

GE

Damping coefficient. See comments 10 and 11. Default = 0.0 (Real)

LAM

Laminate option. If blank, all plies must be specified and all stiffness terms are developed. The following options are supported: SYM: Only plies on the bottom half of the composite lay-up needs to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top.

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Field

Contents MEM: All plies must be specified, but only membrane terms MID1 are developed. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). BEND: All plies must be specified, but only bending terms MID2 are developed. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SMEAR: All plies must be specified, stacking sequence is ignored, and MID1 is set equal to MID2 on the derived equivalent PSHELL, while MID3, MID4, TS/T, and 12I/T**3 are set to zero. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SMEARZ0: All plies must be specified, stacking sequence is ignored. While the laminate is still considered to be made of homogenized (smeared) material, the effect of offset Z0 is taken into account. Hence, if Z0 is not equal to -0.5*Thick, the equivalent PSHELL will include MID1, MID2 and MID4. MID3 is still set to zero, that is no transverse shear deformation is considered. SMCORE: All plies must be specified. The last ply specifies core properties and the previous plies specify face sheet properties. The face sheet properties are calculated without regard for stacking sequence; half of the total face sheet thickness is then placed on top of the core, and half is placed on the bottom, to produce a symmetric laminate. Stiffness of the core is ignored while its density is included in inertia calculations. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SYMEM: Only plies on the bottom half of the composite lay-up needs to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top. Only membrane terms are developed for the full laminate. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SYBEND: Only plies on the bottom half of the composite lay-up needs to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top. Only bending terms are developed for the full laminate. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SYSMEAR: Only plies on the bottom half of the composite lay-up needs to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top. Stacking sequence is ignored, and MID1 is set equal to MID2 on the derived equivalent PSHELL, while MID3, MID4, TS/T and 12I/T**3 are set to zero. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). Default = blank, that is all plies must be specified (SYM, MEM, BEND, SMEAR, SMCORE, SYMEM, SYBEND or SYSMEAR)

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Field

Contents

MIDi

Material IDs of individual plies. The plies are identified by consecutively numbering them from 1 at the bottom layer. The MIDs must refer to MAT1, MAT2, MAT4, MAT5, or MAT8 bulk data entries. If MIDi is not specified, default is the last defined MIDi. Default = last defined MIDi (Integer>0 or blank, except that MID1 must be specified)

Ti

Thicknesses of individual plies. If Ti is not specified, default is the last defined Ti. Default = last defined Ti (Real > 0.0 or blank, except that T1 must be specified)

THETAi

Orientation angle, in degrees, of the longitudinal direction of each ply relative to the x-axis of the material coordinate system associated with a given element. If no material coordinate system is prescribed for the element, the angle is measured relative to side 1-2 of this element. Default = 0.0 (Real or blank)

SOUTi

Stress, Strain and Failure Index output request for individual plies. See comments 2 and 3. Default = NO (YES or NO)

DS

Design switch. If non-zero (1.0), the elements associated with this PCOMP data are included in the topology design volume or space. Default = blank (Real = 1.0 or blank)

Comments 1.

TREF specified on the PCOMP entry overrides reference temperatures given for individual ply materials. If TREF is not specified (blank) on the PCOMP card, then all the ply materials must have the same reference temperature.

2.

Stress, Strain and Failure Index output for individual plies is activated by setting SOUTi to YES for a given ply. In addition, the I/O Options CSTRESS (controlling Stress and Failure Index output) and/or CSTRAIN (controlling Strain output) must be defined. Failure Index output also requires that the FT and SB fields be defined and that stress/strain allowables on the referenced materials are defined.

3.

An additional piece of information available with ply results is "failure index for the element," which is the maximum of failure indices for individual plies in this element. Note that only the plies with SOUTi set to YES are considered in the evaluation of this maximum.

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OptiStruct 13.0 Reference Guide 1773 Proprietary Information of Altair Engineering

4.

If all plies specify zero transverse shear coefficients (G1Z, G2Z on MAT8 card, isotropic G for MAT1, not available for MAT2), the in-plane shear modulus will be used to determine transverse shear stiffness of the composite. Note: If just one layer has a nonzero value specified for transverse shear modulus, this substitution is not being performed, and user-specified values are being used for all plies.

5.

The signs given to stress limits for compression and tension (ST, SC, for MAT1; Xt, Xc, and so on for MAT8) are of no relevance. Absolute values are taken and used in the appropriate context to calculate failure indices.

6.

For com bottom and top surfaces of the shell are produced. Note: These shell stresses are calculated using homogenized shell properties, and should be interpreted with caution.

7. This is because the membrane-bending coupling resulting from composite offset is not included in the differential stiffness matrix. Hence, the preferred method of incorporating offset in buckling analysis is the element offset ZOFFS. 8.

Element GRID thicknesses cannot be defined for elements that reference PCOMP data.

9.

Plies are listed from the bottom surface upwards, in respect to the element’s normal direction. In the image below, (a) shows the stacking sequence for a non-symmetrical laminate, and (b) shows the stacking sequence for a symmetrical laminate.

10. GE given on the PCOMP entry will be used for the element, and the values supplied on material entries for individual plies are ignored. You are responsible for supplying the equivalent damping value on the PCOMP entry. 11. To obtain the damping coefficient GE, multiply the critical damping ratio C/C0 by 2.0. 12. For convenience, element output for the SMEAR and SMCORE options includes both homogenized shell stresses and individual ply stresses. However, because stacking sequence is ignored in these options, individual ply stresses will only be valid in cases of

1774 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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pure membrane deformation. 13. Note that Hill’s failure theory does not differentiate between compressive and tensile strength. Hence, while different values of respective strength limits are accepted, it is still recommended that Xt is set to be equal to Xc and Yt is set to be equal to Yc when this criteria is used. Xt and Xc are allowable tensile and compressive stresses in the principle x direction of the material. Yt and Yc are allowable tensile and compressive stresses in the principle y direction of the material. 14.

Failure index calculation according to Maximum Strain Theory is based on mechanical component of strain only, not on total strain. This is because only the mechanical strain contributes to actual damage of the respective ply (pure thermal expansion produces no damaging effects).

15. According to the formula, some failure criteria (for example, Tsai-Wu and Hoffman) would produce a negative ply failure, depending on the problem. 16. If ‘PARAM, SRCOMPS, YES’ is added to the input file, strength ratios with respect to designated failure theory are output for composite elements that have failure indices requested. 17. The following two formats are permissible for the Z0 field: Real Number: It represents the distance from the shell element reference plane to the bottom surface of the shell (Default = -0.5 * Thick, Thick being the composite total thickness (Real or blank)). Surface: Top: The shell reference plane, the plane defined by the grid points, and the top surface of the shell are coplanar. This makes the effective "Real" Z0 value equal to the composite total thickness (-1.0 * Thick). See Figure 1.

Figure 1: Top option for Z0

Bottom: The shell reference plane, the plane defined by the grid points, and the bottom surface of the shell are coplanar.

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OptiStruct 13.0 Reference Guide 1775 Proprietary Information of Altair Engineering

This makes the effective "Real" Z0 value equal to 0. See Figure 2.

Figure 2: Bottom option for Z0

Automatic offset control is available in composite free-size and sizing optimization where the specified offset values are automatically updated based on thickness changes. 18. This card is represented as a property in HyperMesh.

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PCOMPG Bulk Data Entry PCOMPG – Composite Laminate Property Description Defines the structure and properties of a composite laminate material, allowing for global ply identification. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PC OMPG

PID

Z0

NSM

SB

FT

TREF

GE

LAM

GPLYID1

MID1

T1

THETA1

SOUT1

GPLYID2

MID2

T2

THETA2

SOUT2

…

…

…

…

…

DS

Example

(1)

(2)

(3)

PC OMP

100

-0.5

101

120

2

103

(4)

(5)

(6)

(7)

1.E5

STRN

100.

0.2

0.0

YES

120

0.6

0.0

NO

120

0.2

0.0

YES

(8)

(9)

(10)

1.0

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Field

Contents

PID

Unique composite property identification number. No default (Integer > 0)

Z0

Real number or character input (Top/Bottom) Real Number - It represents the distance from the shell element reference plane to the bottom surface of the shell (Default = -0.5 * Thick, Thick being the composite total thickness (real or blank)). Character Input - See comment 18.

NSM

Nonstructural mass per unit area. No default (Real)

SB

Allowable interlaminar shear stress (shear stress in the bonding material). Disregarded if blank or 0.0. No default (Real > 0.0)

FT

Failure theory code. If blank, no failure calculations are performed. The following failure theory codes are supported: HILL for Hill theory, HOFF for Hoffman theory, TSAI for Tsai-Wu theory, STRN for Maximum Strain Theory. See comments 14 through 16. Default = no failure calculations are performed (HILL, HOFF, TSAI, or STRN)

TREF

Reference (stress free) temperature. See comment 1. Default = 0.0 (Real)

GE

Damping coefficient. See comments 10 and 11. Default = 0.0 (Real)

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Field

Contents

LAM

Laminate option. If blank, all plies must be specified and all stiffness terms are developed. The following options are supported: MEM: All plies must be specified, but only membrane terms MID1 are developed. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). BEND: All plies must be specified, but only bending terms MID2 are developed. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SMEAR: All plies must be specified, stacking sequence is ignored, and MID1 is set equal to MID2 on the derived equivalent PSHELL, while MID3, MID4, TS/T, and 12I/T**3 are set to zero. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SMEARZ0: All plies must be specified, stacking sequence is ignored. While the laminate is still considered to be made of homogenized (smeared) material, the effect of offset Z0 is taken into account. Hence, if Z0 is not equal to -0.5*Thick, the equivalent PSHELL will include MID1, MID2 and MID4. MID3 is still set to zero, that is no transverse shear deformation is considered. SMCORE: All plies must be specified. The last ply specifies core properties and the previous plies specify face sheet properties. The face sheet properties are calculated without regard for stacking sequence; half of the total face sheet thickness is then placed on top of the core, and half is placed on the bottom, to produce a symmetric laminate. Stiffness of the core is ignored while its density is included in inertia calculations. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SYMEM: Only plies on the bottom half of the composite lay-up needs to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top. Only membrane terms are developed for the full laminate. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SYBEND: Only plies on the bottom half of the composite lay-up needs to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top. Only bending terms are developed for the full laminate. Prescribed Z0 is ignored (assumed to be: -0.5* Thick). SYSMEAR: Only plies on the bottom half of the composite lay-up needs to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top. Stacking sequence is ignored, and MID1 is set equal to MID2 on the derived equivalent PSHELL, while MID3, MID4, TS/T and 12I/T**3 are set to zero. Prescribed Z0 is ignored (assumed to be: 0.5* Thick).

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Contents Default = blank, that is all plies must be specified (SYM, MEM, BEND, SMEAR, SMCORE, SYMEM, SYBEND or SYSMEAR)

GPLYID#

Global Ply identification number, See comment 12. No default (Integer > 0)

MID#

Material IDs of individual plies. The plies are identified by consecutively numbering them from 1 at the bottom layer. The MIDs must refer to MAT1, MAT2, MAT4, MAT5, or MAT8 bulk data entries. If MID# is not specified, default is the last defined MID#. Default = last defined MID# (Integer > 0 or blank, except that MID1 must be specified)

T#

Thicknesses of individual plies. If T# is not specified, default is the last defined T#. Default = last defined T# (Real > 0.0 or blank, except that T1 must be specified)

THETA#

Orientation angle, in degrees, of the longitudinal direction of each ply relative to the x-axis of the material coordinate system associated with a given element. If no material coordinate system is prescribed for the element, the angle is measured relative to side 1-2 of this element. Default = 0.0 (Real or blank)

SOUT#

Stress and failure index output request for individual plies. See comments 2 and 3. Default = NO (YES or NO)

DS

Design switch. If non-zero (1.0), the elements associated with this PCOMP data are included in the topology design volume or space. Default = blank (Real = 1.0 or blank)

Comments 1.

TREF specified on the PCOMPG entry overrides reference temperatures given for individual ply materials. If TREF is not specified (blank) on the PCOMPG card, then all the ply materials must have the same reference temperature.

2.

For SOUTi to take effect, CSTRESS must be requested in the I/O options section of the input deck. Individual ply results will be available in addition to shell stresses and strains

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based on the homogenized composite properties. 3.

An additional piece of information available with ply results is "failure index for the element", which is the maximum of failure indices for individual plies in this element. Note that only the plies with SOUTi set to YES are considered in the evaluation of this maximum.

4.

If all plies specify zero transverse shear coefficients (G1Z, G2Z on MAT8 card, isotropic G for MAT1, not available for MAT2), the in-plane shear modulus will be used to determine transverse shear stiffness of the composite. Note: If just one layer has a nonzero value specified for transverse shear modulus, this substitution is not being performed, and user-specified values are being used for all plies.

5.

The signs given to stress limits for compression and tension (ST, SC, for MAT1; Xt, Xc, and so on for MAT8) are of no relevance. Absolute values are taken and used in the appropriate context to calculate failure indices.

6. bottom and top surfaces of the shell are produced. Note: These shell stresses are calculated using homogenized shell properties, and should be interpreted with caution. 7. This is because the membrane-bending coupling resulting from composite offset is not included in the differential stiffness matrix. Hence, the preferred method of incorporating offset in buckling analysis is the element offset ZOFFS. 8.

Element GRID thicknesses cannot be defined for elements that reference PCOMPG data.

9.

Plies are listed from the bottom surface upwards, in respect to the element’s normal direction. The image below shows the stacking sequence for a non-symmetrical laminate.

10. GE given on the PCOMP entry will be used for the element, and the values supplied on material entries for individual plies are ignored. You are responsible for supplying the equivalent damping value on the PCOMPG entry.

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OptiStruct 13.0 Reference Guide 1781 Proprietary Information of Altair Engineering

11. To obtain the damping coefficient GE, multiply the critical damping ratio C/C0 by 2.0. 12. The global ply identification number must be unique with respect to other plies in the entry. 13. For convenience, element output for the SMEAR and SMCORE options includes both homogenized shell stresses and individual ply stresses. However, because stacking sequence is ignored in these options, individual ply stresses will only be valid in cases of pure membrane deformation. 14. Note that Hill’s failure theory does not differentiate between compressive and tensile strength. Hence, while different values of respective strength limits are accepted, it is still recommended that Xt is set to be equal to Xc and Yt is set to be equal to Yc when this criteria is used. Xt and Xc are allowable tensile and compressive stresses in the principle x direction of the material. Yt and Yc are allowable tensile and compressive stresses in the principle y direction of the material. 15. Failure index calculation according to Maximum Strain Theory is based on mechanical component of strain only, not on total strain. This is because only the mechanical strain contributes to actual damage of the respective ply (pure thermal expansion produces no damaging effects). 16. According to the formula, some failure criteria (for example, Tsai-Wu and Hoffman) would produce a negative ply failure, depending on the problem. 17. If ‘PARAM, SRCOMPS, YES’ is added to the input file, strength ratios with respect to designated failure theory are output for composite elements that have failure indices requested. 18. The following two formats are permissible for the Z0 field: Real Number: It represents the distance from the shell element reference plane to the bottom surface of the shell (Default = -0.5 * Thick, Thick being the composite total thickness (Real or blank)). Surface: Top: The shell reference plane, the plane defined by the grid points, and the top surface of the shell are coplanar. This makes the effective "Real" Z0 value equal to the composite total thickness (-1.0 * Thick). See Figure 1.

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Figure 1: Top option for Z0

Bottom: The shell reference plane, the plane defined by the grid points, and the bottom surface of the shell are coplanar. This makes the effective "Real" Z0 value equal to 0. See Figure 2.

Figure 2: Bottom option for Z0

Automatic offset control is available in composite free-size and sizing optimization where the specified offset values are automatically updated based on thickness changes. 19. This card is represented as a property in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1783 Proprietary Information of Altair Engineering

PCOMPP Bulk Data Entry PCOMPP – Composite Laminate Property for Ply-Based Composite Definition Description Defines the properties of a composite laminate material used in ply-based composite definition. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PC OMPP

PID

Z0

NSM

SB

FT

TREF

GE

(9)

(10)

Example

(1)

(2)

(3)

PC OMPP

1

-0.1

(4)

(5)

(6)

(7)

HILL

20

Field

Contents

PID

Unique composite property identification number.

(8)

(9)

(10)

No default (Integer > 0) Z0

Real number or character input (Top/Bottom) Real Number - It represents the distance from the shell element reference plane to the bottom surface of the shell (Default = -0.5 * Thick, Thick being the composite total thickness (Real or blank)). Character Input - See comment 12.

NSM

Nonstructural mass per unit area. No default (Real)

SB

Allowable interlaminar shear stress (shear stress in the bonding material). Disregarded if blank or 0.0. No default (Real > 0.0)

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Field

Contents

FT

Failure theory code. If blank, no failure calculations are performed. The following failure theory codes are supported: HILL for Hill theory, HOFF for Hoffman theory, TSAI for Tsai-Wu theory, STRN for Maximum Strain Theory. See comment 10. Default = no failure calculations are performed (HILL, HOFF, TSAI or STRN).

TREF

Reference (stress free) temperature. See comment 2. Default = 0.0 (Real)

GE

Damping coefficient. See comments 6 and 7. Default = 0.0 (Real)

Comments 1.

The PCOMPP card is used in combination with the STACK and PLY cards to create composite properties through the ply-based definition.

2.

TREF specified on the PCOMPP entry overrides reference temperatures given for individual ply materials. If TREF is not specified (blank) on the PCOMPP card, then all the ply materials must have the same reference temperature.

3. bottom and top surfaces of the shell are produced. Note: These shell stresses are calculated using homogenized shell properties, and should be interpreted with caution. 4. correct. This is because the membrane-bending coupling resulting from composite offset is not included in the differential stiffness matrix. Hence, the preferred method of incorporating offset in buckling analysis is the element offset ZOFFS. 5.

Element GRID thicknesses cannot be defined for elements that reference PCOMPP data.

6.

GE given on the PCOMPP entry will be used for the element, and the values supplied on material entries for individual plies are ignored. You are responsible for supplying the equivalent damping value on the PCOMPP entry.

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OptiStruct 13.0 Reference Guide 1785 Proprietary Information of Altair Engineering

7.

To obtain the damping coefficient GE, multiply the critical damping ratio C/C0 by 2.0.

8.

Note that Hill’s failure theory does not differentiate between compressive and tensile strength. Hence, while different values of respective strength limits are accepted, it is still recommended that Xt is set to be equal to Xc and Yt is set to be equal to Yc when this criteria is used. Xt and Xc are allowable tensile and compressive stresses in the principle x direction of the material. Yt and Yc are allowable tensile and compressive stresses in the principle y direction of the material.

9.

Failure index calculation according to Maximum Strain Theory is based on mechanical component of strain only, not on total strain. This is because only the mechanical strain contributes to actual damage of the respective ply (pure thermal expansion produces no damaging effects).

10. According to the formula, some failure criteria (for example, Tsai-Wu and Hoffman) would produce a negative ply failure, depending on the problem. 11. If ‘PARAM, SRCOMPS, YES’ is added to the input file, strength ratios with respect to designated failure theory are output for composite elements that have failure indices requested. 12. The following two formats are permissible for the Z0 field: Real Number: It represents the distance from the shell element reference plane to the bottom surface of the shell (Default = -0.5 * Thick, Thick being the composite total thickness (Real or blank)). Surface: Top: The shell reference plane, the plane defined by the grid points, and the top surface of the shell are coplanar. This makes the effective "Real" Z0 value equal to the composite total thickness (-1.0 * Thick). See Figure 1.

Figure 1: Top option for Z0

Bottom: The shell reference plane, the plane defined by the grid points, and the bottom surface of

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the shell are coplanar. This makes the effective "Real" Z0 value equal to 0. See Figure 2.

Figure 2: Bottom option for Z0

Automatic offset control is available in composite free-size and sizing optimization where the specified offset values are automatically updated based on thickness changes. 13. This card is represented as a property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1787 Proprietary Information of Altair Engineering

PCOMPX Bulk Data Entry PCOMPX – Optional Composite Laminate Property Extension for Geometric Nonlinear Analysis Description Defines additional composite laminate properties for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

PC OMPX

PID

ISHELL

ISH3N

ISMSTR

DM

DN

ITHIC K

IPLAS

(7)

(8)

(9)

HM

HF

HR

(10)

Example

(1)

(2)

PC OMP

73

PC OMPX

(3)

(4)

(5)

(6)

(7)

(8)

(9)

120

0.2

0.0

YES

120

0.6

45.0

YES

73

24

Field

Contents

PID

Property ID of the associated PSHELL. See comment 1.

(10)

No default (Integer > 0) ISHELL

Flag for CQUAD4 element formulation. 1 - Q4, visco-elastic hourglass modes orthogonal to deformation and rigid modes (Belytschko) 2 - Q4, visco-elastic hourglass without orthogonality (Hallquist) 3 - Q4, elastic-plastic hourglass with orthogonality

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Field

Contents 4 - Q4 with improved type 1 formulation (orthogonalization for warped elements) 12 - QBAT or DKT18 shell formulation 24 - QEPH shell formulation Default as defined by XSHLPRM (Integer)

ISH3N

Flag for CTRIA3 element formulation. 1 - Standard triangle (C0) 2 - Standard triangle (C0) with modification for large rotation 30 - DKT18 31 - DKT_S3 Default as defined by XSHLPRM (Integer)

ISMSTR

Flag for shell small strain formulation. 1 - Small strain from time = 0 2 - Full geometric non-linearity with optional small strain formulation activation by time step XSTEP, TYPEi = SHELL, TSCi = CST 3 - Alternative small strain formulation from time = 0 (ISHELL =2 only). 4 - Full geometric non-linearity (Time step limit has no effect) Default as defined by XSHLPRM (Integer)

HM

Shell membrane hourglass coefficient (ISHELL = 1, 2, 3, and 4 only). Default = 0.01 (Real, 0.0 < HM < 0.05) Except ISHELL = 3: Default = 0.1 (Real)

HF

Shell out of plane hourglass coefficient (ISHELL = 1, 2, 3, and 4 only). Default = 0.01 (Real, 0.0 < HF < 0.05)

HR

Shell rotation hourglass coefficient (ISHELL = 1, 2, 3, and 4 only). Default = 0.01 (Real, 0.0 < HR < 0.05) Except ISHELL = 3: Default = 0.1 (Real)

DM

Shell membrane damping (with MATX27, MATX36 only). Default: See comment 7 (Real)

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Field

Contents

DN

Shell numerical damping (ISHELL = 12, 24; ISH3N = 30 only). Default: See comment 8 (Real)

ITHICK

Flag for shell resultant stresses calculation. CONST - Thickness is constant VAR - Thickness change is taken into account Default as defined by XSHLPRM (CONST or VAR)

IPLAS

Flag for shell plane stress plasticity (with MATX27 only). RAD - Radial return NEWT - Iterative projection with 3 Newton iterations Default as defined by XSHLPRM (RAD or NEWT)

Comments 1.

The property identification number must be that of an existing PCOMP, PCOMPG, or PCOMPP bulk data entry. Only one PCOMPX property extension can be associated with a particular PCOMP, PCOMPG, or PCOMPP.

2.

PCOMPX is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

Q4: Original 4 node OptiStruct shell with hourglass perturbation stabilization. QEPH: Formulation with physical hourglass stabilization for general use. QBAT: Modified BATOZ Q4 24 shell with 4 Gauss integration points and reduced integration for in-plane shear. No hourglass control is needed for this shell. DKT18: BATOZ DKT18 thin shell with 3 Hammer integration points.

4.

If the small strain option (ISMSTR) is set to 1 or 3, engineering strain and stress are used; otherwise they are true strain and stress.

5.

For ITHICK = VAR it is recommended to use IPLAS = NEWT.

6.

If ITHICK = VAR or IPLAS = NEWT, the small strain option is automatically deactivated.

7.

Defaults for DM: Material

Element type

ISHELL/ISH3N

Default

MATX27

except QEPH, QBAT

except 12, 24

5%

QEPH

24

1.5%

QBAT

12

0%

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8.

9.

Material

Element type

ISHELL/ISH3N

Default

MATX36

except QEPH

except 24

0%

QEPH

24

1.5%

Defaults for DN: Element type

ISHELL/ ISH3N

Default

Usage

QBAT

12

0.1%

All stress terms, except transverse shear

QEPH

24

1.5%

Hourglass stress

DKT18

12/30

0.01%

Membrane stress only

This card is represented as extension to a PCOMP, PCOMPG, and PCOMPP property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1791 Proprietary Information of Altair Engineering

PCONT Bulk Data Entry PCONT – Contact Property Description Defines properties of CONTACT interface. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PC ONT

PID

GPAD

STIFF

MU1

MU2

C LEARANC E

(9)

(10)

FRIC ESL

Examples

(1)

(2)

PC ONT

34

(3)

(4)

(5)

(6)

0.3

0.25

(7)

(8)

(9)

(10)

Enforced stick condition: PC ONT

34

STIC K

Field

Contents

PID

Property identification number. No default (Integer > 0)

GPAD

“Padding” of the interface to account for additional layers, such as shell thickness. This value is subtracted from the contact gap opening as calculated from the location of nodes. See comment 1. Default = THICK (Real, NONE or THICK)

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Field

Contents

STIFF

Relative stiffness of contact interface. See comment 2. Default = AUTO (AUTO, SOFT, HARD or Real > 0.0)

MU1

Coefficient of static friction ( s). See comments 3 and 4. Default = 0.0 (Real > 0.0 or STICK or FREEZE)

MU2

Coefficient of kinetic friction ( k). (Ignored in linear analysis). Default = MU1 (0.0 < Real < MU1)

CLEARANCE

Prescribed initial gap opening between master and slave, irrespective of the actual distance between the nodes. See comment 11. Default = not prescribed. (Real or blank).

FRICESL

Frictional elastic slip – distance of sliding up to which the frictional transverse force increases linearly with slip distance. Specified in physical distance units (similar to U0 and GPAD). See Comment 7. •

Non-zero value or blank activates respective friction model based on Elastic Slip Distance.

•

Zero value activates friction model based on fixed transverse stiffness KT.

Default = AUTO (Real > 0.0 or AUTO) Comments 1.

The initial contact gap opening is calculated automatically based on the relative location of slave and master nodes (in the original, undeformed mesh). To account for additional material layers covering master and slave objects, the GPAD entry can be used. GPAD option THICK automatically accounts for shell thickness on both sides of the contact interface (this also includes the effects of shell element offset ZOFFS or composite offset Z0).

2.

Option STIFF=AUTO determines the value of normal stiffness for each contact element using the stiffness of surrounding elements. Additional options SOFT and HARD create respectively softer or harder penalties. SOFT can be used in cases of convergence difficulties and HARD can be used if undesirable penetration is detected in the solution.

3.

Prescribing MU1=STICK is interpreted in OptiStruct as an enforced stick condition – such contact interfaces will not enter the sliding phase. Of course, the enforced stick only applies to contacts that are closed. Note that, in order to effectively enforce the stick condition, frictional offset may need to be turned off (See comment 8).

4.

Prescribing MU1=FREEZE enforces zero relative motion on the contact surface – the contact gap opening remains fixed at the original value and the sliding distance is zero. Also, rotations at the slave node are matched to the rotations of the master patch. The

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FREEZE condition applies to all respective contact elements, no matter whether open or closed (hence, GPAD is of no relevance in this case). Also, this condition is effective irrespective of the frictional offset setting. If FRIC is not explicitly defined on the PCONTX/PCNTX# entries, the MU1 value on the CONTACT or PCONT entry is used for FRIC in the /INTER entries for Geometric Nonlinear Analysis. Otherwise, FRIC on PCONTX/PCNTX# overwrites the MU1 value on CONTACT/ PCONT. 5.

The CONTACT element force-displacement behavior is different in linear and nonlinear analysis (see Nonlinear Gap and CONTACT Analysis for more information on nonlinear solutions). In linear analysis, the contact stiffness is constant and depends on the initial contact gap opening U0 as calculated from the positions of Slave and Master (and considering padding GPAD). Note that for open contact elements, a very small stiffness value of KB =10-14 *STIFF is used to avoid numerical singularities.

C ONTAC T element force deflection curve for linear analysis

The CONTACT force displacement behavior in nonlinear analysis is illustrated in the figure below. While the contact is open, its normal stiffness is essentially zero (a small value of KB =10-14 *STIFF is used to avoid singularities). When the contact element closes, the stiffness becomes STIFF.

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C ONTAC T element force deflection curve for nonlinear analysis

6.

When contact is open, there is no transverse stiffness. When the contact is closed, friction is activated and the contact has stiffness KT=mu1*STIFF in the transverse direction (KT=0.1*STIFF in case of STICK). This acts as a linear spring in linear solution sequences. For nonlinear solution sequences, frictional force increases with sliding distance in proportion to KT until it reaches static friction force MU1 * Fx, Fx being the normal force in the contact element. With further transverse deformation, friction becomes kinetic and the friction force is MU2 * Fx. See the figure below for a onedimensional illustration.

C ONTAC T element frictional behavior in nonlinear analysis

Note that the nonlinear contact element's force-displacement behavior may produce negative contributions to the compliance of the structure. As an example, when slave and master bodies have initial overlap and the contact releases elastic energy during the solution. 7.

Effective in Release 12.0, two models of friction are available in nonlinear analysis: (a) Model based on fixed slope KT (previously existing),

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(b) Model based on Elastic Slip Distance FRICESL (introduced in v12.0 and current default). This latter model typically shows better performance in solution of frictional problems thanks to more stable handling of transitions from stick to slip. Key differences between the two available models are illustrated in the figure below (F 1 and F 2 represent two different values of normal force F x ):

C omparison of the two available friction models for contact elements.

Model (a), based on fixed stiffness KT, is relatively simple, yet has certain drawback in modeling nonlinear friction. Namely, in Coulomb friction the frictional resistance depends upon normal force. Using fixed KT will predict different range of stick/slip boundary for different normal forces, and thus may qualify the same configuration as stick or slip, depending on normal force. Model (b), based on Elastic Slip Distance, provides unique identification of stick or slip and generally performs better in solution of problems with friction. This model does require prescribing elastic slip distance FRICESL – for contact interfaces this value is determined automatically as 0.5% of typical element size on all Master contact surfaces. The model (b), which is currently the default, is recommended for solution of nonlinear problems with friction. For backwards compatibility, the model based on fixed KT can be activated by prescribing FRICESL=0 on PCONT or CONTPRM card. 8.

The model of friction in OptiStruct is relatively simple. The frictional force is always directed back to the point where the slave and master first came into contact (changed status from open to closed). Its location is estimated using proportional interpolation between the current position and the last converged solution before penetration. OptiStruct CONTACT should not be used for modeling frictional problems with complex deformation paths and changing sliding directions.

9.

The presence of friction can introduce moment loadings and counter-intuitive results into the problem by way of frictional offset. The reason for this is that, for contact elements with non-zero length (distance between slave node and master segment), the actual location of the contact interface is presumed to be in the middle of the contact element’s length (see figure below).

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C ONTAC T presumed contact surface

The frictional forces act along this contact surface. Transferring these forces to the slave and master objects requires an offset operation that produces both forces and moments at slave and master. Similarly, the sliding distance at the contact interface is a result of nodal displacements and rotations of the slave node and master segment (see figure below).

C ONTAC T sliding with friction

Master segments, which consist of several nodes, can effectively resist these offset forces and moments. However, for slave bodies that do not support moments (nodes of solid elements, for example), this offset may render friction ineffective because the free rotations at slave nodes offer no effective resistance to friction. With the stick condition formally satisfied, for example, slave and master can move relative to each other (see figure below).

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C ONTAC T stick (zero sliding distance)

In practice, for contact interfaces that are initially open, AUTOSPC will effectively fix respective unsupported rotations. However, for contacts that are initially closed (for example, pre-penetrating contact with MORIENT=NORMAL) the frictional terms will prevent AUTOSPC from being effective. Hence, respective SPC on rotations need to be applied manually to respective slave nodes. Effective in the Release 12.0, to avoid such counter-intuitive behavior, the frictional offset operation is by default turned off if the model involves friction or stick and contains at least one nonlinear subcase (of NLSTAT type). (Note that for consistency, this affects both linear and nonlinear contact elements.) This produces more intuitive results with friction. However, it may violate the rigid body balance of the body. Note: FREEZE condition is enforced using a special formulation where the above caveat does not apply and the offset operation is always applied. The above default setting can be changed via the GAPOFFS command on the GAPPRM card. 10. The presence of friction, due to its strongly nonlinear, non-conservative nature, may cause difficulties in nonlinear convergence, especially when sliding is present. If frictional resistance is essential to the solution of the problem and convergence problems are encountered, enforcing the stick condition (by prescribing KT>0 and MU=0) may be a viable solution that will often result in better convergence than with Coulomb friction. Note however, that this only applies to problems in which minimal sliding is expected. In the case of larger sliding motions, the stick condition may lead to divergence through a "tumbling" mode. 11. Prescribing CLEARANCE overrides the default contact behavior of calculating initial gap opening from the actual distance between Slave and Master. CLEARANCE now becomes the distance that Slave and Master have to move towards each other in order to close the contact. Negative value of CLEARANCE means that the bodies have initial prepenetration.

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Warning: When prescribing CLEARANCE, it is important to correctly restrict the contact zones and pick search distance SRCHDIS so that only desired Slave-Master pairs are involved. With prescribed CLEARANCE, all contact elements created on a given interface, even those where Slaves are geometrically distant from the respective Master surface, will be considered to be at prescribed initial gap and participate in resolving the contact condition.

Note: CLEARANCE cannot be prescribed together with (nonzero) GPAD. Blank GPAD field in presence of CLEARANCE is interpreted as NONE. 12. This card is represented as a property in HyperMesh.

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PCONTHT Bulk Data Entry PCONTHT – Define Conductivity for Contact in Heat Transfer Analysis Description Defines conductivity for CONTACT elements in heat transfer analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

PC ONTHT

PID

KC

KO

TPID

TC ID

(8)

(9)

(10)

Examples

(1)

(2)

(3)

PC ONTHT

2

1E6

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Contact with automatic determination of KC: PC ONTHT

2

AUTO

Minimum data required to prescribe pressure based conductivity for contact: PC ONTHT

2

10

Clearance and pressure based conductivity for contact (see comments 3 and 4): PC ONTHT

2

1E6

10

20

Field

Contents

PID

Property identification number. Must match with a PID of a PCONT bulk data entry. See comment 1.

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Field

Contents No default (Integer > 0)

KC

Conductivity for the closed contact. See comment 2.

KO

Conductivity for the open contact. See comment 2. Default = 10-14 * KC (Real > 0.0) This default is also set when KO =0.

TPID

Identification number of a TABLED# entry. This table specifies conductivity based on contact pressure. See comments 2, 3, and 4. Default = 0 (Integer > 0)

TCID

Identification number of a TABLED# entry. This table specifies conductivity based on contact clearance. See comments 2, 3, and 4. Default = 0 (Integer > 0)

Comments 1.

PCONTHT provides heat transfer conductivity for CONTACT element. PCONTHT must match PID with an existing PCONT.

2.

KC and KO represent conductivity values for closed and open contacts. Theoretically, while higher conductivity values enforce a perfect conductor, excessively high values may cause poor conditioning of the conductivity matrix. If any such symptoms are observed, it may be beneficial to reduce the value of conductivity, or use conductivity based contact clearance and pressure. To facilitate reasonable values for KC, automatic calculation is supported, specifically: Option KC=AUTO determines the value of KC for each contact element using the conductivity of surrounding elements.

3.

TPID points to a TABLED# entry that specifies conductivity based on contact pressure. TPID overrides KC.

4.

TCID points to a TABLED# entry that specifies contact based on contact clearance. TCID overrides KO. TPID can be specified together with TCID. When TPID is specified together with TCID, conductivity is determined from the table with TCID for open contact, and from the table with TPID for closed contact.

5.

PCONTHT is not supported for surface-to-surface contact (DISCRET=S2S on CONTACT/ TIE).

6.

Thermal-structural analysis problems involving contact are fully coupled since contact/gap status changes thermal conductivity. Refer to Contact-based Thermal Analysis in the User’s Guide for more information.

7.

This card is represented as a property in HyperMesh.

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PCONTX Bulk Data Entry PCONTX – Extended CONTACT Property for Geometric Nonlinear Analysis Description Defines properties of a CONTACT interface for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

PC ONTX

PID

STFAC

FRIC

GAP

IDEL

INAC TI

TSTART

TEND

ISYM

IEDGE

FANG

IGAP

ISTF

STIF1

VISS

VISF

BMULT

IBC

MULTIMP

IFRIC

IFORM

IFILT

FFAC

C1

C2

C3

C4

C5

(8)

(9)

(10)

C TYPE

STMIN

STMAX

C6

Example

(1)

(2)

PC ONT

34

PC ONTX

34

(3)

(4)

(5)

(6)

(7)

(8)

Field

Contents

PID

Property identification number of the associated PCONT.

(9)

(10)

No default (Integer > 0)

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Field

Contents

STFAC

Interface stiffness scale factor. Default as defined by CONTPRM (Real > 0)

FRIC

Coulomb friction. Default as defined by CONTPRM (Real > 0)

GAP

Gap for impact activation (See comments 4 and 6). Default as defined by CONTPRM (Real > 0)

IDEL

Flag for node and segment deletion. Default as defined by CONTPRM (Integer = 0, …, 2) 0 - No deletion. 1 - When all the elements (shells, solids) associated to one segment are deleted, the segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface. 2 - When a shell or a solid element is deleted, the corresponding segment is removed from the master side of the interface. Additionally, non-connected nodes are removed from the slave side of the interface.

INACTI

Flag for handling of initial penetrations (See comment 8). Default as defined by CONTPRM (Integer = 0, …, 5) 0 - No action. 1 - Deactivation of stiffness on nodes. 2 - Deactivation of stiffness on elements. 3 - Change slave node coordinates to avoid small initial penetrations. 4 - Change master node coordinates to avoid small initial penetrations. 5 - Gap is variable with time but initial gap is slightly de-penetrated as follows: gap0 = gap - P0 – 0.05*(gap - P0 ) Valid in explicit analysis: 0, 1, 2, 3 and 5. Valid in implicit analysis: 0, 3 and 4. Invalid entries are ignored.

CTYPE

Implicit contact type. Default = TYPE7 (Character = TYPE5, TYPE7)

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Field

Contents

TSTART

Start time Default = 0.0 (Real > 0)

TEND

Time for temporary deactivation. Default = 1030 (Real > 0)

The following entries are relevant for explicit analysis only. ISYM

Flag for symmetric contact. Default as defined by CONTPRM (Character = SYM, UNSYM) SYM – Symmetric contact. UNSYM – Master-slave contact. If SSID defines a grid set, the contact is always a master-slave contact.

IEDGE

Flag for edge generation from slave and master surfaces. Default as defined by CONTPRM (Character = NO, ALL, BORD, FEAT) NO – No edge generation. All – All segment edges are included. BORD – External border of slave and master surface is used. FEAT – External border as well as features defined by FANG are used.

FANG

Feature angle for edge generation (Only with IEDGE = FEAT). Default as defined by CONTPRM (Real > 0)

IGAP

Flag for gap definition. Default as defined by CONTPRM (Character = CONST, VAR) CONST - Gap is constant and equal to GAP (See comment 6). VAR - Gap is variable (in space, not in time) according to the characteristics of the impacting surfaces and nodes (See comment 7).

ISTF

Flag for stiffness definition (See comment 5). Default as defined by CONTPRM (Integer = 0, …, 5) 0 - The stiffness is computed according to the master side characteristics. 1 - STIF1 is used as interface stiffness. 2, 3, 4 and 5 - The interface stiffness is computed from both master and slave characteristics.

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Field

Contents

STIF1

Interface stiffness (Only with ISTF = 1) Default = 0.0 (Real > 0)

STMIN

Minimum stiffness (Only with ISTF > 1). Default as defined by CONTPRM (Real > 0)

STMAX

Maximum stiffness (Only with ISTF > 1). Default as defined by CONTPRM (Real > 0)

IBC

Flag for deactivation of boundary conditions at impact applied to the slave grid set. Default as defined by CONTPRM (Character = X, Y, Z, XY, XZ, YZ, XYZ)

MULTIMP

Maximum average number of impacted master segments per slave node Default = 4 for SMP; 12 for SPMD (Integer > 0)

VISS

Critical damping coefficient on interface stiffness. Default as defined by CONTPRM (Real > 0)

VISF

Critical damping coefficient on interface friction. Default as defined by CONTPRM (Real > 0)

BMULT

Sorting factor. Can be used to speed up the sorting algorithm. Is machine-dependent. Default as defined by CONTPRM (Real > 0)

IFRIC

Friction formulation flag (See comment 8). Default as defined by CONTPRM (Character = COUL, GEN, DARM, REN) COUL - Static Coulomb friction law. GEN - Generalized viscous friction law. DARM - Darmstad friction law. REN - Renard friction law.

IFORM

Type of friction penalty formulation (See comment 9). Default as defined by CONTPRM (Character = VISC, STIFF) VISC - Viscous (total) formulation. STIFF - Stiffness (incremental) formulation.

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Field

Contents

IFILT

Friction filtering flag (See comment 10). Default as defined by CONTPRM (Character = NO, SIMP, PER, CUTF) NO - No filter is used. SIMP - Simple numerical filter. PER - Standard -3dB filter with filtering period. CUTF - Standard -3dB filter with cutting frequency.

FFAC

Friction filtering factor. Default as defined by CONTPRM (Real = 0.0 < FFAC < 1.0)

C1, C2, C3, Coefficients to define variable friction coefficient in IFRIC = GEN, DARM, C4, C5, C6 REN. Default as defined by CONTPRM (Real > 0) Comments 1.

The property identification number must be that of an existing PCONT bulk data entry. Only one PCONTX property extension can be associated with a particular PCONT.

2.

PCONTX is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

If FRIC is not explicitly defined on the PCONTX/PCNTX# entries, the MU1 value on the CONTACT or PCONT entry is used for FRIC in the /INTER entries for Geometric Nonlinear Analysis. Otherwise, FRIC on PCONTX/PCNTX# overwrites the MU1 value on CONTACT/ PCONT.

4.

In implicit analysis, different contact formulations are used for contact where slave and master set do not overlap and where they overlap (self-contact). In the case of self-contact, the gap cannot be zero and a constant gap is used. For small initial gaps, the convergence will be more stable and faster if GAP is larger than the initial gap. In implicit analysis, sometimes a stiffness with scaling factor reduction (for example, STFAC = 0.01) or reduction in impacted thickness (if rigid one) might reduce unbalanced forces and improve convergence, particularly in shell structures under bending where the effective stiffness is much lower than membrane stiffness; but it should be noted that too low of a value could also lead to divergence.

5. and/or the slave segment stiffness Ks. The master stiffness is computed from Km = STFAC * B * S * S/V for solids, Km = 0.5 * STFAC * E * t for shells. The slave stiffness is an equivalent nodal stiffness computed as Ks = STFAC * B * V- 3 for solids, Ks = 0.5 * STFAC * E * t for shells.

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In these equations, B is the Bulk Modulus, S is the segment area, and V is the volume of a solid. There is no limitation to the value of stiffness factor (but a value larger than 1.0 can reduce the initial time step). The interface stiffness is then K = max (STMIN, min (STMAX, K1)) with ISTF = 0, K1 = Km ISTF = 2, K1 = 0.5 * (Km + Ks) ISTF = 3, K1 = max (Km, Ks) ISTF = 4, K1 = min (Km, Ks) ISTF = 5, K1 = Km * Ks / (Km + Ks) 6.

The default for the constant gap (IGAP = CONST) is the minimum of t, average thickness of the master shell elements; l/10, l – average side length of the master solid elements; lmin/2, lmin – smallest side length of all master segments (shell or solid).

7.

The variable gap (IGAP = VAR) is computed as gs + gm with: gm - master element gap with gm = t/2, t: thickness of the master element for shell elements. gm = 0 for solid elements. gs - slave node gap: gs = 0 if the slave node is not connected to any element or is only connected to solid or spring elements. gs = t/2, t - largest thickness of the shell elements connected to the slave node.

If the slave node is connected to multiple shells and/or beams or trusses, the largest computed slave gap is used. 8.

INACTI = 3, 4 are only recommended for small initial penetrations and should be used with caution because: the coordinate change is irreversible. it may create other initial penetrations if several surface layers are defined in the interfaces. it may create initial energy if the node belongs to a spring element. INACTI = 5 works as follows:

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9.

IFRIC defines the friction model. IFRIC = COUL – Coulomb friction with F T < FRIC * F N . For IFRIC > 0 the friction coefficient is set by a function (m = m (p, V)), where p is the pressure of the normal force on the master segment and V is the tangential velocity of the slave node. The following formulations are available: IFRIC = 1 - Generalized viscous friction law m = FRIC + C1 * p + C2 * V + C3 * p * v + C4 * p2 + C5 * v2 IFRIC = 2 - Darmstad law m = C1 · e(C 2 V ) · p2 + C3 · e(C 4 V ) · p + C5 · e(C 6 V ) IFRIC = 3 - Renard law

0 < V < C5

C5 < V < C6

C6 < V

where:

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The first critical velocity Vcr1 second critical velocity Vcr2 (C5 < C6). The static friction coefficient C1 and the dynamic friction coefficient C2, must be lower than the maximum friction C3 (C1 < C3) and C2 < C3). The minimum friction coefficient C4, must be lower than the static friction coefficient C1 and the dynamic friction coefficient C2 (C4 < C1 and C4 < C2). 10. IFORM selects two types of contact friction penalty formulation. The viscous (total) formulation (IFORM = VISC) computes an adhesive force as F adh

T

F T = min (µF N , F adh) The stiffness (incremental) formulation (IFORM = STIFF) computes an adhesive force as F adh = F T old + ∆F T ∆F T = K * VT * dt F T new = min (µF N , F adh) 11. the tangential friction forces are smoothed using a filter: F T = α * F'T + (1 - α) * F'T - 1 where, F T - Tangential force F'T - Tangential force at time t F'T - 1 - Tangential force at time t-1 α - filtering coefficient IFILT = SIMP – α = FFAC IFILT = PER – α = 2 dt/FFAC, where dt/T = FFAC, T is the filtering period IFILT = CUTF – α = 2

* FFAC * dt, where FFAC is the cutting frequency

12. This card is represented as an extension to a PCONT property in HyperMesh.

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PCONV Bulk Data Entry PCONV – Free Convection Property Definition Description Defines a free convection boundary condition properties. Format (1)

(2)

(3)

(4)

(5)

PC ONV

PC ONID

MID

FORM

EXPF

(6)

(7)

(8)

Field

Contents

PCONID

Convection property identification number of a PCONV card.

(9)

(10)

No default (Integer > 0) MID

Material property identification number of MAT4 card. No default (Integer > 0)

FORM

Types of formula used for free convection. Default = 0, Integer 0, 1, 10, 11, 20, 21

EXPF

Free convection exponent. For FORM = 0, 10, and 20, EXPF = 0.0 For FORM = 1, 11, and 21, EXPF = 1.0

Comments 1.

Every CONV card must refer a PCONV card.

2.

Heat transfer coefficient (H) is specified on MAT4 card with MID.

3.

FORM specifies the convection formula type. If FORM = 0, 10, 20, q = H * (T - TAMB)E XP F * (T - TAMB) If FORM = 1, 11, 21 q = H * (T E XP F - TAMBE XP F )) where, T is grid temperature and TAMB is the ambient temperature.

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4.

EXPF is the free convection temperature exponent. If FORM = 0, 10, 20, EXPF = 0.0 for linear convection. If FORM = 1, 11, 21, EXPF = 1.0 for linear convection. Therefore, linear convection formula is: q = H * (T-TAMB)

5.

This card is represented as a group in HyperMesh.

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PDAMP Bulk Data Entry PDAMP – Scalar Damper Property Description Specifies the damping of a scalar damper element using defined CDAMP1 or CDAMP3 entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PDAMP

PID1

B1

PID2

B2

PID3

B3

PID4

B4

(10)

Example

(1)

(2)

(3)

(4)

(5)

PDAMP

14

2.3

2

6.1

Field

Contents

PID#

Property identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) B#

Force per unit velocity. No default (Real)

Comments 1.

Damping values are defined directly on the CDAMP2 entry and therefore do not require a PDAMP entry.

2.

A structural viscous damper, CVISC, may also be used for geometric grid points.

3.

Up to four damping properties may be defined on a single entry.

4.

This card is represented as a property in HyperMesh.

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PEAKOUT Bulk Data Entry PEAKOUT – Peak Identification Criteria Description Defines criteria used for the automatic identification of loading frequencies at which result peaks occur. Other result output may then be requested at these “peak” loading frequencies. This feature is only supported for frequency response solution sequences. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PEAKOUT

SID

NPEAK

NEAR

FAR

LFREQ

HFREQ

RTYPE

PSC ALE

GRIDC

GID1

C ID1

C UTOFF1

GID2

C ID2

C UTOFF2

GID3

C ID3

C UTOFF3

...

...

...

...

...

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PEAKOUT

396

5

0.5

100.0

0.0

200.0

DISP

DB

GRIDC

65

1

11

66

1

10

67

1

11

68

1

11

Field

Contents

SID

Set identification number.

(10)

No default (Integer > 0)

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Field

Contents

NPEAK

Desired number of peaks. See comment 2. Default = 5 (Integer > 0)

NEAR

Minimum allowed distance between two peaks. If two peaks are closer than this value, the loading frequency of the lower peak will be ignored. See comment 2. Default = 0.0 (Real > 0.0)

FAR

Maximum allowed distance between two peaks. Additional peaks will be selected (in addition to NPEAK) if the distance between the peaks is greater than this value. See comment 2. Default = largest applied loading frequency (Real > 0.0)

LFREQ

Starting loading frequency for peak identification. See comment 2. Default = 0.0 (Real > 0.0)

HFREQ

Ending loading frequency for peak identification. See comment 2. Default = largest applied loading frequency (Real > 0.0)

RTYPE

Result type for peak identification for the structural domain. The result for a structural degree of freedom can be displacement (DISP), velocity (VELO), or acceleration (ACCE). Default = DISP (DISP, VELO or ACCE)

PSCALE

Pressure scaling method for peak identification for the fluid domain. The result for a fluid grid can be the scale of pressure, decibels (DB) or Aweighted decibels (DBA). See comment 3 for decibel calculations and reference pressure settings. For DBA, standard A-weighting is used. Default = DBA (DB, DBA or NONE)

GRIDC

Flag indicating that a degree-of-freedom list for peak identification is to follow.

GID#

Grid identification number. No default (Integer > 0)

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Field

Contents

CID#

Component identification number. No default (1 < Integer < 6)

CUTOFF#

The cutoff value can be a real value or an integer value. See comment 2. If the entry is a real value, then this is the value of the cutoff (in the same unit specified by RTYPE and PSCALE). If the entry is an integer value, then this is the identification number of a TABLED1, TABLED2, TABLED3, or TABLED4 entry defining the cutoff as a function of frequency (in the same unit specified by RTYPE and PSCALE). Default = 0.0 (Real or Integer > 0)

Comments 1.

There can be multiple PEAKOUT cards with the same SETID.

2.

The following example shows how the different criteria work in identifying peaks.

Figure 1: Plot of the Acoustic Response vs. Frequency

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OptiStruct 13.0 Reference Guide 1815 Proprietary Information of Altair Engineering

Figure 1 shows a plot of the Acoustic Response versus frequency for a chosen degree-offreedom. The total frequency range can be reduced to the frequency range of interest by defining LFREQ and HFREQ. The search area can be further reduced by defining CUTOFF such that low magnitude peaks can be ignored. In the remaining region, 5 peaks (P1, P2, P3, P4, and P5) can easily be identified. Should NPEAK be set to 4, the resulting frequency set would consist of the frequencies corresponding to the peaks P4, P5, P1, and P3, with P5 being omitted. In order to ensure that peaks are neither too far apart nor too close together, the FAR and NEAR criteria, respectively, may be used. In the above example, should a value of 50HZ be defined for FAR, P4 would be selected in addition to the other peaks because D2 (~54 Hz) is greater than 50Hz, and so an additional peak is required to satisfy the FAR criterion. Similarly, should a value of 15Hz be defined for NEAR, then P2 will be omitted, as D1 (~11 Hz) is less than 15Hz. 3.

The dB value is calculated using 20 * log10 (P/P0), where P0 is the reference pressure. The reference pressure is dependent on the units specified on the UNITS input data. If the units are SI, the value is set as 2.0E-5 Pa. If they are CGS, it is set as 2.0E-4 barye. If they are MPa, it is set as 2.0E-11 MPa. If they are BG or EE, then it is set as 4.17E-7 lbf/ft 2. If no UNITS data is present, the default value is 2.0E-11 MPa.

4.

If you wish to include interior points of a superelement (in a CMS model) for the purposes of peak identification using the PEAKOUT bulk data entry, the SEINTPNT entry can be used in the subcase information section to convert the interior grid points to exterior grid points (since points referenced by PEAKOUT should be exterior points only).

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PELAS Bulk Data Entry PELAS – Scalar Elastic Property Description Used to define the stiffness and stress coefficient of a scalar elastic element (spring) by means of the CELAS1 or CELAS3 entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PELAS

PID

K

GE

S

PID

K

GE

S

(10)

Example

(1)

(2)

(3)

PELAS

7

4.29

(4)

(5)

(6)

(7)

7.92

27

2.17

Field

Contents

PID

Unique scalar elastic property identification number.

(8)

(9)

(10)

No default (Integer > 0) K

Elastic property value. No default (Real)

GE

Damping Coefficient. See comments 3 and 4. Default = 0.0 (Real)

S

Stress coefficient. Default = 0.0 (Real)

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OptiStruct 13.0 Reference Guide 1817 Proprietary Information of Altair Engineering

Comments 1.

Be careful using negative spring values.

2.

One or two elastic spring properties may be defined on a single entry.

3.

To obtain the damping coefficient GE, multiply the critical damping ratio, C/C0, by 2.

4.

If PARAM, W4 is not specified, GE is ignored in transient analysis.

5.

The element force of a spring is calculated from the equation:

F = k * (u1 – u2) Where, k is the stiffness coefficient for the scalar element and u1 is the displacement of the first degree-of-freedom listed on the CELAS entry. Element stresses are calculated from the equation: s = S * F, where, S is the stress coefficient as defined above. 6.

This card is represented as a property in HyperMesh.

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PELAST Bulk Data Entry PELAST – Frequency-dependent Elastic Spring Property Description Defines the frequency dependent property values for a PELAS bulk data entry. Format (1)

(2)

(3)

(4)

(5)

PELAST

PID

TKID

TGEID

TKNID

(6)

(7)

(8)

(9)

(10)

Field

Contents

PID

Property identification number. Must match with a PID of a PELAS bulk data entry. No default (Integer > 0)

TKID

Identification number of a TABLED# entry that defines the force per unit displacement versus frequency relationship. Default = 0 (Integer > 0)

TGEID

Identification number of a TABLED# entry that defines the element structural damping coefficient versus frequency relationship. Default = 0 (Integer > 0)

TKNID

Identification number of a TABLED# entry that defines the nonlinear force versus displacement relationship. Default = 0 (Integer > 0)

Comments 1.

Each PELAST entry must have a matching PELAS entry.

2.

PELAST is ignored in all solution sequences except frequency response analysis. Nominal values from the PELAS entry are used in all the analyses except frequency response analysis.

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OptiStruct 13.0 Reference Guide 1819 Proprietary Information of Altair Engineering

3.

If a particular TABLED id is blank or 0, the corresponding nominal value from the PELAS entry will be used.

4.

The TKNID table is currently unused in nonlinear analysis and is ignored.

5.

This card is represented as a property in HyperMesh.

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PERBC Bulk Data Entry PERBC – Defines a connection between opposite edges/faces of the structure (Periodic Boundary Conditions). Description The PERBC bulk data entry can be used to define a connection between opposite edges/faces of the structure. This entry is used to apply Periodic Boundary Conditions to the model. Format (1)

(2)

(3)

(4)

(5)

PERBC

ID

GSID

RLID

TOL

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

PERBC

2

45

32

0.01

Field

Contents

ID

Set identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) GSID

Identification number of a SET of grid points on one side of the structure. (Integer > 0)

RLID

Identification number of a RELOC bulk data entry that maps the nodes on one side of the structure to the other. An exact one-to-one match between the two sides is required. (Integer > 0)

TOL

Specifies the numeric value defining the maximum distance between two grid points to allow equivalence. All grid points in the set defined by GSID and the set of grid points on the other side of the structure (mapping defined by the RELOC entry) are considered for equivalence based on the tolerance. (Real > 0.0)

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OptiStruct 13.0 Reference Guide 1821 Proprietary Information of Altair Engineering

Comments 1.

The PERBC entry can be used to apply periodic boundary conditions, to match results from one side of the structure to another.

2.

The referenced RELOC Bulk Data Entry should be defined with TYPE=MOVE or TYPE=ROTATE. For TYPE=ROTATE, a simple rotation about a single axis should only be defined. All grids on one side of the structure (defined via GSID) and matching grids on the other side should cannot have a coordinate system (Field CD on GRID entry) defined. If RELOC(ROTATE) is specified, then all matching grids will have CD assigned automatically to match the structure.

3.

Periodic Boundary Conditions are supported for all solution sequences (except OptiStructMulti-body Dynamics (OS-MBD) and Geometric Nonlinear Analysis (ANALYSIS=NLGEOM/ IMPDYN/EXPDYN)) and all optimization types. In shape optimization, when GRID’s identified on the PERBC entry are in or near the optimized zone, their location changes should be properly linked through DVGRID, otherwise the results may be incorrect.

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Altair Engineering

PFAST Bulk Data Entry PFAST – CFAST Element Property Description Define properties of connector (CFAST) elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PFAST

PID

D

MC ID

MFLAG

KT1

KT2

KT3

KR1

KR2

KR3

MASS

GE

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PFAST

9

0.3

20

1

12800.0

8000.0

8000.0

(9)

(10)

0.8

Field

Contents

PID

Identification number of a PFAST entry. No default (Integer > 0)

D

Diameter of the connector. See comment 2. No default (Real > 0.0)

MCID

Identification number of the element stiffness coordinate system. See comment 3.

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OptiStruct 13.0 Reference Guide 1823 Proprietary Information of Altair Engineering

Field

Contents

MFLAG

Flag to indicate how the coordinate system specified by MCID will be used. If MFLAG = 0, MCID defines a relative coordinate system. If MFLAG = 1, MCID defines an absolute coordinate system. Default = 0 (Integer)

KTi

Stiffness values in directions 1 through 3. Default = 0.0 (Real)

KRi

Rotational stiffness values in directions 4 through 6. Default = 0.0 (Real)

MASS

Mass of the fastener. See comment 5. Default = 0.0 (Real)

GE

Structural damping. Default = 0.0 (Real)

Comments 1.

For a CFAST element, no material needs to be specified in the corresponding PFAST card - the stiffness of the element is directly specified in the PFAST card with KTi and KRi entries.

2.

The diameter D will not be involved in the stiffness calculation directly. It is used along with GA and GB to find appropriate auxiliary points and related shell elements and grids. In this case, the stiffness contribution of the fastener depends not only on the stiffness values specified for KTi and KRi, but also the diameter D, because the location of the auxiliary points will be used to weight the contribution of the shell element grids to GA and GB of the fastener.

3.

Element stiffness coordinate system. The three stiffness values KT1, KT2 and KT3 will be applied along the three axes of the element coordinate system. The unit vectors of the three axes are denoted as e1, e2 and e3. a) If MCID = -1, MFLAG will be ignored and e1 will be defined as:

e2 is defined as being perpendicular to e1 and lined up with the closest axis of the basic system. This is accomplished by taking the inner product of e1 with the basic system unit vectors. The smallest will define the basic system direction which is closest to the plane

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Altair Engineering

perpendicular to e1* e2 is then defined as the projection of the basic direction onto this perpendicular plane. For example, assume m is the unit vector of the closest axis of the basic system. The direction of e2 can be calculated as:

Unify this vector, then

At last, e3 can be calculated by the cross product of e1 and e2 as follows: e3 = e1 x e2 b) If MCID > 0 and MFLAG = 0, e1 will be defined as:

in which XA and XB are the coordinates of GA and GB. The T2 direction specified by MCID will be used to define the orientation vector v of the fastener. Then, e3 can be obtained as:

At last, the e2 can be easily calculated by the cross product of e3 and e1 as follows: e2 = e3 x e1 c) used directly as e1, e2 and e3. The element forces will be computed in the coordinate system defined in comment 3(a). d) If MCID refers to a cylindrical or spherical coordinate system, the local origin used to locate the system is selected as follow: (i) if GA of the CFAST is specified, use GA as the local origin; (ii) if GA is not specified but GS is specified, use GS as the local origin; (iii) if neither GA nor GS is specified, use the point (XS, YS, ZS) as the local origin. 4.

The final length of the CFAST element is defined by the distance between GA and GB. If the length is zero, the normal to shell patch A is used to define the axis of the fastener.

5.

For the mass of the fastener, half of the value defined in the MASS entry is placed directly onto the translational degrees-of-freedom of GA and GB. Then they are distributed, via auxiliary points, to corresponding shell grids. As the result, while the mass will be represented correctly for general representation of the fastener in the vibrations of the structure, the moments of inertia relative to the local axes of the fastener will only be

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OptiStruct 13.0 Reference Guide 1825 Proprietary Information of Altair Engineering

roughly approximated.

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PFAT Bulk Data Entry PFAT – Fatigue Properties Description Defines element properties for fatigue analysis Format (1)

(2)

(3)

(4)

(5)

(6)

PFAT

ID

Layer

Finish

Treatme nt

Kf

(7)

(8)

(9)

Field

Contents

ID

Each PFAT card must have a unique ID. This ID may be referenced from a FATDEF definition.

(10)

No default (Integer > 0) Finish

Material Surface Finish, a result of manufacturing process. See comment 3. Default = NONE (NONE, POLISH, GROUND, MACHINE, HOTROLL, FORGE or any float value between 0.0 and 1.0) When it is a float value, it will be used to modify the fatigue limit by multiplied with the original fatigue limit.

Treatment

Material Surface Treatment for Material S-N Curve, a process used to enhance the fatigue life. See comment 3. Default = NONE (NONE, NITRIDED, SHOTPEEN, COLDROLL or any float value great than 0.0) When it is a float value, it will be used to modify the fatigue limit by multiplied with the original fatigue limit.

Layer

Region Layer for shell elements. See comment 1. Default = 0 (0 = Worst, 1 = Top, 2 = Bottom).

Kf

Fatigue strength reduction factor. See comments 2 and 3. Default = 1.0 (Real > 1.0)

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OptiStruct 13.0 Reference Guide 1827 Proprietary Information of Altair Engineering

Comments 1.

If shell elements are used, it is necessary to specify the appropriate layer or Surface of results to use Top or Bottom. Worst is the worst result of Top and Bottom (the one with larger damage).

2.

Fatigue strength reduction factor takes into account the effect of notch effects, size effects, and loading type influence,

where, Cnotch , Csize, and Cloading are correction factors for notch effect, size effect, and loading type influence. 3.

Finish, Treatment and Kf are ignored in FOS analysis (TYPE=FOS on FATPARM).

4.

This card is represented as a loadcollector in HyperMesh.

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PFPATH Bulk Data Entry PFPATH – Transfer Path Analysis Description Bulk Data Entry for One-Step Transfer Path Analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PFPATH

SID

C ONPT

RID

RTYPE

C ONEL

C ONREL

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

PFPATH

10

11

12

DISP

18

23

(8)

(9)

(10)

Argument

Options

SID



setid

The SID is referenced by a PFPATH card in the control section.

CONPT



gsid

The connection points with a SID of type GRID SET.

RID



rsid

The response SID of type GRIDC. Contribution to each response DOF through the connection points will be calculated.

Altair Engineering

Description

OptiStruct 13.0 Reference Guide 1829 Proprietary Information of Altair Engineering

Argument

Options

Description

RPTYPE

DISP/VELO/ACCE Default = DISP

Criterion for the type of the response; the response type corresponding to a structural degree of freedom could be displacement, velocity or acceleration.

CONEL



esid

The ELEMENT set consists of elements connected to the connection GRIDs in CONPT. These elements represent connecting paths from the rest of the system to the user-defined control volume.

CONREL



rsid

The RIGID set consists of the RIGID elements, connected to the connection GRIDs in CONPT. These rigid elements represent connecting paths from the rest of the system to the user defined control volume.

Comments 1.

There can be multiple PFPATH cards with the same SID.

2.

If CONREL is specified in the 7th entry, the RIGID element IDs must be unique.

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PFBODY Bulk Data Entry PFBODY – Flexible Body Definition for Multi-body Simulation Description Defines a flexible body out of a list of finite element properties, elements, and grid points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PFBODY

BID

BODY_NAME

TYPE1

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

…

TYPE2

ID9

ID10

…

TYPE#

…

G4

G5

G6

(10)

…

C MS

C TYPE

UB_FREQ

NMODES

FLXNODE

NOAUTO/C 1

G1

G2

G3

FLXNODE

C2

G8

G9

…

DTYPE

DVAL

…

DAMPING

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Example 1

(1)

(2)

PFBODY

3

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(10)

C ontrol_arm

PSHELL

23

21

PBEAM

9

59

48

C ONM2

2345

GRID

400

401

402

C MS

CB

FLXNODE

123

400

499

FLXNODE

123456

402

300

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PFBODY

3

901

902

903

1000

1001

50

Example 2

Linkage

PSOLID

13

15

C MS

CB

2000.0

FLXNODE

NOAUTO

FLXNODE

123

900

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(1)

(2)

(3)

(4)

(5)

(6)

FLXNODE

123456

11

12

13

DAMPING

C RATIO

0.8

Field

Contents

BID

Unique body identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) BODY_NAME

Unique body name. This name is used as the Flex H3D file name to which the reduced flexible body information will be written out for the PFBODY. Default = OUTFILE_body_.h3d (Character string)

TYPE#

Flag indicating that the following list of IDs refer to entities of this type. All property definitions; CELAS2, CONM2, PLOTEL, RBE2, RBE3, RBAR, RROD, and GRID are valid types for this field. No default (PBAR, PBARL, PBEAM, PBEAML, PBUSH, PCOMP, PCOMPP, PCOMPG, PDAMP, PELAS, PGAP, PROD, PSHEAR, PSHELL, PSOLID, PVISC, PWELD, CELAS2, CONM2, PLOTEL, RBE2, RBE3, RBAR, RROD, or GRID)

ID#

Identification numbers of entities of the preceding TYPE flag. No default (Integer > 0)

CMS

CMS flag indicating that information on the method used for reducing the flexible body is to follow.

CTYPE

Component Mode Synthesis method to be employed. CB - Craig-Bampton CC - Craig-Chang Default = CB (CB or CC)

UB_FREQ

Upper bound frequency for the eigenvalue analysis. If 0.0 or blank, no

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OptiStruct 13.0 Reference Guide 1833 Proprietary Information of Altair Engineering

Field

Contents upper bound is used. See comments 8 and 9. Default = blank (Real > 0.0, or blank)

NMODES

Number of modes to be extracted from eigenvalue analysis. If set to -1 or blank, number of modes is limitless. See comments 8 and 9. Default = blank (Integer > -1, or blank)

FLXNODE

FLXNODE flag indicating that flexible body interface node information is to follow. See comment 11.

NOAUTO

NOAUTO flag to not automatically determine the interface nodes for the flexible body.

C#

Component number indicating the interface degrees-of-freedom for the following list of grids. No default (up to 6 unique digits (0 < digit < 6) may be placed in the field with no embedded blanks)

G#

Grid identification numbers. (Integer > 0)

DAMPING

DAMPING flag indicating the flexible body modal damping.

DTYPE

Damping option. Default = DEFAULT (DEFAULT or CRATIO)

DVAL

Damping ratio value if DTYPE is specified as CRATIO. (Real > 0.0)

Comments 1.

A maximum of 56 characters may be given for BODY_NAME.

2.

Flex H3D file name will be .h3d or OUTFILE_body_.h3d in the outfile directory.

3.

Any number of property definitions; CELAS2, CONM2, PLOTEL, RBAR, RBE2, RBE3 or RROD elements or grid points can be given.

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4.

At least one property definition, element, or grid point must be given.

5.

A property definition; CELAS2, CONM2, PLOTEL, RBE2, RBE3, RBAR or RROD element or grid point can only belong to one body (flexible or rigid).

6.

All property definitions, elements and grid points defined on a PFBODY bulk data entry form one flexible body.

7.

CMS definition defines the component mode synthesis method to reduce the flexible body for the multi-body analysis. Exactly one must be defined for each PFBODY.

8.

UB_FREQ and NMODES cannot both be blank.

9.

When UB_FREQ = 0.0 and NMODES = 0, this is a special case where no eigen modes will be included in CMS mode generation.

10. If FLXNODE is not defined, a default set of interface nodes and degrees-of-freedom. will be generated based on the actual interface nodes and degrees-of-freedom of the flexible body. 11. One FLXNODE line can have up to six interface grid IDs. No continuation lines are allowed. Add multiple FLXNODE lines to add more than six interface nodes. 12. This card is represented as a group in HyperMesh.

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OptiStruct 13.0 Reference Guide 1835 Proprietary Information of Altair Engineering

PGAP Bulk Data Entry PGAP – Gap Element Property Description Defines properties of the gap (CGAP or CGAPG) elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PGAP

PID

U0

F0

KA

KB

KT

MU1

MU2

GPAD

FRIC ESL

Examples

(1)

(2)

(3)

(4)

(5)

PGAP

2

.025

2.5

1E6

(6)

(7)

(8)

(9)

1E6

0.25

0.25

0.3

0.3

(10)

Frictionless contact with automatic determination of U0 and KA: PGAP

2

AUTO

AUTO

Minimum data required to prescribe Coulomb friction: PGAP

2

1E6

Enforced stick condition (See comment 8): PGAP

2

1E6

AUTO

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Field

Contents

PID

Property identification number. No default (Integer > 0)

U0

Initial gap opening. Default = 0.0 (Real or AUTO). See comment 2.

F0

Preload. (Ignored in linear analysis). Default = 0.0 (Real > 0.0)

KA

Axial stiffness for the closed gap. See comments 3 and 7. No default (Real > 0.0 or AUTO, SOFT or HARD)

KB

Axial stiffness for the open gap. See comment 3. Default = 10-14 * KB (Real > 0.0). This default is also set when KB=0.

KT

Transverse stiffness when the gap is closed. See comments 4 and 7. Default = MU1 * KA (Real > 0.0 or AUTO)

MU1

Coefficient of static friction (ms). See comments 8 through 10. (Ignored in linear analysis). Default = 0.0 (Real > 0.0 or STICK or FREEZE)

MU2

Coefficient of kinetic friction (mk). (Ignored in linear analysis). Default = MU1 (0.0 < Real < MU1)

GPAD

“Padding” to be added to account for additional layers on the surface of obstacles A and B. Positive value reduces the initial gap opening. See comment 11. Default = NONE (Real or NONE or THICK; THICK applies only to CGAPG elements)

FRICESL

Frictional elastic slip – distance of sliding up to which the frictional transverse force increases linearly with slip distance. Specified in physical distance units (similar to U0 and GPAD). See comment 5.

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OptiStruct 13.0 Reference Guide 1837 Proprietary Information of Altair Engineering

Field

Contents Non-zero value activates respective friction model based on Elastic Slip Distance. Zero value or blank activates friction model based on prescribed transverse stiffness KT. Default = 0.0 (Real > 0.0)

Comments 1.

The gap element coordinate system is presented in the following figure. See the CGAP or CGAPG entry for a more detailed description.

The C GAP or C GAPG Element C oordinate System

2.

With the optional value AUTO, the initial gap opening U0 is calculated automatically, based on the distance between nodes GA and GB (in the original, undeformed mesh). For gap elements with prescribed coordinate systems, this becomes a projection of vector GA->GB onto the prescribed axis on the gap element (axis 1 of the coordinate system).

3.

The gap element force-displacement behavior is different in linear and nonlinear analysis (see Nonlinear Quasi-Static Analysis for more information on nonlinear solutions). In linear analysis, the gap stiffness is constant and depends on the initial gap opening U0 (as shown in the figure below).

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Altair Engineering

C GAP or C GAPG Element Force Deflection C urve for Linear Analysis

The gap force displacement behavior in nonlinear analysis is illustrated in the figure below. While the gap is open, its normal stiffness is defined by KB. When the gap relative displacement UA - UB becomes equal to the initial opening U0, first contact occurs. The gap stiffness becomes KA upon contact.

C GAP or C GAPG Element Force Deflection C urve for Nonlinear Analysis

4.

When the gap is open, there is no transverse stiffness. When the gap is closed, friction is activated and the gap has stiffness KT in the transverse direction (see 5 below for alternative version). KT acts as a linear spring in linear solution sequences. For nonlinear solution sequences, frictional force increases with sliding distance in proportion to KT until it reaches static friction force MU1 * Fx, Fx being the normal force in the gap element. With further transverse deformation, friction becomes kinetic and the friction force is MU2 * Fx. See the figure below for a one-dimensional illustration.

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OptiStruct 13.0 Reference Guide 1839 Proprietary Information of Altair Engineering

C GAP or C GAPG Element Frictional Behavior in Nonlinear Analysis

5. In addition to the above formulation, in Release 12.0 an additional model of friction has been introduced, based on Elastic Slip Distance and activated by presence of non-zero FRICESL. This model typically has better performance in solution of frictional problems thanks to more stable handling of transitions from stick to slip. Key differences between the two available models are illustrated in the figure below (F 1 and F 2 represent two different values of normal force F x ):

C omparison of the two available friction models for gap elements.

Model (a), based on fixed stiffness KT, is relatively simpler and only requires prescribing coefficient of friction MU1 and MU2 (while KT can be determined automatically). However, in Coulomb friction the frictional resistance depends upon normal force. Using fixed KT will predict different range of stick/slip boundary for different normal forces, and thus may qualify the same configuration as stick or slip, depending on normal force.

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Model (b), based on Elastic Slip Distance, provides unique identification of stick or slip and generally performs better in solution of problems with friction. This model does require prescribing elastic slip distance FRICESL (for gap elements, there is no automatic determination of FRICESL – a recommended value is about 0.5% of typical element size in the neighborhood of the gap element). 6. Note that the nonlinear gap element's force-displacement behavior may produce negative contributions to the compliance of the structure. For example, if KB > 0 and initial gap opening U0 > 0, then the gap is essentially "preloaded" with an attractive force KB*U0. As such a gap closes, the work done (and, hence, the gap's contribution to compliance) is negative. Such very small negative contributions may even be produced if the KB field is blank or zero – this is due to the default non-zero value of KB applied in such cases. In most situations, such small negative contributions get overridden by the overall positive compliance of the entire structure. However, in some cases they may lead to negative total compliance. 7. Reasonable gap stiffness: the gap stiffness values KA and KT essentially represent penalty springs that are hard enough to prevent perceptible penetration of contacting nodes. While, theoretically, higher stiffness values enforce the contact conditions more precisely, excessively high values may cause difficulties in convergence or poor conditioning of the stiffness matrix (this is especially true for KT). If any such symptoms are observed, it may be beneficial to reduce the value of gap stiffness. A reasonable range of gap stiffness is of the order of: (103 to 106 ) * E * h where, E is the typical value of elastic modulus and h is the typical element size in the area surrounding the gap elements. Such a range will generally keep the gap penetration below one thousandth / one millionth of the element size, respectively. A good value for KT is of the order of 0.1*KA. To facilitate reasonable values of KA and KT, automatic calculation of these parameters is supported, specifically: Option KA=AUTO determines the value of KA for each gap element using the stiffness of surrounding elements. Additional options SOFT and HARD create respectively softer or harder penalties. SOFT can be used in cases of convergence difficulties and HARD can be used if undesirable penetration is detected in the solution. Option KT=AUTO automatically calculates the value of KT. If MU1>0, the result here is the same as with blank KT -- its value is calculated as MU1*KA. However, if MU1=0 or blank, KT=AUTO produces a non-zero value of KT, calculated as KT=0.1*KA. Therefore, KT=AUTO can be used to prescribe enforced stick conditions (see below). 8.

Prescribing MU1=STICK is interpreted as an enforced stick condition. (This can also be accomplished by prescribing KT>0 or KT=AUTO with MU1=0 or blank). Such gap elements will not enter the sliding phase. Of course, the enforced stick only applies to gaps that are closed. Note that, in order to effectively enforce stick condition on gaps of non-zero length,frictional offset may need to be turned off (See comment 10).

9.

Prescribing MU1=FREEZE enforces zero relative motion of the gap – the gap opening remains fixed at the original value and the sliding distance is zero. Also, rotations at GA node are matched to the rotations of GB or the obstacle patch B. The FREEZE conditions applies no matter whether the gap is open or closed (hence, U0 is of no relevance in this case). The prescribed values of KB and KT are ignored. The value of KA is respected,

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although it is recommended that it is set to AUTO or HARD, to assure good connection. Also, this condition is effective irrespective of the frictional offset setting. 10. The presence of friction or stick can introduce moment loadings and counter-intuitive results into the problem by way of frictional offset. The reason is that for gap elements with non-zero length (distance between GA and GB), the actual location of the contact interface is presumed to be in the middle of the gap length (see figure below).

C GAP or C GAPG Presumed C ontact Surface

The frictional forces act along this contact surface. Transferring these forces to the grid points GA and GB requires an offset operation that produces both forces and moments at the gap grid points. Similarly, the sliding distance at the gap interface is a result of nodal displacements and rotations at GA and GB (see figure below).

C GAP or C GAPG Sliding with Friction

For contact between bodies that do not support moments (solid elements, for example), this offset may render friction ineffective because the free rotations at gap nodes offer no effective resistance to friction. With the stick condition formally satisfied, for example, nodes GA and GB can move relative to each other (see figure below).

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C GAP or C GAPG Stick (Zero Sliding Distance)

In practice, for gaps that are initially open, AUTOSPC will effectively fix respective unsupported rotations. However, for gap elements that are initially closed (U0 < 0 or U0=AUTO with CID=FLIP), the frictional terms will prevent AUTOSPC from being effective. Hence, respective SPC on rotations need to be applied manually. (Note that this only applies to "individual" gap end nodes GA and GB and is not needed for elements or patches of nodes on the obstacle side of GAPG elements). Effective in the Release 12.0, to avoid such counter-intuitive behavior, the frictional offset operation is by default turned off if the model involves friction or stick and contains at least one nonlinear subcase (of NLSTAT type). (Note that for consistency, this affects both linear and nonlinear gap elements.) This produces more intuitive results with friction. However, it may violate the rigid body balance of the body. For linear gap analysis and for FREEZE condition, the offset operation is applied by default (this produces correct rigid body balance, especially in natural frequency analysis). The above default setting can be changed via the GAPOFFS command on the GAPPRM card. 11. The GPAD option allows you to account for additional layers on the surface on obstacles A and B, such as shell thickness or coatings on the surface of solids. Positive value substracts from the gap opening U0, when calculated using AUTO option (GPAD is only allowed when U0 is set to AUTO). The GPAD option THICK automatically accounts for shell thickness on both sides of the gap (this also includes the effects of shell element offset ZOFFS or composite offset Z0). The THICK option applies only to CGAPG elements and is ignored for CGAP. 12. This card is represented as a property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1843 Proprietary Information of Altair Engineering

PGAPHT Bulk Data Entry PGAPHT – Gap Element Heat Transfer Conduction Property for Heat Transfer Analysis Description Defines heat transfer conduction properties of the gap (CGAP or CGAPG) elements for heat transfer analysis. Format (1)

(2)

(3)

(4)

PGAPHT

PID

KAHT

KBHT

(5)

(6)

(7)

(8)

(9)

(10)

TC ID

Examples

(1)

(2)

(3)

PGAPHT

2

1E6

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Contact with automatic determination of KAHT: PGAPHT

2

AUTO

Minimum data required to prescribe clearance based contact conduction (see comments 2 and 3): PGAPHT

2

10

Field

Contents

PID

Property identification number. No default (Integer > 0)

KAHT

Total conduction for the closed gap. See comment 2.

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Field

Contents No default (Real > 0.0 or AUTO)

KBHT

Total conduction for the open gap. See comment 2. Default = 10-14 * KAHT (Real > 0.0) This default is also set when KBHT=0.

TCID

Identification number of a TABLED# entry. This table specifies total gap conduction based on gap clearance. See comments 2, 3, and 4. Default = 0 (Integer > 0)

Comments 1.

PGAPHT provides heat transfer conductivity for CGAP/CGAPG element. PGAPHT must match PID with an existing PGAP.

2.

KAHT and KBHT represent total gap conduction values for closed and open gaps. Theoretically, while higher conduction values enforce a perfect conductor, excessively high values may cause poor conditioning of the conductivity matrix. If any such symptoms are observed, it may be beneficial to reduce the value of gap conduction, or use conduction based contact clearance and pressure. To facilitate reasonable values of KAHT, automatic calculation is supported, specifically: Option KAHT=AUTO determines the value of KAHT for each gap element using the conduction of surrounding elements.

3. TCID points to a TABLED# entry that specifies total conduction based on gap clearance. TCID overrides KBHT. TCID is ignored for linear CGAP/CGAPG elements. 4. Thermal-structural analysis problems involving contact are fully coupled since contact/gap status changes thermal conductivity. Refer to Contact-based Thermal Analysis in the User’s Guide for more information. 5. This card is represented as a property in HyperMesh.

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PGASK Bulk Data Entry PGASK – Gasket Element Property Definition Description Defining the properties for solid gasket elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PGASK

PID

MIDG

MID1

C ORDM

H0

GAP

VOID

LEAKP

STABMT

Example

(1)

(2)

(3)

(4)

(5)

PGASK

1

2

1

1

(6)

(7)

(8)

(9)

(10)

0.5

Field

Contents

PID

Unique gasket element property identification number. No default (Integer > 0)

MIDG

A MGASK entry identification number that defines thickness-direction and transverse shear behaviors of the gasket. No default (Integer > 0)

MID1

A MAT1 entry identification number that defines membrane properties and mass density of the gasket. Blank means zero membrane stiffness, zero membrane thermal expansion coefficient, and zero mass density. Default = blank (Integer > 0 or blank)

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Field

Contents

CORDM

Material coordinate system identification number. See comment 3. -1 means the element local coordinate system, while 0 means the basic coordinate system. Default = -1 (Integer > -1)

H0

Prescribed initial thickness of the gasket. See comment 4. 0.0 or blank means using initial thickness of the gasket element. Default = 0.0 (Real > 0.0)

GAP

Initial open gap of the gasket. See comment 5. Default = 0.0 (Real > 0.0)

VOID

Initial void of the gasket. See comment 5. Default = 0.0 (Real > 0.0)

LEAKP

Leakage pressure. See comment 6. Default = blank (Real > 0.0 or blank)

STABMT

Membrane and transverse shear stabilization flag. 0 - no stabilization. 1 - a stabilization stiffness is used if membrane or transverse shear stiffness is zero. Default = 0 (Integer = 0 or 1)

Comments 1.

All gasket element property entries must have unique identification numbers.

2.

PGASK refers to two material entries, MGASK and MAT1. MGASK defines the thicknessdirection and transverse shear behaviors of the gasket material, and MAT1 defines the membrane behavior of the gasket material. The thickness-direction stiffness is defined with the unit of stress per unit displacement (the pressure—closure distance relationship for the thickness compression), the transverse shear stiffness is defined with either the unit of stress per unit displacement or the unit of force per unit area, and the membrane stiffness is defined with the unit of force per unit area (the stress—strain relationship).

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3.

The gasket material coordinate system can be defined as the element local coordinate system (CORDM = -1) or a prescribed system (CORDM = Integer > 0). The material local 3-direction is taken as the gasket thickness direction, and the material local 1-direction and 2-direction are taken as the gasket membrane principle directions. If the angle between the prescribed thickness direction (the material local 3-direction) and the default one (the element local 3-direction) is larger than 20 degrees, a warning will be provided.

4.

The initial thickness includes initial open gap and initial void of the gasket.

5.

The total closure of a gasket element consists of the mechanical closure and the thermal closure, that is:

Ctotal = Cmech + Cthermal The thermal closure, Cthermal, is calculated as:

Cthermal = ALPHA * (Tref - T) * (H0 - GAP - VOID) The effective closure, C, which is used to determine pressure with the loading/unloading of tables defined in the MGASK card, is calculated as:

C = Cmech – GAP If there is no initial open gap (GAP=0), C and Cmech are identical. 6.

The sealing status of gasket is detected with the leakage pressure. If the gasket pressure is larger than the leakage pressure, it is detected to be sealed – the output status index value is 1; otherwise, it is leaking – the output status index value is 0.

7.

For gasket in contact, STABMT is recommended to be 1, if its membrane or transverse shear stiffness is zero.

8.

The continuation entry is optional.

9.

This card is represented as a property in HyperMesh.

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PHFSHL Bulk Data Entry PHFSHL – Shell Element Property for One-Step Stamping Simulation Description Defines the thickness, material, blank holder, binder and Forming Limit Curve references for a shell property in a one-step stamping simulation. Format (1)

(2)

(3)

(4)

(5)

(6)

PHFSHL

PID

MID

T

BHID

(7)

(8)

(9)

(10)

FLDID

Example

(1)

(2)

(3)

(4)

(5)

PHFSHL

1

1

0.01

6

(6)

(7)

(8)

(9)

(10)

2

Field

Contents

PID

Unique shell element property identification number. No default (Integer > 0)

MID

Material identification number of a MATHF entry. No default (Integer > 0)

T

Thickness No default (Real > 0.0)

BHID

Blank holder ID referring to a BLKHDF entry. No default (Integer > 0 or blank)

FLDID

User-defined Forming Limit Curve ID referring to FLDATA entry. No default (Integer > 0 or blank)

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Comments 1.

This entry is only valid with an @HyperForm statement in the first line of the input file.

2.

All shell element property entries must have unique identification numbers.

3.

PHFSHL is referenced by CTRIA3 and CQUAD4 entries.

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PLOAD Bulk Data Entry PLOAD – Static Pressure Load Description Defines a static pressure load on a triangular or quadrilateral element. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

PLOAD

SID

P

G1

G2

G3

G4

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

PLOAD

1

-4.0

16

32

11

0

Field

Contents

SID

Load set identification number.

(8)

(9)

(10)

(Integer > 0) P

Pressure.

G1,...G4 Grid point identification numbers. (Integer > 0; G4 may be 0) Comments 1.

The grid points define either a triangular or a quadrilateral element to which a pressure is applied. If G4 is zero or blank, the element is triangular.

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In the case of a triangular element, the assumed direction of the pressure is computed according to the right-hand rule using the sequence of grid points G1, G2, and G3. 2.

The total load on the element, AP, is divided into three equal parts and applied to the grid points as concentrated loads. A minus sign in field 3 reverses the direction of the load.

3.

In the case of a quadrilateral element, the grid points G1, G2, G3, and G4 should form a consecutive sequence around the perimeter. The right-hand rule is applied to find the assumed direction of the pressure.

4.

This card is represented as a pressure load in HyperMesh.

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PLOAD1 Bulk Data Entry PLOAD1 – Applied Load on CBAR or CBEAM Elements Description Defines concentrated, uniformly distributed, or linearly distributed applied loads to the CBAR or CBEAM elements at user-chosen points along the axis. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PLOAD1

SID

EID

TYPE

SC ALE

X1

P1

X2

P2

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PLOAD1

25

1065

MY

FRPR

0.2

2.5E3

0.8

3.5E3

Field

Contents

SID

Load set identification number.

(10)

No default (Integer > 0) EID

CBAR or CBEAM element identification number. No default (Integer > 0)

TYPE

Load type. See comment 5. No default (FX, FY, FZ, FXE, FYE, FZE, MX, MY, MZ, MXE, MYE or MZE)

SCALE

Determines scale factor for X1, X2. See comments 6, 7, 8 and 9. No default (LE, FR, LEPR or FRPR)

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Field

Contents

X1, X2

Distances along the CBAR or CBEAM element axis from end A. For X1: No default; For X2: Default = blank (Real, 0 < X1 < X2)

P1, P2

Load factors at positions X1, X2. Default = blank (Real or blank)

Comments 1.

In the static solution sequences, the load set ID (SID) is selected by the LOAD command in the Subcase Information section.

2. positions X1 and X2, having an intensity per unit length of bar equal to P1 at X1 and equal to P2 at X2, except as noted in comments 8 and 9. 3.

If X2 is blank or equal to X1, a concentrated load of value P1 will be applied at position X1.

4. will be applied between positions X1 and X2, except as noted in comments 8 and 9. 5.

Load TYPE is used as follows to define loads: "FX", "FY" or "FZ": Force in the x, y, or z direction of the basic coordinate system. "MX", "MY" or "MZ": Moment in the x, y, or z direction of the basic coordinate system. "FXE", "FYE" or "FZE": Force in the x, y, or z direction of the element’s coordinate system. "MXE", "MYE" or "MZE": Moment in the x, y, or z direction of the element’s coordinate system.

6.

If SCALE = "LE" (length), the xi values are actual distances along the element axis, and, if

7.

If SCALE = "FR" (fractional), the xi values are ratios of the distance along the axis to the

8.

If SCALE = "LEPR" (length projected), the xi values are actual distances along the element element.

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PLOAD1 C onvention on Beam or Bar Elements

If SCALE = "LE", the total load applied to the bar is P1 (X2 – X1) in the y-basic direction. If SCALE = "LEPR", the total load applied to the bar is P1 (X2 – X1) cosα in the y-basic direction. 9.

If SCALE = "FRPR" (fractional projected), the Xi values are ratios of the actual distance to in terms of the projected length of the bar.

10. Element identification numbers for CBAR and CBEAM entries must be unique. 11. Loads on CBEAM elements defined with PLOAD1 entries are applied along the line of the shear centers. 12. If on the TYPE field of the PLOAD1 entry, the element coordinate system direction (for example, TYPE = FYE) option is selected, then the projection (SCALE=FRPR or LEPR) option is ignored and the result is the same as the SCALE=FR (or LE) option. 13. This card is represented as a pressure load in HyperMesh.

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PLOAD2 Bulk Data Entry PLOAD2 – Pressure Load on a Two-Dimensional Structural Element Description Defines a uniform static pressure load applied to two-dimensional elements. Only QUAD4 or TRIA3 elements may have a pressure load applied to them via this entry. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PLOAD2

SID

P

EID

EID

EID

EID

EID

EID

(10)

Example

(1)

(2)

(3)

PLOAD2

21

-3.6

(4)

(5)

(6)

4

16

(7)

(8)

(9)

(10)

2

Alternate Format and Example (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PLOAD2

SID

P

EID1

“THRU”

EID2

blank

blank

blank

PLOAD2

1

30.4

16

THRU

48

Field

Contents

SID

Load set identification number.

(10)

(Integer > 0)

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Field

Contents

P

Pressure value.

EID, EID1, EID2

Element identification number. (Integer > 0; EID1 0)

EID1, EID2

Element identification number. (Integer > 0, EID1 < EID2)

P1, P2, P3, P4

Load per unit surface area (pressure) at the corners of the face of the element (real or blank). (P1 is the default for P2, P3, and P4).

G1

Identification number of a grid point connected to a corner of the face. Required data for solid elements only (Integer or blank). For PYRA elements, this grid must be on an edge of the quadrilateral face.

G3

Identification number of a grid point connected to a corner diagonally opposite to G1 on the same face of a HEXA or PENTA element. Required data for quadrilateral faces of HEXA and PENTA elements only (Integer or blank). G3 must be omitted for a triangular surface on a PENTA element and the quadrilateral face on a PYRA element. For triangular faces of PYRA elements, this grid must be on the edge next to the quadrilateral face. G1 and G3 must define a positive direction into the element using the right hand rule.

G4

Identification number of the TETRA grid point located at the corner not on the face being loaded. This is required data and is used for TETRA elements only.

CID

Coordinate system identification number. (Integer > 0)

N1, N2, N3

Components of vector measured in coordinate system defined by CID (Real). Used to define the direction (but not the magnitude) of the load intensity. See comment 10.

Comments 1.

The continuation is optional. If fields 2, 3, 4, and 5 of the continuation are blank, the load is assumed to be a pressure acting normal to the face. If these fields are not blank, the load acts in the direction defined in these fields. Note that, if CID is a curvilinear coordinate system, the direction of load may vary over the surface of the element. The load intensity is the load per unit of surface area, not the load per unit of area normal to

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the direction of loading. 2.

For solid elements the direction of positive pressure (defaulted continuation card) is inward. The load intensity P1 acts at grid point G1 and load intensities P2, P3 (and P4) act at the other corners in a sequence determined by applying the right hand rule to the outward normal.

3.

For plate elements the direction of positive pressure (defaulted continuation) is in the direction of positive normal, determined by applying the right hand rule to the sequence of connected grid points. The load intensities PI, P2, P3 (and P4) act respectively at corner points G1, G2, G3 (and G4). (See plate connection).

4.

If P2, P3 (and P4) are blank fields, the load intensity is uniform and equal to P1. P4 has no meaning for a triangular face and may be left blank in this case.

5.

Equivalent grid point loads are computed by linear (or bilinear) interpolation of load intensity, followed by numerical integration using isoperimetric shape functions. Note that uniform load intensity does not necessarily result in equal equivalent grid point loads.

6.

G1 and G3 are ignored for TRIA3, TRIA6, QUAD4, and QUAD8 elements.

7.

The alternate form is available only for TRIA3, TRIA6, QUAD4, and QUAD8 elements. The continuation card may be used in the alternate form.

8.

For triangular faces of PENTA elements, G1 is an identification number of a corner grid point that is on the face being loaded and the G3 or G4 field is left blank. For faces of TETRA elements, G1 is an identification number of a corner grid point that is on the face being loaded and G4 is an identification number of the corner grid point that is not on the face being loaded. Since a TETRA has only four corner points, this point, G4, is unique and different for each of the four faces of a TETRA element.

9.

For the quadrilateral face of the PYRA element, G1 is an identification number of a corner grid point on the face and the G3 or G4 field is left blank. For the triangular faces, G1 and G3 must specify the grids on the edge of the face that borders the quadrilateral face and the grids must be ordered so that they define an inward normal using the right hand rule.

10. N1, N2, and N3 are not supported in NLGEOM subcases. 11. This card is represented as a pressure load in HyperMesh.

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PLOADX1 Bulk Data Entry PLOADX1 – Static Pressure Load on Axisymmetric Element Description Defines a static surface traction on the CTAXI and CTRIAX6 axisymmetric elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PLOADX1

SID

EID

PA

PB

GA

GB

Theta

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PLOADX1

3

20

10.5

12.5

11

13

15.0

Field

Contents

SID

Load set identification number.

(9)

(10)

(Integer > 0) EID

Element identification number. (Integer > 0)

PA

Surface traction at grid point GA. No default (Real)

PB

Surface traction at grid point GB. Default = PA (Real or blank)

GA, GB

Identification numbers of two adjacent corner grid points on the element side.

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Field

Contents No default (Integer > 0)

Theta

Angle between surface traction and inward normal to the line segment. Default = 0.0 (Real or blank)

Comments 1.

The surface traction is assumed to vary linearly along the element side between GA and GB.

2.

The surface traction is input as force per unit area.

3.

“Theta” is measured counter-clockwise from the inward normal of the straight line between GA and GB, to the vector of the applied load, as shown in the figure below. Positive pressure is in the direction of inward normal to the line segment.

Pressure Load on C TRAX6 and C TAXI Elements

4.

This card is represented as a pressure load in HyperMesh.

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PLOTEL Bulk Data Entry PLOTEL – Dummy Plot Element Definition Description Defines a one-dimensional dummy element for use in plotting. Format (1)

(2)

(3)

(4)

PLOTEL

EID

G1

G2

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

PLOTEL

29

35

16

(5)

(6)

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) G1,G2

Grid point identification numbers of connection points.

Comments 1.

This element is not used in the model during any of the solution phases of a problem. It is used to simplify the plotting of structures with large numbers of collinear grid points, where the plotting of each grid point along with the elements connecting them would result in a confusing plot.

2.

Element identification numbers should be unique with respect to all other element identification numbers.

3.

Only one PLOTEL element may be defined on a single entry.

4.

This card is represented as a plot element in HyperMesh.

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OptiStruct 13.0 Reference Guide 1863 Proprietary Information of Altair Engineering

PLOTEL3 Bulk Data Entry PLOTEL3 – Dummy Plot Element Definition Description Defines a three-noded, two-dimensional dummy element for use in plotting. Format (1)

(2)

(3)

(4)

(5)

PLOTEL3

EID

G1

G2

G3

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

PLOTEL3

29

35

16

22

(6)

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) G1, G2, G3

Grid point identification numbers of connection points.

Comments 1.

This element is not used in the model during any of the solution phases of a problem. It is used to simplify the plotting of large structures.

2.

Element identification numbers should be unique with respect to all other element identification numbers.

3.

This card is represented as a tria3 element in HyperMesh.

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PLOTEL4 Bulk Data Entry PLOTEL4 – Dummy Plot Element Definition Description Defines a four-noded, two-dimensional dummy element for use in plotting. Format (1)

(2)

(3)

(4)

(5)

(6)

PLOTEL4

EID

G1

G2

G3

G4

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

PLOTEL4

29

35

16

22

23

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) G1, G2, G3, G4

Grid point identification numbers of connection points.

Comments 1.

This element is not used in the model during any of the solution phases of a problem. It is used to simplify the plotting of large structures.

2.

Element identification numbers should be unique with respect to all other element identification numbers.

3.

This card is represented as a quad4 element in HyperMesh.

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OptiStruct 13.0 Reference Guide 1865 Proprietary Information of Altair Engineering

PLSOLID Bulk Data Entry PLSOLID – Nonlinear Hyperelastic Solid Element Property Description The PLSOLID bulk data entry defines the properties of nonlinear hyperelastic solid elements, referenced by CHEXA, CPENTA, and CTETRA bulk data entries. The MATHE hyperelastic material can be referenced to define corresponding material properties. Format (1)

(2)

(3)

PLSOLID

PID

MID

(4)

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PLSOLID

Field

Contents

PEID

Unique solid element property identification number. No default (Integer > 0)

MID

Identification number of a MATHE bulk data entry. No default (Integer > 0)

Comments 1.

All solid element property entries must have unique identification numbers.

2.

The PLSOLID bulk data entry can be referenced by a CHEXA, CPENTA or CTETRA bulk data entry.

3.

This card is represented as a property in HyperMesh.

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PLY Bulk Data Entry PLY – Ply Information for Ply-based Composite Definition Description Defines the properties of a ply used in ply-based composite definition. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PLY

ID

MID

T

THETA

SOUT

TMANUF

DID

ESID1

ESID2

ESID3

ESID4

ESID5

ESID6

ESID7

ESID9

…

(9)

(10)

ESID8

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

PLY

1

2

0.1

45

YES

0.01

(8)

(9)

(10)

1

Field

Contents

ID

Unique ply identification number. No default (Integer > 0)

MID

Material identification number. Must refer to a MAT1, MAT2 or MAT8 bulk data entry. No default (Integer > 0)

T

Ply thickness. No default (Real > 0.0)

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Field

Contents

THETA

Ply orientation angle, in degrees, of the longitudinal direction relative to the xaxis of the material coordinate system associated with a given element. If no material coordinate system is prescribed for the element, the angle is measured relative to side 1-2 of this element. Default = 0.0 (Real or blank)

SOUT

Stress, Strain, and Failure Index output request. See comments 2 and 3. Default = NO (YES or NO)

TMANUF

Thickness of one manufacturable ply. See comment 4. Default = blank (Real or blank)

DID

Draping identification number. Must refer to a DRAPE bulk data entry. Default = blank (Integer > 0)

ESID#

Element SET identification numbers. Lists the elements for which this PLY card is defined. No continuation line indicates that all elements should be included. Default = blank (Integer > 0)

Comments 1.

The PLY card is used in combination with the PCOMPP and STACK cards to create composite properties through the ply-based definition.

2.

Stress, Strain and Failure Index output for the PLY is activated by setting SOUT to YES. In addition, the I/O Options CSTRESS (controlling Stress and Failure Index output) and/or CSTRAIN (controlling Strain output) must be defined. Failure Index output also requires that the FT and SB fields be defined on the corresponding PCOMPP card, and that stress/ strain allowables on the referenced materials are defined.

3.

An additional piece of information available with ply results is "failure index for the element," which is the maximum of failure indices for individual plies in this element. Note that only the plies with SOUT set to YES are considered in the evaluation of this maximum.

4.

TMANUF defines the thickness of one manufacturable ply. This parameter is used during sizing optimization to automatically create discrete design variables such that the thickness of the ply bundle is equal to a multiple of TMANUF.

5.

This card is represented as a ply in HyperMesh.

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PMASS Bulk Data Entry PMASS – Scalar Mass Property Description Defines the mass value of a scalar mass element (CMASS1 or CMASS3 entry). Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PMASS

PID1

M1

PID2

M2

PID3

M3

PID4

M4

(10)

Example

(1)

(2)

(3)

(4)

(5)

PMASS

7

4.29

6

13.2

Field

Contents

PIDi

Property identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) Mi

Value of scalar mass. (Real)

Comments 1.

Mass values are defined directly on the CMASS2 entry, and therefore do not require a PMASS entry.

2.

Up to four mass values may be defined by this entry.

3.

This card is represented as a property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1869 Proprietary Information of Altair Engineering

PRBODY Bulk Data Entry PRBODY – Rigid Body Definition for Multi-body Simulation Description Defines a rigid body out of a list of finite element properties, elements and grid points. Format (1)

(2)

PRBODY

BID

(3)

(4)

(5)

(6)

(7)

(8)

(9)

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

…

TYPE2

ID1

ID2

…

TYPE#

…

IXY

IXZ

IYZ

C ID

(10)

BODY_NAME

TYPE1

…

MASS

M

INERTIA

IXX

IYY

IZZ

C OG

X,G

Y

Z

Example 1

(1)

(2)

PRBODY

3 PSHELL

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

ARM1 23

21

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(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PBEAM

9

59

48

C ONM2

2345

GRID

400

401

402

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PRBODY

4

11

13

15

22

99

88

130.0

123.0

0.0

0.0

0.0

Example 2

PBAR

LEVER 10

44

MASS

100.0

INERTIA

120.0

C OG

29

Field

Contents

BID

Unique body identification number. No default (Integer > 0)

BODY_NAME

Unique body name. This body name for this PRBODY. Default = OUTFILE_body_ (Character string)

TYPE#

Flag indicating that the following list of IDs refer to entities of this type. All property definitions; CELAS2, CONM2, PLOTEL, RBE2, RBE3, RBAR, RROD, and GRID are valid types for this field.

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OptiStruct 13.0 Reference Guide 1871 Proprietary Information of Altair Engineering

Field

Contents No default (PBAR, PBARL, PBEAM, PBEAML, PBUSH, PCOMP, PCOMPP, PCOMPG, PDAMP, PELAS, PGAP, PROD, PSHEAR, PSHELL, PSOLID, PVISC, PWELD, CELAS2, CONM2, PLOTEL, RBE2, RBE3, RBAR, RROD, GRID)

ID#

Identification numbers of entities of the preceding TYPE flag. No default (Integer > 0)

MASS

Flag to overwrite the finite element mass of the body. Indicates that a mass value is to follow.

M

Mass. (Real > 0.0)

INERTIA

Flag to overwrite the finite element inertia of the body. Indicates that the inertia properties are to follow.

IXX,IYY,IZZ, IXY,IXZ,IYZ

Moments of inertia. (For IXX, IYY, IZZ Real > 0.0; For IXY, IXZ, IYZ Real)

CID

Coordinate system identification number to define the orientation of the inertia tensor. (Integer > 0 or blank)

COG

Flag to overwrite the finite element center of gravity of the body. Indicates that the center of gravity is to follow.

X, Y, Z

Location of the center of gravity. (Real)

G

Grid point identification number to optionally supply X, Y, and Z. (Integer > 0)

Comments 1.

Any number of property definitions; CELAS2, CONM2, PLOTEL, RBAR, RBE2, RBE3 or RROD elements or grid points can be given.

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2.

At least one property definition, element, or grid point must be given.

3.

A property definition; CELAS2, CONM2, PLOTEL, RBE2, RBE3, RBAR or RROD element or grid point can only belong to one rigid or flexible body.

4.

All property definitions, elements and grid points defined on a PRBODY bulk data entry form one rigid body. The mass and inertia properties are defined by the finite element and mass properties unless they are overwritten by the mass and inertia properties given on the continuation lines.

5.

The mass, inertia and center of gravity input is optional if element/property information is provided in the PRBODY definition.

6.

If one of MASS, INERTIA or COG continuations is provided, all three continuations must be provided.

7.

A CID of zero or blank references the basic coordinate system.

8.

MASS must be positive non-zero values.

9.

If just the principal inertia is specified, IXX, IYY, and IZZ must be positive non-zero values and they must satisfy the condition: the sum of two inertia values must be greater than the third (IXX + IYY > IZZ, IYY+IZZ > IXX, IZZ+IXX > IYY).

10. This card is represented as a group in HyperMesh.

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OptiStruct 13.0 Reference Guide 1873 Proprietary Information of Altair Engineering

PRETENS Bulk Data Entry PRETENS – 1D or 3D Bolt Pretension Section Description Defines 1D or 3D pretensioned bolt section. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PRETENS

SID

EID

SURFID

NTYP

G1/X1/ C ID

G2 / X2

G3 / X3

SPNTID

Examples

1D pretensioned bolt: (1)

(2)

(3)

PRETENS

2

5

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

3D pretensioned bolt: (1)

(2)

PRETENS

3

(3)

4

Field

Contents

SID

Unique section identification number.

EID

Element identification number of a bar, beam or rod element for defining 1D pretensioned bolt. (Integer > 0 for 1D pretensioned bolt, or blank for 3D pretensioned bolt)

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Field

Contents

SURFID

Identifier of SURF card which defines cutting section of 3D pretensioned bolt. (Integer > 0 for 3D pretensioned bolt, or blank for 1D pretensioned bolt) See comment 2.

NTYP

Type of determination of normal to the pretension section. See comment 3. AUTO – automatic determination based on the configuration of the pretension section. GRIDS – use G1, G2, G3 to define the plane of pretension – normal to this plane defines the pretension direction. VECTOR – use the vector X1, X2, X3 to define pretension direction. CID – use prescribed coordinate system. Default = blank = AUTO (AUTO, GRIDS, VECTOR, or CID).

G1, G2, G3

Three grid identifiers that define the plane where its normal is the direction of the bolt. Default = blank (Integer > 0). When prescribed, all three nodes must be prescribed.

X1, X2, X3

Coordinates, in basic system, of the vector that defines direction of pretension. Default = blank (Real). The length of the vector must be non-zero.

CID

Identifier of a coordinate system that defines direction of pretension. For rectangular system, the local x-axis defines the pretension direction; For cylindrical and spherical systems, the local z-axis defines the pretension direction. Default = blank (Integer > 0).

SPNTID

SPOINT that defines the DOF containing the pretension deformation and load. Default is not to output the pretension deformation in results files.

Comments 1.

Each 1D pretension section defines only one element.

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OptiStruct 13.0 Reference Guide 1875 Proprietary Information of Altair Engineering

2.

A surface defined by SURFID should be constructed by solid elements on the same side of the surface.

3.

The default direction of pretension is defined automatically from the configuration of the pretension section. For 1D elements, it is along the axis of the respective 1D element. For 3D pretension, it is defined as the average normal to the respective SURFace (average of respective element normals).

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PRETPRM Bulk Data Entry PRETPRM – Parameters for 1D and 3D bolt pretensioning Description Defines parameters that control initial loading conditions on pretension sections for 1D and 3D bolt pretensioning. These parameters also control the printing of diagnostic information about pretension sections. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

PRETPRM

PARAM1

VAL1

PARAM2

VAL2

- etc -

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

PRETPRM

INILOAD

ZEROF

PRTSW

YES

Field

Contents

PARM#

Name of the parameter

VAL#

Value of the parameter

(6)

(7)

(8)

(9)

(10)

The available parameters and their values are listed below (click the parameter name for parameter descriptions).

Parameter

Description

Values

INILOAD

Defines the handling of initial loading conditions on pretension sections that have been defined, but not yet explicitly loaded via PRETENSION command.

"ZEROF” or “ZEROA” Default = “ZEROF”

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OptiStruct 13.0 Reference Guide 1877 Proprietary Information of Altair Engineering

Parameter

Description

Values

PRTSW

Switch for printing diagnostic information about pretension sections.

Default = NO

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PRETPRM, INILOAD Parameter INILOAD

Values

Description

"ZEROF” or “ZEROA” Default = “ZEROF”

Defines the handling of initial loading conditions on pretension sections that have been defined, but not yet explicitly loaded via PRETENSION command. If “ZEROF”, in a pretensioning subcase, for any pretension section without pretension load, zero force will be applied. This is equivalent to prescribing zero PTFORCE. If “ZEROA”, zero relative deformation is enforced on the pretension section defined above. This is equivalent to prescribing zero PTADJST.

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OptiStruct 13.0 Reference Guide 1879 Proprietary Information of Altair Engineering

PRETPRM, PRTSW Parameter PRTSW

Values

Description

Default = NO

Switch for printing diagnostic information about pretension sections. If NO, diagnostic information will not be printed. If YES, diagnostic information will be printed to the .out file.

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PROD Bulk Data Entry PROD – Rod Property Description Defines the properties of a rod, which is referenced by the CROD entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PROD

PID

MID

A

J

C

NSM

(9)

(10)

Example

(1)

(2)

(3)

(4)

PROD

17

23

42.6

(5)

(6)

(7)

(8)

(9)

(10)

0.5

Field

Contents

PID

Unique rod property identification number. No default (Integer > 0)

MID

Material identification number. See comment 1. No default (Integer > 0)

A

Area of rod. No default (Real)

J

Torsional constant. No default (Real)

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Field

Contents

C

Coefficient to determine torsional stress. Default = 0.0 (Real)

NSM

Nonstructural mass per unit length. No default (Real)

Comments 1.

For structural problems, MID may reference only a MAT1 material entry. For heat transfer problems, MID may reference only a MAT4 material entry.

2.

All rod property entries must have unique property identification numbers.

3.

Torsional stress is calculated as follows:

CM J Where,

M

is the torsional moment

C is the coefficient specified in field C J is the torsional constant specified in field J 4.

This card is represented as a property in HyperMesh.

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PSEAM Bulk Data Entry PSEAM – CSEAM Element Property Description Define properties of connector (CSEAM) elements. Format (1)

(2)

(3)

(4)

(5)

(6)

PSEAM

PID

MID

TYPE

W

T

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

PSEAM

30

2

LINE

0.8

Field

Contents

PID

Property identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) MID

Material identification number of a MAT1 or MAT9 entry. See comment 1. No default (Integer > 0)

TYPE

Type of seam weld generated. Default = LINE (Character)

W

Width of the seam weld. See comment 2. No default (Real > 0)

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OptiStruct 13.0 Reference Guide 1883 Proprietary Information of Altair Engineering

Field

Contents

T

Thickness of the seam weld. See comment 3. No default (Real > 0)

Comments 1.

Material MID is used to calculate the stiffness of the connector (the fictitious CHEXA). MID can only refer to the MAT1 or MAT9 bulk data entry.

2.

The distance between GS and GE is the length of the element. The width of the seam weld is measured perpendicular to the length and lies in the plane of Shell A or B. See figure below.

3.

If the entry of T is left blank, the thickness of this seam weld will be calculated as the averaged thickness of Shell A and B.

4.

This card is represented as a property in HyperMesh.

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PSEC Bulk Data Entry PSEC – Section Property Definition Description Defines property information for planar section elements used in the definition of arbitrary beam cross-sections. Format (1)

(2)

(3)

(4)

PSEC

PID

MID

T

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

PSEC

5

100

0.1

(5)

Field

Contents

PID

Property identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) MID

Identification number of a material definition. No default (Integer > 0)

T

Thickness. No default (Real > 0.0)

Comments 1.

All property identification numbers within a section definition must be unique with respect to all other property identification numbers within the same section definition.

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OptiStruct 13.0 Reference Guide 1885 Proprietary Information of Altair Engineering

2.

This entry is only valid when it appears between the BEGIN and END statements.

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PSHEAR Bulk Data Entry PSHEAR – Shear Panel Property Description Defines the properties of a shear panel. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

PSHEAR

PID

MID

T

NSM

F1

F2

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

PSHEAR

21

2

.001

(5)

(6)

Field

Contents

PID

Unique shear property identification number.

(7)

(8)

(9)

(10)

(Integer > 0) MID

Material identification number of a MAT1 entry. (Integer > 0)

T

Thickness of shear panel.

NSM

Nonstructural mass per unit area. (Real)

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OptiStruct 13.0 Reference Guide 1887 Proprietary Information of Altair Engineering

Field

Contents

F1

Effectiveness factor for extensional stiffness along edges 1-2 and 3-4. See comment 2. Default = 0.0 (Real > 0.0)

F2

Effectiveness factor for extensional stiffness along edges 2-3 and 1-4. See comment 2. Default = 0.0 (Real > 0.0)

Comments 1.

The effective extensional area is defined by means of equivalent rods on the perimeter of the element. If F1 < 1.01, the areas of the rods on edges 1-2 and 3-4 are set equal to (F1 ×× T ×× PA)/(L12 + L34), where PA is the panel surface areas - half the vector cross product area of the diagonals - and L12 and L34 are the lengths of sides 1-2 and 34. Thus, if F1 = 1.0, the panel is fully effective for extension in the 1-2 direction. If F1 > 1.01, the areas of the rods on edges 1-2 and 3-4 are each set equal to 0.5 ×× F1 ×× T.

Extensional Area for Shear Panel

Thus, if F1 = 30, the effective width of skin contributed by the panel to the flanges on edges 1-2 and 3-4 is equal to 15T. The significance of F2 for edges 2-3 and 1-4 is similar. 2.

Poisson's ratio coupling for extensional effects is ignored.

3.

This card is represented as a property in HyperMesh.

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PSHELL Bulk Data Entry PSHELL – Shell Element Property Description Defines the membrane, bending, transverse shear, and membrane-bending coupling of shell elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PSHELL

PID

MID1

T

MID2

12I/T3

MID3

TS/T

NSM

Z1

Z2

MID4

T0

ZOFFS

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PSHELL

203

204

1.90

205

1.2

206

0.8

6.32

+.95

-.95

(10)

0.1

Field

Contents

PID

Unique shell element property identification number. (Integer > 0)

MID1

Material identification number for membrane. See comment 3. (Integer > 0)

T

Default value for the membrane thickness (Real > 0.0). If T0 is defined for topology optimization, T is the total thickness.

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OptiStruct 13.0 Reference Guide 1889 Proprietary Information of Altair Engineering

Field

Contents

MID2

Material identification number for bending. See comment 3. (Integer > -1 or blank)

12I/T3

Bending stiffness parameter. Default = 1.0 (Real > 0.0 or blank)

MID3

Material identification number for transverse shear. See comment 3. (Integer > 0 or blank, must be blank unless MID2 > 0)

TS/T

Transverse shear thickness divided by the membrane thickness. Default = .833333 (Real > 0.0 or blank)

NSM

Nonstructural mass per unit area. (Real)

Z1,Z2

Fiber distances for stress computation. The positive direction is determined by the right hand rule and the order in which the grid points are listed on the connection entry. (Real or blank, See comment 7 for defaults)

MID4

Material identification number for membrane-bending coupling. (Integer > 0 or blank, must be blank unless MID1>0 and MID2>0, may not be equal to MID1 or MID2). See comments 10 and 11.

T0

The base thickness of the elements in topology optimization. Only for MAT1, T0 can be >0.0. If T0 is blank, then the elements are not included in the topology design volume or space. (Real > 0.0 or blank for MAT1, Real = 0.0 or blank for MAT2, MAT8)

ZOFFS

Offset from the plane defined by element grid points to the shell reference plane. Real or Character Input (Top/Bottom). See comment 15.

Comments 1.

All shell element property entries must have unique identification numbers.

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2.

The structural mass is computed from the density using the membrane thickness and membrane material properties.

3.

MID1 cannot be left blank. The effect of leaving an MID2 or MID3 field blank is: MID2 (If left blank)

Pure membrane in plane stress – no bending, coupling, or transverse shear stiffness. MID3 and MID4 must also be blank.

MID3 (If left blank)

No transverse shear deformation is considered (this is actually accomplished by enforcing very high transverse shear stiffness).

If MID2 = -1

Plane strain. In-plane stiffness only. No bending or transverse shear stiffness. See comments 13 and 14.

4.

The continuation is not required.

5.

This entry is used in connection with the CTRIA3, CQUAD4, CTRIA6, and CQUAD8 entries.

6.

PSHELL entries may reference MAT1, MAT2, MAT4, MAT5, and MAT8 material property entries.

7.

The default for Z1 is -T/2, and for Z2 it is +T/2. T is the local plate thickness, defined by T on this entry. For free-sizing optimization, Z1 and Z2 definitions are ignored and the defaults of –T/2 and +T/2 are used for each element.

8.

If MID3 references a MAT2 material, then G33 on the MAT2 data must be blank.

9.

If MID3 references a MAT8 material, then G1Z and G2Z must not be blank.

10. MID4 provides a way to represent shells with offset (shell element centerline being offset from the plane of the grid points) or shells with material properties that are not symmetric with respect to the middle surface of the shell. However, whenever possible, the preferred method of representing such shells is through the use of element offset ZOFFS or the composite property PCOMP. This is because MID4 does not provide sufficient information about the shell structure to correctly calculate all respective results, specifically: The shell stresses calculated in the presence of MID4 are generally incorrect, as they do not reflect the actual shell offset or the non-uniform material structure. The effects of MID4 are not considered in the calculation of differential stiffness. Hence, it is recommended that MID4 be left blank in buckling analysis. 11. If MID4 points to a MAT2 card with a material ID greater than 400,000,000, then the thermal membrane-bending coefficients A1, A2, and A12 have a modified interpretation, and represent [G]*[alpha] rather then [alpha]. Here, [G] is a matrix composed of G11, G22,…G33. This is to maintain consistency with respective terms generated internally by the PCOMP card. 12. Thermal expansion coefficients provided for materials referenced as MID2 or MID3 are ignored in shell analysis - only the thermal expansion terms for materials referenced as MID1 (membrane) and MID4 (coupling) are considered. Furthermore, the reference temperature (TREF) for the shell property is taken from the material referenced as MID1 TREF's provided for other MID's are ignored.

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OptiStruct 13.0 Reference Guide 1891 Proprietary Information of Altair Engineering

13. Plane strain (MID2=-1) MID1 must reference a MAT1 entry. 14. In plane strain computations, in-plane loads are interpreted as line loads with a value equal to the load, divided by the thickness. Thus, if a thickness of "1.0" is used, the value of the line-load equals the load value. Pressure can be approximated with multiple line loads where the pressure value equals the line-load, divided by the length between the loads. 15. The shell reference plane can be offset from the plane defined by the element nodes by means of ZOFFS. In this case all other information, such as material matrices or fiber locations for the calculation of stresses, is given relative to the offset reference plane. Shell results, such as shell element forces, are output on the offset reference plane. ZOFFS can be used in all types of analysis and optimization. ZOFFS can be input in two different formats: 1. Real: A positive or a negative value of ZOFFS is specified in this format. A positive value of ZOFFS implies that the reference plane of each shell element is offset a distance of ZOFFS along the positive z-axis of its element coordinate system. 2. Surface: This format allows you to select either “Top” or “Bottom” option to specify the offset value. Top: The top surface of the shell element and the plane defined by the element nodes are coplanar. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL element. (The sign of the ZOFFS value would depend on the direction of the offset with respect to the positive z-axis of the element coordinate system, as defined in the Real section). See Figure 1.

Figure 1: Top option in ZOFFS

Bottom: The bottom surface of the shell element and the plane defined by the element nodes are coplanar. This makes the effective "Real" ZOFFS value equal to half of the thickness of the PSHELL element. (The sign of the ZOFFS value would depend on the direction of the offset with

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respect to the positive z-axis of the element coordinate system, as defined in the Real section). See Figure 2.

Figure 2: Bottom option in ZOFFS

When ZOFFS is used, both MID1 and MID2 must be specified; otherwise singular matrices would result. Moreover, while offset is correctly applied in geometric stiffness matrix and thus can be used in linear buckling analysis, caution is advised in interpreting the results. Without offset, a typical simple structure will bifurcate and loose stability “instantly” at the critical load, shown in Figure (a). With offset though, the loss of stability is gradual and asymptotically reaches a limit load, as shown below in Figure (b).

Thus, the structure with offset can reach excessive deformation before the limit load is reached. Note that the above illustrations apply to linear buckling – in a fully nonlinear limit load simulation, additional instability points may be present on the load path. 16. This card is represented as a property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1893 Proprietary Information of Altair Engineering

PSHELLX Bulk Data Entry PSHELLX – Optional SHELL Property Extension for Geometric Nonlinear Analysis Description Defines additional SHELL properties for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PSHELLX

PID

ISHELL

ISH3N

ISMSTR

NIP

HM

HF

HR

DM

DN

ITHIC K

IPLAS

(10)

Example

(1)

(2)

(3)

(4)

(5)

PSHELL

73

7

1.0

7

PSHELLX

73

24

(6)

(7)

(8)

(9)

(10)

7

5

Field

Contents

PID

Property ID of the associated PSHELL. See comment 1. No default (Integer > 0)

ISHELL

Flag for CQUAD4 element formulation. Default as defined by XSHLPRM (Integer) 1 - Q4, visco-elastic hourglass modes orthogonal to deformation and rigid modes (Belytschko). 2 - Q4, visco-elastic hourglass without orthogonality (Hallquist).

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Field

Contents 3 - Q4, elastic-plastic hourglass with orthogonality. 4 - Q4 with improved type 1 formulation (orthogonalization for warped elements). 12 - QBAT or DKT18 shell formulation. 24 - QEPH shell formulation.

ISH3N

Flag for CTRIA3 element formulation. Default as defined by XSHLPRM (Integer) 1 - Standard triangle (C0). 2 - Standard triangle (C0) with modification for large rotation. 30 - DKT18. 31 - DKT_S3.

ISMSTR

Flag for shell small strain formulation. Default as defined by XSHLPRM (Integer) 1 - Small strain from time = 0. 2 - Full geometric non-linearity with optional small strain formulation activation by time step XSTEP, TYPEi = SHELL, TSCi = CST. 3 - Alternative small strain formulation from time = 0 (ISHELL =2 only). 4 - Full geometric non-linearity (Time step limit has no effect).

NIP

Number of integration points through the thickness. NIP = 0 defines global integration. Default as defined by XSHLPRM (0 < Integer < 10)

HM

Shell membrane hourglass coefficient (ISHELL = 1, 2, 3, and 4 only). Default = 0.01 (Real, 0.0 < HM < 0.05) Except ISHELL = 3: Default = 0.1 (Real)

HF

Shell out of plane hourglass coefficient (ISHELL = 1, 2, 3, and 4 only). Default = 0.01 (0.0 < Real < 0.05)

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Field

Contents

HR

Shell rotation hourglass coefficient (ISHELL = 1, 2, 3, and 4 only). Default = 0.01 (0.0 < Real < 0.05) Except ISHELL = 3: Default = 0.1 (Real)

DM

Shell membrane damping (with MATX27 and MATX36 only). Default: See comment 11 (Real)

DN

Shell numerical damping (ISHELL = 12, 24, ISH3N = 30 only) Default: See comment 12 (Real)

ITHICK

Flag for shell resultant stresses calculation. Default as defined by XSHLPRM (CONST or VAR) CONST - Thickness is constant. VAR - Thickness change is taken into account.

IPLAS

Flag for shell plane stress plasticity (with MATX2, MATX27, and MATX36 only). Default as defined by XSHLPRM (RAD or NEWT) RAD - Radial return. NEWT - Iterative projection with 3 Newton iterations.

Comments 1.

The property identification number must be that of an existing PSHELL bulk data entry. Only one PSHELLX property extension can be associated with a particular PSHELL.

2.

PSHELLX is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

Q4: Original 4 node OptiStruct shell with hourglass perturbation stabilization. QEPH: Formulation with physical hourglass stabilization for general use. QBAT: Modified BATOZ Q4g 24 shell with 4 Gauss integration points and reduced integration for in-plane shear. No hourglass control is needed for this shell. DKT18: BATOZ DKT18 thin shell with 3 Hammer integration points.

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4.

If the small strain option (ISMSTR) is set to 1 or 3, engineering strain and stress are used; otherwise they are true strain and stress.

5.

ISHELL = 2 is incompatible with NIP = 1.

6.

Global integration (NIP = 0) is only compatible with MAT1, MATS1, MATX2, and MATX36.

7.

For MAT1, membrane only behavior happens if NIP = 1. Otherwise, NIP is ignored and global integration (NIP = 0) is used.

8.

For ITHICK = VAR it is recommended to use IPLAS = NEWT.

9.

If ITHICK = VAR or IPLAS = NEWT, the small strain option is automatically deactivated.

10. For MATX2, the default value for IPLAS and global integration (NIP=0) is IPLAS = RAD. 11. For MATS1, MATX36 the default value for IPLAS and global integration (NIP=0) is IPLAS = NEWT. 12. Defaults for DM: Material

Element type

ISHELL/ISH3N Default

MATX27

except QEPH, QBAT

except 12, 24

5%

QEPH

24

1.5%

QBAT

12

0%

except QEPH

except 24

0%

QEPH

24

1.5%

MATX36

13. Defaults for DN: Element type ISHELL/ISH3N

Default

Usage

QBAT

12

0.1%

All stress terms, except transverse shear.

QEPH

24

1.5%

Hourglass stress.

DKT18

12/30

0.01%

Membrane stress only.

14. This card is represented as an extension to a PSHELL property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1897 Proprietary Information of Altair Engineering

PSLDX6 Bulk Data Entry PSLDX6 – Optional SOLID Property Extension for Geometric Nonlinear Analysis Description Defines additional orthotropic SOLID properties for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PSLDX6

PID

ISOLID

NIP

ISMSTR

IC PRE

IFRAME

DN

QS

QB

HV

DTMIN

C ID

IP

IORTH

Vx

Vy

Vz

THETA

(10)

Example

(1)

(2)

(3)

PSOLID

77

7

PSLDX6

77

24

(4)

(5)

(6)

(7)

(8)

Field

Contents

PID

Property ID of the associated PSOLID. See comment 1.

(9)

(10)

No default (Integer > 0) ISOLID

Flag for solid elements formulation. Default as defined by XSOLPRM (Integer) 1 - Standard 8-node solid element, 1 integration point. Viscous hourglass formulation with orthogonal and rigid deformation modes compensation (Belytschko). 2 - Standard 8-node solid element, 1 integration point. Viscous

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Field

Contents hourglass formulation without orthogonality (Hallquist). 12 - Standard 8-node solid, full integration (no hourglass). 14 - HA8 locking-free 8-node solid element, co-rotational, full integration, variable number of Gauss points. 17 - H8C compatible solid full integration formulation. 24 - HEPH 8-node solid element. Co-rotational, under-integrated (1 Gauss point) with physical stabilization.

NIP

Number of integration points (ISOLID = 14 and 16 only). Default as defined by XSOLPRM (Integer = ijk) 2 < i, j, k < 9 < 3, 2 < j < 9

for ISOLID =14 for ISOLID =16

where: i = Number of integration points in local x direction. j = Number of integration points in local y direction. k = Number of integration points in local z direction. ISMSTR

Flag for small strain formulation (ISOLID = 1, 2, 14, and 24 only). Default as defined by XSOLPRM (Integer) 1 - Small strain from time = 0. 2 - Full geometric non-linearity with small strain formulation activation by time step. 3 - Simplified small strain formulation from time=0 (non-objective formulation). 4 - Full geometric non-linearity. Time step limit has no effect. 10 - Lagrange type total strain.

ICPRE

Flag for reduced pressure integration (ISOLID = 14 and 24 only). Default = OFF (ON, OFF, or VAR) VAR - Variable state between ICPRE = ON and ICPRE = OFF in function of plasticity state.

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Field

Contents

IFRAME

Flag for element coordinate system formulation (ISOLID = 1, 2, 12, and 17 only). Default as defined by XSOLPRM (ON or OFF)

DN

Numerical damping for stabilization (ISOLID =24 only). Default = 0.1 (Real)

QS

Quadratic bulk viscosity. Default = 1.1 (Real)

QB

Linear bulk viscosity. Default = 0.05 (Real)

HV

Hourglass viscosity coefficient. Default = 0.1 (0.0 < Real < 0.15)

DTMIN

Minimum time step. Default = 0.0 (Real)

CID

Coordinate system identification number to define orthotropic directions. (Integer > 0)

IP

Reference plane. Default = 0 (Integer) 0 - Use CID (CID must be different from 0) 1 - Plane (r,s) and angle THETA 2 - Plane (s,t) and angle THETA 3 - Plane (t,r) and angle THETA 11 - Plane (r,s) and orthogonal projection of reference vector (Vx, Vy, and Vz) on plane (r,s) 12 - Plane (s,t) and orthogonal projection of reference vector (Vx,

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Field

Contents Vy, and Vz) on plane (s,t) 13 - Plane (t,r) and orthogonal projection of reference vector (Vx, Vy, and Vz) on plane (t,r)

IORTH

Flag for orthotropic system formulation. (Integer = 0, 1) 0 - The first axis of orthotropy is maintained at constant angle with respect to the orthonormal co-rotational element coordinate system. 1 - The first orthotropy direction is constant with respect to a nonorthonormal isoparametric coordinates.

Vx

X component for reference vector. (Real)

Vy

Y component for reference vector. (Real)

Vz

Z component for reference vector. (Real)

THETA

Orientation angle in degrees of orthotropic with first reference plane direction. Default = 0.0 (Real)

Comments 1.

The property identification number must be that of an existing PSOLID bulk data entry. Only one PSLDX6 property extension can be associated with a particular PSOLID.

2.

PSLDX6 is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

PSLDX6 is only compatible with 8-node linear solid elements. Quadratic 20-node brick and 6-node pentahedron elements are not compatible, these element types should only be used with PSOLIDX.

4.

The ISOLID flag is not used with CTETRA elements. For elements with 4 and 10 nodes, the number of integration points is fixed at 1 and 4, respectively.

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OptiStruct 13.0 Reference Guide 1901 Proprietary Information of Altair Engineering

5.

For fully-integrated solids (SOLID =12), the deviatoric behavior is computed using 8 Gauss points; bulk behavior is under-integrated to avoid element locking. It is currently compatible with material MAT1, MATS1, MATX33, and MATX36.

6.

With the small strain option (ISMSTR), strain and stress is engineering strain and stress. Otherwise, it is true strain and stress.

7.

In time history and animation files, the stress tensor is written in the co-rotational frame.

8.

Fully-integrated elements (ISOLID =12) only use full geometric non-linearity (corresponds to ISMSTR = 4). Time step limit has no effect.

9.

ISMSTR =10 is only compatible with materials using total strain formulation (MATX42).

10. The time step control XSTEP, TYPEi = SOLID, TSCi = CST only works on elements with ISMSTR =2. 11. Co-rotational formulation: For ISOLID = 1, 2, 12 and IFRAME = ON, the stress tensor is computed in a co-rotational coordinate system. This formulation is more accurate if large rotations are involved. It comes at the expense of higher computation cost. It is recommended in case of elastic or visco-elastic problems with important shear deformations. The co-rotational formulation is compatible with 8 node solids. 12. For HA8 (ISOLID = 14) elements: this element uses a locking-free general solid formulation, co-rotational. The number of Gauss points is defined by NIP flag: for example, combined with NIP = 222 gives an 8 Gauss integration point element, similar to ISOLID = 12. The HA8 formulation is compatible with all material laws. Under-integration for pressure should be used (ICPRE = ON in case of elastic or visco-elastic material; ICPRE = VAR in case of elasto-plastic material). 13. For H8C (SOLID = 17) elements: Their brick deviatoric behavior is the same as ISOLID = 12, but the bulk behavior can be chosen with ICPRE, and is compatible with all solid type material laws. ICPRE = VAR is the default value and ICPRE = OFF will not reduce pressure integration. 14. For HEPH (ISOLID = 24) elements: This element uses an hourglass formulation similar to QEPH shell elements. 15. ICPRE = VAR is only available for elasto-plastic material law. 16. The hourglass formulation is viscous for ISOLID = 0, 1, and 2. 17. Hourglass viscosity coefficient, HV is not active with 8 point integration. 18. This card is represented as an extension to a PSOLID property in HyperMesh.

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PSOLID Bulk Data Entry PSOLID – Solid Element Property Description Defines the properties of solid elements, referenced by CHEXA, CPENTA, CPYRA and CTETRA bulk data entries. Format (1)

(2)

(3)

(4)

(5)

PSOLID

PID

MID

C ORDM

(6)

(7)

(8)

(9)

ISOP

FC TN

DS

(10)

Example

(1)

(2)

(3)

PSOLID

2

100

(4)

(5)

(6)

(7)

(8)

(9)

(10)

1

Field

Contents

PID

Unique solid element property identification number. No default (Integer > 0)

MID

Identification number of a MAT1, MAT4, MAT5, MAT9, MAT10 or MATPE1 bulk data entry. No default (Integer > 0)

CORDM

MID of material coordinate system. The default is 0, which is the basic coordinate system. Default = 0 (Integer > -1)

ISOP

Special integration schemes for elasto-plastic nonlinear quasi-static analysis. The values available are:

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OptiStruct 13.0 Reference Guide 1903 Proprietary Information of Altair Engineering

Field

Contents FULL – full integration, using the same integration schemes as for linear applications. MODPLAST – (default) uses special handling of pressure approximation, designed to circumvent the volumetric locking due to incompressibility of plastic flow. The specific details differ depending on the type and order of the element. REDPLAST – besides special handling for pressure approximation, uses reduced integration for second-order hexa and penta, and for 8noded hexa elements (reduced integration is not practically viable in other element types, since it would create extensive spurious modes). See comments 2 and 3. (Character: FULL, MODPLAST, REDPLAST or blank)

FCTN

Fluid element flag. SMECH indicates a structural element; PFLUID indicates a fluid element. PORO indicates poro-elastic material. Default = SMECH (SMECH, PFLUID or PORO)

DS

Design switch. If non-zero, the elements associated with this PSOLID data are included in the topology design volume or space. Not valid for fluid elements. Default = blank (Integer or blank)

Comments 1.

All solid element property entries must have unique ID numbers.

2.

Special integration flags MODPAST and REDPLAST affect only elasto-plastic materials (as identified by presence of MATS1) in nonlinear quasi-static subcases. They do not affect element behavior in linear analysis.

3.

The FULL option in the ISOP field provides stable and convergent results, although it may appear “stiff” and converge rather slowly in cases of significant plastic deformation. MODPLAST uses special handling for volumetric pressure term, in effect providing good resolution of plastic flow while avoiding excessive flexibility that would lead to spurious modes. REDPLAST adds further release of locking tendencies and usually the “softest” behavior. It may, theoretically, exhibit spurious deformation modes in single unattached elements, although in practice these modes should vanish in fields of many elements.

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4.

If FCTN = 'PFLUID', then the MID must reference a MAT10 entry. If FCTM=PORO, then MID must reference a poro-elastic material entry.

5.

Stresses are calculated in the material coordinate system. The material coordinate system may be defined as the basic coordinate system (CORDM = 0), a defined system (CORDM = Integer > 0), or the element coordinate system (CORDM = -1). Refer to the CHEXA, CPENTA, CPYRA and CTETRA pages of the Reference Guide for details on how the material coordinate system is defined for each element.

6.

If the material referenced by MID is a MAT9 material definition, then CORDM defines the material coordinate system for Gij on the MAT9 entry.

7.

This card is represented as a property in HyperMesh.

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OptiStruct 13.0 Reference Guide 1905 Proprietary Information of Altair Engineering

PSOLIDX Bulk Data Entry PSOLID – Optional SOLID Property Extension for Geometric Nonlinear Analysis Description Defines additional SOLID properties for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PSOLIDX

PID

ISOLID

NIP

ISMSTR

IC PRE

IFRAME

DN

QS

QB

HV

DTMIN

LAMBDAV

MUV

IHKT

(10)

Example

(1)

(2)

(3)

PSOLID

77

7

PSOLIDX

77

24

(4)

(5)

(6)

(7)

(8)

Field

Contents

PID

Property ID of the associated PSOLID. See comment 1.

(9)

(10)

No default (Integer > 0) ISOLID

Flag for solid elements formulation. Default as defined by XSOLPRM (Integer) 1 - Standard 8-node solid element, 1 integration point. Viscous hourglass formulation with orthogonal and rigid deformation modes compensation (Belytschko). 2 - Standard 8-node solid element, 1 integration point. Viscous

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Field

Contents hourglass formulation without orthogonality (Hallquist). 12 - Standard 8-node solid, full integration (no hourglass). 14 - HA8 locking-free 8-node solid element, co-rotational, full integration, variable number of Gauss points. 16 - Quadratic 20-node solid, full integration, variable number of Gauss points. 17 - H8C compatible solid full integration formulation. 24 - HEPH 8-node solid element. Co-rotational, under-integrated (1 Gauss point) with physical stabilization.

NIP

Number of integration points (ISOLID = 14, 16 only). Default as defined by XSOLPRM (Integer = ijk) 2 < i, j, k < 9 < 3, 2 < j < 9

for ISOLID =14 for ISOLID =16

where: i = Number of integration points in local x direction. j = Number of integration points in local y direction. k = Number of integration points in local z direction. ISMSTR

Flag for small strain formulation (ISOLID = 1, 2, 14, and 24 only). Default as defined by XSOLPRM (Integer) 1 - Small strain from time = 0. 2 - Full geometric non-linearity with small strain formulation activation by time step. 3 - Simplified small strain formulation from time=0 (non-objective formulation). 4 - Full geometric non-linearity. Time step limit has no effect. 10 - Lagrange type total strain.

ICPRE

Flag for reduced pressure integration (ISOLID = 14, 17, and 24 only). Default = OFF for ISOLID = 14, 24, ON for ISOLID = 17 (ON, OFF, or VAR)

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Field

Contents VAR - Variable state between ICPRE = ON and ICPRE = OFF in function of plasticity state.

IFRAME

Flag for element coordinate system formulation (ISOLID = 1, 2, 12, 17 only). Default as defined by XSOLPRM (ON or OFF)

DN

Numerical damping for stabilization (ISOLID =24 only). Default = 0.1 (Real)

QS

Quadratic bulk viscosity. Default = 1.1 (Real)

QB

Linear bulk viscosity. Default = 0.05 (Real)

HV

Hourglass viscosity coefficient. Default = 0.1 (0.0 < Real < 0.15)

DTMIN

Minimum time step. Default = 0.0 (Real)

LAMBDAV

Numerical Navier Stokes viscosity No default (Real)

MUV

Numerical Navier Stokes viscosity No default (Real)

IHKT

Hourglass tangent modulus flag (ISOLID = 24 only) Default = 1 (Integer = 1, 2) 1 - Elastic modulus or numerical tangent modulus estimation. 2 - Advanced tangent modulus estimation.

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Comments 1.

The property identification number must be that of an existing PSOLID bulk data entry. Only one PSOLIDX property extension can be associated with a particular PSOLID.

2.

PSOLIDX is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

The ISOLID flag is not used with CTETRA elements. For these elements with four and ten nodes, the number of integration points is fixed at one and four, respectively.

4.

For fully integrated solids (SOLID =12), the deviatoric behavior is computed using 8 Gauss points; bulk behavior is under-integrated to avoid element locking. It is currently compatible with material MAT1, MATS1, MATX33, and MATX36.

5.

With the small strain option (ISMSTR), strain and stress is engineering strain and stress. Otherwise, it is true strain and stress.

6.

In time history and animation files, the stress tensor is written in the co-rotational frame.

7.

Fully integrated elements (ISOLID =12) only uses full geometric non-linearity (corresponds to ISMSTR = 4). Time step limit has no effect.

8.

ISMSTR = 10 is only compatible with materials using total strain formulation (MATX42).

9.

The time step control XSTEP, TYPEi = SOLID, TSCi = CST only works on elements with ISMSTR = 2.

10. Co-rotational formulation: For ISOLID = 1, 2, 12 and IFRAME = ON, the stress tensor is computed in a co-rotational coordinate system. This formulation is more accurate if large rotations are involved. It comes at the expense of higher computation cost. It is recommended in case of elastic or visco-elastic problems with important shear deformations. The co-rotational formulation is compatible with 8 node solids. 11. HA8 (ISOLID = 14) elements: this element uses a locking-free general solid formulation, co-rotational. The number of Gauss points is defined by NIP flag: for example, combined with NIP = 222 gives an 8 Gauss integration point element, similar to ISOLID = 12. The HA8 formulation is compatible with all material laws. Under-integration for pressure should be used (ICPRE = ON in case of elastic or visco-elastic material; ICPRE = VAR in case of elasto-plastic material). 12. H8C (SOLID = 17) elements: Their brick deviatoric behavior is the same as ISOLID = 12, but the bulk behavior can be chosen with ICPRE, and is compatible with all solid type material laws. ICPRE = VAR is the default value and ICPRE = OFF will not reduce pressure integration. 13. HEPH (ISOLID = 24) elements: This element uses an hourglass formulation similar to QEPH shell elements. 14. ICPRE = VAR is only available for elasto-plastic material law. 15. The hourglass formulation is viscous for ISOLID = 0, 1, and 2. 16. Hourglass viscosity coefficient HV is not active with 8 point integration.

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OptiStruct 13.0 Reference Guide 1909 Proprietary Information of Altair Engineering

17. It is recommended to use IHKT=2 (ISOLID=24) and Lagrange type total strain, ISMSTR=10 for foam or rubber materials, like MATX42 and MATX82. For elasto-plastic type material, IHKT=2 will have a tighter yield stress criterion for an hourglass stress computation. 18. This card is represented as an extension to a PSOLID property in HyperMesh.

1910 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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PTADD Bulk Data Entry PTADD – Pretension Load Combination (Superposition) Description Defines a pretension load as a linear combination of load sets defined via PTFORCE, PTFORC1, PTADJST and PTADJS1 entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PTADD

PSID

S

S1

L1

S2

L2

S3

L3

S4

L4

(10)

-etc-

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

PTADD

6

2.0

3.0

2

2.0

3

Field

Contents

PSID

Pretensioning load set identification number.

S

Scale factor. (See comment 1)

(8)

(9)

(10)

No default (Real) Si

Scale factor. (See comment 1) No default (Real)

Li

Pretension load set identification number defined via entry types enumerated above. (See comment 1) No default (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1911 Proprietary Information of Altair Engineering

Comments 1. The pretension load as a linear combination is defined by:

Where, S and Si are the scale factors. Li is the pretension load set defined via PTFORCE, PTFORC1, PTADJST andPTADJS1 entries.

1912 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PTADJS1 Bulk Data Entry PTADJS1 – Pretension Adjustment Definition, Alternate Form Description Defines adjustment (additional shortening) on a set of pretension sections. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

PTADJS1

PSID

ADJ

SID1

SID2

SID3

SID4

SID5

SID6

SID7

SID8

SID9

-etc-

Example

(1)

(2)

(3)

(4)

(5)

(6)

PTADJS1

3

0.05

1

3

4

(7)

Field

Contents

PSID

Pretensioning load set identification number.

(8)

(9)

(10)

(Integer > 0) ADJ

Adjustment applied on this section (positive value means shortening). See comment 2. (Real)

SIDi

Pretension section identification number. (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1913 Proprietary Information of Altair Engineering

Comments 1.

PTADJS1 can be referred by PTADD or by the PRETENSION command in the subcase directly.

2.

Pretensioning adjustment shortens the pretensioned bolt by “removing” the prescribed amount of material. This represents the effect of turning the nut by a prescribed distance (number of turns).

3.

Pretensioning adjustment is an additional shortening applied to a pretension section. This means that, when adjustment is applied to a section that has already been pretensioned, the final effect will be a sum of the status reached in the preceding pretensioning subcase plus the amount of ADJ.

1914 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PTADJST Bulk Data Entry PTADJST – Pretensioning Adjustment Description PTADJST defines the adjustment (shortening) on a pretension section. Format (1)

(2)

(3)

(4)

(5)

PTADJST

PSID

SID

ADJ

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

PTADJST

3

5

0.5

(5)

(6)

(7)

Field

Contents

PSID

Pretensioning load set identification number.

(8)

(9)

(10)

(Integer > 0) SID

Pretension section identification number. (Integer > 0)

ADJ

Adjustment applied on this section (positive value means shortening). See comment 2. (Real)

Comments 1.

PTADJST can be referred by PTADD or by the PRETENSION command in the subcase directly.

Altair Engineering

OptiStruct 13.0 Reference Guide 1915 Proprietary Information of Altair Engineering

2.

Pretensioning adjustment shortens the pretensioned bolt by “removing” the prescribed amount of material. This represents the effect of turning the nut by a prescribed distance (number of turns).

3.

Pretensioning adjustment using PTADJST can also be used to define additional shortening to a pretensioned section. Therefore, when adjustment is applied to a section that has already been pretensioned, the final effect will be a sum of the status reached in the preceding pretensioning subcase plus the amount of adjustment through PTADJST.

1916 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PTFORCE Bulk Data Entry PTFORCE – Pretensioning Force Description Defines pretensioning force on pretension section. Format (1)

(2)

(3)

(4)

PTFORC E

PSID

SID

F

(5)

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

PTFORC E

3

5

0.5

(5)

(6)

(7)

Field

Contents

PSID

Pretensioning load set identification number.

(8)

(9)

(10)

(Integer > 0) SID

Pretension section identification number. (Integer > 0)

F

Pretensioning force applied on this section. (Positive value creates tension). See comment 2. (Real)

Comments 1.

PTFORCE can be referred by PTADD or by the PRETENSION command in the subcase directly.

Altair Engineering

OptiStruct 13.0 Reference Guide 1917 Proprietary Information of Altair Engineering

2.

Pretensioning force is actually a pair of forces, applied to the opposite sides of the pretension section. This represents the effect of tightening the nut by a prescribed longitudinal force (which is related to the applied torque).

1918 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PTFORC1 Bulk Data Entry PTFORC1 – Pretensioning Force Definition, Alternate Form Description Defines pretensioning force on a set of pretension sections. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

PTFORC 1

PSID

F

SID1

SID2

SID3

SID4

SID5

SID6

SID7

SID8

SID9

-etc-

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

PTFORC 1

3

500.0

1

3

4

(7)

Field

Contents

PSID

Pretensioning load set identification number.

(8)

(9)

(10)

(Integer > 0) F

Pretensioning force applied on this set of sections. (Positive value creates tension). See comment 2. (Real)

SIDi

Pretension section identification number. (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1919 Proprietary Information of Altair Engineering

Comments 1. PTFORC1 can be referred by PTADD or by the PRETENSION command in the subcase directly. 2. Pretensioning force is actually a pair of forces, applied to the opposite sides of the pretension section. This represents the effect of tightening the nut by a prescribed longitudinal force (which is related to the applied torque).

1920 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PTUBE Bulk Data Entry PTUBE – Tube Property Description PTUBE defines the properties of a thin-walled cylindrical tube element, referenced by a CTUBE entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

PTUBE

PID

MID

OD

T

NSM

OD2

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

PTUBE

2

6

6.29

0.25

Field

Contents

PID

Unique identification number.

(6)

(7)

(8)

(9)

(10)

(Integer > 0) MID

Material identification number. (Integer > 0)

OD

Outside diameter of tube. (Real > 0.0)

T

Thickness of tube. (Real; T < ½ OD)

Altair Engineering

OptiStruct 13.0 Reference Guide 1921 Proprietary Information of Altair Engineering

Field

Contents

NSM

Nonstructural mass per unit length. (Real)

OD2

Diameter of tube at second grid point – G2 on CTUBE entry. See comment 4. Default = OD (OD or blank)

Comments 1.

If T is zero, a solid circular rod is assumed.

2.

All PTUBE entries must have unique property identification numbers.

3.

For structural problems, PTUBE entries may only reference MAT1 material entries.

4.

Tapered tubes are not allowed.

5.

PTUBE data is converted to PROD data as it is read. CTUBE data is converted to CROD data.

6.

This card is represented as a property in HyperMesh.

1922 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PVISC Bulk Data Entry PVISC – Viscous Damping Element Property Description Defines properties of a one-dimensional viscous damping element (CVISC entry). Format (1)

(2)

(3)

(4)

(5)

PVISC

PID1

C E1

C R1

(6)

(7)

(8)

(9)

PID2

C E2

C R2

(10)

Example

(1)

(2)

(3)

(4)

PVISC

3

6.2

3.94

(5)

Field

Contents

PID#

Property identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) CE1, CE2

Viscous damping values for extension in units of force per unit velocity. No default (Real)

CR1, CR2

Viscous damping values for rotation in units of force per unit velocity. No default (Real)

Comments 1.

Viscous properties are material independent; in particular, they are temperature independent.

Altair Engineering

OptiStruct 13.0 Reference Guide 1923 Proprietary Information of Altair Engineering

2.

One or two viscous element properties may be defined on a single entry.

3.

This card is represented as a property in HyperMesh.

1924 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PWELD Bulk Data Entry PWELD – WELD Element Property Description Defines properties of connector (CWELD) elements. Format (1)

(2)

(3)

(4)

PWELD

PID

MID

D

(5)

(6)

(7)

(8)

(9)

MSET

(10)

TYPE

Example

(1)

(2)

(3)

(4)

PWELD

30

2

2.5

(5)

Field

Contents

PID

Property identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) MID

Material identification number. See comment 1. No default (Integer > 0)

D

Diameter of the connector. See comment 1. No default (Real > 0.0)

MSET

Flag to eliminate m-set degrees-of-freedom. See comment 2. Default = OFF (ON or OFF)

Altair Engineering

OptiStruct 13.0 Reference Guide 1925 Proprietary Information of Altair Engineering

Field

Contents

TYPE

Indicates type of connection. See comment 3. SPOT indicates spot weld connector. blank indicates general connector. Default = blank (SPOT or blank)

Comments 1.

Material MID, diameter D, and the length are used to calculate the stiffness of the connector in 6 directions. MID can only refer to the MAT1 bulk data entry. The length is the distance of GA to GB (see below).

Length and Diameter of Weld connector

2.

MSET = ON generates explicit m-set constraints. MSET = OFF (default) incorporates constraints at the element stiffness matrix level avoiding explicit m-set constraint equations. The exact same results will be obtained regardless of this choice.

3.

If TYPE="SPOT" and if the formats PARTPAT, ELPAT, or ELEMID on the CWELD entry are used, then the effective length for the stiffness of the CWELD element is set to regardless of the distance GA to GB. t A and t B are the shell thicknesses of shell A and B respectively. For all other cases, the effective length of the CWELD element is equal to the true length, the distance of GA and GB, as long as the ratio of

1926 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

length to diameter is in the range 0.2 < L/D 5.0. If L is below the range, the effective length is set to Le = 0.2D and if L is above the range, the effective length is set to Le = 5.0D. 4.

This card is represented as a property in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1927 Proprietary Information of Altair Engineering

QBDY1 Bulk Data Entry QBDY1 – Heat Flux Boundary Condition (Form 1) Description Defines a uniform heat flux for CHBDYE elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

QBDY1

SID

Q0

EID1

EID2

EID3

EID4

EID5

EID6

(7)

(8)

(9)

(10)

Alternate Format (1)

(2)

(3)

(4)

(5)

(6)

QBDY1

SID

Q0

EID1

“THRU”

EID2

Field

Contents

SID

Load set identification number.

(10)

No default (Integer > 0) Q0

Heat flux into element. No default (Real)

EID#

CHBDYE surface element identification numbers. With alternate format using “THRU” EID2 > EID1.

Comments 1.

QBDY1 entries must be selected with the Case Control command LOAD=SID in order to be used in static analysis. The total power into an element is given by the equation:

2.

The sign convention for Q0 is positive for heat input.

1928 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

3.

This card is represented as a flux load in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1929 Proprietary Information of Altair Engineering

QVOL Bulk Data Entry QVOL – Volume Heat Addition Description Defines a rate of volumetric heat addition in a conduction element. Format (1)

(2)

(3)

QVOL

SID

QVOL

EID6

...

(4)

...

(5)

(6)

(7)

(8)

(9)

EID1

EID2

EID3

EID4

EID5

...

...

...

...

...

(10)

...

Field SID

Contents Load set identification number. No default (Integer > 0)

QVOL

Power input per unit volume produced by a heat conduction element. No default (Real)

EID#

A list of heat conduction elements. No default (Integer > 0 or “THRU” or “BY”)

Comments 1.

EID# has material properties (MAT4/MAT5) that include HGEN, the scale factor for volumetric heat generation. This association is made through the element EID.

2.

QVOL provides the constant volumetric heat generation rate. QVOL is positive for heat generation. For steady-state analysis, the total power into an element is:

Where, HGEN is the scale factor from the MAT4 and MAT5 data.

1930 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

3.

For use in steady-state analysis, the load set is selected with the Case Control command LOAD=SID.

4.

This card is represented as a flux load in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1931 Proprietary Information of Altair Engineering

RADPRM Bulk Data Entry RADPRM – Parameters definition entry for Geometric Nonlinear Analysis Description Defines the parameters for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

RADPRM

PARAM1

VALUE1

PARAM5

VALUE5

(5)

(6)

PARAM2 VALUE2 PARAM3

(7)

(8)

(9)

(10)

VALUE3

PARAM4

VALUE4

Example

(1)

(2)

(3)

(4)

(5)

RADPRM

HMNAME

YES

RBE2RBD

YES

(6)

(7)

Field

Contents

PARAMi

Name of parameter. See below for allowable names.

VALi

Value of parameter.

(8)

(9)

(10)

The available parameters and their values are listed below (click the parameter name for detailed parameter descriptions).

Parameter

Brief Description

Value

HMNAME

RADPRM, HMNAME controls the conversion of the YES or NO component, property and material names in Default = NO geometric nonlinear analysis.

RBE2RBD

RBE2 is converted to /RBE2 by default in YES or NO geometric nonlinear analysis. This parameter can

1932 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Parameter

Brief Description

Value

be used to convert RBE2 to /RBODY, instead of / Default = NO RBE2. Comments 1.

The parameters defined by RADPRM bulk card are only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

Altair Engineering

OptiStruct 13.0 Reference Guide 1933 Proprietary Information of Altair Engineering

RADPRM, HMNAME Parameter HMNAME

Values

Description

YES or NO Default = NO

RADPRM, HMNAME controls the conversion of the component, property and material names in geometric nonlinear analysis. If YES, the converter will keep the component, property and material names defined by HyperMesh comments in the bulk model file, and print them in a RADIOSS Starter file. If NO, the converter will print intermediate names automatically.

1934 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

RADPRM, RBE2RBD Parameter RBE2RBD

Values

Description

YES or NO Default = NO

RBE2 is converted to /RBE2 by default in geometric nonlinear analysis. This parameter can be used to convert RBE2 to /RBODY, instead of /RBE2. Note RBE2 can be converted to /RBODY only if all six degrees of freedom of the slave nodes are dependent on the master node. Otherwise, the solver errors out when RBE2RBD = YES. Note that if the master node of the RBE2 is connected to other elements or in the case of hierarchical RBE2’s, RADPRM, RBE2RBD activation is not recommended.

Altair Engineering

OptiStruct 13.0 Reference Guide 1935 Proprietary Information of Altair Engineering

RADSND Bulk Data Entry RADSND – Defines Grids (microphone locations) where sound levels will be calculated and the locations of the corresponding source (vibrating panel) grids. Description Defines a set of grid points where the sound will be calculated as well as the panels that are generating the sound. Format (1)

(2)

(3)

RADSND

RSID

MSET

"PANEL"

PID

(4)

(5)

(6)

(7)

PID

PID

- etc. -

(8)

(9)

(10)

Example

(1)

(2)

(3)

RADSND

10

100

PANEL

101

(4)

(5)

(6)

(7)

(8)

(9)

(10)

103

Field

Contents

RSID

Radiated sound set ID. No default (Integer > 0)

MSET

ID of a SET of field grids (microphone locations) at which sound levels will be calculated. The sound levels output at these grid points are due to panel vibrations (specified separately in the PANEL and PIDi fields, see comment 4). No default (Integer > 0)

PANEL

Flag indicating that the following panel ID’s will contribute to the sound at the MSET grids (see comment 4).

1936 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents Character (No default)

PIDi

Panel ID of the "PANELG" data entry of type "SOUND" data. No default (Integer > 0)

Comments 1.

At least the first panel ID is required.

2.

Multiple continuations or multiple RADSND with the same SID are allowed if more than 7 SOUND panels need to be defined.

3.

The RADSND bulk data entry is referenced by the RADSND command in the Subcase Information section of the input data.

4.

The MSET and PIDi fields are used to specify the microphone locations (receiving grids) and the vibrating panels (source grids) respectively. RADSND data entry field MSET

Description References microphone grid sets (receiving grids). Outputs are generally calculated at these locations.

PANEL, PIDi

Reference vibrating panel ID’s (source grids). Outputs can also be requested at these locations.

Altair Engineering

OptiStruct 13.0 Reference Guide 1937 Proprietary Information of Altair Engineering

RANDPS Bulk Data Entry RANDPS – Power Spectral Density Specification Description Defines load set power spectral density factors for use in random analysis having the frequency dependent form S (F) = (X + iY) G(F).

jk

Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

RANDPS

SID

J

K

X

Y

TID

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

RANDPS

5

3

7

2.0

2.5

4

Field

Contents

SID

Random analysis set identification number.

(8)

(9)

(10)

(Integer > 0) J

Subcase identification number of excited load set. (Integer > 0)

K

Subcase identification number of applied load set. (Integer > 0; K > J)

X, Y

Components of complex number. (Real)

1938 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

TID

Identification number of a TABRNDi entry which defines G(F). Integer > 0

Comments 1.

If J = K, then Y must be 0.0.

2.

For TID = 0, G(F) = 1.0.

3.

Set identification number must be selected in the Subcase Information section (RANDOM = SID) to activate the RANDPS data.

Altair Engineering

OptiStruct 13.0 Reference Guide 1939 Proprietary Information of Altair Engineering

RANDT1 Bulk Data Entry RANDT1 – Autocorrelation Function Time Lag Description Defines time lag constants for use in random analysis autocorrelation function computation. Format (1)

(2)

(3)

(4)

(5)

(6)

RANDT1

SID

N

T0

TMAX

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

RANDT1

5

10

3.2

9.6

(6)

(7)

Field

Contents

SID

Random analysis set identification number.

(8)

(9)

(10)

(Integer > 0) N

Number of time lag intervals. (Integer > 0)

TO

Starting time lag. (Real > 0.0)

TMAX

Maximum time lag. (Real > TO)

1940 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Comments 1.

At least one RANDPS entry must be present with the same set identification number.

2.

The time lags defined on this entry are given by

3.

Time lag sets must be selected in the Subcase Information section (RANDOM = SID) to activate the RANDT1 data.

Altair Engineering

OptiStruct 13.0 Reference Guide 1941 Proprietary Information of Altair Engineering

RBAR Bulk Data Entry RBAR – Rigid Bar Description Defines a rigid bar with six degrees-of-freedom at each end. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RBAR

EID

GA

GB

C NA

C NB

C MA

C MB

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

RBAR

5

1

2

234

123

(7)

Field

Contents

EID

Unique element identification number.

GA,GB

Grid point identification number of connection points.

(8)

(9)

(10)

(Integer > 0 or ) See comment 6. CNA,CNB

Independent degrees-of-freedom in the global coordinate system for the element at grid points GA and GB. Up to six unique digits (0 < digit < 6) may be placed in each field with no embedded blanks, or the field may be left blank. See comment 1.

CMA,CMB

Component numbers of dependent degrees-of-freedom in the global coordinate system assigned by the element at grid points GA and GB. Up to six unique digits (0 < digit < 6) may be placed in each field with no embedded blanks, or the field may be left blank. See comment 2.

1942 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Comments 1.

The total number of components in CNA and CNB must equal six, for example, CNA = 1236, CNB = 34. Furthermore, they must jointly be capable of representing any general rigid body motion of the element.

2.

If both CMA and CMB are zero or blank, all of the degrees-of-freedom not in CNA and CNB are made dependent.

3.

The degree of freedom declared dependent on this entry may not be: Included in a single point constraint (SPC or SPC1). Declared a dependent degree-of-freedom on any other RBAR, RBE1, RBE2, RBE3, or RROD entry. Declared a dependent degree-of-freedom on an MPC set referenced by a subcase.

4.

Element identification numbers must be unique.

5.

Rigid elements are ignored in heat transfer analysis.

6.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on RBAR entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

7.

This card is represented as a weld element in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1943 Proprietary Information of Altair Engineering

RBE1 Bulk Data Entry RBE1 – Rigid Body Element, Form 1 Description Defines a rigid body connected to an arbitrary number of grid points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

RBE1

EID

GN1

C N1

GN2

C N2

GN3

C N3

GN4

C N4

GN5

C N5

GN6

C N6

GM1

C M1

GM2

C M2

GM3

C M3

GM4

C M4

GM5

C M5

etc.

"UM"

(9)

(10)

Example

(1)

(2)

(3)

(4)

RBE1

14

100

123456

UM

101

123

(5)

(6)

102

123

Field

Contents

EID

Unique element identification number.

(7)

(8)

(9)

(10)

No default (Integer) GNi

Grid points at which independent degrees-of-freedom for the element are assigned. No default (Integer or ) See comment 7.

1944 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

CNi

Independent degrees-of-freedom in the global coordinate system for the rigid element at grid point(s) GNi.

UM

UM flag indicating the start of the dependent degrees-of-freedom.

GMi

Grid points at which dependent degrees-of-freedom for the element are assigned. No default (Integer or ) See comment 7.

CMi

Dependent degrees-of-freedom in the global coordinate system for the rigid elements at grid point(s) GMi. No default (Integers 1 through 6 with no embedded blanks)

Comments 1.

The total number of components in CN1 to CN6 must equal six; furthermore, they must jointly be capable of representing and general rigid body motion of the element. The first continuation entry is not required if there are fewer than four GN points.

2.

The degree-of-freedom declared dependent on this entry may not be: Included in a single point constraint (SPC or SPC1). Declared a dependent degree-of-freedom on any other RBAR, RBE1, RBE2, RBE3, or RROD entry. Declared a dependent degree-of-freedom on an MPC set referenced by a subcase.

3.

A degree-of-freedom cannot be both independent and dependent for the same element. However, both independent and dependent components can exist at the same grid point.

4.

Element identification numbers must be unique.

5.

Rigid elements, unlike MPCs, may not be selected for use in individual subcases; they apply to all subcases.

6.

Rigid elements are ignored in heat transfer analysis.

7.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on RBE1 entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

Altair Engineering

OptiStruct 13.0 Reference Guide 1945 Proprietary Information of Altair Engineering

RBE2 Bulk Data Entry RBE2 – Rigid Body Element, Form 2 Description Defines a rigid body whose independent degrees-of-freedom are specified at a single grid point and whose dependent degrees-of-freedom are specified at an arbitrary number of grid points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

RBE2

EID

GN

CM

GM1

GM2

GM3

GM4

GM5

GM6

GM7

GM8

-etc.-

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RBE2

9

8

12

10

12

14

15

16

(10)

20

Field

Contents

EID

Unique element identification number.

GN

The grid point to which all six independent degrees-of-freedom for the element are assigned. (Integer > 0 or ) See comment 5.

CM

Component number of the dependent degrees of freedom in the global coordinate system (local output coordinate system) at grid points GM1, GM2, and so on. Up to six unique digits (1 < digit < 6) may be placed in the field with no embedded blanks.

1946 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

GM1,GM2, etc. Grid points at which dependent degrees-of-freedom are assigned. (Integer > 0 or ) See comment 5. Comments 1.

The components indicated by CM are made dependent at all grid points, GMi.

2.

The degree-of-freedom declared dependent on this entry may not be: Included in a single point constraint (SPC or SPC1). Declared a dependent degree-of-freedom on any other RBAR, RBE1, RBE2, RBE3, or RROD entry. Declared a dependent degree-of-freedom on an MPC set referenced by a subcase.

3.

Element identification numbers must be unique.

4.

Rigid elements are ignored in heat transfer analysis.

5.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on RBE2 entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

6.

This card is represented as a rigid or rigidlink element in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1947 Proprietary Information of Altair Engineering

RBE3 Bulk Data Entry RBE3 – Interpolation Constraint Element Description Defines the motion at a "reference" grid point as the weighted average of the motions at a set of other grid points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

RBE3

EID

blank

REFGRID

REFC

WT1

C1

G1,1

G1,2

G1,3

WT2

C2

G2,1

G2,2

etc.

WT3

C3

G3,1

G3,2

etc.

WT4

C4

G4,1

G4,2

etc.

"UM"

GM1

C M1

GM2

C M2

GM3

C M3

blank

blank

GM4

C M4

GM5

C M5

etc.

blank

Example

(1)

(2)

RBE3

14

(3)

(4)

(5)

(6)

(7)

(8)

(9)

100

1234

1.0

123

1

3

2

5

4.7

1

2

4

6

5.2

7

8

9

5.1

1

15

16

UM

15

123

5

13

7

3

1948 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(10)

Altair Engineering

Field

Contents

EID

Unique element identification number.

REFGRID

Reference grid point. This is the dependent GRID. Some, or all, of the dependent degrees-of-freedom of this grid can be made independent by redefining all of the dependent degrees-of-freedom following the UM flag. (Integer > 0 or ) See comment 9.

REFC

Global components of motion whose values will be computed at the reference grid point. Any of the digits 1, 2, ..., 6 with no embedded blanks. (Integer > 0)

WTi

Weighting factor for components of motion on the following entry at grid points Gi,j. (Real)

Ci

Global components of motion that have weighting factor WTi, at grid points Gi,j. Any of the digits 1, 2, ..., 6, with no embedded blanks. (Integer > 0)

Gi,j

Grid point whose components Ci have weighting factor WTi in the averaging equations. (Integer > 0 or ) See comment 9.

UM

Optional flag indicating that a data set redefining the entire dependent degreeof-freedom set is to follow. The default is that all of the components in REFC at the reference grid point form the dependent degree-of-freedom set. See comments 4, 5 and 6.

GMi

Grid points with components in the redefined dependent degree-of-freedom set. (Integer > 0 or ) See comment 9.

CMi

Components of motion at GMi in the redefined dependent degree-of-freedom set. Any of the digits 1 through 6, with no embedded blanks. (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1949 Proprietary Information of Altair Engineering

Comments 1.

It is recommended that for most applications only the translation components 123 be used for Ci. An exception is the case where the Gij are collinear. A rotation component may then be added to one grid point, to stabilize its associated rigid body mode for the element.

2.

Blank spaces may be left at the end of a Gij sequence.

3.

The default for the dependent degree-of-freedom set should be used except in cases where you want to redefine some or all REFC components as the dependent degree-offreedom set. If the default is not used for the dependent degree-of-freedom set: The total number of components therein (that is, the total number of dependent degrees-of-freedom defined by the element) must be equal to the number of components in REFC (four components in the example). The components therein must be a subset of the components mentioned in REFC and Gij_Ci. The coefficient matrix [Rm] in the constraints equation [RM] {um} + [Rn] {un} = 0 must be nonsingular, where um denotes the dependent degree-of-freedom set and un denotes the independent degree-of-freedom set.

4. When the AMSES or AMLS eigenvalue solver is used, the UM data should be used when loaded RBE3 have more than 500 DOF. Large loaded RBE3 will dramatically increase the run times for AMSES or AMLS because the residual vectors will contain many DOF, unless the UM data is used to make the loaded center GRID independent. When UM data is used, the stiffness matrix becomes full for all the independent DOF of the RBE3, which can increase the run time for very large RBE3. The number of grids can be reduced using a HyperMesh macro. The macro is listed as Script 1068 in the Altair HyperWorks Script Exchange: www.altairhyperworks.com 5. UM data should not be used on large unloaded RBE3, as this will lead to an increase in the run time. 6. Dependent degrees-of-freedom assigned by one rigid element may not also be assigned dependent by another rigid element or by a multi-point constraint, and may not be specified on SPC data. 7. In version 5.0, the RBE3 element calculation was modified in order to make the results independent of the units used in the model. For this purpose, the weights of the rotational degrees-of-freedom have been scaled by the square of the average distance between the independent grid points and the reference point. This change will only affect the results if independent grid points with rotational degrees-of-freedom exist in the RBE3 element. The previous RBE3 formulation can be enforced with the debug statement debug, OLDRBE3,1.0. 8. Rigid elements are ignored in heat transfer analysis. 9. Supported local entries in specific parts can be referenced by the use of “fully qualified references” on RBE3 entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry

1950 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references. 10. This card is represented as an rbe3 element in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1951 Proprietary Information of Altair Engineering

RCROSS Bulk Data Entry RCROSS – Cross-Power Spectral Density Functions Output Description Defines a pair of response quantities for computing the cross-power spectral density functions in random response analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RC ROSS

SID

RTYPE1

ID1

C OMP1

RTYPE2

ID2

C OMP2

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RC ROSS

20

DISP

50

2

STRESS

150

8

4

Field

Contents

SID

RCROSS set identification number.

(10)

No default (Integer > 0) RTYPE#

Type of response quantity. At least one field must be selected. If either RTYPE1 or RTYPE2 is blank, then the blank field takes the default from the defined field. See comment 2.

ID#

Element, grid, or scalar point identification number. No default (Integer > 0)

COMP#

Component code (item) identification number. See comment 3. No default (Integer > 0)

1952 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Comments 1.

This entry is required for computing the cross-power spectral density function. SID must be selected with the I/O Option RCROSS. Fields RTYPE1, ID1, and COMP1 represent the first response quantity and fields RTYPE2, ID2, and COMP2 represent the second response quantity.

2.

The keywords for field RTYPE# are listed as follows:

3.

Keyword

Description

DISP

Displacement vector

VELO

Velocity vector

ACCEL

Acceleration vector

STRESS

Element Stress

STRAIN

Element Strain

For elements, COMP# represents a component of the element stress or strain as described in the following table. Element

Stress/Strain Item

Number code

All Solid Elements

Normal X

6 or 12

Normal Y

7 or 13

Normal Z

8 or 14

Shear XY

9 or 15

Shear YZ

10 or 16

Shear XZ

11 or 17

Normal X at Z1

3 or 4

Normal X at Z2

10 or 11

Normal Y at Z1

5 or 6

Normal Y at Z2

12 or 13

Shear XY at Z1

7 or 8

All Shell Elements

Altair Engineering

OptiStruct 13.0 Reference Guide 1953 Proprietary Information of Altair Engineering

Element

Stress/Strain Item

Number code

Shear XY at Z2

14 or 15

For grid points, COMP# represents a component of the displacement, velocity or acceleration as described in the following table: Response

Number code

Translation X

1 or 7

Translation Y

2 or 8

Translation Z

3 or 9

Rotation X

4 or 10

Rotation Y

5 or 11

Rotation Z

6 or 12

For scalar points, COMP# should always be 1.

1954 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

RELOC Bulk Data Entry RELOC – Grid Point Relocation Description The RELOC bulk data entry can be used to map grid points from one location to another. This entry allows you to translate, match, rotate or mirror grid points. The grid ID fields can be input as either numeric or fully qualified references to grid points in the model. Format The format of this entry depends on the TYPE field input; the various versions are listed as follows: Translation (TYPE = MOVE) Format 1 (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

RELOC

ID

TYPE

GID1

GID2

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

RELOC

ID

TYPE

dx

dy

dz

(8)

(9)

(10)

(10)

Format 2

Rotation (TYPE = ROTATE) Format 1 (1)

(2)

(3)

(4)

(5)

(6)

(7)

RELOC

ID

TYPE

GID1

ang_x

ang_y

ang_z

Matching (TYPE = MATCH) Format 1 (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RELOC

ID

TYPE

GIDA1

GIDA2

GIDA3

GIDB1

GIDB2

GIDB3

Altair Engineering

OptiStruct 13.0 Reference Guide 1955 Proprietary Information of Altair Engineering

Mirroring (TYPE = MIRROR) Format 1 (1)

(2)

(3)

(4)

(5)

(6)

(7)

RELOC

ID

TYPE

GIDA1

GIDA2

GIDA3

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RELOC

1

MATC H

1001

1012

3992

123

564

665

Field

Contents

ID

Set identification number.

(10)

(Integer > 0) TYPE

This field specifies the type of mapping between grid points in a model. The format of the RELOC card is different for different values of the TYPE field (see Comment 2 for detailed information on each option). (MOVE, ROTATE, MATCH, or MIRROR)

Translation (Format 1) GID1

Grid point identification number for translation to the reference point location. Grid point GID1 is moved from its original location to the GID2 location. (Integer > 0 or ) See comment 4.

GID2

Reference grid point identification number for translation. GID2 is used as a reference point to move another grid point (GID1) from its original location to the GID2 location. (Integer > 0 or ) See comment 4.

Translation (Format 2) dx, dy, dz

Defines the distance that the referenced part (INSTNCE entry) should be translated in the basic coordinate system. Each entry specifies the corresponding distance moved in the X, Y, and Z axes, respectively (see Comment 2). (Real or blank)

1956 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

Rotation (Format 1) GID1

Specifies the identification number of a grid point that will be used as a center of rotation based on the angles specified in the following fields. (Integer > 0 or ) See comment 4.

ang_x, ang_y, ang_z

Defines the angle (in degrees) of rotation about the X, Y, and Z axes, respectively with the grid point (GID1) as the center of rotation. In a 2D model, only ang_z is specified (see Comment 2). (Real or blank)

Matching (Format 1) GIDA1, GIDA2, GIDA3

Specifies the identification numbers of grid points (initial location) that will be moved to match with the corresponding grid points GIDB1,2,3 (final location, defined in the following fields). Any rotation, translation or mirroring required to complete this matching process is accomplished internally by OptiStruct. These three grid points cannot be collinear. (Integer > 0 or ) See comment 4.

GIDB1, GIDB2, GIDB3

Specifies the identification numbers of grid points which will be matched with the corresponding grid points defined in the GIDA1,2,3 fields. Any rotation, translation or mirroring required to complete this matching process is accomplished internally by OptiStruct. These three grid points cannot be collinear. (Integer > 0 or ) See comment 4.

Mirroring (Format 1) GIDA1, GIDA2, GIDA3

Specifies the identification numbers of grid points about which the entire part (defined via INSTNCE) will be laterally mirrored (flipped) by 180 degrees. The grid points GIDA1,2,3 define an absolute plane of symmetry flip. Any rotation or translation required to complete this mirroring process is accomplished internally by OptiStruct. The three grid points specified for mirroring cannot be collinear. In a 2D model, only GIDA1 and GIDA2 should be specified. (Integer > 0 or ) See comment 4.

Comments 1.

A RELOC entry can be referenced by a INSTNCE entry to define the location of a part in the full model.

2.

The following illustrations depict part relocation examples for each of the four TYPE field options. All grid point ID’s used on the RELOC entry can belong to any part in the model. Only their initial locations are relevant. All RELOC entries are evaluated before any parts

Altair Engineering

OptiStruct 13.0 Reference Guide 1957 Proprietary Information of Altair Engineering

are moved. This may not always produce the expected result in some cases as the sequence of moves affects the final part locations. For example, if RELOC, MATCH is defined using three grid points on part A and three grid points in part B, this may not result in a final structure with the two parts being connected, if part B is moved again after this matching process. To avoid such cases, it is strongly recommended to assign the grid points that define the initial location to a part that has to be moved and the grid points that define the final location, to a part that will not be moved (for example, the global structure). Translation - Format 1:

Format 1 (Special case, assumes that Part B does not relocate)

1958 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Translation - Format 2:

D

dx

2

dy

2

dz

2

Where,

D is the distance moved by the part referenced on the INSTNCE entry. dx, dy and dz are the distances moved by the part along the X, Y and Z axes. Rotation - Format 1:

Altair Engineering

OptiStruct 13.0 Reference Guide 1959 Proprietary Information of Altair Engineering

Matching - Format 1:

Format 1 (Special case – Part B does not relocate)

1960 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Mirroring - Format 1:

3.

In a 2D model, only two TYPE options are allowed: ROTATE and MIRROR. All grid points in the model should have the same Z coordinate. Rotation and mirroring are defined in the XY plane. Rotation in a 2D model defined in the X-Y plane (1)

(2)

(3)

(4)

RELOC

ID

ROTATE

GID1

(5)

(6)

(7)

(8)

(9)

(10)

(8)

(9)

(10)

ang_z

Mirroring in a 2D model defined in the X-Y plane

4.

(1)

(2)

(3)

(4)

(5)

RELOC

ID

MIRROR

GIDA1

GIDA2

(6)

(7)

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on RELOC entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN bulk data entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

Altair Engineering

OptiStruct 13.0 Reference Guide 1961 Proprietary Information of Altair Engineering

RFORCE Bulk Data Entry RFORCE – Rotational Force Description Defines a static loading condition due to a centrifugal force field. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

RFORC E

SID

G

C ID

A

R1

R2

R3

(9)

(10)

RAC C

Example

(1)

(2)

(3)

RFORC E

2

5

(4)

(5)

(6)

(7)

(8)

0.0

0.0

1.0

2.2

(9)

(10)

1.0

Field

Contents

SID

Load set identification number. No default (Integer > 0)

G

Grid point identification number through which the rotation vector acts. Default = 0 (Integer > 0)

CID

Coordinate system defining the components of the rotation vector.

1962 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents Default = 0 (Integer > 0)

A

Scale factor of the rotational velocity in revolutions per unit time. Default = 0.0 (Real)

R1,R2,R3

Rectangular components of rotation direction vector. The vector defined will pass through point G. No default (Real; R12 + R22 + R32 > 0.0)

RACC

Scale factor of the rotational acceleration in revolutions per unit time squared. (Real)

Comments 1.

The rotational forces that are created with an RFORCE entry for a constant angular velocity (A), act in the positive radial direction. They represent the initial forces on the structure due to a constant angular velocity. The rotational forces defined for a constant angular acceleration (RACC), act in the same direction as the angular acceleration. They would be opposite to the inertia forces on the structure due to a constant angular acceleration. The following plot shows that the RFORCE vector at node Gi is given by:

where, angular velocity =

angular acceleration =

Altair Engineering

OptiStruct 13.0 Reference Guide 1963 Proprietary Information of Altair Engineering

RFORC E vector at node Gi

2.

G = 0 or blank means the basic coordinate system origin.

3.

CID = 0 or blank signifies that the rotation vector acts at the origin of the basic coordinate system.

4.

The RFORCE load is selected for use in a subcase by the Subcase Information entry LOAD.

5.

The load vector generated by this entry can be printed using the I/O Option OLOAD.

6.

The continuation line containing RACC is optional.

7.

For CONM1 and CONM2 entries, OptiStruct calculates the torque, due to rotation, as follows:

where, I is the moment of inertia. 8.

This card is represented as a loadcollector in HyperMesh.

1964 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

RGYRO Bulk Data Entry RGYRO – Rotor Dynamics Description Bulk Data Entry for the inclusion of data required to perform Rotor Dynamics analysis in Modal Frequency Response Analysis and/or Modal Complex Eigenvalue Analysis. The RGYRO Bulk Data Entry is referenced by a corresponding RGYRO Subcase Information Entry in a specific subcase. Format (1)

(2)

(3)

(4)

RGYRO

RID

SYNC FLG

(5)

REFROTR SPDUNIT

(6)

(7)

(8)

(9)

SPDLOW

SPDHIGH

SPEED

(10)

Example

(1)

(2)

(3)

(4)

(5)

RGYRO

14

ASYNC

3

FREQ

(6)

(7)

(8)

(9)

(10)

55

Argument

Options

Description

RID



setid:

The SID is referenced by a RGYRO card in the subcase information section.

SYNCFLG



SYNC:

Synchronous Rotor dynamic analysis is selected, if SYNC is input in this field.

ASYNC:

Asynchronous Rotor dynamic analysis is selected, if ASYNC is input in this field.

rotid:

Reference rotor ID. This field selects the rotor that will be used in THE Rotor dynamic analysis.

(no default)

REFROTR

0>

Altair Engineering

OptiStruct 13.0 Reference Guide 1965 Proprietary Information of Altair Engineering

Argument

Options

Description

(no default)

SPDUNIT



RPM:

RPM specifies that the entries SPDLOW, SPDHIGH and SPEED are input in Revolutions Per Minute.

FREQ:

FREQ specifies that the entries SPDLOW, SPDHIGH and SPEED are input in revolutions per unit time.

(No default)

SPDLOW



Minimum rotor speed for synchronous analysis.

Default = 0.0

SPDHIGH



Maximum rotor speed for synchronous analysis.

Default = 99999.0

SPEED





If an integer value is input, it references a RSPEED bulk data entry that specifies a set of reference rotor speeds for asynchronous analysis (See comment 2).



If a real number is input, the value is considered constant and a single reference rotor speed value is specified (See comment 2).

Default = 0

Default = 0.0

Comments 1.

Multiple RGYRO bulk data entries with the same RID cannot exist.

2.

The values entered on some optional fields of the RGYRO bulk data entry depend on factors such as: solution sequence used, type of analysis performed, and the value of specific parameters. The following table shows some of the optional fields and their relevance based on the listed factors. Synchronous analysis is performed when the rotor speed is equal to the modal frequency (Complex eigenvalue analysis) or the frequency of the forcing function (Frequency response analysis) and Asynchronous analysis is

1966 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

performed when the user specified rotor speed is used for the analysis. Synchronous/ Solution Sequence Asynchronous Analysis Modal Frequency Response Analysis

Modal Complex Eigenvalue Analysis

3.

Required Entry

PARAM, GYROAVG

Comment

Synchronous

None

0

-

Synchronous

SPDLOW, SPDHIGH

-1

3, 4

Asynchronous

SPEED

0

-

Asynchronous

SPEED

-1

4

Synchronous

SPDLOW, SPDHIGH

-

3, 4

Asynchronous

SPEED

-

4

When multiple rotors are present within the system being modeled, one of the rotors is chosen as a reference rotor. The speeds of the rest of the rotors are linearly dependent of the reference rotor. Scale factors S1 and S2 are used to relate the speeds.

S1 S 2 *

ref

Where, is the speed of a rotor (different from the reference rotor) S1 and S2 are scale factors ref

is the speed of the reference rotor

The scale factors S1 and S2 will be calculated by a least-mean-square fit of the relative rotor speeds specified on the RSPINR entries (between SPDLOW to SPDHIGH of the reference rotor). If the SPDLOW or SPDHIGH values are beyond the range specified on the RSPINR entry, the values will be extrapolated from the RSPINR entry values. 4.

PARAM, WR3 and PARAM, WR4 are necessary for rotor damping.

Altair Engineering

OptiStruct 13.0 Reference Guide 1967 Proprietary Information of Altair Engineering

RLOAD1 Bulk Data Entry RLOAD1 – Frequency Response Dynamic Load, Form1 Description Defines a frequency-dependent dynamic load of the form for use in frequency response problems. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RLOAD1

SID

EXC ITEID

DELAY

DPHASE

TC

TD

TYPE

(10)

Example

(1)

(2)

(3)

RLOAD1

5

3

(4)

(5)

(6)

(7)

(8)

(9)

(10)

1

Field

Contents

SID

Set identification number. No default (Integer > 0)

EXCITEID

Identification number of the DAREA, SPCD, FORCEx, MOMENTx, PLOADx, RFORCE, or GRAV entry set that defines A. No default (Integer > 0)

DELAY

Defines time delay . If it is a non-zero integer, it represents the identification number of a DELAY bulk data entry that defines . If it is real, then it directly defines the value of that will be used for all degrees-of-freedom that are excited by this dynamic load entry. Default = 0 (Integer > 0, or Real)

1968 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

DPHASE

Defines phase . If it is a non-zero integer, it represents the identification number of a DPHASE bulk data entry that defines . If it is real, then it directly defines the value of that will be used for all degrees-of-freedom that are excited by this dynamic load entry. Default = 0 (Integer > 0, or Real)

TC

Set identification number of the TABLED1, TABLED2, TABLED3 or TABLED4 entry that gives C( ). See comment 2. Default = 0 if TD is non-zero (Integer > 0)

TD

Set identification number of the TABLED1, TABLED2, TABLED3 or TABLED4 entry that gives D( ). See comment 2. Default = 0 if TC is non-zero (Integer > 0)

TYPE

Identifies the type of the dynamic excitation. Default = 0 (See comment 5)

Comments 1.

Dynamic load sets must be selected in the I/O Options or Subcase Information sections with the command DLOAD = SID.

2.

If any DELAY, DPHASE, TC, or TD fields are blank or zero, the corresponding , , C( ), or D( ) will be zero. Either TC or TD may be blank or zero, but not both.

3.

RLOAD1 loads may be combined with RLOAD2 loads only by specification on a DLOAD entry. This means that the SID on a RLOAD1 entry must not be the same as that on a RLOAD2 entry.

4.

SID must be unique for all RLOAD1 and RLOAD2 entries.

5.

The type field identifies the type of dynamic excitation. Valid entries for this field are listed alongside a description of the dynamic excitation with they invoke. Type

Description

0, L, LO, LOA, LOAD

Applied load; EXCITEID references DAREA data.

1, D, DI, DIS, DISP

Enforced displacement; EXCITEID references SPCD data.

2, V, VE, VEL, VELO

Enforced velocity; EXCITEID references SPCD data.

Altair Engineering

OptiStruct 13.0 Reference Guide 1969 Proprietary Information of Altair Engineering

Type

Description

3, A, AC, ACC, ACCE

Enforced acceleration; EXCITEID references SPCD data.

6.

When EXCITEID refers to an SPCD entry, the modal space will be augmented with displacement vector(s) from linear static analysis with unit prescribed displacement at each of the SPCD degrees-of-freedom.

7.

All static structural loads can be referenced by EXCITEID by referring to the SID on the structural load. The structural loads are FORCE, FORCE1, FORCE2, MOMENT, MOMENT1, MOMENT2, PLOAD, PLOAD1, PLOAD2, PLOAD4, RFORCE, and GRAV. EXCITEID cannot reference the LOAD and LOADADD Bulk Data entries.

8.

This card is represented as a loadcollector in HyperMesh.

1970 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

RLOAD2 Bulk Data Entry RLOAD2 – Frequency Response Dynamic Load, Form 2 Description Defines a frequency-dependent dynamic load of the form:

for use in frequency response problems. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RLOAD2

SID

EXC ITEID

DELAY

DPHASE

TB

TP

TYPE

(10)

Example

(1)

(2)

(3)

RLOAD2

5

3

(4)

(5)

(6)

(7)

(8)

(9)

(10)

7

Field

Contents

SID

Set identification number. No default (Integer > 0)

EXCITEID

Identification number of the DAREA, SPCD, FORCEx, MOMENTx, PLOADx, RFORCE, or GRAV entry set that defines A. No default (Integer > 0)

DELAY

Defines time delay . If it is a non-zero integer, it represents the identification number of a DELAY bulk data entry that defines . If it is real, then it directly defines the value of that will be used for all degrees-of-freedom that are excited by this dynamic load entry.

Altair Engineering

OptiStruct 13.0 Reference Guide 1971 Proprietary Information of Altair Engineering

Field

Contents Default = 0 (Integer > 0, or Real)

DPHASE

Defines phase . If it is a non-zero integer, it represents the identification number of a DPHASE bulk data entry that defines . If it is real, then it directly defines the value of that will be used for all degrees-of-freedom that are excited by this dynamic load entry. Default = 0 (Integer > 0, or Real)

TB

Set identification number of the TABLED1, TABLED2, TABLED3 or TABLED4 entry that gives B( ). No default (Integer > 0)

TP

Set identification number of the TABLED1, TABLED2, TABLED3 or TABLED4 entry that gives in degrees. Default = 0 (Integer > 0)

TYPE

Identifies the type of the dynamic excitation. Default = 0 (See comment 5)

Comments 1.

Dynamic load sets must be selected in the I/O Options or Subcase Information sections with the command DLOAD = SID.

2.

If any DELAY, DPHASE, or TP fields are blank or zero, the corresponding , , or be zero.

3.

RLOAD2 loads may be combined with RLOAD1 loads only by specification on a DLOAD entry. This means that the SID on a RLOAD2 entry must not be the same as that on a RLOAD1 entry.

4.

SID must be unique for all RLOAD1 and RLOAD2 entries.

5.

The TYPE field identifies the type of dynamic excitation. Valid entries for this field are listed below alongside a description of the dynamic excitation which they invoke. Type

Description

0, L, LO, LOA, LOAD

Applied load; EXCITEID references DAREA data.

1, D, DI, DIS, DISP

Enforced displacement; EXCITEID references SPCD data.

1972 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

will

Altair Engineering

Type

Description

2, V, VE, VEL, VELO

Enforced velocity; EXCITEID references SPCD data.

3, A, AC, ACC, ACCE

Enforced acceleration; EXCITEID references SPCD data.

6.

When EXCITEID refers to an SPCD entry, the modal space will be augmented with displacement vector(s) from linear static analysis with unit prescribed displacement at each of the SPCD degrees-of-freedom.

7.

All static structural loads can be referenced by EXCITEID by referring to the SID on the structural load. The structural loads are FORCE, FORCE1, FORCE2, MOMENT, MOMENT1, MOMENT2, PLOAD, PLOAD1, PLOAD2, PLOAD4, RFORCE, and GRAV. EXCITEID cannot reference the LOAD and LOADADD Bulk Data entries.

8.

This card is represented as a loadcollector in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1973 Proprietary Information of Altair Engineering

ROTORG Bulk Data Entry ROTORG – Grids for the Rotor Line Model (Rotor Dynamics). Description This Bulk Data Entry is used for the specification of grids that determine the Rotor Line model. Format (1)

(2)

ROTORG ROTORID

(3)

(4)

(5)

(6)

GRID1

GRID2

…

GRIDn

(3)

(4)

(5)

(6)

GRID1

THRU

GRID2

(7)

(8)

(9)

(10)

(7)

(8)

(9)

(10)

Alternate Format (1)

(2)

ROTORG ROTORID

Example

(1)

(2)

(3)

(4)

(5)

(6)

ROTORG

25

2345

2356

2400

2450

(6)

(7)

(8)

(9)

(10)

(7)

(8)

(9)

(10)

Example (Alternate Format)

(1)

(2)

(3)

(4)

(5)

ROTORG

30

2300

THRU

2400

Argument

Options

Description

ROTORID

0>

setid:

The identification number of a rotor.

1974 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Argument

Options

Description

GRIDi

0>

List of grids that define the rotor line model.

No default

THRU (Optional)

Flag indicating that a range of grid identification numbers is defined. The initial and final grids are specified on the fields either side of the field containing the THRU flag.

Comments 1.

All grid point entries specified on the ROTORG entry must be unique. The program will run into an error, if duplicate grid entries are specified.

2.

Multiple ROTORG entries can be defined with the same ROTORID.

3.

This ROTORG entry is used to define a Rotor Line model; therefore, for a specific ROTORID, all grids specified on the ROTORG entry must be collinear. OptiStruct automatically checks if the grids are collinear during a run.

4.

If superelements are not used, connections between grids in the Rotor Line model and those not listed on the ROTORG entry must be defined using MPC’s or rigid elements.

5.

If superelements are used, connections between grids in the Rotor Line model and those in the residual structure must be defined using MPC’s or rigid elements.

6.

The mass of the Rotor Line model should be defined on the grids defined on the grids specified by the ROTORG bulk data entry.

Altair Engineering

OptiStruct 13.0 Reference Guide 1975 Proprietary Information of Altair Engineering

RROD Bulk Data Entry RROD – Rigid Pin-Ended Rod Description Defines a pin-ended rod that is rigid in extension. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

RROD

EID

GA

GB

C MA

C MB

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

RROD

14

1

1115

2

(6)

(7)

(8)

Field

Contents

EID

Unique element identification number.

GA,GB

Grid point identification numbers of connection points.

(9)

(10)

(Integer > 0 or ) See comment 6. CMA,CMB

Component number of one and only one dependent translational degreeof-freedom in the global coordinate system assigned by you to either GA or GB. Integer equal to 1, 2, or 3, or blank. Either CMA or CMB must contain the integer and the other must be blank.

Comments 1.

Element identification numbers must be unique.

2.

Forces of constraint are not recovered.

1976 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

3.

The degree-of-freedom selected to be dependent must have a non-zero component along the axis of the rod. This implies that the rod must have finite length.

4.

The degree-of-freedom declared dependent on this entry may not be: Included in a single point constraint (SPC or SPC1). Declared a dependent degree-of-freedom on any other RBAR, RBE1, RBE2, RBE3, or RROD entry. Declared a dependent degree-of-freedom on an MPC set referenced by a subcase.

5.

Rigid elements are ignored in heat transfer analysis.

6.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on RROD entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

7.

This card is represented as a rod element in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1977 Proprietary Information of Altair Engineering

RSPEC Bulk Data Entry RSPEC – Response Spectrum Analysis Specifications Description Specifies directional combination method, modal combination method, excitation direction(s), response spectra and scale factors. Format (1)

(2)

(3)

(4)

(5)

(6)

RSPEC

RID

DC OMB

MC OMB

C LOSE

DTISPEC 1

SC ALE1

X11

X12

X13

DTISPEC 2

SC ALE2

X21

X22

X23

DTISPEC 3

SC ALE3

X31

X32

X33

(7)

(8)

(9)

(10)

Example 1

(1)

(2)

(3)

(4)

(5)

RSPEC

35

ALG

SRSS

1.0

7

1.3

0.5

0.5

(1)

(2)

(3)

(4)

(5)

RSPEC

35

SRSS

C QC

0.0

(6)

(7)

(8)

(9)

(10)

-1.

Example 2

(6)

(7)

1978 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(8)

(9)

(10)

Altair Engineering

(1)

(2)

(3)

(4)

(5)

(6)

7

1.3

0.5

0.5

-1.

4

2.0

-2

-0.0

-1.

2

17.

0.5

-2.5

-1.

Field

Contents

RID

RSPEC identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) DCOMB

Method for directional combination. Can be either algebraic (ALG) or square root of sum of squares (SRSS). Default = ALG (ALG or SRSS)

MCOMB

Method for modal combination. Can be either absolute sum (ABS), square root of sum of squares (SRSS), complete quadratic combination (CQC), or Navy Reseach Laboratory’s SRSS (NRL). Default = ABS (ABS, SRSS, CQC, or NRL)

CLOSE

Modal frequency closeness parameter. Default = 1.0 (Real)

DTISPECi

Response spectrum reference. ID of a DTI,SPECSEL entry. No default (Integer > 0)

SCALEi

Scale factor for excitation. No default (Real 0.0)

Xij

Components of a vector representing ground excitation i, j = 1..3

Comments 1.

All RSPEC cards must have unique ID numbers.

2.

DTISPEC2/SCALE2/X21/X22/X23 and DTISPEC3/SCALE3/X31/X32/X33 are optional ground excitations for multi-directional excitation. The directions of excitation have to be orthogonal to each other and will be reported as error otherwise.

3.

Refer to Response Spectrum Analysis in the User’s Guide for more details.

Altair Engineering

OptiStruct 13.0 Reference Guide 1979 Proprietary Information of Altair Engineering

RSPEED Bulk Data Entry RSPEED – Reference Rotor Speed Values Description This bulk data entry is used to specify a set of reference rotor speed values for asynchronous analysis in Rotor Dynamics. Format (1)

(2)

(3)

(4)

(5)

(6)

RSPEED

SID

S1

DS

NDS

(7)

(8)

(9)

(10)

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

RSPEED

25

1500

50

5

(6)

Argument

Options

Description

SID

0>

Set identification number.

No default

S1

0.0>

Specifies the first reference rotor speed in the set.

No default

DS

0.0> No default

Specifies the increment in reference rotor speed. This value is added to each successive entry starting from the first entry (S1).

1980 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Argument

Options

Description

NDS

0>

Number of reference rotor speed increments.

Default = 1 Comments 1.

The RSPEED bulk data entry is referenced by the SPEED field on the RGYRO bulk data entry. If an integer value is specified in the SPEED field, multiple reference rotor speeds specified in the RSPEED entry are used in asynchronous analysis.

2.

In asynchronous frequency response analysis, if the RSPEED bulk data entry is referenced in RGYRO, only the first frequency is considered. In complex eigenvalue analysis, the full range specified by RSPEED is considered.

3.

The following formula is used to populate the set of reference rotor speeds:

Ri

( S1 ( DS ) * i)

i 1 to NDS

R1 , R2 , … RNDS represent the set of reference rotor speeds S1 is the first reference rotor speed DS is the reference rotor speed increment NDS is the number of reference rotor speed increments

Altair Engineering

OptiStruct 13.0 Reference Guide 1981 Proprietary Information of Altair Engineering

RSPINR Bulk Data Entry RSPINR – Relative Rotor Spin Rates (Rotor Dynamics) Description This entry defines the relative spin rates between rotors during a rotor dynamic analysis in Modal Complex Eigenvalue or Frequency Response solution sequences. Format (1)

(2)

(3)

(4)

(5)

(6)

SPINR

ROTORID

GRIDA

GRIDB

SPDUNIT

SPTID

GR

(7)

(8)

(9)

(10)

ALPHAR1 ALPHAR2

Example

(1)

(2)

(3)

(4)

(5)

(6)

RSPINR

130

2400

2401

FREQ

200

0.03

(7)

(8)

(9)

(10)

5600

Argument

Options

Description

ROTORID

0>

setid

Rotor identification number

No default

GRIDA

0>

GRIDA identifies a grid on the Rotor Line Model.

No default

GRIDA and GRIDB define the positive rotor spin direction. The vector connecting GRIDA and GRIDB is the positive direction vector. The rotor axis is defined using the ROTORG bulk data entry and the two grids (GRIDA, GRIDB) are also specified on the ROTORG bulk data entry.

1982 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Argument

Options

GRIDB

0>

GRIDB identifies a grid on the Rotor Line Model.

No default

GRIDA and GRIDB define the positive rotor spin direction. The vector connecting GRIDA and GRIDB is the positive direction vector. The rotor axis is defined using the ROTORG bulk data entry and the two grids (GRIDA, GRIDB) are also specified on the ROTORG bulk data entry.



RPM:

RPM specifies that the relative spin rates are input in Revolutions Per Minute.

FREQ:

FREQ specifies that the relative spin rates are input in revolutions (cycles) per unit time.

SPDUNIT

Description

(No default)

SPTID

0/Real> (No default)

0> If an integer value (must be greater than 0) is input, it references a DDVAL bulk data entry that specifies the relative rotor spin rates (see comment 3).

GR

Default = 0.0

ALPHAR1

Default = 0.0

Altair Engineering

If a real number is input, the value is considered constant.

Rotor Structural Damping Factor (see comments 4 and 6).

Scale factor applied to the rotor mass matrix for Rayleigh Damping (see comments 5 and 6).

OptiStruct 13.0 Reference Guide 1983 Proprietary Information of Altair Engineering

Argument

Options

ALPHAR2



Description

Scale factor applied to the rotor stiffness matrix for Rayleigh Damping (see comments 5 and 6).

Default = 0.0 Comments 1.

A RSPINR entry must exist for each rotor line model defined using the ROTORG bulk data entry.

2.

GRIDA and GRIDB define the positive rotor spin direction. The vector connecting GRIDA and GRIDB is the positive direction vector. The rotor axis is defined using the ROTORG bulk data entry and the two grids (GRIDA, GRIDB) are also specified on the ROTORG bulk data entry.

3.

An integer or a real number can be input in the SPTID field. If SPTID is an integer, it references a DDVAL bulk data entry that specifies the relative rotor spin rates. Each rotor must be assigned the same number of spin rates. To determine relative spin rates, the table entries which contain the sequence of spin rates are correlated. The i’th entry for each rotor corresponds to the relative spin rates between rotors at RPMi/FREQi. The spin rates for the reference rotor must be specified in ascending or descending order.

4.

Rotor structural damping factor (GR) can be incorporated as either equivalent viscous damping or structural damping depending on the solution sequence.

BRotor

structural

GR WR3

K rotor

Or,

K rotor

(1 iGR ) K rotor

Where,

WR3 is a parameter defined by PARAM, WR3 GR is defined as a field on the RSPINR bulk data entry. The selection depends on the following factors: Modal frequency response or Complex eigenvalue analysis. Synchronous or Asynchronous solutions. Value of PARAM, GYROAVG. 5.

The Rayleigh damping value for the rotor is calculated as:

Brotor

Rayleigh

R1

( M rotor )

R2

(K rotor )

1984 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

6.

The damping and circulation terms added to the corresponding analysis equations are listed in the table below. Refer to the Rotor Dynamics section in the User's Guide for detailed information. Solution Sequence Analysis

Damping

i ([ BR ]

Frequency Response (ASYNC)

Circulation

R1 [ M R ]

R 2 [ K R ])

R

i (GR[ K R ] [ K 4 R ])

[ BR ] Frequency Response (ASYNC + GYROAVG, -1)

i

Frequency Response (SYNC)

i ([ BR ]

R1

[M R ]

R2

[ BRC ] (

ref

)

GR

R1 [ M R ]

R 2 [ K R ])

R

i (GR[ K R ] [ K 4 R ])

Frequency Response (SYNC + GYROAVG, -1)

i

Altair Engineering

i

[M R ]

GR [KR ] WR3

[ BR ] Complex Eigenvalue (ASYNC)

R1

R1

[M R ]

GR [KR ] WR3

R2

[KR ]

R

R1

GR

1 [ K 4 R[ B ] C] R WR 4 GR R

R2

R1

GR

[ BRC ] [ BR ]

[KR ]

R1

[ M RC ]

R1

( ) 1 [RK 4 Rref] WR 4

[ M RC ]

R1

[ K RC ]

[ K 4CR ]

[ K RC ]

[ K RC ]

[ K 4CR ]

[ M RC ]

GR [ K RC ] WR3

[ K RC ]

[ K 4CR ] R2

1

[ K RC ]

[ BRC ]

R2

1

[ K RC ]

R2

R2

1

[ M RC ]

[ K 4CR ]

1 [ K 4CR ] WR 4

[ M RC ]

[ K RC ]

[ K RC ]

R2

1

GR [ K RC ] WR3

[ BRC ] ( )

[ M RC ]

[ K RC ]

[ BRC ]

[KR ]

1 R ( ref ) [ K 4R ] WR 4

GR [KR ] WR3

R1

R2

[ K RC ]

1 [ K 4CR ] WR 4

OptiStruct 13.0 Reference Guide 1985 Proprietary Information of Altair Engineering

Solution Sequence Analysis

Damping

Circulation

[ BRC ] [ BR ] Complex Eigenvalue (SYNC)

i

R1

[M R ]

GR [KR ] WR3

R2

[KR ]

R

GR

1 [ K 4 R[ B ] C] R WR 4 GR R

R1

[ M RC ]

[ K RC ] R1

R2

1

[ M RC ]

[ K RC ]

[ K 4CR ] R2

1

[ K RC ]

[ K RC ]

[ K 4CR ]

Where,

[ BR ]

is the rotor viscous damping

[M R ]

is the rotor mass

[K R ]

is the rotor stiffness

[ K 4R ] C R

[B ]

is the circulation, due to rotor viscous damping

C R

[M ] [ K RC ] C R

[K 4 ] R1

is the rotor material damping

is the circulation, due to rotor ‘mass’ is the circulation, due to rotor structural ‘stiffness’ is the circulation, due to rotor material damping

and

R2

[ BR ]Rayleigh

are used to define the Rayleigh viscous damping, as follows: R1

[M R ]

R2

[K R ]

WR3 and WR4 are defined by the parameters PARAM, WR3 and PARAM, WR4, respectively. 7.

Rotor damping is cumulative and caution should be exercised when multiple damping effects are assigned.

1986 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

RSPLINE Bulk Data Entry RSPLINE – Interpolation Constraint Element Description Defines multi-point constraints for the interpolation of displacements at grid points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RSPLINE

EID

D/L

G1

G2

C2

G3

C3

G4

C4

G5

C5

G6

…

…

…

…

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

RSPLINE

73

0.05

27

28

123456

29

123

75

123

71

Field

Contents

EID

Unique element identification number.

(8)

(9)

(10)

30

No default (Integer > 0) D/L

Ratio of the diameter of the elastic tube to the sum of the lengths of all segments. Default = 0.1 (Real > 0.0)

G#

Grid point identification number. No default (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1987 Proprietary Information of Altair Engineering

Field

Contents

C#

Components to be constrained. See comment 2. Default = blank (blank or any combination of the Integers 1 through 6)

Comments 1.

Displacements are interpolated from the equations of an elastic beam passing through the grid points. This is a linear method only element.

2.

A blank field for C# indicates that all six degrees-of-freedom at G# are independent. Since G1 must be independent, no field is provided for C1. Since the last grid point must also be independent, the last field must be a G#, not a C#. For the example shown G1, G3 and G6 are independent. G2 has six constrained degrees-of-freedom, while G4 and G5 each have three.

3.

Dependent (that is constrained) degrees-of-freedom assigned by one rigid element may not also be assigned dependent by another rigid element or by a multi-point constraint.

4.

Degrees-of-freedom declared to be independent by one rigid body element can be made dependent by another rigid body element or by a multi-point constraint.

5.

Rigid elements (including RSPLINE), unlike MPCs, form part of the model and do not need to be selected from within a subcase definition.

6.

Rigid elements are ignored in heat transfer problems.

7.

The constraint coefficient matrix is affected by the order of the Gi Ci pairs on the RSPLINE entry. The order of the pairs should be specified in the same order that they appear along the line that joins the two regions. If this order is not followed, then the RSPLINE will have folds in it that may yield some unexpected interpolation results.

8.

The independent degrees-of-freedom that are the rotation components most nearly parallel to the line joining the regions should not normally be constrained.

9.

The default RSPLINE implementation has larger-than-expected in-plane rotation at the two RSPLINE end nodes and where RSPLINE have sharp angles. Applying PARAM,RSPLICOR reduces such rotation and yields better results.

10. Rigid elements are ignored in heat transfer analysis.

1988 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

RSSCON Bulk Data Entry RSSCON – Shell-to-Solid Element Connector Description Defines multi-point constraints to model clamped connections of shell-to-solid elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RSSC ON

RBID

TYPE

ES1

EA1

EB1

ES2

EA2

EB2

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RSSC ON

110

GRID

11

12

13

14

15

16

Field

Contents

RBID

Unique element identification number.

(10)

No default (Integer > 0) TYPE

Type of connectivity. “ELEM” - connection is described with element identification numbers. “GRID” - connection is described with grid point. Default = ELEM (GRID or ELEM)

ES1

Shell element identification number if TYPE = “ELEM.” Shell grid point identification number if TYPE = “GRID.” No default (Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 1989 Proprietary Information of Altair Engineering

Field

Contents

EA1

Solid element identification number if TYPE = “ELEM.” Solid grid point identification number if TYPE = “GRID.” No default (Integer > 0)

EB1

Solid grid-point identification number for TYPE = “GRID” only. Default = blank (Integer > 0 or blank)

ES2

Shell grid-point identification number for TYPE = “GRID” only. Default = blank (Integer > 0 or blank)

EA2

Solid grid-point identification number for TYPE = “GRID” only. Default = blank (Integer > 0 or blank)

EB2

Solid grid-point identification number for TYPE = “GRID” only. Default = blank (Integer > 0 or blank)

Comments 1.

RSSCON generates a multipoint constraint that models a clamped connection between a shell and a solid element. The shell degrees-of- freedom are considered dependent. The translational degrees-of- freedom of the shell edge are connected to the translational degrees-of- freedom of the upper and lower solid edge. The rotational degrees-offreedom of the shell are connected to the translational degrees-of-freedom of the lower and upper edges of the solid element face. Poisson’s ratio effects are considered in the translational degrees-of-freedom.

2.

The shell grid point must lie on the line connecting the two solid grid points. It can have an offset from this line, which can not be more than 5% of the distance between the two solid grid points. The shell grid points that are out of the tolerance will not be constrained, and a fatal message will be issued. This tolerance is adjustable. Refer to PARAM,TOLRSC and PARAM,SEPIXOVR.

3.

When using the TYPE = “ELEM” option: The elements may be first or second order. When a straight shell element edge and a solid element are connected, the geometry of the shell edge is not changed to fit the solid face. When a curved shell element edge and a solid element are connected, the two solid edges and solid face are not changed to match the shell edge.

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It is not recommended to connect more than one shell element to the same solid using the ELEM option. If attempted, conflicts in the multipoint constraint relations may lead to UFM 6692. 4.

When using TYPE = “GRID” option: The GRID option does not verify that the grids used are valid shell and/or solid grids. The GRID option is not recommended for 2nd order elements.

5.

It is recommended that the height of the solid element’s face is approximately equal to the shell element’s thickness of the shell. The shell edge should then be placed in the middle of the solid face.

6.

The shell edge may coincide with the upper or lower edge of the solid face.

7.

The RSSCON entry, unlike MPCs, is part of the model and does not need to be selected in a subcase definition.

8.

RSSCON is ignored in heat-transfer problems.

Altair Engineering

OptiStruct 13.0 Reference Guide 1991 Proprietary Information of Altair Engineering

RWALADD Bulk Data Entry RWALADD – Rigid Wall Combination for Geometric Nonlinear Analysis Description Defines a rigid wall set as a union of rigid walls defined via RWALL entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

RWALADD

SID

S1

S2

S3

S4

S5

S6

S7

S8

S9

etc.

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

RWALADD

101

2

3

1

6

4

Field

Contents

SID

Set identification number.

(8)

(9)

(10)

(Integer > 0) Sj

Set identification numbers of rigid wall sets defined via RWALL entries. (Integer > 0)

Comments 1.

Multipoint constraint sets must be selected with the Subcase Information command RWALL=SID.

2.

The Sj must be unique and may not be the identification number of a rigid wall set defined by another RWALADD entry.

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3.

RWALADD entries take precedence over RWALL entries. If both have the same SID, only the RWALADD entry will be used.

4.

This card is represented as a loadcollector in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 1993 Proprietary Information of Altair Engineering

RWALL Bulk Data Entry RWALL – Rigid Wall for Geometric Nonlinear Analysis Description Defines a rigid wall for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

RWALL

SID

RWTYPE

SLID

GISD1

GSID2

FRIC

DIST

G0/X0

Y0

Z0

IFILT

FFAC

X1

Y1

Z1

X2

Y2

Z2

DIA

MASS

VX

VY

VZ

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

RWALL

2

PLANE

SLIDE

23

5

2

1

21

11

24

12

340

7

13

(7)

(8)

(9)

(10)

3

32

Field

Contents

SID

Load set identification number. No default (Integer > 0)

1994 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Field

Contents

RWTYPE

Rigid wall type. PLANE – Infinite plane. CYL – Infinite cylinder of diameter DIA. SPHER – Sphere of diameter DIA. PARAL - Parallelogram. Default = PLANE (PLANE, CYL, SPHERE, or PARAL)

SLID

Flag for sliding. SLIDE – Sliding. TIED – Tied. SLFRIC – Sliding with friction. Default = SLIDE (SLIDE, TIED, or SLFRIC)

GSID1

Grid set ID defining slave grids to be added to the rigid wall. (Integer > 0)

GSID2

Grid set ID defining slave grids to be deleted from the rigid wall. (Integer > 0)

FRIC

Friction coefficient (ignored if SLID = TIED, SLIDE). Default = 0.0 (Real > 0)

DIST

Distance for slave search (See comment 2). (Real > 0)

G0

Grid identifier defining M, definition ignores Y0, Z0. Moving rigid wall. (Integer > 0)

X0, Y0, Z0

Coordinates of a point M defining rigid wall location if G0 not defined. Rigid wall does not move. (Real)

IFILT

Friction filtering flag (See comment 4).

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OptiStruct 13.0 Reference Guide 1995 Proprietary Information of Altair Engineering

Field

Contents Default = 0 (Integer = 0, …, 3) 1 – Direct user input of filtering coefficient. 2 – Filtering coefficient corresponds to a 3dB filtering level. 3 - Filtering coefficient corresponds to a 3dB filtering level for user defined frequency (frequency defined in terms of time step number).

FFAC

Friction filtering factor. Default = 0.0 (Real)

X1, Y1, Z1

Coordinates of a point defining M1 for RWTYPE = PLANE, CYL, PARAL. (Real)

X2, Y2, Z2

Coordinates of a point defining M2 for RWTYPE = PARAL. (Real)

DIA

Diameter for RWTYPE = CYL, SPHER. (Real > 0)

MASS

Mass of moving rigid wall if G0 is defined. (Real > 0)

VX, VY, VZ

Components of initial velocity if G0 is defined. (Real)

Comments 1.

RWALL must be selected in the subcase with RWALL = SID or by RWALADD. It can only be selected in geometric nonlinear analysis subcases which are defined by an ANALYSIS = NLGEOM, IMPDYN or EXPDYN subcase entry.

2.

Initially the slave nodes can be defined at a distance lower than DIST.

3.

Nodal thickness of rigid wall slave nodes is not taken into account.

4.

IFILT defines the method for computing the friction filtering coefficient. Friction filtering slave node in contact are filtered using a simple rule: F T = α * F'T + (1 - α) * F'T-1

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where, F T - Tangential force F'T - Tangential force at time t F'T-1 - Tangential force at time t-1 α - filtering coefficient IFILT = 1 – α = FFAC IFILT = 2 – α = 2 dt * freq, where dt = time step, and freq = FFAC IFILT = 3 – α = 2 5.

6.

/ N, with 1/freq = T = N * dt, and N = FFAC

Surface input type Type

Description

PLANE

MM1 defines the normal direction.

CYL

MM1 defines the axis of the cylinder.

SPHER

M is the center of the sphere.

PARAL

MM1 and MM2 define the parallelogram with the normal as cross product MM1 x MM2.

This card is represented as a rigid wall in HyperMesh.

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OptiStruct 13.0 Reference Guide 1997 Proprietary Information of Altair Engineering

SECT Bulk Data Entry SECT – Section Definition for Section Force Output in Geometric Nonlinear Analysis Description Defines a section for force output in geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SEC T

SC ID

G0

G1

G2

GRSET

ELSET

IFRAME

C ID

(10)

DT

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

SEC T

2

234

665

723

3

4

Field

Contents

SCID

Section identification number.

(8)

(9)

(10)

No default (Integer > 0) G0, G1, G2

Grid points defining the local axes of the section. G0 and G1 define the local x-axis while G0, G1, and G3 define the local xy-plane. No default (Integer > 0)

GRSET

Grid set ID. No default (Integer > 0)

ELSET

Element set ID. Only sets of SOLID, SHELL, ROD, BAR, and BEAM elements can be used. (Integer > 0)

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Field

Contents

IFRAME

Flag for computing the center of the output coordinate system. The local system is defined by G0, G1, and G2. Default = 0 (Integer = 0, 1, 2, 3, 10, 11, 12, 13) 0 – Origin of the local system defined by G0, G1, and G2 1 – Geometrical center of the section grid in the local system defined by G0, G1, and G2 2 – Center of gravity of the section in the local system defined by G0, G1, and G2 3 – Origin of the basic system in the local system defined by G0, G1, and G2 10 – Origin of the basic system 11 – Geometrical center of the section in the basic system 12 – Center of gravity of the section in the basic system 13 – Origin of the basic system

CID

Moving coordinate system identifier for automatic definition of a section. Only CORD1R and CORD3R can be selected (See comment 4). Default = 0 (Integer > 0)

DT

Time step for saving the data. Default = DTTH defined on XSOM (Real > 0)

Comments 1.

SECT output must be selected for time history output with XHIST. It is only available for geometric nonlinear analysis subcases which are defined by an ANALYSIS = NLGEOM, IMPDYN or EXPDYN subcase entry.

2.

Moments are computed with respect to the section center defined by the parameter IFRAME and expressed in the local section frame.

3.

Normal force is the component normal to the XY plane of the section. The tangential force is the component in the plane of the section.

4.

For CID > 0: G0, G1, G2 blank – the local system of the section is built from the grid points defining the CORD1R or CORD3R. The element set is created automatically from the elements intersected by the xyplane of CID.

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OptiStruct 13.0 Reference Guide 1999 Proprietary Information of Altair Engineering

The grid set is created automatically from the grid points of the intersected elements on the positive z-axis defined by the xy-plane plane of the frame. 5.

This card is represented as an interface in HyperMesh.

2000 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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SENSOR Bulk Data Entry SENSOR – Sensor Definition Description Defines a sensor for geometric nonlinear analysis. Sensors may be used to activate loads (see NLOAD1). Format (1)

(2)

(3)

(4)

(5)

SENSOR

SID

STYPE

DELAY

NAC C

(6)

(7)

(8)

(9)

(10)

Continuation lines if STYPE = ACCEL (number of continuation lines = NACC) AID1

DIR1

AMIN1

TMIN1

AID2

DIR2

AMIN2

TMIN2

…

…

Continuation line if STYPE = DIST G1

G2

DMIN

DMAX

Continuation line if STYPE = SENS, AND, OR SID1

SID2

Continuation line if STYPE = NOT SID1

Continuation line if STYPE = INTER C ID

Altair Engineering

OptiStruct 13.0 Reference Guide 2001 Proprietary Information of Altair Engineering

Continuation line if STYPE = RWAL RWID

Example

(1)

(2)

(3)

(4)

SENSOR

100

AC C EL

1

7

X

500.0

(5)

(6)

(7)

(8)

(9)

(10)

0.03

Field

Contents

SID

Unique sensor identification number. No default (Integer > 0)

STYPE

Sensor type. May be one of: TIME – Start Time ACCE – Accelerometer DIST – Nodal distance SENS – Activation with sensor SID1, deactivation with sensor SID2 INTER – Interface activation and deactivation RWAL – Rigid wall activation and deactivation AND – ON as long as sensors SID1 and SID2 are ON NOT – ON as long as sensor SID1 is OFF OR – ON as long as sensors SID1 and SID2 are ON No default (ACCEL, AND, DIST, INTER, NOT, OR, RWAL, SENS, or TIME)

DELAY

Time delay. (Real > 0)

NACC

Number of accelerometers ACCEL. (0 < Integer < 6)

AID#

Accelerometer identifier, references the ID of an ACCLR bulk data entry. (Integer > 0)

2002 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Field

Contents

DIR#

Direction of accelerometer #. May be one of: X – X direction Y – Y direction Z – Z direction

XY – XY plane

YZ – YZ plane

ZX – ZX plane

XYZ – total acceleration No default (X, Y, Z, XY, XZ, YZ, or XYZ) AMIN#

Minimum absolute value for acceleration for accelerometer #. (Real > 0)

TMIN#

Minimum duration of AMIN for accelerometer #. (Real > 0)

G1

Grid ID 1. (Integer > 0)

G2

Grid ID 2. (Integer > 0)

DMIN

Distance minimum. (Real > 0)

DMAX

Distance maximum. (Real > 0)

SID1

Activation sensor identifier, references the ID of another SENSOR bulk data entry. (Integer > 0)

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OptiStruct 13.0 Reference Guide 2003 Proprietary Information of Altair Engineering

Field

Contents

SID2

Deactivation sensor identifier, references the ID of another SENSOR bulk data entry. (Integer > 0)

CID

Contact identifier, references the ID of a CONTACT bulk data entry. (Integer > 0)

RWID

Rigid Wall identifier, references the ID of a RWALL bulk data entry. (Integer > 0)

Comments 1.

A sensor can only be activated once.

2.

For STYPE=TIME, the sensor is activated after the time delay (DELAY).

3.

For STYPE=ACCE, the sensor is activated if one of the accelerometers gives an acceleration greater than AMIN during a time greater than TMIN. The time of activation of the sensor is the time at which the above criteria is first met plus the time delay (DELAY).

4.

For STYPE=DIST, the sensor is activated once the distance between G1 and G2 moves outside the allowable range (between DMIN and DMAX). The time of activation of the sensor is the time at which the above criteria is first met, plus the time delay (DELAY).

5.

For STYPE=SENS, the sensor is activated once the referenced sensor SID1 is activated. The minimum activation duration is given by the time delay (DELAY). After this minimum activation duration, the sensor is deactivated if referenced sensor SID2 is activated. If there is no SID2 referenced, then the sensor is deactivated after the time delay.

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6.

For STYPE=AND, the sensor is activated once both the referenced sensors (SID1 and SID2) are activated.

7.

For STYPE=OR, the sensor is activated once either of the referenced sensors (SID1 or SID2) are activated.

8.

For STYPE=NOT, the sensor is active whenever the referenced sensor SID1 is not active.

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OptiStruct 13.0 Reference Guide 2005 Proprietary Information of Altair Engineering

9.

For STYPE=INTER, the sensor is activated once the referenced contact (CID) is impacted. The sensor is deactivated if there is no impact during a time equal to the time delay (DELAY).

10. For STYPE=RWAL, the sensor is activated once the referenced rigid wall (RWID) is impacted. The sensor is deactivated if there is no impact during a time equal to the time delay (DELAY).

2006 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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SET Bulk Data Entry SET – Set Definition Description Defines a set of grids, elements, design variables, MBD entities, mode numbers, frequencies or times for reference by other input definitions. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SET

SID

TYPE

SUBTYPE/ OPERATOR

ID1/ MODE1/ REAL1/ NAME1/ SID1/ X1/G1/ ALL

ID2/ MODE2/ REAL2/ NAME2/ SID2/ Y1

ID3/ MODE3/ REAL3/ NAME3/ SID3/ Z1

ID4/ MODE4/ REAL4/ NAME4/ SID4/ X2/G2

ID5/ MODE5/ REAL5/ NAME5/ SID5/ Y2

ID6/ MODE6/ REAL6/ NAME6/ SID6/ Z2

ID7/ MODE7/ REAL7/ NAME7/ SID7

ID8/ MODE8/ REAL8/ NAME8/ SID8

ID9/ MODE9/ REAL9/ NAME9/ SID9

…

…

…

…

…

…

…

…

…

(10)

Alternate Format for ID Ranges (1)

(2)

(3)

(4)

SET

SID

TYPE

SUBTYPE

ID1

THRU

ID2

ID7

…

ENDTHRU

(5)

(6)

(7)

(8)

(9)

EXC EPT

ID3

ID4

ID5

ID6

(10)

…

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OptiStruct 13.0 Reference Guide 2007 Proprietary Information of Altair Engineering

Example 1 The following set contains the grids 1, 17, 22, 23, 29, 33, 35, 48, 88, 93 and 102. It is defined using a simple ID list (assuming that these GRID cards are present in the Bulk Data). (1)

(2)

(3)

(4)

SET

56

GRID

LIST

88

93

17

33

102

22

(5)

(6)

(7)

(8)

(9)

1

23

29

35

48

(10)

Example 2 The following set contains the elements 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 33, 34, 34, 35, 36, 37, 38, 41, 42, 43, 44, 45, 94, 95, 96. 97, 98, 99, 106, 107, 108, 109, 110, 111, 120, 121 and 125. It is defined using a combination of ID ranges and lists. (1)

(2)

(3)

(4)

(5)

(6)

(7)

SET

56

ELEM

LIST

11

THRU

22

33

THRU

45

EXC EPT

39

40

94

THRU

111

EXC EPT

100

101

104

105

ENDTHR U

120

121

125

(8)

(9)

102

103

(10)

Example 3 The following set includes any element included in sets 29, 30 or 31. It is defined as Boolean set.

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(1)

(2)

(3)

(4)

SET

50

ELEM

OR

29

30

31

(5)

(6)

(7)

(8)

(9)

(10)

Example 4 The following set defines GRID/Component list; intended for use by PFMODE. (1)

(2)

(3)

SET

11

GRIDC

12

T1

(4)

(5)

(6)

(7)

15

R2

128

T3

(8)

(9)

(10)

(8)

(9)

(10)

(9)

(10)

Example 5 The following set defines list of strings. (1)

(2)

(3)

SET

11

LABEL

LABEL1

LABEL2

(4)

(5)

(6)

(7)

TOP

UPPER

LOWER

LEFT

Example 6 The following set defines list of all elements with specific properties. (1)

(2)

(3)

(4)

(5)

(6)

SET

11

ELEM

PROP

EXC EPT

PHSELL

1

12

15

thru

128

(7)

(8)

555

Example 7

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OptiStruct 13.0 Reference Guide 2009 Proprietary Information of Altair Engineering

The following set outputs all of the grids on PLOTEL. (1)

(2)

(3)

(4)

SET

ID

GRID

ELTYPE

(5)

(6)

(7)

(8)

(9)

(10)

PLOTEL

Field

Contents

SID

Unique set identification number. See comment 1. No default (Integer > 0)

TYPE

Identifies what type of entities the set is comprised of. See comment 2 for description of the types. No default (GRID, ELEM, RIGID, GRIDC, DESVAR, MODE, FREQ, TIME, LABEL or PLY)

SUBTYPE

Indicates how the set is defined. See comment 2 for description of subtypes. Default = LIST (LIST, BBOX, PROP, MAT or ELTYPE)

OPERATOR

Operators supported in defining Boolean sets (see comments 4, 5, and 6.) No default (OR, AND, NOT, MINUS)

ID#

ID list. Only valid for certain combinations of TYPE and SUBTYPE. The entity to which the ID corresponds depends on the TYPE and SUBTYPE of the set (see comment 2). ID ranges may be used in combination with ID lists. The keywords EXCEPT and THRU are used to define ID ranges. The keyword ENDTHRU identifies the end of an ID range and is required if an ID list is to follow where the first value is within the previous range. ID lists following EXCEPT must be in ascending order and must exist within the previous range. No default (Integer > 0)

MODE#

Mode number list. Only valid when TYPE is MODE (see comment 2). Mode number ranges may be used in combination with Mode number lists. The same rules apply as for ID ranges. No default (Integer > 0)

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Field

Contents

REAL#

Real value list. Only valid when TYPE is FREQ or TIME (see comment 2). No default (Real)

NAME#

Keyword list. Only valid for certain combinations of TYPE and SUBTYPE. The keyword EXCEPT is allowed only as the first entry in a keyword list. Default = Undefined (see comment 2)

SID#

Identification number of another SET definition. Used in defining Boolean sets. Only valid when OPERATOR is defined in SUBTYPE/OPERATOR field (see comments 4, 5, 6, and 7). No default (Integer > 0 or )

X1, Y1, Z1 X2, Y2, Z2

X, Y & Z coordinates of two opposing corners of a cuboid. Only valid when SUBTYPE is BBOX (see comment 2). No default (Real)

G1, G2

Grid ID’s (G1, G2) can be used instead of (X1, Y1, Z1), (X2, Y2, Z2) data (see field descriptions above). G1, G2 should be defined in the basic coordinate system (CP field on the GRID entries should be blank).

ALL

Keyword used for ID lists to indicate that all IDs of the appropriate entity type are to be included in the set. Only valid in first field of ID list. May be followed by keyword EXCEPT (see below).

THRU

Keyword used for ID ranges to indicate that all IDs between the preceding ID and the following ID are to be included in the set. Definition of range may contain list of exceptions in the following form: N1 THRU N2 EXCEPT N3 N4 ... ENDTHRU where N1 < N3 < N4... < N2; N1 < N2

EXCEPT

Keyword used for ID ranges and keyword lists to indicate that the following IDs or keywords are to be excluded from the set. Only valid in first field for keyword lists. When ALL is given as the first entry for an ID list, EXCEPT may be given as the second entry, in which case all subsequent IDs are excluded from the set of ALL entities of the defined TYPE.

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OptiStruct 13.0 Reference Guide 2011 Proprietary Information of Altair Engineering

Field

Contents

ENDTHRU

Optional keyword used after EXCEPT to indicate the end of an excluded ID list definition.

Comments 1.

SID must be unique with respect to all other SET definitions (regardless of type). It must also be unique with respect to any SURF entries and any legacy SET/PSET I/O Options definitions.

2.

The following table describes subtype combinations and the set TYPEs for which they are valid. TYPE

SUBTYPE

Description

GRID

LIST or undefined

This is a set of grids - structural grids (GRID) or scalar points (SPOINT) - defined either as a simple list of grid IDs, or as some combination of ranges of grid IDs and lists of grid IDs.

BBOX

This is a set of grids defined by a bounding box. The fields X1, Y1, and Z1 provide the coordinates of one corner and X2, Y2, and Z2 the coordinates of an opposing corner of a cuboid. All grids contained within this cuboid are included in the set. The bounding box can also be defined using the G1 and G2 fields instead of (X1, Y1, and Z1) and (X2, Y2, and Z2), respectively.

ELEM

LIST or undefined

This is a set of elements defined either as a simple list of element IDs, or as some combination of ranges of element IDs and lists of element IDs.

BBOX

This is a set of elements defined by a bounding box. The fields X1, Y1, and Z1 provide the coordinates of one corner and X2, Y2, and Z2 the coordinates of an opposing corner of a cuboid. All elements whose centroids are contained within this cuboid are included in the set. The bounding box can also be defined using the G1 and G2 fields instead of (X1, Y1, and Z1) and (X2, Y2, and Z2), respectively.

PROP

This is a set of elements defined in one of the following ways: 1.

Through a list of property IDs, or some combination

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TYPE

SUBTYPE

Description of ranges of property IDs and lists of property IDs. If multiple properties have the same ID (as PBAR and PSHELL may), they are all considered. All elements referencing the selected properties are included in the set. 2.

Through a list of property types. All elements referencing properties of the listed type (PBAR, PCOMP, PSHELL, and so on) are included in the set.

3.

Through a list of excluded property types. All elements except those referencing properties of the listed type, following the keyword EXCEPT, are included in the set.

4.

List of property types or list of excluded property types may be followed by some combination of ranges of property IDs and lists of property IDs. All elements referencing properties satisfying both requirements (type and ID) are included in (or accepted from) the set.

MAT

This is a set of elements defined through a list of material IDs, or some combination of ranges of material IDs and lists of material IDs. All elements referencing properties, that in turn reference the selected materials, are included in the set.

ELTYPE

This is a set of elements defined in one of the following ways: 1.

Through a list of element types. All elements of the listed type (CQUAD4, CHEXA, CBEAM, and so on) are included in the set.

2.

Through a list of excluded element types. All elements except those of the listed type, following the keyword EXCEPT, are included in the set.

In addition to all valid element types, the following element type groupings may be used:

Altair Engineering

SOLID

for CTETRA, CPYRA, CPENTA and CHEXA elements referencing structural property definitions

FLAT

for CQUAD4, CQUAD8, CTRIA3 and CTRIA6 elements.

OptiStruct 13.0 Reference Guide 2013 Proprietary Information of Altair Engineering

TYPE

SUBTYPE

Description SHELL

for FLAT elements referencing properties with non-zero MID2.

MEMBRANE for FLAT elements referencing properties with zero MID2. BEAM

for CBAR and CBEAM elements.

ROD

for CONROD and CROD elements.

FLUID

for CTETRA, CPYRA, CPENTA and CHEXA elements referencing fluid property definitions.

For rigid elements (RROD, RBAR, RBE1, RBE2 and RBE3). See RIGID below. RIGID

LIST or undefined

This is a set of Rigid elements defined either as a simple list of Rigid element IDs, or as a combination of ranges of Rigid element IDs and lists of Rigid element IDs.

GRIDC

LIST or undefined

This is a set of GRID/Component pairs.

DESVAR

LIST or undefined

This is a set of design variables defined either as a simple list of design variable IDs, or as some combination of ranges of design variable IDs and lists of design variable IDs.

MODE

LIST or undefined

This is a set of mode numbers defined as a simple list of mode numbers, or as some combination of ranges of mode numbers and lists of mode numbers.

FREQ

LIST or undefined

This is a set of real values representing frequencies defined simply as a list of real values.

TIME

LIST or undefined

This is a set of real values representing times defined simply as a list of real values.

LABEL

LIST or undefined

List of arbitrary labels. Each label must start with a letter and contain only letters or digits.

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TYPE

SUBTYPE

Description

PLY

LIST or undefined

This is a set of ply ID’s defined in the PLY or PCOMPG data entries.

3.

SET definitions using IDs may refer to non-existing entities. This is allowed, but the actual SET will contain only grids or elements which are actually present in the structure.

4.

The Boolean operators OR, AND, NOT and MINUS are recognized for SET combinations. These operators are described here: Operator Description OR

An entity is included in the SET if it is included in at least one of the constituent sets. Is the entity in set1 or set2 or set3 …?

AND

An entity is included in the SET if it is included in all of the listed sets. Is the entity in set1 and set2 and set3 …?

NOT

An entity is included in the SET if it is not included in the listed set. Is the entity in set1?; if not then it is included in this set. Only one set may be listed for the NOT operator.

MINUS

An entity is included in the SET if it is included in the first set, but not in the second set. Only two sets may be listed for when this operator is used.

5.

Boolean SET definitions can only be used when all listed sets are of the same TYPE.

6.

Boolean SET definitions can reference other Boolean sets, but circular references must be avoided. Boolean SET can be defined only for GRID, ELEM, or RIGID set types.

7.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on SET entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN bulk data entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references. The SET bulk data entry can be used in the global part to reference SET’s defined within different parts. These SET entries in the global part can contain fully qualified references to part-specific SET data only if logical operators (OPERATOR field) are used. For example: The following SET entry exists in part “A”: BEGIN, FEMODEL, A SET, 29, ELEM, LIST

Altair Engineering

OptiStruct 13.0 Reference Guide 2015 Proprietary Information of Altair Engineering

15 THRU 30 … END, FEMODEL, A Referencing SET, 29 in the global part “G”: BEGIN, FEMODEL, G SET, 78, ELEM, OR A.29 … END, FEMODEL, G 8.

This card is represented as a set in HyperMesh.

2016 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SET1 Bulk Data Entry SET1 – Set Definition Description Defines a list of structural grid points or element identification numbers. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SET1

SID

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

etc.

(10)

Example 1

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SET1

3

31

62

93

124

16

17

18

(10)

19

Example 2

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SET1

6

29

32

THRU

50

61

THRU

70

17

57

Field

Contents

SID

Unique identification number.

(10)

(Integer > 0)

Altair Engineering

OptiStruct 13.0 Reference Guide 2017 Proprietary Information of Altair Engineering

Field

Contents

IDi

List of structural grid point or element identification numbers. (Integer > 0 or "THRU, ENDTHRU, and EXCEPT"; for the "THRU" option, ID1 < ID2)

Comments 1.

When using "THRU," missing ID's are ignored.

2.

All set ID’s must be unique for all bulk data SET, SET1, SET3, and solution control SET data.

3.

The use of keywords THRU, ENDTHRU, and EXCEPT are allowed.

4.

This card is represented as a set in HyperMesh.

2018 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SET3 Bulk Data Entry SET3 – Set Definition Description Defines a set of grids or elements. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SET3

SID

TYPE

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

etc.

(10)

Example 1

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SET3

1

PROP

11

12

13

15

18

21

(10)

Alternate Format and Example (1)

(2)

(3)

(4)

(5)

(6)

SET3

SID

TYPE

ID1

"THRU"

ID2

SET3

33

GRID

20

THRU

60

Field

Contents

SID

Unique identification number.

(7)

(8)

(9)

(10)

(Integer > 0) TYPE

Set type (Character). Valid options include "GRID," "ELEM," and "PROP."

Altair Engineering

OptiStruct 13.0 Reference Guide 2019 Proprietary Information of Altair Engineering

Field

Contents

IDi

Identifiers of grid points, elements, or properties. (Integer > 0)

Comments 1.

If the set type is PROP, then a list of elements associated with the property ID's listed is created.

2.

All set ID’s must be unique for all bulk data SET, SET1, SET3, and solution control SET data.

3.

The use of keywords THRU, ENDTHRU, and EXCEPT are allowed.

4.

This card is represented as a set in HyperMesh.

2020 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SLOAD Bulk Data Entry SLOAD – Static Scalar Load Description Defines concentrated static loads on scalar, grid or fluid points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

SLOAD

SID

S1

F1

S2

F2

S3

F3

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

SLOAD

21

3

4.5

4

29.0

Field

Contents

SID

Load set identification number.

(7)

(8)

(9)

(10)

No default (Integer > 0) S#

Identification number of a scalar, grid or fluid point. No default (Integer > 0)

F#

Load magnitude. No default (Real)

Comments 1.

SLOAD may be referenced as the EXCITEID on an ACSRCE bulk data entry.

2.

Up to three loads may be defined on a single entry.

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OptiStruct 13.0 Reference Guide 2021 Proprietary Information of Altair Engineering

SOLVTYP Bulk Data Entry SOLVTYP – Solver Selection for Static Analysis and Geometric Nonlinear Implicit Analysis Description This bulk data entry can be used to define the solver type to be used for linear and nonlinear static analysis and geometric nonlinear implicit analysis. Format (1)

(2)

(3)

(4)

SOLVTYP

SID

SOLVER

(5)

(6)

(7)

(8)

(9)

(10)

Continuation line for SOLVER = PCG, MIXED and AUTO PC ON

MAXIT

ITOL

TOL

Continuation line for SOLVER = MUMPS ORDM

Example

(1)

(2)

(3)

SOLVTYP

4

PC G

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

FAI

Alternate Example

(1)

(2)

(3)

SOLVTYP

1

MUMPS

2022 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

PORD

Field

Contents

SID

Unique set identification number. No default (Integer > 0)

SOLVER

Indicates the solver to be used. See comments 2, 3 and 4. BCS – Boeing Solver (direct solver). MUMPS – MUMPS Solver (direct solver). PCG - Preconditioned Conjugate Gradient (iterative solver). MIXED – Mixed solver using both BCS and PCG. AUTO – Select automatic between BCS and PCG. Default = BCS - for linear static analysis and geometric nonlinear implicit dynamic analysis (ANALYSIS = IMPDYN); Default = MIXED - for geometric nonlinear implicit static analysis (ANALYSIS = NLGEOM).

PCON

Indicates the type of pre-conditioner to be used. NO - No Pre-conditioner DJ - Diagonal Jacobi ICH - Incomplete Cholesky SICH - Stabilized Incomplete Cholesky FAI - Factored Approximate Inverse Default = FAI (Character)

MAXIT

Maximum number of iterations Default = Number of degrees-of-freedom of the system (Integer > 0 or blank)

ITOL

Convergence criteria for preconditioned iterative solver. RROM - Relative residual of original matrices ||r|| < TOL * ||b|| RRPM1 - Relative residual of preconditioned matrices ||r|| < TOL * ||

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OptiStruct 13.0 Reference Guide 2023 Proprietary Information of Altair Engineering

Field

Contents b|| RRPM2 - Relative residual of preconditioned matrices ||r|| < TOL * || A|| * ||x|| If the solver solves Ax = b, the residual is r = Ax - b. Default = RRPM2 (Character)

TOL

Convergence tolerance. Default = 1.0e-5 for ITOL = RROM, RRPM1 or single precision machine precision (3.0e-8) for ITOL = RRPM2 (Real > 0 or blank)

ORDM

Ordering method for the MUMPS solver (see comments 8 and 9). AMD – Approximate minimum degree method (AMD) PORD – PORD package METIS – METIS package AUTO – Automatically select between PORD and METIS. Default = METIS (Character)

Comments 1.

SOLVTYP bulk data must be referenced by a SOLVTYP subcase statement. It only applies to linear static subcases, geometric nonlinear implicit static analysis (ANALYSIS=NLGEOM) and geometric nonlinear implicit dynamic analysis (ANALYSIS=IMPDYN).

2.

In optimization of linear static subcases, if iterative solver is selected, and if the responses DRESP1, RTYPE = DISP, LAMA, STRESS, STRAIN, CSTRESS, CSTRAIN, CFAILURE, or FORCE are present the solver is automatically reverted to the direct solver.

3.

MUMPS is the default non-symmetric solver for nonlinear contact analysis when friction is present; it is also available as an optional symmetric solver for static runs. MUMPS is SMP parallelized. Generally, MUMPS performance is similar to or better than the performance of BCS, especially for 2D models. MUMPS stands for “Multifrontal Massively Parallel sparse direct Solver”. For more details, see http://graal.ens-lyon.fr/MUMPS/index.php?page=home

4.

Overview of default settings and options for the SOLVER field:

2024 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SOLVER =BCS

SOLVER =MUMPS

SOLVER =PCG

SOLVER =MIXED

SOLVER =AUTO

Linear static analysis

Default

Optional

Optional

N/A

N/A

Nonlinear static analysis

Default

Optional

N/A

N/A

N/A

Nonlinear contact analysis (when friction is present)

Optional

Default

N/A

N/A

N/A

Geometric nonlinear implicit static analysis (NLGEOM)

Optional

N/A

Optional

Default

Optional

Geometric nonlinear implicit dynamic analysis (IMPDYN)

Default

N/A

Optional

Optional

Optional

Subcase type

5.

The iterative solver is a preconditioned conjugate gradient solver. A Factored Approximate Inverse Preconditioner is the default method. This solver is also SMP parallelized.

6.

The performance of the iterative solver depends on the conditioning of the stiffness matrix. For compact solid models, the iterative solver may perform considerably better than the direct solver in terms of memory usage and elapsed times for a single linear static subcase. In the case of multiple linear static subcases, the iterative solver may perform worse than the direct solver. The breakeven point is at about 4-6 subcases. The performance depends on model, hardware, operating system, and potentially the system load. The performance may be below expectations on Itanium-based computers.

7.

When the automatic solver option (SOLVER = AUTO) has been chosen, PCG is used first, the solver will be changed automatically to direct solver (BCS) if PCG performance is estimated slower than direct solver. In this case, direct solver will be used for the remainder of the run.

8.

ORDM = PORD provides better performance for a shell-type model.

9.

For further information about the MUMPS solver ordering method (ORDM) options, refer to the MUMPS 4.10 manual.

10. This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 2025 Proprietary Information of Altair Engineering

SPC Bulk Data Entry SPC – Single-Point Constraint Description Defines sets of single-point constraints, enforced displacements for static analysis, and thermal boundary conditions for heat transfer analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

SPC

SID

G

C

D

G

C

D

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

SPC

2

32

436

0.0

(6)

(7)

Field

Contents

SID

Identification number of single-point constraint set.

(8)

(9)

(10)

(Integer > 0) G

Grid or scalar point identification number. (Integer > 0 or )

C

Component numbers. (Integer zero or blank for scalar points, or up to six unique digits (0 < digit < 6) may be placed in the field with no embedded blanks for grid points. The components refer to the coordinate system referenced by the grid points.)

D

Value of enforced displacement for all coordinates designated by G and C. (Real)

Comments

2026 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

1.

The degree-of-freedom declared dependent on this entry may not be: Included in a single point constraint (SPC or SPC1). Declared a dependent degree-of-freedom on any RBAR, RBE1, RBE2, or RROD entry. Declared a dependent degree-of-freedom on an MPC set referenced in the same subcase.

2.

Single-point forces of constraint are recovered during stress data recovery.

3.

Up to twelve single-point constraints may be defined on a single entry.

4.

Continuations are not allowed.

5.

SPC degrees-of-freedom may be redundantly specified as permanent constraints on the GRID entry.

6.

For static analyses, SPCs can be used to define enforced displacements.

7.

For static and dynamic analyses, when the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/ C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

8.

For linear steady-state heat transfer analysis, an SPC may be used to define a temperature boundary condition. For thermal boundary conditions, the component should be 0 or blank when the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK(default) or STRICT. When SPSYNTAX is set to MIXED 1 is also accepted as the component.

9.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on SPC entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

10. This card is represented as a constraint load in HyperMesh.

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OptiStruct 13.0 Reference Guide 2027 Proprietary Information of Altair Engineering

SPC1 Bulk Data Entry SPC1 – Single-Point Constraint, Alternate Form Description Defines sets of single-point constraints and thermal boundary conditions. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SPC 1

SID

C

G1

G2

G3

G4

G5

G6

G7

G8

G9

-etc.-

(7)

(8)

(9)

(10)

Alternate Format (1)

(2)

(3)

(4)

(5)

(6)

SPC 1

SID

C

G1

"thru"

G2

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SPC 1

3

2

7

3

10

9

6

5

THRU

8

33

71

2

2

87

“thru”

SPC 1

(10)

100

Field

Contents

SID

Identification number of single-point constraint set. (Integer > 0)

2028 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

C

Component number. (Integer zero or blank for scalar points, or up to six unique digits (0 < digit < 6) may be placed in the field with no embedded blanks for grid points. The components refer to the coordinate system referenced by the grid points.)

Gi

Grid or scalar point identification numbers. (Integer > 0)

Comments 1.

The degree-of-freedom declared dependent on this entry may not be: Included in another single-point constraint (SPC or SPC1). Declared a dependent degree-of-freedom on any RBAR, RBE1, RBE2, or RROD entry. Declared a dependent degree-of-freedom on an MPC set referenced in the same subcase.

2.

Note that enforced displacements are not available via this entry.

3.

Any number of continuations may appear.

4.

Multiple “thru” sequences can be used on a single card, and can span across continuation lines.

5.

SPC degrees-of-freedom may be redundantly specified as permanent constraints on the GRID entry.

6.

If the "thru" comment is used, G1 and G2 must exist, but the grid points between G1 and G2 are not required to exist.

7.

For static and dynamic analyses, when the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or MIXED, it is allowed that when grid lists are provided for a given component, that the grid references be either scalar points (SPOINT) or structural grid points (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When SPSYNTAX is set to STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid references are to scalar points (SPOINT), and that the component be > 1 when the grid references are to structural grid points (GRID). When the component is greater than 1, the grid references must always be a structural grid (GRID).

8.

For linear steady-state heat transfer analysis, SPC1 may be used to define temperature boundary conditions; however, unless paired with an SPCD entry, the enforced temperature is 0.0. For thermal boundary conditions, the component should be 0 or blank when the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT. When SPSYNTAX is set to MIXED, 1 is also accepted as the component.

9.

This card is represented as a constraint load in HyperMesh.

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OptiStruct 13.0 Reference Guide 2029 Proprietary Information of Altair Engineering

SPCADD Bulk Data Entry SPCADD – Single-Point Constraint Set Combination Description Defines a single-point constraint set as a union of single-point constraint sets defined via SPC or SPC1 entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SPC ADD

SID

S1

S2

S3

S4

S5

S6

S7

S8

S9

(10)

-etc-

Example

(1)

(2)

(3)

(4)

(5)

(6)

SPC ADD

101

3

2

9

1

(7)

Field

Contents

SID

Identification number for new single-point constraint set.

(8)

(9)

(10)

(Integer > 0) Si

Identification numbers of single-point constraint sets defined via SPC or SPC1 entries. (Integer > 0 or ) See comment 5.

Comments 1.

The Si field should not reference the identification number of a single-point constraint set defined by another SPCADD entry.

2.

The Si values must be unique.

2030 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

3.

SPCADD entries take precedence over SPC or SPC1 entries. If both have the same set ID, only the SPCADD entry is used.

4.

If all Si are non-existent the solver will exit with an error termination.

5.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on SPCADD entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

6.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 2031 Proprietary Information of Altair Engineering

SPCD Bulk Data Entry SPCD – Enforced Motion Value Description Defines an enforced displacement value for static analysis, an enforced displacement, velocity or acceleration for dynamic analysis and a thermal boundary condition for heat transfer (or transient heat transfer) analysis. It can also be used to define the EXCITEID field (Amplitude “A”) of dynamic loads in RLOAD1, RLOAD2, TLOAD1 and TLOAD2 bulk data entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

SPC D

SID

G

C

D

G

C

D

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

SPC D

100

32

436

-2.6

5

1

+2.9

Field

Contents

SID

Identification number of a static load set.

(9)

(10)

(Integer > 0) G

Grid or scalar point identification number. (Integer > 0 or ) See comment 9.

C

Component numbers in the global coordinate system. (6 > Integer > 0; up to six unique such digits may be placed in the field with no embedded blanks)

D

Value of enforced motion for all grids and components designated by G and C.

2032 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents (Real)

Comments 1.

The degree-of-freedom (G and C) referenced on this entry must also be referenced on an SPC or SPC1 bulk data entry and selected by the SPC subcase information command in the same subcase.

2.

For use in linear static and linear steady state heat transfer analyses, the load set identification number must be selected by the LOAD subcase information command.

3.

Values of D will override the values specified on an SPC bulk data entry if selected for use in the same subcase.

4.

For use in dynamic analysis, the load set identification number must be referenced by the EXCITEID field of an RLOAD1, RLOAD2, TLOAD1, or TLOAD2 bulk data entry that has enforced motion specified in its TYPE field.

5.

The bulk data LOAD combination entry cannot combine an SPCD load.

6.

This method of applying enforced displacements in static analysis is equivalent to that of using an SPC entry. For static and dynamic analyses, when the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/ component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/ component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

7.

The SPCD units for rotational degrees of freedom is radians.

8.

For use in transient heat transfer analysis, the load set identification number must be referenced by the EXCITEID field of a TLOAD1 or TLOAD2 bulk data entry that has enforced temperature specified in its TYPE field (TYPE = 1).

9.

Supported local entries in specific parts can be referenced by the use of “fully qualified references” on SPCD entries in the model. A fully qualified reference (“PartName.number”) is similar to the format of a numeric reference. “PartName” is the name of the part that contains the referenced local entry (part names are defined on the BEGIN Bulk Data Entry in the model). “number” is the identification number of a referenced local entry in the part “PartName”. See Parts and Instances in the User’s Guide for detailed information on the use of fully qualified references.

10. This card is represented as a constraint load in HyperMesh.

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OptiStruct 13.0 Reference Guide 2033 Proprietary Information of Altair Engineering

SPOINT Bulk Data Entry SPOINT – Scalar-Point Description Defines scalar points. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SPOINT

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

(5)

(6)

(7)

(8)

(9)

(10)

Alternate Format (1)

(2)

(3)

(4)

SPOINT

ID1

"THRU"

ID2

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SPOINT

3

18

1

4

16

2

6

THRU

8

47

99

THRU

128

Field

Contents

ID#

Scalar point identification number.

(10)

No default (0 < Integer) Comments 1.

A scalar point defined by its appearance on the connection entry for a scalar element (see the CELAS, CMASS, and CDAMP entries) need not appear on an SPOINT entry.

2034 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

2.

All scalar point identification numbers must be unique with respect to all other scalar and grid points.

3.

This entry is used primarily to define scalar points appearing in single-point or multipoint constraint equations to which no scalar elements are connected.

4.

If the alternate format is used, all scalar points ID1 through ID2 are defined. ID1 must be less than ID2.

5.

Alternate format can be combined with regular format, and it can span across continuation lines.

6.

This card is represented as a node in HyperMesh.

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OptiStruct 13.0 Reference Guide 2035 Proprietary Information of Altair Engineering

STACK Bulk Data Entry STACK – Stacking Information for Ply-Based Composite Definition Description Defines the stacking information and stacking sequence for ply-based composite definition. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

STAC K

ID

LAM

PLYID1

PLYID2

PLYID3

PLYID4

PLYID5

PLYID6

PLYID7

…

(10)

Optional continuation lines for substack definitions: SUB

SID1

SNAME1

SPLYID1 1

SPLYID1 2

SPLYID1 3

SPLYID1 4

SPLYID1 5

SPLYID1 6

SPLYID1 7

...

...

...

...

...

...

...

Optional continuation lines for interface definitions: INT

IPLYID11 IPLYID12

Example 1

Defines a stack consisting of 8 plies with the SMEAR option (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

STAC K

1

SMEAR

1010100

1020100

1010200

1020200

1010300

1020300

1010400

1020400

(10)

Example 2

2036 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Defines a stack with substack and interface information. They ply layout is shown below.

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

STAC K

2

SUB

1

top

11

12

13

14

SUB

2

left

21

22

23

24

SUB

3

right

31

32

33

34

SUB

4

middle

41

42

43

INT

14

21

INT

14

31

INT

21

41

INT

43

31

Altair Engineering

(9)

(10)

OptiStruct 13.0 Reference Guide 2037 Proprietary Information of Altair Engineering

Field

Contents

ID

Unique stack identification number. No default (Integer > 0)

LAM

Laminate option. If blank, all plies must be specified and all stiffness terms are developed. The following options are supported: SYM:

Only plies on the bottom half of the composite lay-up need to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top.

MEM:

All plies must be specified, but only membrane terms are developed.

BEND:

All plies must be specified, but only bending terms are developed.

SMEAR:

All plies must be specified, stacking sequence is ignored, and MID1 is set equal to MID2 on the derived equivalent PSHELL, while MID3, MID4, TS/T, and 12I/T**3 are set to zero.

SMEARZ0:

All plies must be specified, stacking sequence is ignored. While the laminate is still considered to be made of homogenized (smeared) material, the effect of offset Z0 is taken into account. Hence, if Z0 is not equal to -0.5*Thick, the equivalent PSHELL will include MID1, MID2 and MID4. MID3 is still set to zero, that is no transverse shear deformation is considered.

SMCORE:

All plies must be specified. The last ply specifies core properties and the previous plies specify face sheet properties. The face sheet properties are calculated without regard for stacking sequence; half of the total face sheet thickness is then placed on top of the core, and half is placed on the bottom, to produce a symmetric laminate. Stiffness of the core is ignored while its density is included in inertia calculations.

SYMEM:

Only plies on the bottom half of the composite lay-up need to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top. Only membrane terms are developed for the full laminate.

SYBEND:

Only plies on the bottom half of the composite lay-up need to be specified. These plies are automatically symmetrically reflected to the top half of the composite and given consecutive numbers from bottom to top. Only bending terms are developed for the full laminate.

SYSMEAR:

Only plies on the bottom half of the composite lay-up need to be specified. These plies are automatically symmetrically reflected to the

2038 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents top half of the composite and given consecutive numbers from bottom to top. Stacking sequence is ignored, and MID1 is set equal to MID2 on the derived equivalent PSHELL, while MID3, MID4, TS/T and 12I/ T**3 are set to zero. Default = blank, that is all plies must be specified (SYM, MEM, BEND, SMEAR, SMCORE, SYMEM, SYBEND or SYSMEAR)

PLYID#

PLY identification number. No default (Integer > 0)

SUB

SUB flag indicating that substack data is to follow.

SID#

Substack identification number. No default (Integer > 0)

SNAME #

Substack user-defined name.

SPLYID #

PLY identification number.

INT

INT flag indicating that interface data is to follow.

No default (Character)

No default (Integer > 0)

IPLYID# PLY identification number. No default (Integer > 0) Comments 1.

The STACK card is used in combination with the PCOMPP and PLY cards to create composite properties through the ply-based definition.

2.

Plies are listed from the bottom surface upward, in respect to the element’s normal direction. In the image below, (a) shows the stacking sequence for a non-symmetrical laminate, and (b) shows the stacking sequence for a symmetrical laminate.

Altair Engineering

OptiStruct 13.0 Reference Guide 2039 Proprietary Information of Altair Engineering

3.

For convenience, element output for the SMEAR and SMCORE options includes both homogenized shell stresses and individual ply stresses. However, because stacking sequence is ignored in these options, individual ply stresses will only be valid in cases of pure membrane deformation.

4.

Multiple instances of substack and interface continuations are allowed.

5.

This card is represented as a laminate in HyperMesh.

2040 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SUPORT Bulk Data Entry SUPORT – Fictitious Support Description Defines determinate reaction degrees-of-freedom in a free body. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SUPORT

ID1

C1

ID2

C2

ID3

C3

ID4

C4

(10)

Example

(1)

(2)

(3)

SUPORT

16

215

(4)

(5)

Field

Contents

ID#

Grid point identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) C#

Component numbers. No default (Any unique combination, with no embedded blanks, of the integers 1 through 6 for grid points; or 0 for scalar points)

Comments 1.

The SUPORT entry specifies reference degrees-of-freedom for rigid body motion. It is not intended to be used in place of a constraint (SPCi entry or PS on the GRID entry, for example).

2.

SUPORT and/or SUPORT1 entries are required to activate inertia relief unless PARAM, INREL, -2 is specified, then SUPORT and/or SUPORT1 entries are not required.

3.

Be careful not to spell SUPORT with two Ps.

Altair Engineering

OptiStruct 13.0 Reference Guide 2041 Proprietary Information of Altair Engineering

4.

Degrees-of-freedom specified on this entry cannot be defined as dependent degrees-offreedom in rigid body element or constrained in SPCi entry or PS on the GRID entry.

5.

An alternative to SUPORT is the SUPORT1 entry, which is requested by the SUPORT1 I/O Options and Subcase Information command.

6.

This card is represented as a constraint load in HyperMesh.

2042 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SUPORT1 Bulk Data Entry SUPORT1 – Fictitious Support, Alternate Form Description Defines determinate reaction degrees-of-freedom in a free body. The SUPORT1 bulk data entry must be requested in the I/O Options or Subcase Information sections by the SUPORT1 data selection command. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

SUPORT1

SID

ID1

C1

ID2

C2

ID3

C3

(9)

(10)

Example

(1)

(2)

(3)

(4)

SUPORT1

5

16

215

(5)

(6)

Field

Contents

SID

Set identification number. See comment 1.

(7)

(8)

(9)

(10)

No default (Integer > 0) ID#

Grid point identification number. No default (Integer > 0)

C#

Component numbers. No default (Any unique combination, with no embedded blanks, of the integers 1 through 6 for grid points; or 0 for scalar points)

Altair Engineering

OptiStruct 13.0 Reference Guide 2043 Proprietary Information of Altair Engineering

Comments 1.

SUPORT1 bulk data entries will not be used unless specifically selected in a subcase definition by the SUPORT1 subcase information entry.

2.

SUPORT bulk data entries are applied in all subcases.

3.

The SUPORT1 bulk data entry must be requested in the I/O Options or Subcase Information sections by the SUPORT1 data selection command. The degrees-of-freedom specified on SUPORT1 will be combined with those on the SUPORT entry.

4.

Be careful not to spell SUPORT with two Ps.

5.

Degrees of freedom specified on this entry cannot be defined as dependent degrees-offreedom in rigid body element or constrained in SPCi entry or PS on the GRID entry.

6.

This card is represented as a constraint load in HyperMesh.

2044 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SURF Bulk Data Entry SURF – Surface Definition Description Defines a face of a 2D or 3D element as part of a surface. Format (1)

(2)

(3)

(4)

(5)

SURF

SRFID

ELFAC E

EID1

GA1

GB1

NORMAL1

EID2

GA2

GB2

NORMAL2

EID3

...

...

...

...

...

(6)

(7)

(8)

(9)

(10)

Alternative Format (faceted surface) In this format, surface is represented as collection of 3- or 4-noded polygons (facets). Each facet is defined by 3 or 4 GRID IDs. (1)

(2)

(3)

(4)

(5)

SURF

SRFID

FAC E

GA1

GB1

GC 1

GD1

GA2

GB2

GC 2

GD2

GA3

...

...

...

...

...

Altair Engineering

(6)

(7)

(8)

(9)

(10)

OptiStruct 13.0 Reference Guide 2045 Proprietary Information of Altair Engineering

Alternative Format (SET Format) A surface may also be defined using a form of the SET bulk data entry. With this approach, the surface is composed of all selected 2D elements and the external faces of all selected 3D elements; that is, those faces that are not connected to any other 3D elements faces in the model. To use this format, the SURF keyword is used in place of the SET keyword and the TYPE must be ELEM. All methods for defining a set of type ELEM are valid for this form of surface definition. Refer to the SET bulk data entry. Field

Contents

SRFID

Surface identification number. No default (Integer > 0)

ELFACE

Flag indicating that the surface is composed of an element face.

EID#

2D or 3D element identification number. No default (Integer > 0)

GA#

Identification number of a grid point at the corner of the desired face of a 3D element. This field must be blank for 2D elements. Default = blank (Integer > 0, blank)

GB#

Optional grid point identification number. Used to identify face of 3D elements. See comment 1. Default = blank (Integer > 0, blank)

NORMAL Identifies the normal direction for a face of the surface. The normal of a face of a surface may be different from the normal of the underlying elements. 0: normal matches the normal of the underlying element. For 3D elements, this is pointing into the element. 1: normal direction is opposite of the underlying element. For 3D elements, this is pointing out of the element. Default = 0 (0 or 1) Comments 1.

GB is used to identify faces of solid elements based on the following table:

2046 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

For HEXA elements:

Identification number of a grid point at a corner of the desired face that is diagonally opposite GA.

For PENTA elements: Quad faces:

Tria faces:

2.

Identification number of a grid point at a corner of the desired face that is diagonally opposite GA. Leave blank.

For TETRA elements:

Identification number of a grid point at the corner opposite the desired face.

For PYRA elements:

Quad faces:

Leave blank

Tria faces:

GA and GB must specify the grids on the edge of the face that borders the quadrilateral face, and the grids must be ordered so that they define an inward normal using the right hand rule.

This card is represented as a contactsurface in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 2047 Proprietary Information of Altair Engineering

SWLDPRM Bulk Data Entry SWLDPRM – Parameters for CWELD and CSEAM Connector Elements Description Defines values of parameters used during the CWELD and CSEAM connectivity search. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SWLDPR M

PARAM1

VAL1

PARAM2

VAL2

PARAM3

VAL3

PARAM4

VAL4

PARAM5

VAL5

-etc.-

(10)

Example

(1)

(2)

(3)

(4)

(5)

SWLDPRM

GSPROJ

15.0

PRTSW

1

(6)

(7)

(8)

(9)

(10)

Alternate Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SWLDPR M

PARAM1

VAL1

PARAM2

VAL2

C TYPE1

PARAM3

VAL3

PARAM4

VAL4

C TYPE2

PARAM5

VAL5

PARAM6

VAL6

PARAM7

VAL7

(10)

-etc.-

Example (Alternate Format)

2048 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

SWLDPRM

GSPROJ

15.0

PRTSW

1

C WELD

GSMOVE

2

NREDIA

3

PROJTO L

0.03

C SEAM

C NRAGLI

150.0

GSPROJ

20.0

SHOWAU X

1

Field

Contents

PARAM#

Name of parameter.

VAL#

Value of parameter

CTYPE

Connector type keyword to control the element specific parameters. Parameters following a keyword will only be applied to the element type specified by the keyword.

(10)

Supported connector types: CWELD or CSEAM While textual values are recommended for clarity, their integer equivalents will also be read. The available parameters and their values are listed below (click the parameter name for parameter descriptions). Parameter

Value

CHKRUN

NO, 0, YES, or 1 Default = NO

CNRAGLI

90.0 < Real < 160.0 or -1.0 Default = 160.0

CNRAGLO

0.0 < Real < 90.0 or -1.0 Default = 20.0

GMCHK

NO, 0, YES, 1, FULL, or 2 Default = NO

GSMOVE

Integer > 0 Default = 0

Altair Engineering

OptiStruct 13.0 Reference Guide 2049 Proprietary Information of Altair Engineering

Parameter

Value

GSPROJ

0.0 < Real < 90.0 or -1.0 Default = 20.0

GSTOL

Real > 0.0 Default = 0.0

NREDIA

O < Integer < 4 Default = 0

PROJTOL

0.0 < Real < 0.5 Default = 0.05

PRTSW

NO, 0, YES, or 1 Default = NO

SHOWAUX

0, 1, 2, 3 Default = 0

Comments 1.

The SWLDPRM entry changes the default settings of parameters for the CWELD and CSEAM connectivity entries. None of the parameters of this entry are required. The default settings should be changed only for diagnostic and debug purposes. Only one SWLDPRM entry is allowed in the bulk data section.

2.

Connectivities are created for the CSEAM element and for the CWELD element with PARTPAT, ELPAT, ELEMID and GRIDID formats. With the parameters on this entry, you can debug and alter the search algorithm which creates these connector elements.

3.

Before the presence of any keyword of the connector, that is CWELD and CSEAM, the parameter set on the entry will be regarded as “global,” and it will be applied to all of the connector elements unless it only serves a specific type of connector.

4.

Any parameter following a connector keyword will only be applied to the element type specified by the keyword until the presence of another keyword.

5.

Blank fields are allowed in this entry. However, blank fields are not allowed between the parameter name and the corresponding parameter value or between the connector keyword and the parameter name followed. If the parameter name or the connector keyword is located just before the continuation field, then the following content must be placed in the first field after the continuation marker.

6.

Further detailed information about the individual connector elements can be found on the pertinent CWELD and CSEAM bulk data entries.

7.

Some of the above parameters apply only to selected connector types. Such information is provided within the detailed description of individual parameters.

2050 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SWLDPRM, CHKRUN Parameter CHKRUN

Values

Description

NO, 0, YES, or 1 Default = NO

Stop or allow the run after the connectivities of all the connector elements have been generated. This parameter must be global, meaning it should be placed before the presence of the first connector keyword. If NO or 0, the solver will run to completion, unless other errors are present. If YES or 1, the solver will stop after connectivity of all connector elements has been checked.

Altair Engineering

OptiStruct 13.0 Reference Guide 2051 Proprietary Information of Altair Engineering

SWLDPRM, CNRAGLI Parameter CNRAGLI

Values

Description

90.0 < Real < 180.0 For CSEAM element only. Minimum angle allowed or -1.0 between the free edges (no other element shares these edges) of shell elements EIDSA and EIDEA or Default = 160.0 EIDSB and EIDEB. The CSEAM element will be rejected if this minimum angle is violated. See the following figure.

If α < CNRAGLI, this CSEAM element is rejected (for clarity suppose that the bold lines are the only couple of free edges, while the others are connected with shell elements not shown in this figure). If CNRAGLI is set to -1.0, the program will skip the checking of CNRAGLI.

2052 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SWLDPRM, CNRAGLO Parameter CNRAGLO

Values

Description

0.0 < Real < 90.0 or -1.0 Default = 20.0

For CSEAM element only. Maximum angle allowed between the normal vectors of EIDSA and EIDEA or EIDSB and EIDEB. The CSEAM element will not be generated if the angle between these two normal vectors is greater than the value of CNRAGLO. This prevents generating single CSEAM element across a very curved shell configuration. See the following figure.

If α > CNRAGLO, this CSEAM element is rejected. The same check is also applied to the angle between the normal vectors of EIDSB and EIDEB. If CNRAGLO is set to -1.0, the program will skip the checking of CNRAGLO.

Altair Engineering

OptiStruct 13.0 Reference Guide 2053 Proprietary Information of Altair Engineering

SWLDPRM, GMCHK Parameter GMCHK

Values

Description

NO, 0, YES, 1, FULL, or 2

A switch to perform geometry check for certain types of connector elements (presently it only applies to CSEAM).

Default = NO If NO or 0, no geometry check. If YES or 1, perform geometry checks for connector elements. If FULL or 2, perform geometry checks for connector elements and output the shell element ID(s) if an error is found. If GMCHK=1 or 2, the program will check whether the CSEAM element spans a cutout or a corner. If the CSEAM element does, an error will be issued. If GMCHK=1 or 2 and GSPROJ > 0, the program will check the angle between the normal vectors of Shell A and Shell B. If the angle is larger than the value defined by GSPROJ, an error will be issued. If GMCHK=1 or 2 and CNRAGLO > 0, the program will check the angle between the normal vectors of EIDSA and EIDEA or EIDSB and EIDEB. If the angle is larger than the value defined by CNRAGLO, an error will be issued. If GMCHK=1 or 2 and CNRAGLI > 0, the program will check the angle between the free edges of shell elements EIDSA and EIDEA or EIDSB and EIDEB. If the angle is smaller than the value defined by CNRAGLI, an error will be issued.

2054 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SWLDPRM, GSMOVE Parameter GSMOVE

Values

Description

Integer > 0 Default = 0

Altair Engineering

Maximum number of times GS for the CWELD (PARTPAT or ELPAT format) or GS/GE for the CSEAM is moved in cases when not all auxiliary points have projections onto the patch of shells.

OptiStruct 13.0 Reference Guide 2055 Proprietary Information of Altair Engineering

SWLDPRM, GSPROJ Parameter GSPROJ

Values

Description

0.0 < Real < 90.0 or -1.0 Default = 20.0

Maximum angle allowed between the normal vectors of Shell A and Shell B. Shell A and Shell B are located on the two different shell surfaces that need to be connected by the connector element. The connector element will not be generated if the angle between these two normal vectors is greater than the value of GSPROJ. This prevents the generation of connector elements between shell components that depart from being parallel to each other. See the following figure.

If α > GSPROJ, this connector element is rejected. Meanwhile, for CSEAM, when locating possible candidate shell elements to support the auxiliary points, the program will also check the angle between the normal vector of the candidate and the thickness direction of the CSEAM element. If the angle is larger than the value defined by GSPROJ, this candidate will be ignored. If the ignored candidate is one of EIDSA, EIDSB, EIDEA or EIDEB, a warning will be issued. If GSPROJ is set to -1.0, the program will skip the checking of GSPROJ.

2056 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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SWLDPRM, GSTOL Parameter GSTOL

Values

Description

Real > 0.0 Default = 0.0

Presently it only applies to CSEAM. Maximum distance between GS-SA, GS-SB, GE-EA and GE-EB for CSEAM. See the following figure.

If the distance is greater than GSTOL, then the connector element will not be generated and an error will be issued. If GSTOL is set to 0.0, the program will skip the checking of GSTOL.

Altair Engineering

OptiStruct 13.0 Reference Guide 2057 Proprietary Information of Altair Engineering

SWLDPRM, NREDIA Parameter NREDIA

Values

Description

0 < Integer < 4 Maximum number of times the diameter (which is used in locating auxiliary points) is reduced by half when not all Default = 0 auxiliary points have projections onto the patch of shells. This parameter is for CWELD (PARTPAT and ELPAT) only.

2058 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

SWLDPRM, PROJTOL Parameter PROJTOL

Values

Description

0.0 < Real < 0.5 Default = 0.05

Altair Engineering

Tolerance to accept the projected points (from GS for CWELD and from GS/GE for CSEAM) if the computed coordinates of the projection point lies outside the shell element but is located within PROJTOL×(dimension of the shell element). PROJTOL is only activated when a search without PROJTOL finds no candidate shell to build connectivity for a connector element. This prevents the search from picking the wrong shell element in cases when PROJTOL is not needed.

OptiStruct 13.0 Reference Guide 2059 Proprietary Information of Altair Engineering

SWLDPRM, PRTSW Parameter PRTSW

Values

Description

NO, 0, YES, or 1

Print diagnostic output for connector elements.

Default = NO

If NO or 0, diagnostic information is not output. If YES or 1, diagnostic information is written to the .out file.

2060 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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SWLDPRM, SHOWAUX Parameter SHOWAUX

Values

Description

NO, 0, YES, or 1 Default = NO

Output fictitious grids representing auxiliary points generated for CWELD and fictitious hexa corner points generated for CSEAM into a file which can be directly imported into HyperMesh to visualize the connector elements. For clarity of visualization, this file also includes the eight-node CHEXA elements with corners at respective auxiliary points for CWELD or at respective fictitious hexa corner points for CSEAM. For each CWELD element, this data will only be output in cases where no error is issued before the definition of auxiliary points. For the CSEAM element, this data will only be output if all seam elements are built successfully. For CWELD, the root file name will be followed with .weldaux.fem. For CSEAM, the root file name will be followed with .seamaux.fem. If SHOWAUX = YES, the displacement/corner stress/grid point stress of the fictitious hexa element will also be output into an H3D file if requested. If NO or 0, no data for the fictitious hexa will be output. If YES or 1, the fictitious grids and hexas will be output (these are the final locations, including all the adjustments due to connector element radius or thickness).

Altair Engineering

OptiStruct 13.0 Reference Guide 2061 Proprietary Information of Altair Engineering

TABDMP1 Bulk Data Entry TABDMP1 – Modal Damping Table Description Defines modal damping as a tabular function of natural frequency. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABDMP 1

TID

TYPE

f1

g1

f2

g2

f3

g3

f4

g4

f5

g5

…

…

…

…

…

…

(7)

(8)

(9)

(10)

Example

(1)

(2)

TABDMP 1

2

2.5

(3)

(4)

(5)

(6)

0.01057

2.6

0.1362

ENDT

Field

Contents

TID

Table identification number.

(10)

No default (Integer > 0) TYPE

Type of damping units. Default = G (G, CRIT, or Q)

2062 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents Natural frequency value in cycles per unit time. No default (Real > 0.0) Damping value. No default (Real)

Comments 1.

Modal damping tables must be selected in the Subcase Information section, using the SDAMPING command. This form of damping is used only in the modal method of frequency response analysis.

2.

A METHOD statement must be present in the SUBCASE.

3.

The frequency values, not both.

4.

Discontinuities may be specified between any two points except the two starting points or two end points. For example, in Figure 1 discontinuities are allowed only between points f2 through f7. Also, if g is evaluated at a discontinuity, then the average value of g is used. In Figure 1, the value of g at f=f3 is g = (g3+g4)/2.

5.

At least one continuation entry must be specified.

6.

Any or that entry.

7.

The end of the table is indicated by the existence of 'ENDT' in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag 'ENDT'.

8.

The TABDMP1 uses the algorithm:

, must be specified in either ascending or descending order, but

entry may be ignored by placing 'SKIP' in either of the two fields used for

where, f is input to the table and g is returned. The table look-up is performed using linear interpolation within the table and linear extrapolation outside the table using the two starting or end points. See Figure 1. No warning messages are issued if table data is input incorrectly.

Altair Engineering

OptiStruct 13.0 Reference Guide 2063 Proprietary Information of Altair Engineering

Figure 1. Example of Table Extrapolation and Discontinuity

9.

The KDAMP option, on the PARAM card, may be used to switch between viscous and structural damping. Viscous is the default and is used when PARAM, KDAMP is not present. KDAMP

Result

1 (default)

B matrix

-1

(1+ig)K matrix

10. If TYPE is 'G' or blank, the damping values as follows:

If TYPE is 'CRIT', the damping values

are in units of equivalent viscous dampers

are in units of fraction of critical damping C/C0.

If TYPE is 'Q', the damping values are in the units of amplification or quality factor, Q. These constants are related by the following equations:

2064 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

11. To achieve identical displacements in Modal frequency response or Modal transient analyses when the SDAMPING bulk data entry is used instead of PARAM, G , the steps described here can be followed: The TYPE field in the TABDMP1 bulk data entry should be set to CRIT. This TABDMP1 bulk data entry is referenced by the SDAMPING subcase information entry. Set the damping value (field ) in the TABDMP1 bulk data entry equal to half of the value of PARAM, G (set the constant value to C/C0). Set PARAM, KDAMP,-1. 12. This card is represented as a loadcollector in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 2065 Proprietary Information of Altair Engineering

TABLED1 Bulk Data Entry TABLED1 – Dynamic Load Tabular Function, Form 1 Description Defines a tabular function for use in generating frequency-dependent and time-dependent dynamic loads. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABLED1

TID

XAXIS

YAXIS

x1

y1

x2

y2

x3

y3

x4

y4

x5

y5

…

…

…

…

…

…

(10)

Example

(1)

(2)

TABLED1

32

-3.0

(3)

(4)

(5)

(6)

(7)

(8)

6.9

2.0

5.6

3.0

5.6

ENDT

Field

Contents

TID

Table identification number.

(9)

(10)

No default (Integer > 0) XAXIS

Specifies a linear or logarithmic interpolation for the x-axis. See comment 6. Default = LINEAR (LINEAR or LOG)

2066 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

YAXIS

Specifies a linear or logarithmic interpolation for the y-axis. See comment 6. Default = LINEAR (LINEAR or LOG)

x#, y#

Tabular values. No default (Real or ENDT)

Comments 1.

xi must be in either ascending or descending order, but not both.

2.

Discontinuities may be specified between any two points except the two starting points or two end points. For example, in Figure 1 discontinuities are allowed only between points x2 through x7 . Also, if y is evaluated at a discontinuity, the average value of y is used. In Figure 1, the value of y at x = x3 is y = (y3+y4)/2 .

3.

At least one continuation entry must be specified.

4.

Any x, y pair may be ignored by placing 'SKIP' in either of the two fields used for that entry.

5.

The end of the table is indicated by the existence of 'ENDT' in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag 'ENDT'.

6.

The TABLED1 uses the algorithm:

where, x is input to the table and y is returned. The table look-up is performed using interpolation within the table and linear extrapolation outside the table using the two starting or end points. See Figure 1. The algorithms used for interpolation or extrapolation are:

Altair Engineering

OptiStruct 13.0 Reference Guide 2067 Proprietary Information of Altair Engineering

where, xj and yj follow xi and yi. No warning messages are issued if table data is input incorrectly.

Figure 1. Example of Table Extrapolation and Discontinuity

7.

Linear extrapolation is not used for Fourier transform methods. The function is zero outside the range of the table.

8.

For frequency-dependent loads, x# is measured in cycles per unit time.

9.

Tabular values on an axis if X-Axis or Y-Axis = LOG must be positive. A fatal message will be issued if an axis has a tabular value < 0.

2068 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

10. This card is represented as a loadcollector in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 2069 Proprietary Information of Altair Engineering

TABLED2 Bulk Data Entry TABLED2 – Dynamic Load Tabular Function, Form 2 Description Defines a tabular function for use in generating frequency-dependent and time-dependent dynamic loads. Also contains parametric data for use with the table. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABLED2

TID

X1

x1

y1

x2

y2

x3

y3

x4

y4

x5

y5

…

…

…

…

…

…

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABLED2

15

-10.5

1.0

-4.5

2.0

-4.2

2.0

2.8

7.0

6.5

SKIP

SKIP

9.0

6.5

ENDT

Field

Contents

TID

Table identification number.

(10)

No default (Integer > 0) X1

Table parameter. See comment 6. No default (Real)

2070 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

x#, y#

Tabular values. No default (Real)

Comments 1.

xi must be in either ascending or descending order, but not both.

2.

Discontinuities may be specified between any two points except the two starting points or two end points. For example, in Figure 1 discontinuities are allowed only between points x2 through x7 . Also, if y is evaluated at a discontinuity, the average value of y is used. In Figure 1, the value of y at x = x3 is y = (y3+y4)/2.

3.

At least one continuation entry must be specified.

4.

Any x, y pair may be ignored by placing 'SKIP' in either of the two fields used for that entry.

5.

The end of the table is indicated by the existence of 'ENDT' in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag 'ENDT'.

6.

The TABLED2 uses the algorithm:

where, x is input to the table and y is returned. The table look-up is performed using interpolation within the table and linear extrapolation outside the table using the two starting or end points. See Figure 1. No warning messages are issued if table data is input incorrectly.

Altair Engineering

OptiStruct 13.0 Reference Guide 2071 Proprietary Information of Altair Engineering

Figure 1. Example of Table Extrapolation and Discontinuity

7.

Linear extrapolation is not used for Fourier transform methods. The function is zero outside the range of the table.

8.

For frequency-dependent loads, X1 and x# are measured in cycles per unit time.

9.

This card is represented as a loadcollector in HyperMesh.

2072 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

TABLED3 Bulk Data Entry TABLED3 – Dynamic Load Tabular Function, Form 3 Description Defines a tabular function for use in generating frequency-dependent and time-dependent dynamic loads. Also contains parametric data for use with the table. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABLED3

TID

X1

X2

x1

y1

x2

y2

x3

y3

x4

y4

x5

y5

…

…

…

…

…

…

(10)

Example

(1)

(2)

(3)

(4)

TABLED3

15

126.9

30.0

2.9

2.9

3.6

(5)

(6)

(7)

(8)

4.7

5.2

5.7

ENDT

Field

Contents

TID

Table identification number.

(9)

(10)

No default (Integer > 0) X1, X2

Table parameters.

Altair Engineering

OptiStruct 13.0 Reference Guide 2073 Proprietary Information of Altair Engineering

Field

Contents

x#, y#

Tabular values. No default (Real)

Comments 1.

xii must be in either ascending or descending order, but not both.

2.

Discontinuities may be specified between any two points except the two starting points or two end points. For example, in Figure 1 discontinuities are allowed only between points x2 through x7 . Also, if y is evaluated at a discontinuity, the average value of y is used. In Figure 1, the value of y at x = x3 is y = (y3+y4)/2.

3.

At least one continuation entry must be specified.

4.

Any x, y pair may be ignored by placing 'SKIP' in either of the two fields used for that entry.

5.

The end of the table is indicated by the existence of 'ENDT' in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag 'ENDT'.

6.

The TABLED3 uses the algorithm:

where, x is input to the table and y is returned. The table look-up is performed using interpolation within the table and linear extrapolation outside the table using the two starting or end points. See Figure 1. No warning messages are issued if table data is input incorrectly.

2074 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Figure 1. Example of Table Extrapolation and Discontinuity

7.

Linear extrapolation is not used for Fourier transform methods. The function is zero outside the range of the table.

8.

For frequency-dependent loads, X1, X2, and x# are measured in cycles per unit time.

9.

This card is represented as a loadcollector in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 2075 Proprietary Information of Altair Engineering

TABLED4 Bulk Data Entry TABLED4 – Dynamic Load Tabular Function, Form 4 Description Defines the coefficients of a power series for use in generating frequency-dependent and time-dependent dynamic loads. Also contains parametric data for use with the table. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABLED4

TID

X1

X2

X3

X4

A0

A1

A2

A3

A4

A5

A6

A7

A8

…

…

…

…

…

…

…

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

TABLED4

28

0.0

1.0

0.0

100

2.91

-0.0329

6.51e-5

0.0

-3.4-7

Field

Contents

TID

Table identification number.

(7)

(8)

(9)

(10)

ENDT

No default (Integer > 0) X#

Table parameters.

2076 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

A#

Coefficients. No default (Real)

Comments 1.

At least one continuation entry must be specified.

2.

The end of the table is indicated by the existence of 'ENDT' in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag 'ENDT'.

3.

TABLED4 uses the algorithm:

where, x is input to the table, y is returned and N is the number of pairs. Whenever x < X3, use X3 for x; whenever x > X4, use X4 for x. There are N + 1 entries in the table. There are no error returns from this table look-up procedure. 4.

For frequency-dependent loads, x# is measured in cycles per unit time.

5.

This card is represented as a loadcollector in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 2077 Proprietary Information of Altair Engineering

TABFAT Bulk Data Entry TABFAT - Fatigue Loading Time History Definition Description Defines y values of each point on the loading time history. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABFAT

ID

y1

y2

y3

y4

y5

y6

y7

y8

…

…

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABFAT

1

0.000

-0.601

0.968

0.515

-0.263

-0.090

-0.582

-0.592

-0.877

-0.726

0.297

-0.899

-0.899

-0.165

0.907

0.936

-0.308

-0.308

-0.689

0.592

0.609

-0.600

-0.492

-0.492

-0.224

2078 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

(10)

Altair Engineering

Field

Contents

ID

Unique identification number. No default (Integer > 0)

y#

Y value of each point on the loading time history curve. No default (Real)

Comments 1.

The TABFAT ID may be referenced by a FATLOAD definition.

2.

This card is represented as a loadcollector in HyperMesh.

3.

Prior to OptiStruct version 11.0, TABFAT was named TABLEFAT.

Altair Engineering

OptiStruct 13.0 Reference Guide 2079 Proprietary Information of Altair Engineering

TABLEM1 Bulk Data Entry TABLEM1 – Material Property Table, Form 1 Description Defines a tabular function for use in generating temperature-dependent material properties. Format (1)

(2)

TABLEM1

TID

x1

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

y1

x2

y2

x3

y3

-etc.-

"ENDT"

Example

(1)

(2)

TABLEM1

32

-3.0

(3)

(4)

(5)

(6)

(7)

(8)

6.9

2.0

5.6

3.0

5.6

ENDT

Field

Contents

TID

Table identification number.

(9)

(10)

(Integer > 0) xi, yi

Tabular values. (Real)

"ENDT"

Flag indicating the end of the table.

2080 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Comments 1.

xi must be in either ascending or descending order, but not both.

2.

Discontinuities may be specified between any two points except the two start points or two end points. For example, in the figure below, discontinuities are allowed only between points x2 through x7 . Also, if y is evaluated at a discontinuity, then the average value of y is used. In the figure, the value of y at x = x3 is y = (y3 +y4)/2.

3.

At least one continuation entry must be specified.

4.

Any xi- yi pair may be ignored by placing 'SKIP' in either of the two fields.

5.

The end of the table is indicated by the existence of "ENDT" in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag "ENDT".

6.

The TABLEM1 uses the algorithm (see comment 7):

y= yT(x) where, x is input to the table and y is returned. The table look-up is performed using linear interpolation within the table and linear extrapolation outside the table using the two start or end points (see figure). No warning messages are issued, if the table data is input incorrectly.

Example of table extrapolation and discontinuity

7. In a nonlinear heat transfer analysis, TABLEM1 uses the following algorithm:

y = zyT(x) Where. x is input to the table, y is returned, and z is supplied from the MAT4 entry. 8.

This card is represented as a loadcollector in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 2081 Proprietary Information of Altair Engineering

TABLEM2 Bulk Data Entry TABLEM2 – Material Property Table, Form 2 Description Defines a tabular function for use in generating temperature-dependent material properties. Also contains parametric data for use with the table. Format (1)

(2)

(3)

TABLEM2

TID

X1

x1

y1

(4)

(5)

(6)

(7)

(8)

(9)

x2

y2

x3

y3

-etc.-

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABLEM2

15

-10.5

1.0

-4.5

2.0

-4.5

2.0

2.8

7.0

6.5

SKIP

SKIP

9.0

6.5

ENDT

Field

Contents

TID

Table identification number.

(10)

(Integer > 0) X1

Table parameter. (Real)

2082 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

xi, yi

Tabular values. (Real)

Comments 1.

xi must be in either ascending or descending order, but not both.

2.

Discontinuities may be specified between any two points except the two starting points or two end points. For example, in the figure below, discontinuities are allowed only between points x2 through x7 . Also, if y is evaluated at a discontinuity, then the average value of y is used. In the figure, the value of y at x = x3 is y = (y3+y4)/2 .

3.

At least one continuation entry must be specified.

4.

Any xi-yi pair may be ignored by placing 'SKIP' in either of the two fields.

5.

The end of the table is indicated by the existence of "ENDT" in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag "ENDT".

6.

The TABLEM2 uses the algorithm:

y= zyT(x – X1) where, x is input to the table, y is returned, and z is supplied from the MATi entry. The table look-up is performed using linear interpolation within the table and linear extrapolation outside the table using the two start or end points (see figure). No warning messages are issued if table data is input incorrectly.

Example of table extrapolation and discontinuity

Altair Engineering

OptiStruct 13.0 Reference Guide 2083 Proprietary Information of Altair Engineering

7.

This card is represented as a loadcollector in HyperMesh.

2084 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

TABLEM3 Bulk Data Entry TABLEM3 – Material Property Table, Form 3 Description Defines a tabular function for use in generating temperature-dependent material properties. Also contains parametric data for use with the table. Format (1)

(2)

(3)

(4)

TABLEM3

TID

X1

X2

x1

y1

x2

(5)

(6)

(7)

(8)

(9)

y2

x3

y3

-etc.-

(10)

Example

(1)

(2)

(3)

(4)

TABLEM3

62

126.9

30.0

2.9

2.9

3.6

(5)

(6)

(7)

(8)

4.7

5.2

5.7

ENDT

Field

Contents

TID

Table identification number.

(9)

(10)

(Integer > 0) X1, X2

Table parameters. See comment 6.

xi, yi

Tabular values. (Real)

Altair Engineering

OptiStruct 13.0 Reference Guide 2085 Proprietary Information of Altair Engineering

Comments 1.

Tabular values for xi must be specified in either ascending or descending order, but not both.

2.

Discontinuities may be specified between any two points except the two start points or two end points. For example, in the figure below, discontinuities are allowed only between points x2 through x7 . Also, if y is evaluated at a discontinuity, then the average value of y is used. In the figure, the value of y at x = x3 is y = (y3+y4)/2 .

3.

At least one continuation entry must be specified.

4.

Any xi-yi pair may be ignored by placing 'SKIP' in either of the two fields.

5.

The end of the table is indicated by the existence of "ENDT" in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag "ENDT".

6.

TABLEM3 uses the algorithm:

where, x is input to the table, y is returned and z is supplied from the MATi entry. The table look-up is performed using linear interpolation within the table and linear extrapolation outside the table using the two starting or end points (see figure). No warning messages are issued if table data is input incorrectly.

Example of table extrapolation and discontinuity

7.

This card is represented as a loadcollector in HyperMesh.

2086 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

TABLEM4 Bulk Data Entry TABLEM4 – Material Property Table, Form 4 Description Defines coefficients of a power series for use in generating temperature-dependent material properties. Also contains parametric data for use with the table. Format (1)

(2)

(3)

(4)

(5)

(6)

TABLEM4

TID

X1

X2

X3

X4

A0

A1

A2

A3

A4

(7)

(8)

(9)

A5

-etc.-

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

TABLEM4

28

0.0

1.0

0.0

100.

2.91

-0.0329

6.51-5

0.0

-3.4-7

Field

Contents

TID

Table identification number.

(7)

(8)

(9)

(10)

ENDT

(Integer > 0) Xi

Table parameters.

Ai

Coefficients. (Real)

Altair Engineering

OptiStruct 13.0 Reference Guide 2087 Proprietary Information of Altair Engineering

Comments 1.

At least one continuation entry must be specified.

2.

The end of the table is indicated by the existence of "ENDT" in the field following the last entry. An error is detected if any continuations follow the entry containing the end-oftable flag "ENDT".

3.

TABLEM4 uses the algorithm:

where, x is input to the table, y is returned, and z is supplied from the MATi entry. Whenever x < X3 , use X3 for x; whenever x > X4 , use X4 for x. There are N + 1 entries in the table. There are no error returns from this table look-up procedure. 4.

This card is represented as a loadcollector in HyperMesh.

2088 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

TABLES1 Bulk Data Entry TABLES1 – Material Property Tabular Function, Form 1 Description Defines a tabular function for use as stress-strain curve in elasto-plastic material properties MATS1, MATX33, MATX65, MATHF, as well as material curve in nonlinear material properties MATX36, MATX42, and MATX70. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TABLES1

TID

x1

y1

x2

y2

x3

y3

x4

y4

x5

y5

…

…

…

…

…

…

(9)

(10)

Example

(1)

(2)

TABLES1

32

-3.0

(3)

(4)

(5)

(6)

(7)

(8)

6.9

2.0

5.6

3.0

5.6

ENDT

Field

Contents

TID

Table identification number.

(10)

No default (Integer > 0) x#, y#

Tabular values. No default (Real, or ENDT)

Comments 1.

xi must be in either ascending or descending order, but not both.

Altair Engineering

OptiStruct 13.0 Reference Guide 2089 Proprietary Information of Altair Engineering

2.

Discontinuities between any two points except the two starting points or two end points. For example, in Figure 1 discontinuities are allowed only between points x2 through x7 . Also, if y is evaluated at a discontinuity, the average value of y is used. In Figure 1, the value of y at x = x3 is y = (y3+y4)/2 .

3.

At least one continuation entry must be specified.

4.

Any x, y pair may be ignored by placing 'SKIP' in either of the two fields used for that entry.

5.

The end of the table is indicated by the existence of 'ENDT' in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag 'ENDT'.

6.

The TABLES1 uses the algorithm:

where, x is input to the table and y is returned. The table look-up is performed using interpolation within the table and linear extrapolation outside the table using the two starting or end points. See Figure 1. The algorithms used for interpolation or extrapolation is:

where, xj and yj follow xi and yi. 7.

For TABLES1 referenced by elasto-plastic material property MATS1, additional requirements apply. See the description of MATS1 for details.

2090 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Figure 1. Example of Table Extrapolation and Discontinuity

8.

Linear extrapolation is not used for Fourier transform methods. The function is zero outside the range of the table.

9.

For frequency-dependent loads, x# is measured in cycles per unit time.

10. Some warning or error messages are issued if table data in input incorrectly. However, since TABLES1 can serve different and distinct purposes, error checking is limited.

Altair Engineering

OptiStruct 13.0 Reference Guide 2091 Proprietary Information of Altair Engineering

TABLEST Bulk Data Entry TABLEST – Material Property Temperature-Dependence Table Description Specifies the material property tables for elasto-plastic, temperature-dependent materials. Format (1)

(2)

TABLEST

TID

T1

(3)

(4)

(5)

(6)

(7)

TID1

T2

TID2

T3

-etc.-

(8)

(9)

(10)

(9)

(10)

Example

(1)

(2)

TABLEST

101

150.0

(3)

(4)

(5)

(6)

10

175.0

20

ENDT

Field

Contents

TID

Table identification number.

(7)

(8)

(Integer > 0) Ti

Temperature values. (Real)

TIDi

Table identification numbers of TABLES1 entries. (Integer > 0)

2092 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Comments 1.

TIDi must be unique with respect to all TABLES1 and TABLEST table identification numbers.

2.

Temperature values must be listed in ascending order.

3.

The end of the table is indicated by the existence of ENDT in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag ENDT.

4.

This table is referenced by MATS1 entries that define elasto-plastic (TYPE = "PLASTIC") materials.

Altair Engineering

OptiStruct 13.0 Reference Guide 2093 Proprietary Information of Altair Engineering

TABRND1 Bulk Data Entry TABRND1 – Power Spectral Density Table Description Defines power spectral density as a tabular function of frequency for use in random analysis. Referenced on the RANDPS entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

TABRND1

ID

XAXIS

YAXIS

blank

blank

blank

blank

blank

f1

g1

f2

g2

f3

g3

f4

g4

Example

(1)

(2)

TABRND1

3

2.5

(3)

(4)

(5)

(6)

.01057

2.6

.01362

ENDT

(7)

(8)

(9)

(10)

etc.

Field

Contents

ID

Table identification number. (Integer > 0)

XAXIS

Specifies a linear or logarithmic interpolation for the x-axis. See comment 6. Default = LINEAR (LINEAR or LOG)

2094 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Field

Contents

YAXIS

Specifies a linear or logarithmic interpolation for the y-axis. See comment 6. Default = LINEAR (LINEAR or LOG)

fi

Frequency value in cycles per unit time. (Real > 0.0)

gi

Power Spectral Density. (Real)

Comments 1.

The fi must be in either ascending or descending order, but not both.

2.

Jumps between two points (

3.

At least two entries must be present.

4.

Any f-g entry may be ignored by placing the BCD string "SKIP" in either of the two field used for that entry.

5.

The end of the table is indicated by the existence of the BCD string "ENDT" in either of the two fields following the last entry. An error is detected if any continuations follow the entry containing the end-of-table flag "ENDT".

6.

The TABRND1 mnemonic infers the use of the algorithm:

) are allowed, but not at the end points.

G = g T(F) where, F is input to the table and G is returned. The table look-up gT(f) is performed using linear extrapolation outside the table using the last two end points at the appropriate table end. At jump points, the average gT(F) is used. There are no error returns from this table look-up procedure.

Altair Engineering

OptiStruct 13.0 Reference Guide 2095 Proprietary Information of Altair Engineering

TEMP Bulk Data Entry TEMP – Grid Point Temperature Field Description Defines temperature at grid points for determination of Thermal Loading and Stress recovery. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

TEMP

SID

G

T

G

T

G

T

blank

{N.C .}

Example

(1)

(2)

(3)

(4)

(5)

(6)

TEMP

3

94

316.2

49

219.8

Field

Contents

SID

LOAD set identification.

(7)

(8)

(9)

(10)

(Integer > 0) G

Grid point identification number. (Integer > 0)

T

Temperature. (Real)

Comments 1.

Temperature sets may be selected for use in a subcase by the TEMPERATURE(LOAD) or TEMPERATURE(BOTH) subcase information entry.

2.

From one to three grid point temperatures may be defined on a single entry.

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3.

In versions of OptiStruct prior to 8.0, thermal loads were selected in the Subcase Information section using the LOAD data selector. In version 8.0, the TEMPERATURE data selector was added to perform this function. It is possible to revert to the old behavior mode by setting the LOADTEMP option to SHAREID in the OptiStruct Configuration File.

4.

This card is represented as a temperature load in HyperMesh.

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OptiStruct 13.0 Reference Guide 2097 Proprietary Information of Altair Engineering

TEMPD Bulk Data Entry TEMPD – Grid Point Temperature Field Default Description Defines a temperature value for all grid points of the structural model that have not been given a temperature on a TEMP entry. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TEMPD

SID

T

SID

T

SID

T

SID

T

(10)

Example

(1)

(2)

(3)

TEMPD

1

216.3

(4)

Field

Contents

SID

LOAD set identification.

(5)

(6)

(7)

(8)

(9)

(10)

(Integer > 0) T

Default temperature value. (Real)

Comments 1.

Temperature sets may be selected for use in a subcase by the TEMPERATURE(LOAD) or TEMPERATURE(BOTH) subcase information entry.

2.

From one to four default temperatures may be defined on a single entry.

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3.

In versions of OptiStruct prior to 8.0, thermal loads were selected in the Subcase Information section using the LOAD data selector. In version 8.0, the TEMPERATURE data selector was added to perform this function. It is possible to revert to the old behavior mode by setting the LOADTEMP option to SHAREID in the OptiStruct Configuration File.

4.

This card is represented as a loadcollector in HyperMesh.

Altair Engineering

OptiStruct 13.0 Reference Guide 2099 Proprietary Information of Altair Engineering

TIC Bulk Data Entry TIC – Transient and Explicit Analysis Initial Condition Description Defines values for the initial conditions of variables used in structural transient analysis and explicit analysis. Both displacement and velocity values may be specified at independent degrees-of-freedom. Format (1)

(2)

(3)

(4)

(5)

(6)

TIC

SID

G

C

U0

V0

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

TIC

100

10

3

0.1

0.5

Field

Contents

SID

Set identification number.

(7)

(8)

(9)

(10)

(Integer > 0) G

Grid or scalar point identification number. See comment 4. (Integer > 0)

C

Component numbers. (Any one of the integers 1 through 6 for grid points, integer zero or blank for scalar points)

U0

Initial displacement. Not applicable in geometric nonlinear analysis.

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Field

Contents (Real or blank)

V0

Initial velocity. (Real or blank)

Comments 1.

Transient analysis initial condition sets must be selected with the IC subcase information command.

2.

If no TIC set is selected in the Subcase Information section, all initial conditions are assumed to be zero.

3.

Initial conditions for coordinates not specified on TIC entries will be assumed to be zero.

4.

In direct transient analysis, wherein the TIC bulk data entry is selected by an IC subcase information command, G may reference only grid or scalar points.

5.

Initial displacement definition is not applicable in explicit analysis. If U0 is defined, a fatal error message will be issued.

6.

The initial conditions for the independent degrees-of-freedom specified by this bulk data entry are distinct from, and may be used in conjunction with, the initial conditions for the enforced degrees-of-freedom specified by NLOAD1, TLOAD1 and/or TLOAD2 bulk data entries.

7.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

8.

Each degree-of-freedom (grid/component pair: G#/C#) should define a unique value for U0 and/or V0 within any TIC ID set, but U0 and V0 may be specified on separate TIC cards. When multiple cards with the same degree-of-freedom are present, only non-zero values for U0 and V0 are used by the solver. When two non-zero values are defined for U0 or for V0 for the same degree-of-freedom, a fatal error message will be issued, even if values match.

9.

This card is represented as a constraint load in HyperMesh.

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OptiStruct 13.0 Reference Guide 2101 Proprietary Information of Altair Engineering

TICA Bulk Data Entry TICA – Explicit Analysis Initial Velocity Relative to an Axis Description Defines values for the initial velocity of a set of grids along and about an axis for explicit analysis. Format (1)

(2)

(3)

(4)

(5)

TIC A

SID

GSID

VT

VR

GA/XA

YA

ZA

GB/XB

(6)

(7)

YB

ZB

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

TIC A

100

10

3.0

4.0

123

0.0

Field

Contents

SID

Set identification number.

(6)

(7)

0.0

1.0

(8)

(9)

(10)

(Integer > 0) GSID

Grid point set identification number. Default = all grids in the model (blank or Integer > 0)

VT

Initial velocity along the axis. (Real)

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Field

Contents

VR

Initial velocity about the axis. (Real)

GA/ XA, YA, ZA

Axis origin. These fields define the origin of the axis. The point may be defined by entering a grid ID in the GA field or by entering X, Y, and Z coordinates in the XA, YA, and ZA fields; these coordinates will be in the basic coordinate system. Default is the origin of the basic system (Real in all three fields or Integer in first field)

GB/ XB, YB, ZB

Direction of vector for axis definition. These fields define a point. The vector goes from the anchor point to this point. The point may be defined by entering a grid ID in the GB field or by entering X, Y, and Z coordinates in the XB, YB, and ZB fields; these coordinates will be in the basic coordinate system. No default (Real in all three fields or Integer in first field)

Comments 1.

Explicit analysis initial condition sets must be selected with the Subcase Information command IC = SID. It can only be selected in explicit subcases which are defined by an ANALYSIS = NLGEOM subcase entry.

2.

TICA is primarily used for simulating the uniform rotation of a structure about an axis by defining VR and an axis. A helical (or spiral) shaped motion can also be achieved by defining VR, VT and an axis.

3.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 2103 Proprietary Information of Altair Engineering

TIE Bulk Data Entry TIE – Tied Definition Description Defines a tied contact. Format (1)

(2)

(3)

TIE

TID

(4)

(5)

(6)

SSID

MSID

(7)

(8)

SRC HDIS

ADJUST

(7)

(8)

(9)

(10)

DISC RET

Example

(1)

(2)

TIE

5

(3)

(4)

(5)

7

8

(6)

(9)

(10)

0.01

N25

Field

Contents

TID

Tied interface identification number. See comment 1. (Integer > 0)

SSID

Identification number of slave entity. See comments 3 and 10. (Integer > 0)

MSID

Identification number of master entity. See comments 4 and 11. (Integer > 0)

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Field

Contents

SRCHDIS Search distance criterion for creating contact condition. When specified, only slave nodes that are within SRCHDIS distance from master surface will have contact condition checked. Default = All slave nodes checked (Real > 0 or blank) ADJUST

Adjustment of slave nodes onto the master surface at the start of a simulation. 0.0, or Integer > 0> Default = NO. NO – no adjustment. AUTO – A real value equal to 5% of the average edge length on the master surface is internally assigned as the depth criterion (see Comment 7). Real > 0.0 – Value of the depth criterion which defines the zone in which a search is conducted for slave nodes (for which contact elements have been created). These slave nodes (with created contact elements) are then adjusted onto the master surface. The assigned depth criterion is used to define the searching zone in the pushout direction (see Comment 7). Integer > 0 – Identification number of a SET entry with TYPE = “GRID”. Only the nodes on the slave entity, which also belong to this SET will be selected for adjustment.

DISCRET Discretization approach type for the construction of contact elements. Default = N2S. N2S – node-to-surface discretization S2S – surface-to-surface discretization

Comments (Nonlinear quasi-static analysis) 1.

TIE contact needs to keep a unique ID from all CONTACT definitions.

2.

The TIE contact is constructed by searching for each slave node for a respective facet of the master surface, which contains the normal projection of the slave and is within SRCHDIS distance from the slave node. If no master segment with normal projection is found, then the nearest segment is picked if the direction from slave to master is within a certain angle (30 degrees) relative to the normal to the master segment. Having found a feasible master segment for the slave node, a tie element is created.

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Figure 1: C reation of a TIE element

If the surface-to-surface (DISCRET=S2S) discretization approach is selected, the CONTACT interface is constructed by searching, for each facet of the slave surface, respective facets of the master surface which contain the normal projection of sample points on the slave facet and is within SRCHDIS distance from the sample points. For a slave node, a contact element is created with the surrounding slave facets and the master facets found by projection of the sample points on the slave facets (Figure 2).

Figure 2: C reation of a contact element (surface-to-surface discretization)

3.

The slave entity (SSID) always consists of grid nodes. It may be specified as: a set of grid nodes defined using SET card. a surface defined using SURF card (the slave nodes are picked from the respective nodes of the SURF faces). a set of elements (shells or solids) defined using SET card. Slave nodes are picked from the respective nodes of the elements in the set. For 3D solids, only nodes on the surface of the solid body are selected; internal nodes are not considered. DISCRET = N2S is recommended if the slave entity is a set of grids (nodes) or a set of solid elements.

4.

The master entity (MSID) may be defined as: a surface defined using SURF card. a set of elements (shells or solids) defined using SET card. For sets of 3D solids,

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element faces on the surface are automatically found and selected as master surface. 5.

TIE element is created of a same structure as FREEZE CONTACT element. TIE element enforces zero relative motion on the contact surface – the contact gap opening remains fixed at the original value and the sliding distance is forced to be zero. Also, rotations at the slave node are matched to the rotations of the master patch.

6.

Presently one TIE element is created for each slave node. This assures reasonably efficient numerical computations without creating an excessive number of tie elements. However, this may require special handling in some cases, such as when a master surface wraps around the slave set. In such cases, switching the role of slave and master may be recommended. Alternatively, multiple TIE elements can be created in order to cover all possible directions of relative motion (a simplified illustration is shown in Figure 3).

Figure 3: Special case - Master surface wraps around a slave node set.

7.

The adjustment of slave nodes doesn’t create any strain in the model. If DISCRET=N2S is selected, it is treated as a change in the initial model geometry. If DISCRET=S2S is selected, it is treated as a change in the initial contact opening/penetration. If a node on the slave entity lies outside the projection zone of the master surface, it will always be skipped during adjustment since no contact element has been constructed for it. If different contact interfaces involve the same nodes, nodal adjustment definitions are processed sequentially in the order of identification numbers of the contact interfaces. Care must be taken to avoid conflicts between the nodal adjustments; otherwise, contact element errors or lack of compliance may occur. a) The ADJUST field must be set to “NO” for self-contact. b) If a real value (the searching depth criterion for adjustment) is input for the ADJUST field, a searching zone for adjustment is defined. The slave nodes in this searching zone, for which contact elements have been created, will be adjusted. If ADJUST is larger than or equal to SRCHDIS, all the slave nodes, for which contact elements have been created, will be adjusted.

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Figure 4: An illustration depicting how ADJUST works.

Depth Criterion The depth criterion (A non-negative real value for ADJUST) is used to define the searching zone for adjustment as shown in Figure 4. This searching zone is created in the pushout direction up to a distance equal to the value of the ADJUST field. The slave nodes within the searching zone (with defined contact elements) are then considered for adjustment based on the rules specified within this comment (Comment 7). c) If the ADJUST field is set to an integer value (the identification number of a grid SET entry), the nodes shared by the slave entity and the grid SET will be checked for contact creation, that is SRCHDIS will be ignored for these nodes, and then adjusted if a projection is found. The nodes belonging to the grid SET but not to the slave entity will be simply ignored. 8.

This card is represented as a group in HyperMesh.

(Geometric nonlinear analysis (ANALYSIS = NLGEOM subcases)) 9.

TIE is implemented as a Tied Contact in geometric nonlinear subcases. A geometric nonlinear subcase is one that has an ANALYSIS = NLGEOM entry in the subcase definition.

10. The slave entity (SSID) always consists of grid nodes. It may be specified as:

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a set of grid nodes defined using SET card. a surface defined using SURF card (the slave nodes are picked from the respective nodes of the SURF faces). a set of elements (shells or solids) defined using SET card. Slave nodes are picked from the respective nodes of the elements in the set. For 3D solids, only nodes on the surface of the solid body are selected; internal nodes are not considered. 11. The master entity (MSID) may be defined as: a surface defined using SURF card. a set of elements (shells or solids) defined using SET card. 12. This card is represented as a group in HyperMesh.

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OptiStruct 13.0 Reference Guide 2109 Proprietary Information of Altair Engineering

TLOAD1 Bulk Data Entry TLOAD1 – Transient Response Dynamic Excitation, Form 1 Description Defines a time-dependent dynamic load or enforced motion of the form:

for use in transient response analysis. Where,

f(t) is the time-dependent dynamic load or enforced motion.

A defines the amplitude of the dynamic excitation and is referenced by the EXCITEID field. (F)t is a user-defined function that defines the time-variant nature of f(t). It is specified by referencing a predefined TABLEDi entry in the TID field. is the time delay defined in the DELAY field. Format (1)

(2)

(3)

(4)

(5)

(6)

TLOAD1

SID

EXC ITEID

DELAY

TYPE

TID

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

TLOAD1

5

7

(4)

(5)

(6)

LOAD

13

Field

Contents

SID

Set identification number.

(7)

(8)

(9)

(10)

(Integer > 0)

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Field

Contents

EXCITEID

Identification number of the DAREA, SPCD, FORCEx, MOMENTx, PLOADx, RFORCE, QVOL, QBDY1 or GRAV entry set that defines {A}. See comments 2 and 3. (Integer > 0)

DELAY

Defines time delay . If it is a non-zero integer, it represents the identification number of DELAY bulk data entry that defines . If it is real, then it directly defines the value of that will be used for all degrees-of-freedom that are excited by this dynamic load entry. See comment 7. (Integer > 0, real or blank)

TYPE

Defines the type of the dynamic excitation. See comments 2 and 3. (Integer, character or blank; Default = 0)

TID

Identification number of TABLEDi entry that gives F(t). (Integer > 0)

Comments 1.

Dynamic excitation sets must be selected with the subcase information command DLOAD=SID.

2.

The type of dynamic excitation is specified by TYPE (field 5) based on the following table: TYPE TYPE of Dynamic Excitation Integer

Character

0

L, LO, LOA, or Applied load (force or moment) LOAD (Default)

1

D, DI, DIS, or DISP

2

V, VE, VEL, or Enforced velocity; EXCITEID references SPC/SPCD data. VELO

3

A, AC, ACC, or ACCE

Altair Engineering

Enforced displacement or temperature; EXCITEID references SPC/SPCD data.

Enforced acceleration; EXCITEID references SPC/SPCD data.

OptiStruct 13.0 Reference Guide 2111 Proprietary Information of Altair Engineering

3.

TYPE (field 5) also determines the manner in which EXCITEID (field 3) is used by the program as described below. Excitation specified by TYPE is applied load. The EXCITEID must reference DAREA, FORCEx, MOMENTx, PLOAD, RFORCE, GRAV, QVOL or QBDY1 entries. Excitation specified by TYPE is enforced motion. The EXCITEID must reference SPC/SPCD entries. TYPE = 1 must be specified if the EXCITEID field references SPCD data used in transient heat transfer analysis to define time-dependent thermal boundary conditions.

4.

TLOAD1 loads may be combined with TLOAD2 loads only by specification on a DLOAD entry. That is, the SID on a TLOAD1 entry may not be the same as that on a TLOAD2 entry.

5.

SID must be unique for all TLOAD1, TLOAD2, RLOAD1, and RLOAD2 entries.

6.

If TLOAD1 entries are selected for Fourier analysis, then the time-dependent loads on the TLOAD1 entries are transformed to the frequency domain. Then the analysis is performed as a frequency response analysis, but the solution and the output are converted to and printed in the time domain.

7.

If DELAY is blank or zero,

8.

When EXCITEID refers to an SPCD entry, the modal space will be augmented with displacement vector(s) from linear static analysis with unit prescribed displacement at each of the SPCD degrees-of-freedom. EXCITEID cannot reference the LOAD and LOADADD bulk data entries.

9.

This card is represented as a loadcollector in HyperMesh.

will be zero.

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TLOAD2 Bulk Data Entry TLOAD2 – Transient Response Dynamic Excitation, Form 2 Description Defines a time-dependent dynamic excitation or enforced motion of the form:

for use in a transient response analysis, where

.

Where, is the time-dependent dynamic load or enforced motion.

A defines the amplitude of the dynamic excitation and is referenced by the EXCITEID field. is the time delay defined in the DELAY field. T1 and T2 are time constants defined in the T1 and T2 fields. B, C, and are the growth coefficient, exponential coefficient, frequency and phase angle respectively and are defined in the corresponding B, C, F and P fields. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

TLOAD2

SID

EXC ITEID

DELAY

TYPE

T1

T2

F

P

C

B

(10)

Example

(1)

(2)

(3)

TLOAD2

4

10

Altair Engineering

(4)

(5)

(6)

(7)

(8)

2.1

4.7

12.0

(9)

(10)

OptiStruct 13.0 Reference Guide 2113 Proprietary Information of Altair Engineering

2.0

Field

Contents

SID

Set identification number. (Integer > 0)

EXCITEID

Identification number of the DAREA, SPCD, FORCEx, MOMENTx, PLOADx, RFORCE, QVOL, QBDY1 or GRAV entry set that defines {A}. See comments 2 and 3. (Integer > 0)

DELAY

Defines time delay . If it is a non-zero integer, it represents the identification number of DELAY bulk data entry that defines . If it is real, then it directly defines the value of that will be used for all degrees-of-freedom that are excited by this dynamic load entry. See comment 4. (Integer > 0, real or blank)

TYPE

Defines the type of the dynamic excitation. See comments 2 and 3. (Integer, character or blank; Default = 0)

T1

Time constant. (Real > 0.0)

T2

Time constant. (Real; T2>T1)

F

Frequency in cycles per unit time. (Real > 0.0; Default = 0.0)

P

Phase angle in degrees. (Real; Default = 0.0)

C

Exponential coefficient.

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Field

Contents (Real; Default = 0.0)

B

Growth coefficient. (Real; Default = 0.0)

Comments 1.

Dynamic excitation sets must be selected with the subcase information command with DLOAD=SID.

2.

The type of dynamic excitation is specified by TYPE (field 5) based on the following table: TYPE TYPE of Dynamic Excitation Integer 0

3.

Character L, LO, LOA, or LOAD

Applied load (force or moment)

1

D, DI, DIS, or DISP

Enforced displacement or temperature; EXCITEID references SPC/SPCD data.

2

V, VE, VEL, or VELO

Enforced velocity; EXCITEID references SPC/SPCD data.

3

A, AC, ACC, or ACCE

Enforced acceleration; EXCITEID references SPC/SPCD data.

(Default)

TYPE (field 5) also determines the manner in which EXCITEID (field 3) is used by the program as described below. If the type of dynamic excitation specified by TYPE is applied load, then EXCITEID must reference DAREA, FORCEx, MOMENTx, PLOAD, RFORCE, GRAV, QVOL or QBDY1 entries. If the type of dynamic excitation specified by TYPE is enforced motion, then EXCITEID must reference SPC/SPCD entries. TYPE = 1 must be specified if the EXCITEID field references SPCD data used in transient heat transfer analysis to define time-dependent thermal boundary conditions

4.

If DELAY is blank or zero,

5.

TLOAD1 loads may be combined with TLOAD2 loads only by specification on a DLOAD entry. That is, the SID on a TLOAD1 entry may not be the same as that on a TLOAD2 entry.

Altair Engineering

will be zero.

OptiStruct 13.0 Reference Guide 2115 Proprietary Information of Altair Engineering

6.

SID must be unique for all TLOAD1, TLOAD2, RLOAD1, and RLOAD2 entries.

7.

TLOAD2 entries cannot be used with Fourier analysis.

8.

The continuation entry is optional.

9.

When EXCITEID refers to an SPCD entry, the modal space will be augmented with displacement vector(s) from linear static analysis with unit prescribed displacement at each of the SPCD degrees-of-freedom. EXCITEID cannot reference the LOAD and LOADADD bulk data entries.

10. This card is represented as a loadcollector in HyperMesh.

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TSTEP Bulk Data Entry TSTEP – Transient Time Step Description Defines time step intervals at which a solution will be generated and output in transient analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

TSTEP

SID

N1

DT1

N01

W3,1

W4,1

N2

DT2

N02

W3,2

W4,2

(9)

(10)

-etc.-

Example

(1)

(2)

(3)

(4)

(5)

TSTEP

2

10

.001

5

9

0.01

1

Field

Contents

SID

Set identification number.

(6)

(7)

(8)

(9)

(10)

No default (Integer > 0) N#

Number of time steps of value DT#. No default (Integer > 1)

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Field

Contents

DT#

Time increment. No default (Real > 0.0)

N0#

Skip factor for output. Every N0i-th step will be saved for output. Default = 1 (Integer > 0)

W3,#

The frequency of interest in radians per unit time; used for the conversion of overall structural damping into equivalent viscous damping. See comment 3. Default = blank (Real > 0.0, or blank)

W4,#

The frequency of interest in radians per unit time; used for the conversion of element structural damping into equivalent viscous damping. See comment 3. Default = blank (Real > 0.0, or blank)

Comments 1.

TSTEP entries must be selected with the Subcase Iinformation command TSTEP = SID.

2.

Note that the entry permits changes in the size of the time step during the course of the solution. Thus, in the example shown, there are 10 time steps of value .001, followed by 9 time steps of value .01. Also, in the case of this example, you have requested that the output be recorded for t = 0.0, .005, .01, .02, .03, and so on.

3.

W3 and W4 define frequencies used in transient analyses to convert structural damping to equivalent viscous damping. See the Reference Guide entries for PARAM,W3 and PARAM,W4 for more details.

4.

Different values for W3 and W4 may be set for each set of time increments. If any of the fields are left blank then the value is taken from the PARAM, W3 or PARAM, W4 definition.

5.

This card is represented as a loadcollector in HyperMesh.

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TSTEPNL Bulk Data Entry TSTEPNL – Parameters for Geometric Nonlinear Implicit Dynamic Analysis Control Description Defines parameters for geometric nonlinear implicit dynamic analysis strategy. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

TSTEPNL

ID

NDT

DT

KSTEP

C ONV

EPSU

EPSP

EPSW

MAXLS

LSTOL

Example

(1)

(2)

TSTEPNL

99

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

0.01

Field

Contents

ID

Each TSTEPNL bulk data card must have a unique ID. No default (Integer > 0)

NDT

Number of implicit load sub-increments. No default (Integer > 0)

DT

Initial time step. No default (Real > 0)

KSTEP

Number of iterations before stiffness update. See comment 3.

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OptiStruct 13.0 Reference Guide 2119 Proprietary Information of Altair Engineering

Field

Contents Default = 6 for BCS solver Default = 3 for PCG solver (Integer > 0)

CONV

Flags to select implicit convergence criteria. Default = UPW (Any combination of U, P and W)

EPSU

Error tolerance for displacement (U) criterion. Default = 1.0E-2 (Real > 0.0)

EPSP

Error tolerance for load (P) criterion. Default = 1.0E-2 (Real > 0.0)

EPSW

Error tolerance for work (W) criterion. Default = 1.0E-3 (Real > 0.0)

MAXLS

Maximum number of line searches allowed for each iteration. Default = 20 (Integer > 0)

LSTOL

Line search tolerance. Default = 1.0E-3 (Real > 0.0)

Comments 1.

The TSTEPNL bulk data entry is selected by the Subcase Information command TSTEPNL = option. Each subcase for which nonlinear implicit dynamic analysis is desired requires a TSTEPNL command.

2.

Additional control for geometric nonlinear implicit dynamic solution schemes (ANALYSIS = IMPDYN) can be defined using TSTEPNX bulk data entry. Defaults will be used if TSTEPNX is not present.

3.

The solution method for geometric nonlinear implicit dynamic analysis (ANALYSIS = IMPDYN) is modified or Quasi-Newton. The frequency of stiffness matrix updates is controlled by KSTEP. For highly nonlinear problems, it is recommended to reduce KSTEP

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for better performance. KSTEP = 1 means full Newton. The initial implicit time step is DT. All subsequent time steps will be determined automatically. Termination time, TTERM, is defined by a TTERM subcase entry or computed from TTERM = NDT*DT. TTERM takes precedence. 4.

The time integration scheme for implicit transient is defined on TSTEPNX. The default method is α-HHT.

5.

For more information about geometric nonlinear analysis, refer to the Geometric Nonlinear Analysis section.

6.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 2121 Proprietary Information of Altair Engineering

TSTEPNX Bulk Data Entry TSTEPNX – Optional Parameters for Geometric Nonlinear Implicit Dynamic Analysis Control Description Defines additional parameters for geometric nonlinear implicit dynamic analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

TSTEPNX

ID

TA0

DTA

DTTH

NPRINT

RFILE

SOLV

TSC TRL

DTMIN

DTMAX

LSMETH

RREFIF

DYNA

ALFA

BETA

GAMA

SMDISP

ITW

DTSC I

LDTN

DTSC D

LARC

(8)

(9)

(10)

NC YC LE

FIXTID/ TOUT

Example 1

(1)

(2)

TSTEPNL

99

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

(5)

(6)

(7)

(8)

(9)

(10)

0.01

Example 2

(1)

(2)

TSTEPNL

99

0.01

TSTEPNX

99

0.1

NEWT

(3)

ARC

(4)

1.e-4

0.1

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Example 3

(1)

(2)

TSTEPNL

99

(3)

99

NEWT

(5)

(6)

0.01

0.01

TSTEPNX

(4)

3

(7)

(8)

(9)

(10)

PW

0.01

0.1

ARC

NEWM

1.e-4

0.1

0.25

0.5

Field

Contents

ID

Identification number of an associated TSTEPNL entry. No default (Integer > 0)

TA0

Start time for writing animation files. Default = 0.0 (Real > 0)

DTA

Output time step for animation files. If zero, no output (See comment 3). Default = DT (Real > 0)

DTTH

Output time step for time history files. If zero, no output (See comment 3). Default = 0.1*DT (Real > 0)

NPRINT

Print every NPRINT iterations. If negative, to .out and standard output; if positive, only to .out file. Default = -1 (Integer)

RFILE

Cycle frequency to write restart file for nonlinear iteration.

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OptiStruct 13.0 Reference Guide 2123 Proprietary Information of Altair Engineering

Field

Contents Default = 5000 (Integer > 0)

SOLV

Geometric nonlinear implicit solution method. NEWT – Modified Newton. BFGS – BFGS quasi-Newton method. Default = NEWT (Character = NEWT, or BFGS)

TSCTRL

Time step control. ARC – Arc-length is used to accelerate and control the convergence. The time step is determined by displacement norm control (arc-length). SIMP – Simple time step control. NONE – No time step control. A warning will be issued. In the case of divergence, the time step will be repeated with half the step size. The run will be terminated according to DTMIN and NCYCLE. Default = ARC (Character)

DTMIN

Minimum geometric nonlinear implicit time step. If DTMIN is reached, simulation will be terminated (See comment 3). Default = 1e-5*DT (Real > 0)

DTMAX

Maximum geometric nonlinear implicit time step from which time step is set constant (See comment 3). Default = 3*DT (Real > 0)

LSMETH

Line search method. Default = ENERGY (Character = NONE, FORCE, ENERGY, or AUTO)

RREFIF

Special residual force computation with contact interfaces present. Default = no special treatment (Integer = 0, …, 5) 0 1 2 3 4

– – – –

Aggressive (modified entirely by the out-of-balance value). Average (modified each time with 200% maximum). Light (modified each time with 20% maximum). No change. – No change; except for the first contact.

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Field

Contents 5

NCYCLE

– Modified automatically (for imposed displacement only).

Maximum number of time steps. If reached, solution will be terminated. NCYCLE = 0 means no limit. Default = no limit (Integer > 0)

FIXTID

Identification number of a TABLEDi entry. The x values of the table define fixed time points that the automatic time step control will adhere to. (Integer > 0)

TOUT

The method to determine the fixed time point. AUTO – Fully automatic time step control. NLOAD - The time points in all TABLEDi that are referenced by NLOAD1 in one subcase. Default = AUTO (AUTO or NLOAD)

DYNA

Implicit transient solution methods. HHT – α-HHT method. NEWM – General Newmark method. Default = HHT (Character = HHT or NEWM)

ALFA

Parameter in α-HHT Method (DYNA = HHT). Default = -0.05 (Real, -1/3 < ALFA < 0.0)

BETA

Parameter in general Newmark method (DYNA = NEWM). Default = 0.25 (Real, -2 * BETA < GAMA < 0.5)

GAMA

Parameter in general Newmark method (DYNA = NEWM). Default = 0.5 (Real, -2 * BETA < GAMA < 0.5)

SMDISP

Perform small displacement and rotation analysis instead of geometric nonlinear analysis. PARAM, SMDISP, YES overwrites this definition. OFF – Geometric nonlinear analysis.

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Field

Contents ON – Small displacements and small rotations analysis. Default = OFF (Character = ON, OFF)

ITW

If the solution of a time step converges within ITW iterations, the next time step will be increased by a factor controlled by DTSCI. Default = 6 for TSCTRL = ARC Default = 2 for TSCTRL = SIMP (Integer > 0)

DTSCI

Maximum scale factor for increasing the time step (TSCTRL = ARC). Scale factor for TSCTRL = SIMP. Default = 1.1 (Real > 0)

LDTN

Maximum number of iterations before resetting and decreasing the time step by a factor of DTSCD. Default = 20 for TSCTRL = ARC Default = 15 for TSCTRL = SIMP (Integer > 0)

DTSCD

Scale factor for decreasing the time step (TSCTRL = ARC, SIMP). Default = 0.67 (Real > 0)

LARC

Input arc-length for TSCTRL = ARC. Default = automatic computation (Real)

Comments 1.

The TSTEPNX bulk data entry is selected by the Subcase Information command TSTEP = option. There must also be a TSTEPNL bulk data entry with the same ID. It is only used in geometric nonlinear implicit dynamic analysis (ANALYSIS = IMPDYN); it is ignored in other analyses.

2.

The solution method for geometric nonlinear implicit analysis is selected by SOLV. The frequency of stiffness matrix updates is controlled by TSTEPNL, KSTEP. For highly nonlinear problems, it is recommended to reduce KSTEP for better performance. KSTEP = 1 means full Newton.

3.

The initial time step DTINI = DT is defined by TSTEPNL.

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4.

For more information about geometric nonlinear analysis, refer to the Geometric Nonlinear Analysis section.

5.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 2127 Proprietary Information of Altair Engineering

UNBALNC Bulk Data Entry UNBALNC – Unbalanced Load (Rotor Dynamics) Description This entry defines the unbalanced rotating load during a rotor dynamic analysis in Frequency Response solution sequences. The unbalanced load is specified in a cylindrical system where the rotor rotation axis is the Z-axis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

UNBALNC

SID

MASS

GRID

X1

X2

X3

ROFFSET

THETA

ZOFFSET

FON

FOFF

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

UNBALNC

200

1.2

3103

1.0

0.0

0.0

0.3

45.0

0.1

2

110

Argument

Options

SID

0>

(8)

(9)

(10)

Description setid

Set identification number.

No default

MASS

0/Real>

Defines the magnitude of unbalanced mass (see comment 4).

(No default)

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Argument

Options

GRID



Description Grid Point identification number of node at which the unbalanced load is applied.

No default

X1, X2, X3



Components of a vector that are used to define a cylindrical coordinate system centered at “GRID”. The vector components are defined from “GRID” in the displacement coordinate system of the grid point at “GRID” (see comment 6).

No default

ROFFSET

0/Real> 0> Default = 1.0



If an integer value (must be greater than 0) is input, it references the identification number of a TABLEDi entry that specifies the offset values as a function of frequency (see comment 4). This field defines the distance by which the unbalanced mass is offset in the X-Y plane perpendicular to the Z direction (spin axis, Figure 1). If a real number is input, the offset value is considered constant.

THETA

Default = 0.0

ZOFFSET

Angular position (in degrees) of the unbalanced mass in the cylindrical coordinate system defined by X1, X2, and X3.

0/Real> 0> Default = 0.0



Altair Engineering

If an integer value (must be greater than 0) is input, it references the identification number of a TABLEDi entry that specifies the offset values as a function of frequency (see comment 4). This field defines the distance by which the unbalanced mass is offset in the Z

OptiStruct 13.0 Reference Guide 2129 Proprietary Information of Altair Engineering

Argument

Options

Description direction (spin axis, Figure 1). If a real number is input, the offset value is considered constant.

F ON

0>

This field defines the starting frequency at which the unbalanced load is applied (see comment 5).

Default = 0.0

F OFF

0>

This field defines the stopping (final) frequency at which the unbalanced load is applied (see comment 5).

Default = 999999.0 Comments 1.

Currently, models containing multiple UNBALNC bulk data entries with the same set identification number (SID) are not supported. Each UNBALNC bulk data entry must have a unique SID.

2.

For frequency response analysis, the UNBALNC bulk data entry is referenced by a DLOAD Subcase Information entry.

3.

An unbalanced load on the rotating system is generated as a consequence of these three factors: Unbalanced mass of the system (rotor) about its axis of rotation (MASS field on the UNBALNC entry). The magnitude of separation between the rotating axis and the unbalanced mass (ZOFFSET and ROFFSET fields on the UNBALNC entry). The angular spin speed of the rotor (specific fields on the RGYRO and RSPINR bulk data entries).

4.

ROFFSET field: Each entry in the TABLEDi entry specifies the distance by which the unbalanced mass is offset in the X-Y plane (perpendicular to the axis of rotation of the rotor). ZOFFSET field: Each entry in the TABLEDi entry specifies the distance by which the unbalanced mass is offset in the Z direction (axis of rotation of the rotor).

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5.

The rotation of the unbalanced load occurs in the positive Z direction which is defined by GRIDA and GRIDB on the RSPINR bulk data entry.

6.

The initial position of the unbalanced mass and the direction of its subsequent rotation are defined with respect to a cylindrical coordinate system. Its angular position is measured from the plane defined by both the Z-axis and the vector (X1, X2, and X3) with THETA=0.0 being the direction of the vector (X1, X2, and X3) itself. The rotation of the unbalanced load occurs in the positive Z direction.

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OptiStruct 13.0 Reference Guide 2131 Proprietary Information of Altair Engineering

USET Bulk Data Entry USET – Set of Degrees-of-Freedom for Residual Vector Calculation Description Defines a set of degrees-of-freedom. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

USET

SNAME

G1

C1

G2

C2

G3

C3

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

USET

U6

564

4

765

1456

8

5

Field

Contents

SNAME

Set name

(9)

(10)

(Character, only U6, ZEROU6 are allowed) Gi

Grid or scalar point identification numbers. No default (Integer > 0)

Ci

Component numbers. (Integer zero or blank for scalar points, or up to 6 unique digits (0 < integer < 6) may be placed in the field with no embedded blanks for grid points. The components refer to the coordinate system referenced by the grid points.)

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Comments 1.

A maximum of 18 degrees-of-freedom can be defined on one USET entry.

2.

If SNAME=ZEROU6, then the degrees-of-freedom are omitted from the set.

3.

For normal modes analysis with the Lanczos eigensolver, the case control command RESVEC=YES must be used to create residual vectors based on the USET DOF . If the AMSES or AMLS eigensolvers are used, the residual vectors will always be created. The residual vectors are calculated using the unit load method.

4.

For modal frequency response and modal transient analysis, the USET residual vectors are always calculated if the AMSES and AMLS eigensolvers are used, and are not calculated if the Lanczos eigensolver is used.

5.

The residual vectors are then exported together with the eigenvectors to the H3D, PUNCH, and OUTPUT2 files. If stress output is requested, the stress state for each mode is output to the H3D, PUNCH, and OUTPUT files.

6.

If SNAME is not U6 or ZEROU6, USET will be ignored.

7.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or STRICT, it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid reference is a scalar point (SPOINT), and that the component be > 1 when the grid reference is a structural grid point (GRID). When SPSYNTAX is set to MIXED, it is allowed for grid/component pairs (G#/C#) that the grid reference be either a scalar point (SPOINT) or a structural grid point (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When the component is greater than 1, the grid reference must always be a structural grid (GRID).

8.

This card is represented as a constraint load in HyperMesh.

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OptiStruct 13.0 Reference Guide 2133 Proprietary Information of Altair Engineering

USET1 Bulk Data Entry USET1 – Set of Degrees-of-Freedom for Residual Vector Calculation, Alternate Form Description Defines a set of degrees-of-freedom. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

USET1

SNAME

C

G1

G2

G3

G4

G5

G6

G7

G8

G9

-etc.-

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

USET1

U6

123

34

88

4

12

19

7

1234

65

(10)

Alternate Format and Example (1)

(2)

(3)

(4)

(5)

(6)

USET1

SNAME

C

G1

“THRU”

G2

USET1

U6

123456

88

THRU

207

Field

Contents

SNAME

Set name

(7)

(8)

(9)

(10)

(Character, only U6, ZEROU6 are allowed)

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Field

Contents

C

Component number. (Integer zero or blank for scalar points, or up to 6 unique digits (0 < integer < 6) may be placed in the field with no embedded blanks for grid points. The components refer to the coordinate system referenced by the grid points.)

Gi

Grid or scalar point identification numbers. (Integer > 0, for THRU option, G1 < G2)

Comments 1.

If the alternate format is used, all points in the sequence G1 through G2 are not required to exist, but there must be at least one boundary degree-of-freedom for the model or a fatal error will result. Any grids implied in the THRU that do not exist will collectively produce a warning message, but will otherwise be ignored.

2.

If SNAME=ZEROU6, then the degrees-of-freedom are omitted from the set.

3.

For normal modes analysis with the Lanczos eigensolver, the case control command RESVEC=YES must be used to create residual vectors based on the USET1 DOF. If the AMSES or AMLS eigensolvers are used, the residual vectors will always be created. The residual vectors are calculated using the unit load method.

4.

For modal frequency response and modal transient analysis, the USET1 residual vectors are always calculated if the AMSES and AMLS eigensolvers are used, and are never calculated if the Lanczos eigensolver is used.

5.

USET1 is applied to normal modes analysis subcases that have the case control RESVEC=YES specified. In such cases, residual vectors are calculated using the unit load method. The residual vectors are then exported together with the eigenvectors to the H3D, PUNCH, and OUTPUT2 files. If stress output is requested, the stress state for each mode is output to the H3D, PUNCH, and OUTPUT files.

6.

If SNAME is not U6 or ZEROU6, USET1 will be ignored.

7.

When the SPSYNTAX setting on the SYSSETTING I/O option is set to CHECK (default) or MIXED, it is allowed that when grid lists are provided for a given component, that the grid references be either scalar points (SPOINT) or structural grid points (GRID) when the component is 0, 1 or blank; interpreting all of these as 0 for scalar points and as 1 for structural grids. When SPSYNTAX is set to STRICT it is required for grid/component pairs (G#/C#) that the component be 0 or blank when the grid references are to scalar points (SPOINT), and that the component be > 1 when the grid references are to structural grid points (GRID). When the component is greater than 1, the grid references must always be a structural grid (GRID).

8.

This card is represented as a constraint load in HyperMesh.

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OptiStruct 13.0 Reference Guide 2135 Proprietary Information of Altair Engineering

XDAMP Bulk Data Entry XDAMP – Raleigh Damping for Geometric Nonlinear Dynamic Analysis Description Defines values for Raleigh damping for geometric nonlinear dynamic analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

XDAMP

DID

GSID

ALFA

BETA

(7)

(8)

(9)

(10)

Example

(1)

(2)

(3)

(4)

(5)

XDAMP

100

34

3.0

1.0

(6)

Field

Contents

DID

Unique damping identification number.

(7)

(8)

(9)

(10)

(Integer > 0) GSID

Grid set identification number. Damping is applied to the grid points in this set. Default = all grids in the model (blank or Integer > 0)

ALFA

Factor for the stiffness matrix contribution. (Real > 0)

BETA

Factor for the mass matrix contribution. (Real > 0)

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Comments 1.

Rayleigh damping is applied to all geometric nonlinear dynamic analysis subcases, implicit and explicit. It is ignored in all other subcases.

2.

In implicit dynamic analysis damping is applied to all grid points and GSID is ignored. Multiple XDAMP is not allowed in implicit dynamic analysis.

3.

XDAMP and PARAM W3/G are mutually exclusive.

4.

Grid sets in all XDAMP statements must contain unique sets of grid points.

5.

The viscous damping matrix B is calculated from the mass matrix M and stiffness matrix K using: B = ALFA * M + BETA * K

6.

This card is represented as an interface in HyperMesh.

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OptiStruct 13.0 Reference Guide 2137 Proprietary Information of Altair Engineering

XHISADD Bulk Data Entry XHISADD – Time History Output Combination for Geometric Nonlinear Analysis Description Defines a time history output set as a union of time history outputs defined via XHIST entries. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

XHISADD

SID

S1

S2

S3

S4

S5

S6

S7

S8

S9

etc.

(10)

Example

(1)

(2)

(3)

(4)

(5)

(6)

(7)

XHISADD

101

2

3

1

6

4

Field

Contents

SID

Set identification number.

(8)

(9)

(10)

(Integer > 0) Sj

Set identification numbers of time history output defined via XHIST entries. (Integer > 0)

Comments 1.

Multipoint constraint sets must be selected with the Subcase Information command XHIST=SID.

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2.

The Sj must be unique and may not be the identification number of a rigid wall set defined by another XHISADD entry.

3.

XHISADD entries take precedence over XHIST entries. If both have the same SID, only the XHISADD entry will be used.

4.

This card is represented as a loadcollector in HyperMesh.

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OptiStruct 13.0 Reference Guide 2139 Proprietary Information of Altair Engineering

XHIST Bulk Data Entry XHIST – Time History Output Request for Geometric Nonlinear Analysis Description Defines the time history output request for geometric nonlinear analysis. Format (1)

(2)

(3)

XHIST

SID

(4)

(5)

(6)

(7)

(8)

(9)

(10)

LABEL

FILE

TYPE

C ID

DTTHM

DATA

VAR1

VAR2

VAR3

VAR4

VAR5

VAR6

VAR7

VAR8

...

ID1

ID2

ID3

ID4

ID5

ID6

ID7

ID8

...

ENTRY

Example

(1)

(2)

XHIST

100

(3)

(4)

(5)

AY

(6)

(7)

(8)

(9)

(10)

GRID

DATA

DEF

AX

ENTRY

345

6687

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Field

Contents

SID

Set identification number. (Integer > 0)

LABEL

(Character or blank)

FILE

Creation of different time history files runnameTnnx(n:0-1,x:blank or a-i). (Characters – A, B, C…, and I, or blank)

TYPE

Entity type. See table 1. (Character according to table)

CID

Frame coordinate system identification. (Integer > 0)

DTTHM

Output time step for time history files. Once it is specified, it will overwrite DTTH on NLPARMX, TSTEPNX and XSTEP to control the output time step of history file specified by FILE in this card.

DATA

DATA flag indicating that data labels follow. If no DATA is specified, the default is VAR1 = DEF.

VARi

Output data label. See table 1. (Character)

ENTRY

ENTRY flag indicating that a list of identifiers is following.

IDi

Entry identifier for TYPE. See table 1. (Integer > 0)

Comments 1.

XHIST sets must be selected with the Subcase Information command XHIST = SID or by XHISADD. It can only be selected in geometric nonlinear analysis subcases which are defined by an ANALYSIS = NLGEOM, IMPDYN or EXPDYN subcase entry.

2.

Table 1 below gives the definitions of TYPE, VARi, and IDi. The notation DEF (DX, DY, DZ, VX, VY, VZ) means that if DEF is selected, all six values following in parenthesis are written at once. However, instead of requesting DEF each value can be requested individually. Details on the output requests can be found in Table 2.

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3.

A property cannot be in several time history groups. In this case, the only variables output in time history are the variables declared in the last option which refers to the property.

4.

It is not possible to have the same grid point several times in the same GRID group. OptiStruct provides an error message in such cases.

5.

If an output coordinate system GRID, CD is specified: coordinates, displacement, linear and angular velocities, linear and angular accelerations of the grid are projected to that system.

6.

If a reference frame is specified: local coordinates, relative displacement, relative linear and angular velocities, relative linear and angular accelerations of the node with respect to the frame are output.

7.

Global results are always written.

8.

The OFF element status information works as follows: OFF = 0 – Element deleted. OFF = 1 – Element active. OFF = 2 – Element active using small strain. OFF = -1 – Element is sleeping (turned rigid).

Table 1: Output Requests TYPE

VARi

IDi

GRID

DEF (DX, DY, DZ, VX, VY, VZ), D (DX, DY, DZ), V (VX, VY, VZ), A (AX, AY, AZ), VR (VRX, VRY, VRZ) AR (ARX, ARY, ARZ), XYZ (X, Y, Z), REACX, REACY, REACZ, REACXX, REACYY, REACZZ

Grid ID

PROP

DEF (IE, KE, XMOM, YMOM, ZMOM, MASS, HE), XCG, YCG, ZCG, XXMOM, YYMOM, ZZMOM, IXX, IYY, IZZ, IXY, IYZ, IZX, RIE, KERB, RKERB, RKE

Property ID

SHELL

DEF (F1, F2, F12, M1, M2, M12, IEM, IEB, EMIN, EMAX, OFF), STRESS (F1, F2, F12, Q1, Q2, M1, M2, M12), STRAIN (E1, E2, E12, SH1, SH2, K1, K2, K12), PLAS (EMIN, EMAX)

Element ID

SOLID

DEF (SX , SY, SZ, SXY, SYZ, SXZ, IE, DENS, PLAS, TEMP, OFF), STRESS (SX, SY, SZ, SXY, SYZ, SXZ), LOCSTRS (LSX, LSY, LSZ, LSXY, LSYZ, LSXZ), BULK, VOL, DAM1, DAM2, DAM3, DAM4, DAM5, DAMA, EPSXX, EPSYY, EPSZZ, EPSXY, EPSXZ, EPSYZ

Element ID

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TYPE

VARi

IDi

RWALL

DEF (FNX, FNY, FNZ, FTX, FTY, FTZ), FN (FNX, FNY, FNZ), FT (FTX, FTY, FTZ)

Load set ID of RWALL

CONTCT

DEF (FNX, FNY, FNZ, FTX, FTY, FTZ), FN (FNX, FNY, FNZ), FT (FTX, FTY, FTZ), M (MX, MY, MZ)

Contact ID

SECT

DEF (FNX, FNY, FNZ, FTX, FTY, FTZ, M1, M2, Load set ID of M3), FN (FNX, FNY, FNZ), FT (FTX, FTY, FTZ), XSECT M (MX, MY, MZ), GLOBAL (FNX, FNY, FNZ, FTX, FTY, FTZ, MX, MY, MZ), LOCAL (F1, F2, F3, M1, M2, M3), CENTER (CX, CY, CZ)

SPRING, BUSH

DEF (FX, FY, FZ, MX, MY, MZ, LX, LY, LZ, RX, RY, RZ, IE, OFF)

Element ID

BEAM, BAR

DEF (F1, F2, M2, M3, IE, OFF), F3, M1

Element ID

ROD

DEF(F, M, IE)

Element ID

Table 2: Output Request Descriptions Type

Output Data Label

Description and Remarks

Global

IE

Internal energy. Global internal energy includes all material internal energy and global spring internal energy, but not spring rotational internal energy.

KE

Kinetic energy.

RKE

Rotational kinetic energy.

CE

Contact energy.

HE

Hourglass energy.

SIE

Spring internal energy.

EFW

External forces work.

TE

Energy sum IE + KE.

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Type

Output Data Label

Description and Remarks

RTE

Total rotational energy IE + KE + RKE.

TTE

Total energy sum IE + KE + RKE + CE + HE.

DTE

Delta energy TTE - EFW.

XMOM, YMOM, ZMOM

Momentum.

DT

Time step.

TER DTE_REL

GRID

PROP

VX, VY, VZ

Velocities.

X, Y, Z

Coordinates.

DX, DY, DZ

Displacement components.

VX, VY, VZ

Velocity components.

AX, AY, AY

Acceleration components.

VRX, VRY, VRZ

Angular velocity components.

ARX, ARY, ARZ

Angular acceleration components.

REACX, REACY, REACZ

Reaction force components

REACXX, REACYY, REACZZ

Reaction moment components

IE

Internal energy.

KE

Kinetic energy.

XMOM, YMOM, ZMOM

Momentum components.

HE

Hourglass energy.

XCG, YCG, ZCG

Center of gravity.

XXMOM, YYMOM, ZZMOM

Rotational momentum components.

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Type

SHELL

Output Data Label

Description and Remarks

IXX, IYY, IZZ, IXY, IYZ, IZX

Inertia matrix components.

RIE

Shear internal energy.

KERB, RKERB

Translational and rotational rigid body energy.

RKE

Rotational kinetic energy.

F1, F2, F12

Stress in direction 1, 2, 12.

Q1, Q2

Mean stress in direction 13, 23.

M1, M2, M12

Moments per unit length per thickness square in direction 1, 2, 12.

IEM, IEB

Internal membrane and bending energy.

EMIN, EMAX

Minimum, maximum equivalent plastic strain.

OFF

Element status. See comment 8.

SOLID

THIC

Thickness.

E1, E2, E12

Stress in direction 1, 2, 12.

SH1, SH2

Shear strain in direction 1, 2.

K1, K2, K12

Curvature in direction 1, 2, 12.

SX , SY, SZ, SXY, SYZ, SXZ

Stress tensor components.

LSX, LSY, LSZ, LSXY, LSYZ, LSXZ

Local stress tensor components.

IE

Internal energy.

DENS

Density.

BULK

Bulk viscosity.

Altair Engineering

Only ISOLID = 1, 2, 12

OptiStruct 13.0 Reference Guide 2145 Proprietary Information of Altair Engineering

Type

Output Data Label

Description and Remarks

VOL

Volume.

PLAS

Plastic strain. Only MATX02.

TEMP

Temperature.

OFF

Element status. See comment 8.

CONTCT

FNX, FNY, FNZ, FTX, FTY, FTZ

Normal and tangential force components.

MX, MY, MZ

Moment components.

RWALL

FNX, FNY, FNZ, FTX, FTY, FTZ

Normal and tangential force components.

SECT

FNX, FNY, FNZ, FTX, FTY, FTZ

Normal and tangential force components.

MX, MY, MZ

Moment components.

F1, F2, F3, M1, M2, M3

Forces and moments in section coordinates.

CX, CY, CZ

Center of the section.

FX, FY, FZ, MX, MY, MZ

Forces and moment components.

LX, LY, LZ

Elongation.

RX, RY, RZ

Rotation.

IE

Internal energy.

OFF

Element status.

F1, F2, F3, M1, M2, M3

Forces and moments in element coordinates

IE

Internal energy

OFF

Element status

SPRING, BUSH

BEAM, BAR

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Type

Output Data Label

Description and Remarks

ROD

F

Axial force

M

Torsional moment

IE

Internal energy

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XSHLPRM Bulk Data Entry XSHLPRM – Default Definition for Shell Element Properties for Geometric Nonlinear Analysis Description Defines default shell element parameters for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

XSHLPRM

ISHELL

ISH3N

ISMSTR

ITHIC K

IPLAS

NIP

IDRIL

(10)

Example

(1)

(2)

XSHLPRM

14

(3)

(4)

(5)

2

(6)

(7)

NEWT

5

Field

Contents

ISHELL

Flag for 4-node shell element formulation.

(8)

(9)

(10)

Default = 24 (Integer) 1 - Q4, visco-elastic hourglass modes orthogonal to deformation and rigid modes (Belytschko). 2 - Q4, visco-elastic hourglass without orthogonality (Hallquist). 3 - Q4, elastic-plastic hourglass with orthogonality. 4 - Q4 with improved type 1 formulation (orthogonalization for warped elements). 12 - QBAT or DKT18 shell formulation. 24 - QEPH shell formulation. ISH3N

Flag for 3-node shell element formulation.

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Field

Contents Default = 2 (Integer) 1 - Standard triangle (C0). 2 - Standard triangle (C0) with modification for large rotation. 30 - DKT18. 31 - DKT_S3.

ISMSTR

Flag for shell small strain formulation. Default = 2 (Integer) 1 - Small strain from time =0 (new formulation compatible with all other formulation flags). 2 - Full geometric non-linearity with optional small strain formulation activation by time step. 3 - Old small strain formulation (only compatible with ISHELL =2). 4 - Full geometric non-linearity (Time step limit has no effect).

ITHICK

Flag for shell resultant stresses calculation. Default = VAR (CONST or VAR) CONST - Thickness is constant. VAR - Thickness change is taken into account.

IPLAS

Flag for shell plane stress plasticity (MATX2, MATX27, and MATX36 only). Default = NEWT (RAD or NEWT) RAD - Radial return. NEWT - Iterative projection with 3 Newton iterations.

NIP

Number of integration points through the thickness. NIP = 0 defines global integration. Default = 5 (Integer 0 < N < 10)

IDRIL

Flag for drilling degree of freedom stiffness.

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Field

Contents If NLGEOM or IMPDYN subcase exists, default = 1, Otherwise, default = 0 (Integer) 0 = No 1 = Yes

Comments 1.

XSHLPRM defines default settings for solid properties that can be overwritten by PSHELLX.

2.

XSHLPRM is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

Q4: Original 4 node OptiStruct shell with hourglass perturbation stabilization. QEPH: Formulation with physical hourglass stabilization for general use. QBAT: Modified BATOZ Q4 24 shell with 4 Gauss integration points and reduced integration for in-plane shear. No hourglass control is needed for this shell. DKT18: BATOZ DKT18 thin shell with 3 Hammer integration points.

4.

ISHELL = 2 is incompatible with one integration point for shell element.

5.

If the small strain option (ISMSTR) is set to 1 or 3, the strain and stress are engineering strain and stress; otherwise they are true strain and stress.

6.

Global integration (NIP = 0) is only compatible with MAT1, MATX2, and MATX36.

7.

For MAT1, membrane only behavior happens if NIP = 1. Otherwise, NIP is ignored and global integration (NIP = 0) is used.

8.

For ITHICK = VAR, it is recommended to use IPLAS = NEWT.

9.

For MATX2, the default value for IPLAS and global integration (NIP=0) is IPLAS = RAD.

10. For MATX36, the default value for IPLAS and global integration (NIP=0) is IPLAS = NEWT. 11. This card is represented as a control card in HyperMesh.

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XSOLPRM Bulk Data Entry XSOLPRM – Default SOLID Properties for Geometric Nonlinear Analysis Description Defines default SOLID properties for geometric nonlinear analysis. Format (1)

(2)

(3)

(4)

(5)

XSOLPRM

ISOLID

ISMSTR

IFRAME

NIP

(6)

(7)

(8)

(9)

(10)

Example

(1)

(2)

XSOLPRM

24

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

222

Field

Contents

ISOLID

Flag for solid elements formulation. Default = 1 for explicit analysis and 14 for implicit analysis (Integer). 1 - Standard 8-node solid element, 1 integration point. Viscous hourglass formulation with orthogonal and rigid deformation modes compensation (Belytschko). 2 - Standard 8-node solid element, 1 integration point. Viscous hourglass formulation without orthogonality (Hallquist). 12 - Standard 8-node solid, full integration (no hourglass). 14 - HA8 locking-free 8-node solid element, co-rotational, full integration, variable number of Gauss points. 16 - Quadratic 20-node solid, full integration, variable number of Gauss points. 17 - H8C compatible solid full integration formulation.

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Field

Contents 24 - HEPH 8-node solid element. Co-rotational, under-integrated. (1 Gauss point) with physical stabilization.

ISMSTR

Flag for small strain formulation (ISOLID = 1, 2, 14, and 24 only). Default = 4 (Integer) 1 - Small strain from time=0. 2 - Full geometric non-linearity with small strain formulation activation by time step. 3 - Simplified small strain formulation from time=0 (non-objective formulation). 4 - Full geometric non-linearity. Time step limit has no effect. 10 - Lagrange type total strain.

IFRAME

Flag for co-rotational element formulation (ISOLID = 1, 2, 12, and 17 only). Default = OFF (ON or OFF)

NIP

Number of integration points (ISOLID = 14, 16 only). Default = 222 (Integer = ijk): 2 < i,j,k < 9

for ISOLID =14

2 < i,k < 3, 2 < j < 9

for ISOLID =16

where: i = Number of integration points in local x direction. j = Number of integration points in local y direction. k = Number of integration points in local z direction. Comments 1.

XSOLPRM defines default settings for solid properties that can be overwritten by PSOLIDX.

2.

XSOLPRM is only applied in geometric nonlinear analysis subcases which are defined by ANALYSIS = NLGEOM, IMPDYN, or EXPDYN. It is ignored for all other subcases.

3.

The ISOLID flag is not used with CTETRA elements. For these, elements with four and ten nodes the number of integration points is fixed at one and four, respectively.

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4.

For fully integrated solids (SOLID =12), the deviatoric behavior is computed using 8 Gauss points; bulk behavior is under-integrated to avoid element locking. It is currently compatible with material MAT1, MATS1, MATX33, and MATX36.

5.

With the small strain option (ISMSTR), strain and stress is engineering strain and stress. Otherwise, it is true strain and stress.

6.

In time history and animation files, the stress tensor is written in the co-rotational frame.

7.

Fully integrated elements (ISOLID =12) only uses full geometric non-linearity (corresponds to ISMSTR = 4). Time step limit has no effect.

8.

ISMSTR = 10 is only compatible with materials using total strain formulation (MATX42).

9.

The time step control XSTEP, TYPEi = SOLID, TSCi = CST only works on elements with ISMSTR = 2.

10. Co-rotational formulation: For ISOLID = 1, 2, 12 and IFRAME = ON, the stress tensor is computed in a co-rotational coordinate system. This formulation is more accurate if large rotations are involved. It comes at the expense of higher computation cost. It is recommended in case of elastic or visco-elastic problems with important shear deformations. The co-rotational formulation is compatible with 8 node solids. 11. HA8 (ISOLID = 14) elements: this element uses a locking-free general solid formulation, co-rotational. The number of Gauss points is defined by NIP flag: for example, combined with NIP = 222 gives an 8 Gauss integration point element, similar to ISOLID = 12. The HA8 formulation is compatible with all material laws. 12. HEPH (ISOLID = 24) elements: This element uses an hourglass formulation similar to QEPH shell elements. 13. The hourglass formulation is viscous for ISOLID = 0, 1, and 2. 14. This card is represented as a control card in HyperMesh.

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XSTEP Bulk Data Entry XSTEP – Parameters for Explicit Analysis Control Description Defines explicit analysis control. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

XSTEP

SID

TA0

DTA

DTTH

NPRINT

RFILE

NITER

NPAMS

DTSC A

DTMIN

TSTYP

TAC T

TYPE1

TSC 1

DT1

DTM1

ESID1

AMST1

TYPE2

TSC 2

DT2

DTM2

ESID2

AMST2

-etc.-

Example

(1)

(2)

XSTEP

2

(3)

0.9

(4)

(5)

(6)

(7)

(8)

(9)

(10)

DETAIL

GRID

C ST

0.9

0.1e-6

Field

Contents

SID

Set identification number. (Integer > 0)

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Field

Contents

TA0

Start time for writing animation files. Default = 0.0 (Real > 0)

DTA

Output time step for animation files. If zero, no output (See comment 3). Default = 0.01*TTERMS (Real > 0)

DTTH

Output time step for time history files. If zero, no output (See comment 3). Default = 0.001*TTERMS (Real > 0)

NPRINT

Print every NPRINT iteration. If negative, to .out and standard output; if positive, only to .out file. Default = -1000 (Integer)

RFILE

Cycle frequency to write restart file for nonlinear iteration. Default = 5000 (Integer > 0)

NITER

Maximum number of iterations in conjugate gradient. Only valid when TSTYP = GRID and TACT = AMS. Default = 1000 (Integer > 0)

NPAMS

Frequency (number of cycles) for writing additional output about the number of iterations before convergence in the conjugate gradient. No default (Integer > 0)

DTSCA

Default scale factor on explicit time step for all elements. Default = 0.9 (Real > 0)

DTMIN

Default minimum explicit time step. Default = 0.0 (Real > 0)

TSTYP

Type of time step control (See comment 2).

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Field

Contents

ELEM

Elemental time step.

GRID

Nodal time step.

CONTACT

Contact interface time step

DETAIL

From definition in continuation lines.

Default = GRID (Character = GRID, ELEM, CONTACT or DETAIL) TACT

Action if minimum time step is reached (For TSTYP = GRID, ELEM, CONTACT, See comment 3). DEF

Default (TSTYP = GRID, CONTACT – Do nothing, ELEM (Shells) = DEL, ELEM (Solids) = STOP).

DEL

Delete (TSTYP = ELEM and CONTACT only).

STOP

Stop run.

CST

Standard mass scaling. Continue with constant time step.

AMS

Advanced mass scaling. Continue with constant time step (TSTYP = GRID and CONTACT only).

Default = DEF (Character = DEF, STOP, DEL, CST, or AMS) TYPEi

Entity type selection (See comment 4). No default (Character = GRID, CONTACT, SHELL, and SOLID)

TSCi

Time step control method (See comment 4). STOP

Stop after reaching DTMi. A restart file will be written. This option is the default for brick and quad elements.

DEL

Element deletion. Elements reaching DTMi are removed. This option is the default for shell elements. For TYPEi = CONTACT, the impacted grid that fixes the time step will be removed from the interface.

CST

Constant time step after reaching DTMi. For TYPEi = SHELL, SOLID (except 8 integration points hexas) the formulation switches to small strain for each

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Field

Contents

element that reaches the DTMi. For TYPEi = GRID, CONTACT, the mass of the grid that reaches DTMi is increased. You should check the evolution of the mass of the model. AMS

Advanced mass scaling. Constant time step after reaching DTMi. Advanced Mass Scaling does not modify the global mass so that the global momentum of the related nodes is conserved. More accurate than TSCi = CST (TYPEi = GRID and CONTACT only).

SET

Forces are reduced to keep constant time step (TYPEi = GRID only).

Default = according to table (blank or Character = STOP, DEL, CST, AMS, SET) DTi

Time step scale factor for entity type (See comment 4). Default = 0.9 (Real > 0.0)

DTMi

Minimum time step for entity type. Default = 0.0 (Real > 0.0)

ESIDi AMS). No default (blank, Integer > 0) AMSTi

Tolerance for advanced mass scaling convergence (Only for TYPEi = AMS). Default = 10-4 (REAL > 0.0)

Comments 1.

The XSTEP bulk data entry is selected by the Subcase Information command XSTEP = option. It is only used in explicit analysis (ANALYSIS = EXPDYN); it is ignored in other analyses.

2.

Any number of continuation lines can be used.

3.

Time step control for explicit analysis

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TSTYP

Elements

Default

Options

Do nothing

AMS, CST, STOP

Shells

DEL

CST, STOP

Solids

STOP

CST, DEL

GRID ELEM

With TSTYP = GRID, the nodal time step is used. With this option, the computation of each cycle is slightly more expensive, but the time step can be higher, mainly for nonoptimized meshes and therefore the overall runtime shorter. For TSTYP = GRID, TACT = CST, the mass of the grid that reaches DTMIN1 is increased. You should check the evolution of the mass of the model. For TSTYP = ELEM, TACT = CST, the element formulation switches to small strain for each element that reaches the DTMIN1. 4.

Overview of default settings and options for TYPEi: Do Nothing

STOP

DEL

CST

AMS

SET

SHELL

N/A

Optional

Default

Optional

N/A

N/A

SOLID

N/A

Default

Optional

Optional

N/A

N/A

CONTACT

Default

Optional

Optional

Optional

Optional

N/A

GRID

Default

Optional

N/A

Optional

Optional

Optional

With TYPEi = GRID, the nodal time step is used. With this option, the computation of each cycle is slightly more expensive, but the time step can be higher, mainly for nonoptimized meshes and therefore the overall runtime shorter. With TYPEi = GRID and TSCi = CST, DTi = 0.67 is recommended. With TYPEi = CONTACT and TSCi = DEL, the impacted node which fixes the time step is removed from the interface. TYPEi = SOLID and TSCi = CST is only active for solid elements with the flag ISMSTR = 2 set on PSOLIDX. This option is not available for 8 integration points. 5.

For more information about geometric nonlinear analysis, refer to the Geometric Nonlinear Analysis section.

6.

TSTYP = NODA and TACT = AMS can activate elementary time step for Advanced Mass Scaling, as well as TYPEi = NODA and TSCi = AMS.

7.

NITER and NPAMS are only valid for Advanced Mass Scaling (AMS). If more NITER iterations have been performed before convergence of the conjugate gradient, the computation stops and error out. If NPAMS is specified, at each NPAMS cycle an additional output is provided including: the number of iterations before convergence of

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the conjugate gradient at this cycle, the final residual norm and the force vector norm. 8.

This card is represented as a loadcollector in HyperMesh.

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Element Quality Check In order to prevent analyses from being carried out on badly discretized models, an element quality check is incorporated into the pre-processing phase. The element quality check is controlled jointly by the CHECKEL parameter (see PARAM, CHECKEL) and the ELEMQUAL bulk data entry. Three types of element quality checks are performed: 1.

Validity check of maximum allowable limits – a bound based on mathematical limitations. Violation will cause singular or ill-conditioned element matrices. Examples are: a reentrant angle (equal to or greater than 180 degrees) in quadrilateral element/surface, 0 collapse in tetra.

2.

Quality check of error limits – whether an element is in the acceptable range.

3.

Quality check of warning limits – whether an element is in the recommended range. Violation may cause poor result quality, but will not stop the solution process.

With the CHECKEL parameter, type 2 and 3 checks may be controlled and the ELEMQUAL bulk data entry may be used to set the error and warning limits. However, the "validity" check, type 1, is always performed – even when the value of PARAM, CHECKEL is NO. A check for collapsed element nodes is performed for all elements. All other property checks are performed after this collapsed node check, and will be skipped if collapsed nodes are found. If the element quality check is activated, the checks for each element are performed according to the following precedence: (1) validity check, (2) quality check for error limits, and (3) quality check for warning limits. Violation of any check will skip the subsequent check(s). The warp angle check on CQUAD4 elements is relaxed for topography optimization. This relaxation prevents premature error termination of the optimization due to element quality concerns. However, be aware that the resulting mesh from a topography optimization may fail the CQUAD4 warp angle check when reanalyzed. The checks performed and the default bound values for each element type are outlined in the following topics: CGASK6 Element Checks and Default Bound Values CGASK8 Element Checks and Default Bound Values CGASK12 Element Checks and Default Bound Values CGASK16 Element Checks and Default Bound Values CTRIA3 Element Checks and Default Bound Values CTRIA6 Element Checks and Default Bound Values CQUAD4 Element Checks and Default Bound Values CQUAD8 Element Checks and Default Bound Values CTAXI / CTRIAX6 Element Checks and Default Bound Values CTETRA Element Checks and Default Bound Values CPENTA Element Checks and Default Bound Values CHEXA Element Checks and Default Bound Values

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CPYRA Element Checks and Default Bound Values

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CGASK6 Element Checks and Default Bound Values CGASK6 Element Check and Default Bounds The element check and default bounds of the CGASK6 element are identical as those of the first-order (6-noded) CPENTA element.

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CGASK8 Element Checks and Default Bound Values CGASK8 Element Check and Default Bounds The element check and default bounds of the CGASK8 element are identical as those of the first-order (8-noded) CHEXA element.

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CGASK12 Element Checks and Default Bound Values CGASK12 Element Check and Default Bounds The element check and default bounds of the CGASK12 element are identical as those of the second-order (15-noded) CPENTA element. Notice that CGASK12 has six 3-node edges of which Hoe Normal Offset and Hoe Tangent Offset are checked.

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CGASK16 Element Checks and Default Bound Values CGASK16 Element Check and Default Bounds The element check and default bounds of the CGASK16 element are identical as those of the second-order (20-noded) CHEXA element. Notice that CGASK16 has 8 3-node edges of which Hoe Normal Offset and Hoe Tangent Offset are checked.

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CTRIA3 Element Checks and Default Bound Values CTRIA3 Element Check The following qualities of the CTRIA3 element are checked: Aspect Ratio The aspect ratio of a CTRIA3 element is defined as the ratio of the maximum side length to the minimum side length. Skew Angle The skew angle of a CTRIA3 element is the difference between 90 degrees and the minimum of three angles: a1, a2 and a3. These angles are defined, for the CTRIA3 element, as the smallest of the angles created when a line drawn from a node to the midpoint of the opposing side intersects a line connecting the midpoints of the adjacent two sides. The skew angle has a range from 0 degrees for a perfect triangle to 90 degrees for a collapsed triangle. SKEW = 90 - MIN(a1,a2,a2 )

Vertex Angle For each vertex, the angle is measured between its two adjacent edges. The minimum and maximum values of the three nodes are reported for the element. CTRIA3 Default Bounds Default values for warning message

Default values for error message

Default values for validity check

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Aspect Ratio

-

50.0

-

500.0

-

1.0E5

Skew Angle

-

75.0

-

85.0

-

90.0

Vertex Angle

15.0

165.0

3.0

177.0

0.0

180.0

Information

The values used for warning and error checks may be adjusted by the ELEMQUAL bulk data entry, but validity checks are hard-coded.

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CQUAD4 Element Checks and Default Bound Values CQUAD4 Element Check The following qualities are checked for CQUAD4 elements: Vertex Angle For each vertex, the angle is measured between its two adjacent edges. The minimum and maximum values of the four nodes are reported for the element. Aspect Ratio The aspect ratio of a CQUAD4 element is the length of its longest side, divided by the length of its shortest side. Skew Angle The skew angle in a CQUAD4 element is calculated by finding the minimum angle between two lines joining opposite mid-sides of the element. Ninety degrees minus the minimum angle found is reported. Warp Angle The warpage of a CQUAD4 element is calculated by splitting the quad into two trias and finding the angle between the two planes which the trias form. The quad is then split again, this time using the opposite corners and forming the second set of trias. The angle between the two planes, which the trias form, is then found. The maximum angle found between the planes is the warp angle of the element.

CQUAD4 Default Bounds Default values for warning message

Default values for error message

Default values for validity check

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Aspect Ratio

-

100.0

-

1000.0

-

1.0E5

Skew Angle

-

60.0

-

75.0

-

90.0

Warp Angle*

-

30.0

-

60.0

-

180.0

Vertex Angle

15.0

165.0

3.0

177.0

0.0

180.0

Information

*Warp angle limits are relaxed to 140/160/179 in topography optimization problems. The values used for warning and error checks may be adjusted by the ELEMQUAL bulk data entry, but validity checks are hard-coded.

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CQUAD8 Element Checks and Default Bound Values CQUAD8 Element Check The following qualities are checked for CQUAD8 elements: Vertex Angle This quality is calculated using only the corner nodes. For each vertex, the angle is measured between its two adjacent edges. The minimum and maximum values of the four nodes are reported for the element. Aspect Ratio This quality is calculated using only the corner nodes. The aspect ratio of a CQUAD8 element is the length of its longest side, divided by the length of its shortest side. Skew Angle This quality is calculated using only the corner nodes. The skew angle in a CQUAD8 element is calculated by finding the minimum angle between two lines joining opposite mid-sides of the element. Ninety degrees minus the minimum angle found is reported. Warp Angle This quality is calculated using only the corner nodes. The warpage of a CQUAD8 element is calculated by splitting the quad into two trias and finding the angle between the two planes which the trias form. The quad is then split again, this time using the opposite corners and forming the second set of trias. The angle between the two planes, which the trias form, is then found. The maximum angle found between the planes is the warp angle of the element. Hoe Normal Offset The hoe normal offset is the maximum of its edges normal offset values. See the definition of hoe normal offset of 3-node edge. Hoe Tangent Offset The hoe tangent offset is the maximum of its edges tangent offset values. See the definition of hoe tangent offset of 3-node edge.

CQUAD8 Default Bounds Default values for warning message

Information

Default values for error message

Default values for validity check

Lower Limit Upper Limit Lower Limit Upper Limit Lower Limit Upper Limit Aspect Ratio

-

100.0

-

1000.0

-

1.0E5

Skew Angle

-

60.0

-

75.0

-

90.0

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Information

Default values for warning message

Default values for error message

Default values for validity check

Lower Limit Upper Limit Lower Limit Upper Limit Lower Limit Upper Limit Warp Angle

-

90.0

-

175.0

-

180.0

Vertex Angle

15.0

165.0

3.0

177.0

0.0

180.0

Hoe Normal Offset

-

0.30

-

0.60

-

1.0E5

Hoe Tangent Offset

-

0.20

-

0.24

-

0.25

The values used for warning and error checks may be adjusted by the ELEMQUAL bulk data entry, but validity checks are hard-coded.

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CTAXI / CTRIAX6 Element Checks and Default Bound Values 3-node CTAXI / CTRIA6 Element Check and Default Bounds The element check and default bounds of the 3-node CTAXI or CTRIAX6 element are identical as those of the CTRIA3 element.

6-node CTAXI / CTRIA6 Element Check and Default Bounds The element check and default bounds of the 6-node CTAXI or CTRIAX6 element are identical as those of the CTRIA3 element.

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CTRIA6 Element Checks and Default Bound Values CTRIA6 Element Check The following qualities of the CTRIA6 element are checked: Aspect Ratio This quality is calculated using only the corner nodes. It is defined as the ratio of the maximum side length to the minimum side length. Skew Angle This quality is calculated using only the corner nodes. It is the difference between 90 degrees and the minimum of three angles: a1, a2 and a3. These angles are defined, for the CTRIA6 element, as the smallest of the angles created when a line drawn from a node to the midpoint of the opposing side intersects a line connecting the midpoints of the adjacent two sides. The skew angle has a range from 0 degrees for a perfect triangle to 90 degrees for a collapsed triangle. Vertex Angle This quality is calculated using only the corner nodes. For each vertex, the angle is measured between its two adjacent edges. The minimum and maximum values of the three nodes are reported for the element. Hoe Normal Offset The hoe normal offset is the maximum of its edges normal offset values. See the definition of hoe normal offset of 3-node edge. Hoe Tangent Offset The hoe tangent offset is the maximum of its edges tangent offset values. See the definition of hoe tangent offset of 3-node edge.

CTRIA6 Default Bounds Default values for warning message

Default values for error message

Default values for validity check

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Aspect Ratio

-

50.0

-

500.0

-

1.0E5

Skew Angle

-

75.0

-

85.0

-

90.0

Vertex Angle

15.0

165.0

3.0

177.0

0.0

180.0

Hoe Normal Offset

-

0.30

-

0.60

-

1.0E5

Information

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Altair Engineering

Default values for warning message

Default values for error message

Default values for validity check

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Lower Limit

Upper Limit

-

0.20

-

0.24

-

0.25

Information

Hoe Tangent Offset

The values used for warning and error checks may be adjusted by the ELEMQUAL bulk data entry, but validity checks are hard-coded.

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Hoe Tangent Offset of 3-node Edge The hoe tangent offset of a 3-node edge is defined as the ratio of the distance between the real and ideal mid-side node and the distance between the corner nodes of the edge. If the mid-side node does not lie on the line connecting the corner nodes (that is the edge has a non-zero normal offset), then its projection on the line is used in the calculation. HTEi

=

Hoe tangent offset of edge i

=

di / li

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Hoe Normal Offset of 3-node Edge The hoe normal offset of a 3-node edge is defined as the ratio between the mid-side node’s normal offset distance (distance between the mid-side node and the line connecting the two corner nodes of the edge) and the distance between the two corner nodes. HNEi

=

Hoe normal offset of edge i

=

hi / li

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CTETRA Element Checks and Default Bound Values CTETRA 1st-order (4-noded) Element Checks The following qualities of the CTETRA 1st-order element are checked: Aspect Ratio The aspect ratio of a CTETRA 1st-order element is defined as the maximum of the aspect ratio of its four triangular faces. Each face is treated as a CTRIA3 element. Face Skew Angle The face skew angle of a CTETRA 1st-order element is defined as the maximum of the skew angles of its four triangular faces. Each face is treated as a CTRIA3 element. Vertex Angle The same vertex angle check is performed for all of the faces, and each is treated as a triangular (CTRIA3) or quadrilateral (CQUAD4) element. The minimum and maximum values reported for the element. Collapse The collapse of a CTETRA 1st-order element is defined as the minimum of four values, each calculated as the ratio between the distance from a vertex to its opposing face, and the square root of the area of the opposing face. collapse = MIN (hi / sqrt(Ai))

i = 1,2,3,4

The reported value is normalized by 1.2408, which gives the equilateral tetra a collapse value of 1. As the tetra collapses, the collapse value approaches 0. Edge Angle An edge angle is the absolute value of the angle between two faces sharing a common edge subtracted from 90 degrees. The edge angle (EA) of a CTETRA 1st-order element is defined as the maximum of its six edge angles. EA = MAX | 90 - ANGLE(Nki, Nli)

i = 1, ... 6

Where, Nki and Nli are the normal vectors of faces k and l that have a common edge i.

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CTETRA 2nd-order (10-noded) Element Checks The following qualities of the CTETRA 2nd-order element are checked: Aspect Ratio This quality is calculated using only the corner nodes. Its definition is the same as that used for the CTETRA 1st-order element. Face Skew Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CTETRA 1st-order element. Vertex Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CTETRA 1st-order element. Collapse This quality is calculated using only the corner nodes. Its definition is the same as that used for the CTETRA 1st-order element. Edge Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CTETRA 1st-order element. Hoe Normal Offset The hoe normal and tangent offsets of the CTETRA 2nd-order element are defined as the maximum of the hoe normal and tangent offsets of its 6 edges, respectively. See the definition of hoe normal offset of 3-node edge. Hoe Tangent Offset The hoe normal and tangent offsets of the CTETRA 2nd-order element are defined as the maximum of the hoe normal and tangent offsets of its 6 edges, respectively. See definition of hoe tangent offset of 3-node edge.

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CTETRA Default Bounds Default values for warning message

Default values for error message

Default values for validity check

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Aspect Ratio

-

100.0

-

1000.0

-

1.0E5

Face Skew Angle

-

75.0

-

85.0

-

90.0

C ollapse

0.001

100.0

0.0

100.0

0.0

1000.0

Edge Angle

-

75.0

-

87.0

-

90.0

Hoe Normal Offset

-

0.30

-

0.60

-

1.0E5

Hoe Tangent Offset

-

0.20

-

0.25

-

0.50

Information

The values used for warning and error checks may be adjusted by the ELEMQUAL bulk data entry, but validity checks are hard-coded.

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CPENTA Element Checks and Default Bound Values CPENTA 1st-order (6-noded) Element Checks The following qualities of the CPENTA 1st-order element are checked: Aspect Ratio The aspect ratio of a CPENTA 1st-order element is defined as the maximum of the aspect ratios of its three quadrilateral faces and two triangular faces. Each quadrilateral face is treated as a CQUAD4 element and each triangular face as a CTRIA3 element. Face Skew Angle The skew angle of a CPENTA 1st-order element is defined as the maximum skew angle among its three quadrilateral faces and two triangular faces. Each quadrilateral face is treated as a CQUAD4 element and each triangular face as a CTRIA3 element. Vertex Angle The same vertex angle check is performed for all of the faces, and each is treated as a triangular (CTRIA3) or quadrilateral (CQUAD4) element. The minimum and maximum values reported for the element. Face Warpage The face warpage of a CPENTA 1st-order element is defined as the maximum warpage among the three quadrilateral faces, each treated as a CQUAD4 element. Twist Angle The twist angle is defined as the rotation of one triangular face with respect to the opposite triangular face. The rotation is computed as follows: first construct a reference plane perpendicular to the line connecting the centroids of the two triangular faces. The three edges of each triangular are then projected to this reference plane. The maximum angle between the corresponding edges of the two projected triangles is reported as the twist angle of the CPENTA 1st-order element. Edge Angle The edge angle is the absolute value of the angle between two faces sharing a common edge, subtracted from 90 degrees. For warped quadrilateral faces, the projected planes defined by the plane vectors are used to compute the face normals (see definition of reference plane for quadrilateral element or face), which are used in the angle calculation. The edge angle of a CPENTA 1st-order is defined as the maximum edge angles in the element.

CPENTA 2nd-order (15-noded) Element Checks The following qualities of the CPENTA 2nd-order element are checked: Aspect Ratio This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPENTA 1st-order element.

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Face Skew Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPENTA 1st-order element. Vertex Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPENTA 1st-order element. Face Warpage This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPENTA 1st-order element. Twist Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPENTA 1st-order element. Edge Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPENTA 1st-order element. Hoe Normal Offset The hoe normal offset is the maximum of its edges normal offset values. See the definition of hoe normal offset of 3-node edge. Hoe Tangent Offset The hoe tangent offset is the maximum of its edges tangent offset values. See the definition of hoe tangent offset of 3-node edge.

CPENTA Default Bounds Default values for warning message

Default values for error message

Default values for validity check

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Aspect Ratio

-

100.0

-

1000.0

-

1.0E5

Skew Angle

-

60.0

-

75.0

-

90.0

Face Warp Angle

-

30.0

-

60.0

-

180.0

Twist Angle

-

30.0

-

75.0

-

90.0

Edge Angle

-

75.0

-

87.0

-

90.0

Information

2180 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

Altair Engineering

Default values for warning message

Default values for error message

Default values for validity check

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Hoe Normal Offset

-

0.30

-

0.60

-

1.0E5

Hoe Tangent Offset

-

0.20

-

0.25

-

0.5

Information

The values used for warning and error checks may be adjusted by the ELEMQUAL bulk data entry, but validity checks are hard-coded.

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Reference Plane for Quadrilateral Element or Face In order to measure the distortion of the quadrilateral face of a solid element, a unique reference plane is defined by two auxiliary plane vectors. The plane vectors are calculated as: PL1 = (V3 + V2 ) - (V1 + V4 ) PL2 = (V3 + V4 ) - (V1 + V2 ) where, V1, V2, V3, and V4 are the vectors that connect the four corner nodes with the centroid of the quadrilateral. These two plane vectors and the centroid are then used to construct the reference plane. These vectors of a non-warping quadrilateral face are shown below:

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CHEXA Element Checks and Default Bound Values CHEXA 1st-order (8-noded) Element Checks The following qualities of the CHEXA 1st-order element are checked: Aspect Ratio The aspect ratio of a CHEXA 1st-order element is defined as the maximum aspect ratio among its six faces; each treated as a CQUAD4 element. Face Skew Angle The face skew angle of a CHEXA 1st-order element is defined as the maximum skew angle among its six faces; each treated as a CQUAD4 element. Vertex Angle The same vertex angle check is performed for all of the faces, and each is treated as a quadrilateral (CQUAD4) element. The minimum and maximum values reported for the element. Face Warpage The face warpage of a CHEXA 1st-order element is defined as the maximum warpage among its six faces; each treated as a CQUAD4 element. Twist Angle The twist angle of a CHEXA 1st-order element is defined as the maximum rotation of one face with respect to its opposite face. The calculation is done as follows: For each face, define two diagonal vectors as: D1 = 0.25 * (PL1 + PL2) D2 = 0.25 * (PL1 + PL2) where, PL1 and PL2 are the place vectors of the face treated as CQUAD4. See the definition of reference plane for quadrilateral element or face. The diagonal vectors for a planar parallelogram can be show below:

Then, for each pair of opposing faces, a reference plane that is perpendicular to the axis connecting the centroids of the faces is constructed. The diagonal vectors D1 and D2 of each of the two opposite faces are projected onto this reference plane. The angles between the projected and the projected are computed as t 1 and t 2. The maximum of t 1 and t 2 is defined as the relative rotation between these two opposite faces (TAF). Finally, the twist angle (TA) of a CHEXA 1st-order is calculated as the maximum relative rotation of its three pairs of opposing faces.

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Edge Angle An edge angle is the absolute value of the angle between two faces sharing a common edge, subtracted from 90 degrees. For warped faces, the projected planes are used to compute the face normals used for the angle calculation. The edge angle of a CHEXA 1storder is defined as the maximum edge angle in the element.

CHEXA 1st-order Default Bounds Default values for warning message

Default values for error message

Default values for validity check

Information Lower Limit Upper Limit Lower Limit Upper Limit Lower Limit Upper Limit Aspect Ratio

-

100.0

-

1000.0

2184 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

-

1.0E5

Altair Engineering

Default values for warning message

Default values for error message

Default values for validity check

Information Lower Limit Upper Limit Lower Limit Upper Limit Lower Limit Upper Limit Face Skew Angle

-

60.0

-

75.0

-

90.0

Face Warp Angle

-

30.0

-

60.0

-

180.0

Twist Angle

-

30.0

-

90.0

-

180.0

Edge Angle

-

60.0

-

85.0

-

90.0

CHEXA 2nd-order (20-noded) Element Checks The following qualities of the CHEXA 2nd-order element are checked: Aspect Ratio This quality is calculated using only the corner nodes. Its definition is the same as that used for the CHEXA 1st-order element. Face Skew Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CHEXA 1st-order element. Vertex Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CHEXA 1st-order element. Face Warpage This quality is calculated using only the corner nodes. Its definition is the same as that used for the CHEXA 1st-order element. Twist Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CHEXA 1st-order element. Edge Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CHEXA 1st-order element. Hoe Normal Offset The hoe normal offset is the maximum of its edges normal offset values. See the definition of hoe normal offset of 3-node edge.

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OptiStruct 13.0 Reference Guide 2185 Proprietary Information of Altair Engineering

Hoe Tangent Offset The hoe tangent offset is the maximum of its edges tangent offset values. See the definition of hoe tangent offset of 3-node edge.

CHEXA 2nd-order Default Bounds Default values for warning message

Default values for error message

Default values for validity check

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Aspect Ratio

-

100.0

-

1000.0

-

1.0E5

Face Skew Angle

-

60.0

-

75.0

-

90.0

Face Warp Angle

-

30.0

-

60.0

-

180.0

Twist Angle

-

30.0

-

75.0

-

180.0

Edge Angle

-

60.0

-

89.0

-

90.0

Hoe Normal Offset

-

0.30

-

0.60

-

1.0E5

Hoe Tangent Offset

-

0.20

-

0.25

-

0.50

Information

The values used for warning and error checks may be adjusted by the ELEMQUAL bulk data entry, but validity checks are hard-coded.

2186 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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CPYRA Element Checks and Default Bound Values CPYRA 1st-order (5-noded) Element Checks The following qualities of the CPYRA 1st-order element are checked: Aspect Ratio The aspect ratio of a CPYRA 1st-order element is defined as the maximum of the aspect ratios of its four triangular faces and the quadrilateral base face. Each triangular face is treated as a CTRIA3 element and the quadrilateral face as a CQUAD4 element. Face Skew Angle The face skew angle of a CPYRA 1st-order element is defined as the maximum of the skew angles of its four triangular faces and the quadrilateral base face. Each triangular face is treated as a CTRIA3 element and the quadrilateral face as a CQUAD4 element. Vertex Angle The same vertex angle check is performed for all of the faces, and each is treated as a triangular (CTRIA3) or quadrilateral (CQUAD4) element. The minimum and maximum values reported for the element. Face Warpage The face skew angle of a CPYRA 1st-order element is defined as the warpage of its quadrilateral base face, which is treated as a CQUAD4 element.

CPYRA 2nd-order (13-noded) Element Checks The following qualities of the CPYRA 2nd-order element are checked: Aspect Ratio This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPYRA 1st-order element. Face Skew Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPYRA 1st-order element. Vertex Angle This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPYRA 1st-order element. Face Warpage This quality is calculated using only the corner nodes. Its definition is the same as that used for the CPYRA 1st-order element.

Altair Engineering

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Hoe Normal Offset The hoe normal offset is the maximum of its edges normal offset values. See the definition of hoe normal offset of 3-node edge. Hoe Tangent Offset The hoe tangent offset is the maximum of its edges tangent offset values. See the definition of hoe tangent offset of 3-node edge.

CPYRA Default Bounds Default values for warning message

Default values for error message

Default values for validity check

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Lower Limit

Upper Limit

Aspect Ratio

-

100.0

-

1000.0

-

1.0E5

Skew Angle

-

60.0

-

75.0

-

90.0

Face Warp Angle

-

30.0

-

60.0

-

180.0

Hoe Normal Offset

-

0.30

-

0.60

-

1.0E5

Hoe Tangent Offset

-

0.20

-

0.25

-

0.5

Information

The values used for warning and error checks may be adjusted by the ELEMQUAL bulk data entry, but validity checks are hard-coded.

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Material Property Check In order to prevent analyses from being carried out on models with poor material definitions, a material property check is incorporated into the pre-processing phase. The material property check is controlled by the CHECKMAT parameter (see the PARAM input format). There are several levels of requirements that material data needs to satisfy: 1.

Symmetry requirements - These are assured by the input formats.

2.

Mathematical requirements - These have to be satisfied so that the stiffness matrix can be formulated at all, and are usually not very strict. For example, to avoid division by zero, MAT1 in 3D must have n¹-1 and n¹0.5. Composite homogenization adds additional mathematical requirements. Failure to meet these criteria will always result in an error termination.

3.

Stability requirements - By default, "semi-stability" combined with "not-all-zeros" stability based on the following definitions is required: Full stability - This means that the material is stable; when pulled it stretches rather than shrinks, etc. For example, E>0 assures stability for a rod. In a mathematical sense, stability assures that the stiffness matrix (with proper support) will be SemiPositive Definite (SPD). Semi-stability - This is a slight extension of stability to include borderline cases such as allowing E=0. It guarantees that the stiffness matrix (with proper support) will be Semi-Positive Semi-Definite (SPSD). However, this can lead to infinite or very large compliances. Not all zeros - This is an additional requirement that at least one deformation mode of the material is active (non-zero stiffness). This avoids element stiffness matrices that are identically zero. However, It does not prevent infinite or very large compliances. An error termination will occur if a material has negative stiffness. A warning is produced if any individual mode of deformation has zero stiffness. An error termination will occur if all modes of deformation have zero stiffness.

4.

Consistency requirements - This is a requirement that user provided data be internally consistent. For example, specifying E, G and Nu for isotropic material may lead to inconsistent data.

5.

Practical material requirements - These are requirements that correspond to typical practical materials. For example, while stability requirements allow for negative Poisson's ratio, the natural materials usually have positive n (although some composites and nanomaterials with negative n exist).

You may choose to perform only those checks that are necessary to avoid crashes in the element routines (that is the Mathematical Requirement checks). This is facilitated through the specification of PARAM,CHECKMAT,NO in the bulk data section of the input deck. The checks performed for MAT1, MAT2, MAT3, MAT8, and MAT9 are outlined in the following topics: Material Property Checks for MAT1 Material Property Checks for MAT2

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Material Property Checks for MAT3 Material Property Checks for MAT8 Material Property Checks for MAT9

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Material Property Checks for MAT1 In addition to the property requirements, there are usage and recalculation rules for MAT1 data.

Usage Rules for MAT1 Data Element Type

E

G

n

ROD, BEAM, BAR

Used for bending and tension.

Used for torsion.

Unused.

QUAD, TRIA

Used in combination with n for bending and membrane.

Used for transverse shear.

Used in combination with E for bending and membrane.

SOLID

Used in combination with n.

Unused.

Used in combination with n.

Recalculation Rules for MAT1 In cases when not all material parameters are given for MAT1, here are the recalculation rules for the remaining parameters. Note that in cases of two prescribed parameters, this is obvious; while in cases of a single prescribed parameter, you are making an assumption as to which one is assumed to be zero. Given E

G

given given

Mean n

E

G

n

given

as given

G = E / 2(1 + n)

as given

as given

as given

n = E/2G - 1

E = 2G(1 + n)

as given

as given

as given

0.0

0.0

0.0

as given

0.0

given given

given

given given given

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not allowed

OptiStruct 13.0 Reference Guide 2191 Proprietary Information of Altair Engineering

Material Requirements for MAT1 The property requirements on MAT1 vary depending on whether it is used for 1D, 2D, or 3D elements. The details are provided in the table below. Material Requirements

MAT1 - 1D

MAT1 - 2D

MAT1 - 3D

Mathematical

n = -1 results in error termination.

n = -1 or n = 1 results in error termination.

Semi-stability

E < 0 or G < 0 results in error termination.

E < 0, G < 0, n < -1 E < 0, n < -1, or n > > or -n > 0.5 results 0.5 results in error in error termination. termination.

PARAM,CHECKMAT,NO will disable this error.

PARAM,CHECKMAT,N O will disable this error.

PARAM,CHECKMAT,N O will disable this error.

If both E = 0 and G = 0, an error termination occurs.

If both E = 0 and G = 0, an error termination occurs.

E < 0 results in error termination.

If either E = 0 or G = 0, a warning is given.

If either E = 0 or G = 0, a warning is given.

A warning is provided

A warning is provided A warning is

n < -1 or n > 0.5 results in a warning (however, this is unused in 1D). Not all zeros

Consistency

n = -1 or n = 0.5 results in error termination.

n). Mathematical for composites

/ 2(1 + n).

After homogenization, if either E = 0 or G = 0, an error termination occurs.

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Material Property Checks for MAT2 MAT2 only applied to 2D elements. Material Requirements

MAT2

Mathematical

none

Semi-stability

If any eigenvalues of [G] < 0, an error termination will occur. PARAM,CHECKMAT,NO will disable this error.

Not all zeros

If all eigenvalues of [G] = 0, an error termination will occur. If any eigenvalue of [G] = 0, a warning is provided.

Consistency

none

Mathematical for composites

After homogenization, if Det[G] = 0, an error termination will occur.

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Material Property Checks for MAT3 MAT3 only applies to axisymmetric elements. Material Requirements Mathematical

MAT3 If EX = 0, ETH = 0, EZ = 0 or NUXTH * NUTHX + NUTHZ * NUZTH + NUZX * NUXZ + 2 * NUXTH * NUTHZ * NUZX = 1, an error termination will occur (See comment 1).

Semi-stability

If EX < 0, ETH < 0, EZ < 0 or GZX < 0, an error termination will occur. PARAM,CHECKMAT,NO will disable this error.

Not all zeros

If GZX = 0, a warning is provided.

Consistency

none

Comments 1.

By substitution of

into NUXTH * NUTHX + NUTHZ * NUZTH + NUZX * NUXZ + 2 * NUXTH * NUTHZ * NUZX = 1, it can be expressed in terms of

2194 OptiStruct 13.0 Reference Guide Proprietary Information of Altair Engineering

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Material Property Checks for MAT8 MAT8 only applies to 2D elements. Material Requirements Mathematical

MAT8 If n1 2 *n2 1 = 1, an error termination will occur (See comment 1).

Semi-stability

E1 < 0, E2 < 0, G1 2 < 0, G1 ,Z < 0, or G2 ,Z < 0 will result in an error termination. PARAM,CHECKMAT,NO will disable this error.

Not all zeros

If E1 = 0, E2 = 0 , and G1 2 = 0, an error termination will occur. If E1 = 0, E2 = 0 , or G1 2 = 0, a warning is provided.

Consistency

E1 *n2 1 = E2 *n1 2 is assured as only n12 is input.

Mathematical for composites

After homogenization, if Det[G] = 0, an error termination will occur.

Comments 1.

By substitution of E1*n21 = E2*n12 into n12*n21 = 1, it can be expressed in terms of n12*n12*E2/E1 = 1.

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OptiStruct 13.0 Reference Guide 2195 Proprietary Information of Altair Engineering

Material Property Checks for MAT9 MAT9 only applies to 3D elements. Material Requirements

MAT9

Mathematical

none

Semi-stability

If any eigenvalues of [G] < 0, an error termination will occur. PARAM,CHECKMAT,NO will disable this error.

Not all zeros

If all eigenvalues of [G] = 0, an error termination will occur. If any eigenvalue of [G] = 0, a warning is provided.

Consistency

none

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Output Data Descriptions for individual output files can be accessed by selecting from the links for each entry, listed below in groups according to type and alphabetically on the Files Created by OptiStruct page. The filenames listed on this page contain only the tail part of the name. For most files, the full filename is controlled by the OUTFILE command (ASSIGN,OUTFILE), and in the absence of OUTFILE, they use the root of input filename. Unless otherwise noted for a specific file type (.#.eigv), all output files have the same root and are located in the same folder. The only exception is .h3d; these files may not have a common root in the filename. HyperMesh

OptiStruct

.amls_singularity.cmf file

.#.asens file

.HM.comp.cmf file

.#.eigv file

.HM.conn.cmf file

.#.sens file

.HM.elcheck.cmf file

.#.grid file

.HM.elcheck.###.cmf file

.#.sh file

.HM.ent.cmf file

.cstr file

.HM.gapstat.cmf file

.dens file

.res file

.disp file .dvgrid file

HyperView/HyperGraph

.echo file

.#.h3d file

.force file

.h3d file

.fsthick file

.hgdata file

.gpf file

_des.h3d file

.grid file

_freq.mvw file

.hist file

_gauge.h3d file

.interface file

_hist.mvw file

.load file

_mass.mvw file

.mass file

_modal.#.mvw file

.mpcf file

_modal.mvw file

.out file

_rand.mvw file

.pret file

_topol.h3d file

.prop file

_tran.mvw file

.rand file

_s#.h3d file

.seplot file

_sens.#.mvw file

.sh file

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_freq.#.mvw file

.spcd file

_mass.#.mvw file

.spcf file .stat file

Nastran

.strn file

.k.op2 file

.strs file

.m.op2 file

_err.grid file

.op2 file

_s#_a.frf file

.pch file

_s#_a.mbd file

.peak file

_s#_a.trn file _s#_d.frf file

OSSmooth

_s#_d.mbd file

.oss file

_s#_d.trn file _s#_v.frf file

Multi-body Dynamics

_s#_v.mbd file

_mbd.h3d file

_s#_v.trn file

_mbd.log file

.#.#.fat file

_mbd.mrf file

.#.mass file

_mbd.mvw file

.desvar file

_mbd.xml file

.pcomp file

.h3d file

_s#_a.#.frf file

.mnf file

_s#_d.#.frf file _s#_v.#.frf file _shuffling.#.fem file _sizing.#.fem file

Patran

Alternative Patran

.#.#.#.dis file

.#.#.dis.# file

.#.#.dis file

.#.dis.# file

.#.#.els file

.#.els.# file

.#.dis file

.dis.# file

.#.els file

.els.# file

HTML Microsoft Excel

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.html file _frames.html file

.#.slk file _gso.slk file

_menu.html file

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List of Files Created by OptiStruct (Alphabetical) The filenames listed on this page contain only the tail part of the name. For most files, the full filename is controlled by the OUTFILE command (ASSIGN,OUTFILE), and in the absence of OUTFILE, they use the root of input filename. Unless otherwise noted for a specific file type (.#.eigv), all output files have the same root and are located in the same folder. The only exception is .h3d; these files may not have a common root in the filename. .#.#.#.dis file .#.#.dis file .#.#.dis.# file .#.#.els file .#.#.fat file .#.asens file .#.dis file .#.dis.# file .#.eigv file .#.els file .#.els.# file .#.grid file .#.h3d file .#.mass file .#.sens file .#.sh file .#.slk file .amls_singularity.cmf file .cntf file .contgap.fem file .cstr file .dens file .desvar file .dis.# file .disp file .dvgrid file .echo file .els.# file .force file .fsthick file .gpf file .grid file

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.h3d file .hgdata file .hist file .HM.comp.cmf file .HM.conn.cmf file .HM.elcheck.cmf file .HM.elcheck.###.cmf file .HM.ent.cmf file .HM.gapstat.cmf file .html file .interface file .k.op2 file .load file .m.op2 file .mass file .mnf file .mpcf file .op2 file .oss file .out file .pch file .pcomp file .peak file .pret file .prop file .rand file .res file .seplot file .sh file .spcd file .spcf file .stat file .strn file .strs file _des.h3d file _err.grid file _frames.html file _freq.#.mvw file

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_freq.mvw file _gauge.h3d file _gso.slk file _hist.mvw file _mass.#.mvw file _mass.mvw file _mbd.h3d file _mbd.log file _mbd.mrf file _mbd.mvw file _mbd.xml file _menu.html file _modal.#.mvw file _modal.mvw file _rand.mvw file _s#.h3d file _s#_a.#.frf file _s#_a.frf file _s#_a.mbd file _s#_a.trn file _s#_d.#.frf file _s#_d.frf file _s#_d.mbd file _s#_d.trn file _s#_v.#.frf file _s#_v.frf file _s#_v.mbd file _s#_v.trn file _sens.#.mvw file _shuffling.#.fem file _sizing.#.fem file _topol.h3d file _tran.mvw file .h3d file

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.#.#.#.dis file The .#.#.#.dis file is a Patran 2.5 ASCII format results file. File Creation This file is created when the PATRAN format is chosen and normal modes analyses are performed. (See documentation for the I/O Option FORMAT). File Contents

Result

Description

Eigenvector

Eigenvector results from normal modes analyses. Output is controlled by the I/O Option DISPLACEMENT.

Comments 1.

One such file is created for each calculated mode at each iteration where the I/O Option RESULTS requests analytical results to be output.

2.

The first # in the file name is the iteration number.

3.

The second # in the file name is the user-defined Subcase ID.

4.

The third # in the file name is the mode number.

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.#.#.dis file The .#.#.dis file is a Patran 2.5 ASCII format results file. File Creation This file is created when the PATRAN format is chosen and linear static analysis is performed. (See documentation for the I/O Option FORMAT). File Contents

Result

Description

Displacement

Displacement results from linear static analysis. Output is controlled by the I/O Option DISPLACEMENT.

Comments 1.

One such file is created for each subcase at each iteration where the I/O Option RESULTS requests analytical results to be output.

2.

The first # in the file name is the iteration number.

3.

The second # in the file name is the user-defined Subcase ID.

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.#.#.dis.# file The .#.#.dis.# file is a Patran 2.5 ASCII format results file. File Creation This file is created when the APATRAN format is chosen and normal modes analyses are performed. (See documentation for the I/O Option FORMAT). File Contents

Result

Description

Eigenvector

Eigenvector results from normal modes analyses. Output is controlled by the I/O Option DISPLACEMENT.

Comments 1.

One such file is created for each calculated mode at each iteration where the I/O Option RESULTS requests analytical results to be output.

2.

The first # in the file name is the user-defined Subcase ID.

3.

The second # in the file name is the mode number.

4.

The third # in the file name is the iteration number.

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.#.#.els file The .#.#.els file is a Patran 2.5 ASCII format results file. File Creation This file is created when the PATRAN format is chosen and linear static analysis is performed. (See documentation for the I/O Option FORMAT). File Contents

Result

Description

Stress

Stress results from linear static analysis. Output is controlled by the I/O Option STRESS (or ELSTRESS).

Comments 1.

One such file is created for each subcase at each iteration where the I/O Option RESULTS requests analytical results to be output.

2.

The first # in the file name is the iteration number.

3.

The second # in the file name is the user-defined Subcase ID.

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.#.#.fat file The .#.#.fat file is an ASCII format result file. File Creation This file is created for fatigue analysis and optimization. File Contents This file contains the average fatigue life/damage, top five damaged elements, and the detailed damage information (contribution from each static loadcase). Comments 1.

The first # in the file name is the iteration number.

2.

The second # in the file name is the user-defined fatigue subcase ID.

3.

If a fatigue optimization is performed, this file is created for each fatigue subcase at the first and last iterations.

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.#.asens file The .#.asens file is an OptiStruct ASCII format results file. File Creation This file is created when an optimization is performed. Creation of this file is controlled by the I/O option OUTPUT. File Contents The file contains sensitivity information for all responses with respect to topology design variables (density) at a given iteration (denoted by the # in the file name). File Format The sensitivities are listed in a single column and are grouped by response. A blank line separates each response grouping. Comments 1.

The # in the file name is the iteration number.

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.#.dis file The .#.dis file is a Patran 2.5 ASCII format results file. File Creation This file is created when the PATRAN format is chosen and shape or topography design variables are present. (See documentation for the I/O Option FORMAT). File Contents

Result

Description

Shape

Shape results from topography or shape optimizations. Output is controlled by the I/O Option DENSRES.

Comments 1.

One such file is created for each iteration where the I/O Option DENSRES requests topography or shape results to be output.

2.

The # in the file name is the iteration number.

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.#.dis.# file The .#.dis.# file is a Patran 2.5 ASCII format results file. File Creation This file is created when the APATRAN format is chosen and linear static analysis is performed. (See documentation for the I/O Option FORMAT). File Contents

Result

Description

Displacement

Displacement results from linear static analysis. Output is controlled by the I/O Option DISPLACEMENT.

Comments 1.

One such file is created for each subcase at each iteration where the I/O Option RESULTS requests analytical results to be output.

2.

The first # in the file name is the user-defined Subcase ID.

3.

The second # in the file name is the iteration number.

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.#.eigv file The _#.eigv file is an OptiStruct binary data file. File Creation This file is created by the subcase information entry EIGVSAVE. The prefix for the file name is controlled by the I/O option EIGVNAME. File Contents

Result

Description

Eigenvalue

Eigenvalue results from normal modes analyses.

Comments 1.

This file is used to store eigenvalue results from normal modes analyses for retrieval by modal frequency response subcases. The EIGVRETRIEVE subcase information entry is used to retrieve values from this file.

2.

The # in the file name is the integer argument given to EIGVSAVE.

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.#.els file The .#.els file is a Patran 2.5 ASCII format results file. File Creation This file is created when the PATRAN format is chosen and topology design variables are present. (See documentation for the I/O Option FORMAT). File Contents

Result

Description

Density

Density results from topology optimizations. Output is controlled by the I/O Option DENSRES.

Comments 1.

One such file is created for each iteration where the I/O Option DENSRES requests topology results to be output.

2.

The # in the file name is the iteration number.

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.#.els.# file The .#.els.# file is a Patran 2.5 ASCII format results file. File Creation This file is created when the APATRAN format is chosen and linear static analysis is performed. (See documentation for the I/O Option FORMAT). File Contents

Result

Description

Stress

Stress results from linear static analysis. Output is controlled by the I/O option STRESS (or ELSTRESS).

Comments 1.

One such file is created for each subcase at each iteration where the I/O option RESULTS requests analytical results to be output.

2.

The first # in the file name is the user-defined Subcase ID.

3.

The second # in the file name is the iteration number.

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.#.grid file The .#.grid file is an OptiStruct ASCII format results file. File Creation This file is created when topography or shape optimization is performed. Output of this file is controlled by the I/O Option SHRES. File Contents

Result

Description

Nodal locations

The nodal coordinates of the model at iteration # of the optimization.

File Format The file uses the following format for each grid in the model: GRID

Id

Cp

X1

X2

X3

GRID

identifies this as a GRID card image.

Id

is the unique grid point identification number.

Cp

is blank.

Cd

Ps

where:

X1, X2, X3 provide the location of the grid point in the global coordinate system. Cd

is the identification number of the coordinate system in which the displacements, degrees-of-freedom, constraints, and solution vectors are defined at the grid point.

Ps

is the SPC associated with the grid.

Comments 1.

The # in the file name is the iteration number.

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.#.h3d file The .#.h3d files are compressed binary files, containing model, analysis, and optimization result data. They can be used to post-process results in HyperView or when using the HyperView Player. File Creation The .#.h3d files are created when the OUTPUT, H3D, , BYITER output option is present and an optimization is performed. File Contents The .#.h3d files contain node and element definitions. In the case of shape optimization, the model is updated to the shape of the respective iteration. The following results are included:

Result

Description

Acceleration

Acceleration results from frequency response, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option ACCELERATION.

Composite ply strain

Ply strain results for composite materials from static analyses. Output is controlled by the I/O option STRAIN and by the SOUTi field on the PCOMP definition.

Composite ply stress

Ply stress results for composite materials from static and analyses. Output is controlled by the I/O option STRESS and by the SOUTi field on the PCOMP definition.

Composite failure indices

Failure indices for composite materials from static analyses. Output is controlled by the I/O option STRESS, by the SOUTi, SB and FT fields on the PCOMP definition and by the related fields on the relevant material definition (see MAT1, MAT2, MAT8).

Density

Density results from topology optimizations. Output is controlled by the I/O option DENSITY.

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Result

Description

Displacement

Displacement results from static, frequency response, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option DISPLACEMENT.

Eigenvector

Eigenvector results from normal modes and linear buckling analyses. Output is controlled by the I/O option DISPLACEMENT.

Element force

Element force results from static, frequency response, acoustic, and transient response analyses. Output is controlled by the I/O option FORCE (or ELFORCE).

Element strain energy

Element strain energy results from static and normal modes analyses. Output is controlled by the I/O option ESE.

Grid point stress

Grid point stress results for 3D elements from static analyses. Output is controlled by the I/O option GPSTRESS (or GSTRESS).

Shape

Shape results from topography or shape optimizations. Output is controlled by the I/O option SHAPE.

Single-point force of constraint

Single-point force of constraint results from static analyses. Output is controlled by the I/O option SPCFORCE.

Strain

Strain results from static, frequency response, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option STRAIN.

Stress

Stress results from static, frequency response, transient response, and multi-body dynamics analyses.

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Result

Description Output is controlled by the I/O option STRESS (or ELSTRESS).

Thickness

Thickness results from size and topology optimizations. Output is controlled by the I/O option THICKNESS.

Velocity

Velocity results from frequency response, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option VELOCITY.

Comments 1.

The # in the file name is the iteration number.

2.

Grid point stresses are output for the entire model and for each individual component. This allows grid point stresses to be accurately obtained at the interface of two components referencing different material definitions.

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.#.mass file The .#.mass file is an ASCII format results file. File Creation This file is created when modal optimization is performed and OUTPUT,HGEFFMASS is presented. File Contents This file contains the total effective mass fraction. File Format The file is formatted into blocks separated by blank lines. Each block represents a modal subcase. The subcases are in order of occurrence in the input deck. Each block contains six columns and a number of rows. The number of rows is equal to the number of requested modes for this subcase. The columns, from left to right, contain the total effective mass fraction for X-translation, Y-translation, Z-translation, X-rotation, Yrotation, and Z-rotation. The summary of each column is 100%. Comments 1.

The # in the file name is the iteration number.

2.

This file is used by the _mass.#.mvw session file which automatically creates bar charts for the results.

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.#.sens file The .#.sens file is an OptiStruct ASCII format results file. File Creation This file is created when an optimization is performed. Creation of this file is controlled by the I/O Option OUTPUT. File Content The file contains sensitivity information for all responses to size and shape design variables at a given iteration (denoted by the # in the file name). File Format The sensitivities are listed in a single column and are grouped by response. A blank line separates each response grouping. Comments 1.

The # in the file name is the iteration number.

2.

The _sens.#.mvw HyperView script file automatically creates histogram plots for the results contained in this file.

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.#.sh file The .#.sh file is an OptiStruct ASCII format results file. File Creation This file is created when an optimization is performed. Output of this file is controlled by the I/O Option SHRES. File Contents Contains information necessary to restart the optimization from a given iteration. Comments 1. The # in the file name is the iteration number.

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.#.slk file The .slk file is a Microsoft Excel SYLK Format results file. File Creation This file is only created when size or shape optimization is performed. Output of this file is controlled by the SENSITIVITY and SENSOUT I/O options. File Contents The file contains sensitivity information for size and shape design variables. File Format The only values that can be changed in this file are those listed in the "New" column. All other values are either fixed or their calculation is fixed. When the .slk file is created, the values in the "New" column match those in the "Reference" column. These values may be adjusted, but should always remain within the design variable's bounds. Each size and shape design variable in the model is listed in the left-hand column of the sensitivity table. Information concerning a particular design variable is given in the row where its label is listed. The current value and the upper and lower bounds of the design variables are given in the columns, "Reference," "Lower," and "Upper" respectively. Each referenced response in the model has its own column. These response columns are on the right-hand side of the sensitivity table. The calculated sensitivity of a response to changes in a design variable at the current iteration is given in the row corresponding to that design variable and the column corresponding to that response. Beneath the list of design variables, in the left-hand column, are the headings "Response lower bound," "Response reference," and "Response upper bound". If a response is constrained, the constraint value will be given in either the "Response lower bound" or the "Response upper bound" row of the column corresponding to that response. The value given in the "Response reference" row is the calculated value of the response using the design variable reference values. At the bottom of the left-hand column are the headings: "Response linear," "Response reciprocal," and "Response conservative". The response values in these rows are the predicted values of the responses for three different approximations. Initially, these values will match one another and the "Response reference" value for each response. This is because these are the predicted values of the response at the given variable settings, which initially are the same settings used to calculate the "Response reference" value. Once the design variable values in the "New" column are altered, these values will change. The "Response linear" row predicts the response value using linear approximation. This is calculated as:

where:

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R1

is the predicted response value.

R0

is the response reference value. are the new values of the design variables. are the reference values of the design variables.

are the sensitivities of the response to the design variables.

The "Response reciprocal" row predicts the response value using reciprocal approximation. This is calculated as:

where: R1

is the predicted response value.

R0

is the response reference value. are the new values of the design variables.

are the reference values of the design variables.

are the sensitivities of the response to the design variables.

The "Response conservative" row predicts the response value using a combination of the above approximations where linear approximation is used, when the sensitivity is positive, and reciprocal approximation is used when the sensitivity is negative. Therefore, if all sensitivities are positive, the conservative prediction will match the linear prediction. If all sensitivities are negative, it will match the reciprocal prediction, but if there is a mixture of positive and negative sensitivities for a given response then the conservative prediction will match neither the linear nor the reciprocal prediction. The normalized values simply show the predicted response as a fraction of the response reference value.

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Comments 1.

The # in the file name refers to the iteration number.

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.amls_singularity.cmf file The .amls_singularity.cmf file is a HyperMesh command file. File Creation This file is created when an AMLS run is performed and singular grid points are detected by AMLS. File Contents This file contains a list of GRID point identification numbers which are found to be singular during an AMLS run. Format *entitysetcreate("^AMLS singular grids",nodes,#) *createmark(nodes,#) List of GRID Identification numbers *entitysetupdate("^AMLS singular grids",nodes,#) Comments 1.

Verify that the corresponding model is loaded in HyperMesh when executing the command file.

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.cntf file The .cntf file is an OptiStruct ASCII format results file. File Creation This file is created when the OPTI format is selected in the CONTF I/O Options Entry for nonlinear quasi-static analysis (NLSTAT) runs. File Contents Result

Description

Contact Forces Contact force results from nonlinear quasi-static analysis (with contact) runs. Output is controlled by the I/O option CONTF. File Format The .cntf file has the following format: For each iteration, the following header is used: iter

Iteration

Numel

iter

is a keyword identifying that the next field is the iteration number.

Iteration

is the Iteration number.

Numel

is the total number of nonlinear quasi-static subcases (with contact) in the entire model.

where:

Within the iteration section, the following information is provided for each subcase: SUBCASE: LOAD: LABEL: CONTACT INTERFACE: TOTAL FORCE ACTING ON MASTER SURFACE (BASIC SYSTEM) CONTACT#

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FORCE-X

FORCE-Y

FORCE-Z

MAGNITUDE

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where: CONTACT#

is the Contact Interface identification number (CTID on the CONTACT Bulk Data Entry).

FORCE-X

is the component of the total contact force along the X-axis of the Basic System.

FORCE-Y

is the component of the total contact force along the Y-axis of the Basic System.

FORCE-Z

is the component of the total contact force along the Z-axis of the Basic System.

MAGNITUDE

is the magnitude of the total contact force acting on the Master Surface

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.contgap.fem file The .contgap.fem file is an ASCII format file. It is used to visualize the internally created contact elements. The contact elements are presented as CGAPG elements. File Creation This file is created when CONTPRM,CONTGAP,YES is used. File Contents The file contains CGAPG elements, PGAP properties, and the auxiliary GRIDs for contact visualization. File Format The formats of GRID, CGAPG, and PGAP are the same as for the bulk data entries. Comments 1.

To visualize the configuration of the contact elements, load the original FEA model in HyperMesh and import this file. Ensure that the FE overwrite option is turned on in the import panel.

2.

During optimization, this file contains the contact elements at the latest iteration. To visualize this configuration correctly for shape optimization, the shape of the FEA model should be updated by applying shape change results.

3.

The parameter GAPPRM,GPCOINC is automatically included in this file.

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.cstr file The .cstr file is an OptiStruct ASCII format results file. File Creation This file is created when the OPTI, OS or BOTH formats are chosen. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Composite stress or strain

Composite stress and strain results from linear static. Output is controlled by the I/O options CSTRESS or CSTRAIN. On PCOMP, SOUT=YES needs to be selected.

File Format The composite stress file format is self-explanatory. It gives the stress, strain and composite failure for each element and its plies. Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

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Altair Engineering

.dens file The .dens file is an OptiStruct ASCII format results file. File Creation This file is created when the OPTI, OS or BOTH formats are chosen and a topology optimization is performed. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Density

Density results from topology optimizations. Output is controlled by the I/O option DENSRES.

File Format The density file has the following format: For each iteration, the following header is used: iter

Iteration

Numel

iter

is a keyword identifying that the next field is the iteration number.

Iteration

is the Iteration number.

Numel

is the total number of elements in entire model.

where:

Within the iteration section, the following information is provided for each element: EID

Mat_dens

EID

is the element identification number.

where:

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Mat_dens

is the element material density. Non-design elements are assigned a material density of 1.0.

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.desvar file The .desvar file is an ASCII format result file. File Creation This file is created when OUTPUT,DESVAR is requested in size or shape optimization. File Contents This file contains the updated design variables at last iteration. File Format The format for design variable output is the same as for the bulk data entries.

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.dis.# file The .dis.# file is a Patran 2.5 ASCII format results file. File Creation This file is created when the APATRAN format is chosen and shape or topography design variables are present. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Shape

Shape results from topography or shape optimizations. Output is controlled by the I/O option DENSRES.

Comments 1.

One such file is created for each iteration where the I/O option DENSRES requests topography or shape results to be output.

2.

The # in the file name is the iteration number.

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.disp file The .disp file is an OptiStruct ASCII format results file. File Creation This file is created when the OPTI, OS or BOTH formats are chosen. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Acceleration

Acceleration results from frequency response analyses. Output is controlled by the I/O option ACCELERATION.

Displacement

Displacement results from linear static, inertia relief, and frequency response analyses. Output is controlled by the I/O option DISPLACEMENT.

Eigenvector

Eigenvector results from normal modes and linear buckling analyses. Output is controlled by the I/O option DISPLACEMENT.

Velocity

Velocity results from frequency response analyses. Output is controlled by the I/O option VELOCITY.

File Format The displacement file has the following format: For each iteration, the following header is used: iter

Iteration

Numids

iter

is a keyword identifying that the next field is the iteration number.

Iteration

is the iteration number.

Numids

is the number of linear static subcases plus the number of calculated normal and buckling modes.

where:

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Within the iteration section, the following header is used for each linear static subcase, normal or linear buckling mode, or direct modal frequency response: LCID

Numnod

Freq

Result: SPCcase (Datatype)

LCID

is the output ID for the subcase or mode. This is not necessarily the same as the subcase ID defined in the input data.

Numnod

is the number of grids in the model.

Freq

is the frequency or Buckling eigenvalue (1.0 for static subcases).

Result

is a keyword declaring the result type given.

where:

DISP indicates displacement result. VELO indicates a velocity result (for frequency response analysis only). ACCE indicates an acceleration result (for frequency response analysis only). SPCcase

is the SPC set identification number for linear static, inertia relief, or frequency response subcases or 1 for eigenvectors.

Datatype

is a keyword indicating the type of subcase involved. (LOAD) declares data is from a static subcase. (EIGV) declares data is from a normal modes subcase. (BKLV) declares data is from a linear buckling subcase. (DFRQ) declares data is from a direct frequency response subcase. (MFRQ) declares data is from a modal frequency response subcase.

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Within the subcase or mode section, the following information is provided for each node: NID

X disp

Y disp

Z disp

NID

is the node identification number.

X

is the X displacement of the node.

Y

is the Y displacement of the node.

Z

is the Z displacement of the node.

where:

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

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.dvgrid file The .dvgrid file is an OptiStruct ASCII format results file. File Creation This file is only created when an analysis is performed. Creation of this file is controlled by the I/O Option OUTPUT. File Contents The file contains shape variable definitions for the displacements or eigenvectors resulting from linear static, inertia relief, or normal modes analyses. File Format DESVAR and DVGRID definitions are provided for each linear static subcase and for each calculated normal mode. Output for linear static subcases begins with a header in the following format: $ $ DESVAR and DVGRIDs for static load case $

subcase_id

where: subcase_id

is the user-defined subcase identification number.

Output for calculated normal modes begins with a header in the following format: $ $ DESVAR and DVGRIDs for eigenvalue load case subcase_id, Mode Number mode_number $ where: subcase_id

is the user-defined subcase identification number.

mode_number is the mode number. The DESVAR and DVGRID definitions are formatted as per the bulk data descriptions.

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.echo file The .echo file is an OptiStruct input file. File Creation Creation of this file is controlled by the I/O option ECHO = PUNCH. File Contents The file represents a copy of the input deck in a form suitable to use for another solution which, when used with the same subcase information and I/O options entries, should generate identical results (round off error may be noticeable if the original input deck uses large field format).

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.els.# file The .els.# file is a Patran 2.5 ASCII format results file. File Creation This file is created when the APATRAN format is chosen and topology design variables are present. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Density

Density results from topology optimizations. Output is controlled by the I/O option DENSRES.

Comments 1.

One such file is created for each iteration where the I/O option DENSRES requests topology results to be output.

2.

The # in the file name is the iteration number.

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.force file The .force file is an OptiStruct ASCII format results file. File Creation Creation of this file is controlled by the FORCE (ELFORCE) I/O option. File Contents

Result

Description

Force

Force results from linear static analysis for ELAS (CELAS1, CELAS2, CELAS3, CELAS4), ROD (CROD), BAR (CBAR, CBEAM), BUSH (CBUSH), PLATE (CQUAD, CTRIA), and GAP (CGAP) elements.

File Format The file is divided up by iteration. Output from each iteration starts with a line in the following format: ITER

Iteration_number

Number_of_subcases

where: ITER

is a keyword denoting the beginning of a new iteration.

Iteration_number

is the Iteration number.

Number_of_subcases is the number of subcases for which this output is created.

Each iteration section is divided up by subcase. Output for each subcase starts with a line in the following format: Id Number_of_elements subcase_label

Frequency

LOAD:Spc_id(Datatype)

where: ID

is the output identification number for the subcase. This is not the same as the subcase ID used in the input data.

Number_of_elem is the number of elements for which this output is requested. ents Frequency

Altair Engineering

is 1.0 for static analysis.

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LOAD

is a keyword declaring applied load information.

Spc_id

is the SID for SPC's referenced by this subcase.

(Datatype)

is a keyword indicating the type of subcase involved. (LOAD) declares data is for a linear static subcase.

Each subcase section is divided up by element-type. Output for each element-type section starts with one of the following formats (depending on the elements present in the model): ELAS #

FORC E

ROD#

FORC E-A FORC E-B

BUSH#

F-X

F-Y

F-Z

BAR#

END

AXIAL

SHEAR-1 SHEAR-2 TORQUE BENDING BENDING -1 -2

PLATE#

MEMB-X MEMB-Y

GAP#

C OMP-X SHEAR-Y SHEAR-Z

M-X

MEMB-XY BEND-X

M-Y

BEND-Y

M-Z

TWISTXY

SHEARXZ

SHEARYZ

Element force output is then listed under these headings, depending on the type of elements for which this output was selected. The format of the element output matches the corresponding header, that is for ROD elements you would get FORCE-A and FORCE-B; whereas, for PLATE elements you would get MEMB-X, MEMB-Y, MEMB-XY, BEND-X, BEND-Y, TWIST-XY, SHEAR-XZ, SHEAR-YZ. The format is: Eid

value1

value2

value3

…

where: Eid

is the element identification number.

value#

is the Force result corresponding to the column header.

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

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.fsthick file The .fsthick file is an OptiStruct ASCII format file. File Creation This file is created when free size optimization is performed and OUTPUT, FSTHICK, YES is present in the I/O Options section. File Contents

Result

Description

Element definition

The element definitions for those elements that were part of a free size design space. The optimized thickness of these elements are provided as nodal thickness values (Ti).

File Format The format for the .fsthick file is the same as for the corresponding bulk data entries.

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.gpf file The .gpf file is an OptiStruct ASCII format results file. File Creation Creation of this file is controlled by the GPFORCE I/O option. File Contents

Result

Description

Grid point force balance table

Grid point force balance table for linear static analysis.

File Format The file is divided up by iteration. Output from each iteration starts with a line in the following format: ITERATION

Iteration_number

ITERATION

is a keyword denoting the beginning of a new iteration.

Iteration_number

is the Iteration number.

where:

Each iteration section contains a force balance table for each node, for which this output format was selected, in each linear static subcase. These tables are given the following header: Grid point forces for node

Node_id

Subcase ID =

Subcase_id

where: Node_id

is the ID of the node to which the force balance table applies.

Subcase_id

is the user-defined subcase ID to which the force balance table applies.

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And the force information is provided, for each contributing element, constraint or load, in the following format: Force_type Element_id x-force

y-force

z-force

xmoment

y-moment

z-moment

where: Force_type

is one of: SPC

Force contribution of single-point constraints.

Appl.

Force contribution of Applied loads.

F-MPC

Force contribution of rigid elements or multi-point constraints.

Elem

Force contribution of elastic elements.

Total

The sum of all the force contributions.

Element_id

is only valid for force contributions from elastic elements. This is the element's ID.

x-force

is the x-translational component of the force.

y-force

is the y-translational component of the force.

z-force

is the z-translational component of the force.

x-moment

is the x-rotational component of the force.

y-moment

is the y-rotational component of the force.

z-moment

is the z-rotational component of the force.

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

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.grid file The .grid file is an OptiStruct ASCII format results file. File Creation This file is created when topography or shape optimization is performed. Output of this file is controlled by the I/O Option SHRES or by the GRID keyword on the OUTPUT card. File Contents

Result

Description

Nodal locations

The nodal coordinates of the model for the last iteration of the optimization.

File Format The file uses the following format for each grid in the model: GRID

Id

Cp

X1

X2

X3

Cd

Ps

where: GRID

identifies this as a GRID card image.

Id

is the unique grid point identification number.

Cp

is the identification number of the coordinate system in which the location of the grid point is defined.

X1, X2, X3 provide the location of the grid point in the global coordinate system. Cd

is the identification number of the coordinate system in which the displacements, degrees-of-freedom, constraints and solution vectors are defined at the grid point.

Ps

is the SPC associated with the grid.

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.h3d file The .h3d file is a compressed binary file, containing both model and result data. It can be used to post-process results in HyperView or when using the HyperView Player. File Creation The .h3d file is created when the H3D format is chosen (see I/O options FORMAT and OUTPUT), and an analysis only run is performed (meaning no design variables or design spaces are defined in the model); the I/O option ANALYSIS is present; or the command line switch analysis is used (see Run Options for OptiStruct). File Contents The .h3d file contains node and element definitions in addition to the following results:

Result

Description

Acceleration

Acceleration results from frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option ACCELERATION.

Composite ply strain

Ply strain results for composite materials from static analyses. Output is controlled by the I/O option STRAIN and by the SOUTi field on the PCOMP definition.

Composite ply stress

Ply stress results for composite materials from static and analyses. Output is controlled by the I/O option STRESS and by the SOUTi field on the PCOMP definition.

Composite failure indices

Failure indices for composite materials from static analyses. Output is controlled by the I/O option STRESS, by the SOUTi, SB and FT fields on the PCOMP definition and by the related fields on the relevant material definition (see MAT1, MAT2, MAT8).

Density

Density results from topology optimizations. Output is controlled by the I/O option DENSITY.

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Result

Description

Displacement

Displacement results from static, frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option DISPLACEMENT.

Eigenvector

Eigenvector results from normal modes and linear buckling analyses. Output is controlled by the I/O option DISPLACEMENT.

Element energy loss per cycle Element energy loss per cycle and energy loss per cycle density output from frequency response analysis. Output is controlled by the I/O option EDE. Element force

Element force results from static, frequency response, acoustic, and transient response analyses. Output is controlled by the I/O option FORCE (or ELFORCE).

Element kinetic energy

Element kinetic energy and kinetic energy density output from frequency response analysis. Output is controlled by the I/O option EKE.

Element strain energy

Element strain energy and strain energy density results from static, normal modes and frequency response analyses. Output is controlled by the I/O option ESE.

Grid point stress

Grid point stress results for 3D elements from static and normal modes analyses. Output is controlled by the I/O option GPSTRESS (or GSTRESS).

Power flow field

Power flow field output from frequency response and acoustic analyses. Output is controlled by the I/O option POWERFLOW.

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Result

Description

Shape

Shape results from topography or shape optimizations. Output is controlled by the I/O option SHAPE.

SPC force

Single-point force of constraint results from static, frequency response, acoustic, and transient response analyses. Output is controlled by the I/O option SPCFORCE.

Strain

Strain results from static, frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option STRAIN.

Stress

Stress results from static, frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option STRESS (or ELSTRESS).

Thickness

Thickness results from size and topology optimizations. Output is controlled by the I/O option THICKNESS.

Velocity

Velocity results from frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option VELOCITY.

Comments 1.

Grid point stresses are output for the entire model and for each individual component. This allows grid point stresses to be accurately obtained at the interface of two components referencing different material definitions.

2.

For dynamic analyses like frequency response, transient response, and multi-body dynamics, it is recommended that sets be used to reduce the amount of model and results output data. The output file can become very large since results are output for each frequency or time step.

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.hgdata file The .hgdata file is a HyperGraph ASCII results file. File Creation This file is created when an optimization is performed. Creation of this file is controlled by the I/O Option DESHIS. File Contents This file may contain the iteration history of the objective function, constraint functions, design variables, and response functions. Contents of this file are controlled by the I/O option HISOUT.

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.hist file The .hist file is an OptiStruct ASCII format results file. File Creation This file is created when an optimization is performed. Creation of this file is controlled by the I/O Option DESHIS. File Contents This file contains the iteration history of the objective function, maximum constrain violation, design variables, DRESP1 type responses, and DRESP2 type responses. Contents of this file are controlled by the I/O option HISOUT. File Format The section outlines the format of the .hist OptiStruct ASCII file.

The file uses the following format: iteration Objective

Max_Const_Violation

Design_variables

DRESP1s

DESP2s

where: iteration

is the iteration number.

Objective

is the value of the objective function.

Max_Const_Violation is the Maximum constraint violation in %. Design_variables

is the value of the design variables. Each design variable is given its own column.

DRESP1s

is the value of the DRESP1s. Each DRESP1 type response is given its own column.

DESP2s

is the value of the DRESP2s. Each DRESP2 type response is given its own column.

Comments 1.

The value of each design variable, DRESP1 response and DRESP2 response, is provided in its own column.

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.HM.comp.cmf file The .HM.comp.cmf file is a HyperMesh command file. File Creation The .HM.comp.cmf file is created when a topology optimization is performed (see Topology Optimization in the OptiStruct User's Guide). File Contents When executed in HyperMesh, the .HM.comp.cmf file organizes all elements in the model into ten new components based on their material densities at the final iteration. The components are named 0.0-0.1, 0.1-0.2, 0.2-0.3, and so on, up to 0.9-1.0. All elements with a material density between 0% and 10% are contained in 0.0-0.1. All elements with a material density between 10% and 20% are contained in 0.1-0.2, and so on. This helps you visualize results by turning components on and off. Comments 1.

Ensure the corresponding model is loaded in HyperMesh when executing the command file.

2.

Since elements cannot be in more than one component in HyperMesh, the original components do not contain any elements.

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.HM.conn.cmf file The .HM.conn.cmf file is a HyperMesh command file. File Creation The .HM.conn.cmf file is created when a topology optimization is performed and 1D elements form part of the topological design space (see Topology Optimization in the OptiStruct Users Guide). File Contents When executed in HyperMesh, the .HM.conn.cmf file creates connector definitions for those 1D elements which formed part of the topological design space and organizes these connectors into ten new components based on their material densities at the final iteration. The components are named 0.0-0.1, 0.1-0.2, 0.2-0.3, and so on, up to 0.9-1.0. The connector corresponding to those elements with a material density between 0% and 10% are contained in the 0.0-0.1 component. The connectors corresponding to those elements with a material density between 10% and 20% are contained in the 0.1-0.2 component, and so on. This helps you to visualize results by turning components on and off. Comments 1.

Make sure that the corresponding model is loaded in HyperMesh when executing the command file.

2.

Connectors are geometric entities in HyperMesh.

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.HM.elcheck.cmf file The .HM.elcheck.cmf file is a HyperMesh command file. File Creation The file is created when an element quality check is performed. File Contents This file contains results from the following tests: 1.

Element quality tests using ELEMQUAL entry and PARAM, CHECKEL.

2.

Incorrectly formed CFAST and CWELD elements.

3.

CBUSH or CELAS elements with excessive stiffness values (PARAM, BUSHSTIF and PARAM, ELASSTIF).

When executed in HyperMesh, the .HM.elcheck.cmf file organizes all elements into separate sets depending on which quality check they fail. One set is created for each failed quality check. This helps you to visualize results by finding (displaying) elements by set. Comments 1.

Ensure the corresponding model is loaded in HyperMesh when executing the command file.

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.HM.elcheck.###.cmf file The .HM.elcheck_###.cmf file is a HyperMesh command file. File Creation The file is created, as required, when an element quality check is performed for optimization iterations. File Contents This file contains results from the following tests: 1.

Element quality tests using ELEMQUAL entry and PARAM, CHECKEL.

2.

Incorrectly formed CFAST and CWELD elements.

3.

CBUSH or CELAS elements with excessive stiffness values (PARAM, BUSHSTIF and PARAM, ELASSTIF).

When executed in HyperMesh, the .HM.elcheck_###.cmf file organizes all elements into separate sets depending on which quality check they fail. One set is created for each failed quality check. This helps you to visualize results by finding (displaying) elements by set. Comments 1.

Ensure the corresponding model is loaded in HyperMesh when executing the command file.

2.

The ### in the file name represents the optimization iteration number.

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.HM.ent.cmf file The .HM.ent.cmf file is a HyperMesh command file. File Creation The .HM.ent.cmf file is created when a topology optimization is performed (see Topology Optimization in the OptiStruct User's Guide). File Contents When executed in HyperMesh, the .HM.ent.cmf file organizes all elements in the model into ten new entity sets based on their material densities at the final iteration. The sets are named 0.0-0.1, 0.1-0.2, 0.2-0.3, and so on, up to 0.9-1.0. All elements with a material density between 0% and 10% are contained in 0.0-0.1. All elements with a material density between 10% and 20% are contained in 0.1-0.2, and so on. You can then visualize the results by masking the entity sets which contain those elements with lower density. Comments 1.

Ensure the corresponding model is loaded in HyperMesh when executing the command file.

2.

The advantage of this method over the .HM.comp.cmf method is that the elements remain in their original components, but can still be selected and masked by entity set.

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.HM.gapstat.cmf file The .HM.gapstat.cmf file is a HyperMesh command file. File Creation This file is created when a nonlinear gap analysis is performed and GAPPRM, HMGAPST is set as YES or 1. File Contents When executed in HyperMesh, the .HM.gapstat.cmf file organizes gap elements into two sets, open or closed, depending on the status of the gap at the end of the analysis. Comments 1.

Be sure that the corresponding model is loaded in HyperMesh when executing the command file.

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.html file The .html file is a HyperText Markup Language file. File Creation This file is always output. File Contents This file contains a problem summary and results summary of the run. The problem summary contains information on the finite element model, subcase definitions, and optimization parameters. The results summary lists the following results for an analysis or the final iteration of an optimization: For linear static subcases: The maximum displacement and the node where this occurs The maximum strain energy density and the element where this occurs The maximum stress and strain for 1D, 2D, and 3D elements and the elements where these occur For normal modes subcases: The frequencies of the calculated modes The maximum deformation and the node where this occurs The maximum strain energy density and the element where this occurs For linear buckling subcases: The buckling factor for the calculated modes The maximum deformation and the node where this occurs

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.interface file The .interface file is an ASCII format results file. File Creation This file is always created when acoustic analysis is performed. File Contents This acoustic coupling interface matrix visualization file contains element definitions. Comments 1.

This file is used to verify the fluid/structure coupling matrix.

2.

Import this file into HyperMesh with the acoustic model already loaded. For best performance, ensure that the FE overwrite option is turned on in the HyperMesh import panel.

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.k.op2 file The .k.op2 file is a Nastran output2 format file containing the stiffness matrix. File Creation This file is created when PARAM, POST, -5 is present in the bulk data section. File Contents This file contains the stiffness matrix.

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.load file The .load file is an OptiStruct ASCII format results file. File Creation Creation of this file is controlled by the OLOAD I/O option. File Contents

Result

Description

Applied Load

Applied load vectors for linear static analysis.

File Format The applied load file has the following format: For each iteration, the following header is used: iter

Iteration

NumIds

iter

is a keyword denoting the beginning of a new iteration.

Iteration

is the iteration number.

Numids

is the number of subcases for which this output is created.

where:

Each iteration section is divided up by subcase. Output for each subcase starts with a line in the following format: Id

Number_of_node s

Frequency

LOAD:Spc_id(Datatype)

subcase_label

where: Id

Altair Engineering

is the output identification number for the subcase. This is not the same as the subcase ID used in the input data.

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Number_of_nodes is the number of nodes for which this output is requested. Frequency

is 1.0 for static analysis.

LOAD

is a keyword declaring applied load information.

Spc_id

is the SID for SPC's referenced by this subcase.

Datatype

is a keyword indicating the type of subcase involved. (LOAD) declares data is for a linear static subcase.

The following information is then provided for each node, for which this output was requested: NID

X force

Y force

Z force

NID

is the node identification number.

X force

is the X force at the node.

Y force

is the Y force at the node.

Z force

is the Z force at the node.

X mom

is the X moment at the node.

Y mom

is the Y moment at the node.

Z mom

is the Z moment at the node.

X mom

Y mom

Z mom

where:

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an Optimization.

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.m.op2 file The .m.op2 file is a Nastran output2 format file containing the mass matrix. File Creation This file is created when PARAM, POST, -5 is present in the bulk data section. File Contents This file contains the mass matrix.

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.mass file The .mass file is an OptiStruct ASCII format results file. File Creation This file is only created when modal analyses are performed. Creation of this file is controlled by the I/O Option OUTPUT. File Contents

Result

Description

Modal Effective Masses

Modal effective mass results from modal analyses. Output is controlled by the I/O option OUTPUT,HGEFFMASS.

File Format The file is formatted into blocks separated by blank lines. Each block represents a modal subcase; the subcases are in order of occurrence in the input deck. Each block contains a number of rows equal to the number of requested modes for that subcase. The columns, from left to right, contain results for modal effective mass for X-translation, Ytranslation, Z-translation, X-rotation, Y-rotation, and Z-rotation. Comments 1.

The _mass.mvw HyperView script file automatically creates plots for the results contained in this file.

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.mnf file The .mnf file is ADAMS modal neutral file. File Creatio n This file is created when OUTPUT, ADAMSMNF is presented during flexible body generation. File Contents This file contains the flexible body models. Comments 1.

If GPSTRESS output is requested in addition to OUTPUT, ADAMSMNF, nodal stress results for solid elements will be written to this file.

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.mpcf file The .mpcf file is an OptiStruct ASCII format results file. File Creation Creation of this file is controlled by the MPCFORCES I/O option. File Contents

Result

Description

Multi-point force of constraint

Multi-point force of constraints for linear static analysis.

File Format The file is divided up by iteration. Output from each iteration starts with a line in the following format: ITERATION

Iteration_number

ITERATION

is a keyword denoting the beginning of a new iteration.

Iteration_number

is the iteration number.

where:

Each iteration section contains the multi-point force of constraint for each node, for which this output format was selected, in each linear static subcase. Each subcase section is given the following header: MPC forces for Subcase

Subcase_id

where: Subcase_id

is the user-defined subcase ID to which the mpc forces apply.

MPC force information is then provided, for each node, in the following format:

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Node_id

x-force

y-force

z-force

x-moment

y-moment

z-moment

where: Node_id

is the node identification number.

x-force

is the x-translational component of the force at the node.

y-force

is the y-translational component of the force at the node.

z-force

is the z-translational component of the force at the node.

x-moment

is the x-rotational component of the force at the node.

y-moment

is the y-rotational component of the force at the node.

z-moment

is the z-rotational component of the force at the node.

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an Optimization.

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.op2 file The .op2 file is a Nastran output2 format for model and results data. File Creation This file is created when the O2, OUT2, or OUTPUT2 formats are chosen. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Acceleration

Acceleration results from frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option ACCELERATION.

Composite ply strain

Ply strain results for composite materials from static analyses. Output is controlled by the I/O option CSTRAIN and by the SOUTi field on the PCOMP definition.

Composite ply stress

Ply stress results for composite materials from static analyses. Output is controlled by the I/O option CSTRESS and by the SOUTi field on the PCOMP definition.

Composite failure indices

Failure indices for composite materials from static analyses. Output is controlled by the I/O option CSTRESS, by the SOUTi, SB and FT fields on the PCOMP definition, and by the related fields on the relevant material definition (see MAT1, MAT2, MAT8).

Density

Density results from topology optimizations. Output is controlled by the I/O option DENSITY. Note: Density results are reported as element strain energy.

Displacement

Displacement results from static, frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option DISPLACEMENT.

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Result

Description

Eigenvector

Eigenvector results from normal modes and linear buckling analyses. Output is controlled by the I/O option DISPLACEMENT.

Element energy loss per cycle

Element energy loss per cycle and energy loss per cycle density output from frequency response analysis. Output is controlled by the I/O option EDE.

Element force

Element force results from static, frequency response, acoustic, and transient response analyses. Output is controlled by the I/O option FORCE (or ELFORCE).

Element kinetic energy

Element kinetic energy and kinetic energy density output from frequency response analysis. Output is controlled by the I/O option EKE.

Element strain energy

Element strain energy and strain energy density results from static, normal modes, frequency response, and transient response analyses. Output is controlled by the I/O option ESE.

Grid point stress

Grid point stress results for 3D elements from static analyses. Output is controlled by the I/O option GPSTRESS (or GSTRESS).

MPC force

Multi-point force of constraint results from static, frequency response, acoustic, and transient response analyses. Output is controlled by the I/O option MPCFORCE.

PSD element strain

Power spectral density function of element strains from random response analysis. Output is controlled by the I/O option STRAIN.

PSD element stress

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Power spectral density function of element stresses from random response analysis.

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Result

Description Output is controlled by the I/O option STRESS.

RMS element strain

Root mean square value of element strains from random response analysis. Output is controlled by the I/O option STRAIN.

RMS element stress

Root mean square value of element stresses from random response analysis. Output is controlled by the I/O option STRESS.

SPC force

Single-point force of constraint results from static, frequency response, acoustic, and transient response analyses. Output is controlled by the I/O option SPCFORCE.

Strain

Strain results from static, frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option STRAIN.

Stress

Stress results from static, frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option STRESS (or ELSTRESS).

Velocity

Velocity results from frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option VELOCITY.

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

2.

In addition to the analysis and optimization results, the finite element model description (nodes, elements, coordinates systems, and properties) is written to the .op2 file. This model can be read by HyperView and fatigue codes. To turn off the model output, use the NOMODEL option on OUTPUT, OP2.

3.

To be able to read the model directly from the .op2 file, newer versions of FEMFAT, Medina (7.4.8 or newer), and Animator (3.0.6.6c or newer) must be used.

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4.

For dynamic analyses like frequency response, transient response, and multi-body dynamics, it is recommended that sets be used to reduce the amount of model and results output data. The output file can become very large since results are output for each frequency or time step.

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.oss file The .oss file is an OSSmooth parameter file. File Creation This file is created when a topology, topography, or shape optimization is performed. File Contents The file contains default settings for running OSSmooth after a successful optimization. Comments 1.

The format of this file is described on the OSSmooth Input Data page.

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.out file The .out file is an ASCII format results file. File Creation This file is always created. File Contents This file provides a commentary on the solution process. File Format The file starts with an OptiStruct banner, and is followed by three sections which outline the problem definition: Optimization File and Parameter Information Finite Element Model Data Information Optimization Problem Parameters Following these, calculated estimates on required memory and disk space are provided under the headings: Memory Estimation Information Disk Space Estimation Information The Analysis Results or Optimization History information sections provide the following information (Some information is output for each iteration during optimization, or as a summary for nonlinear analysis): Element quality information (If any of the warning or error limits are exceeded). Global force balance tables for each linear static subcase. (When SPCFORCE or GPFORCE is a requested output). Objective function value Maximum constrain violation % and the ID of this constraint. Design volume fraction value if topology design variables are present, otherwise the total volume is given, and the total mass. Individual subcase compliances and weightings and the total weighted compliance. Retained responses table If the constraint violation is higher than 1%, the constraint is flagged as V (violated). If the violation is lower than 1%, it is flagged as A (active). For stress constraint in topology optimization, if there is no violation, it is flagged as Inactive; otherwise, it is flagged as Active. User-requested responses table (when RESPRINT or DREPORT is a requested output).

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Most violated constraints table. Design variable values and bounds if shape or size design variables are present. Designed property/material/connectivity items table if size design variables are present. A list of calculated buckling modes and their eigenvalues. A list of calculated normal modes, their frequencies, eigenvalues and weighting and the value of the frequencies weighted across the reciprocal eigenvalues. Center of Gravity table Moment of Inertia table Regional compliance table

Manufacturing Constraints table for Composite Optimization An example table is shown below: COMPOSITE MANUFACTURING CONSTRAINTS ---------------------------------------------------------------------------User-ID Constraint Information Status Max Avg Pct Type Bound Group Elem Viol. Viol. Viol. ---------------------------------------------------------------------------1 PLYPCT LOWER 0.0 ALL Violated 12.1 2.6 2.5 1 PLYPCT LOWER 90.0 ALL Violated 3.0 1.6 0.2 1 PLYPCT UPPER 90.0 ALL Violated 31.8 5.3 14.6 ---------------------------------------------------------------------------Where, Max Viol. – Represents the maximum violation of the specified manufacturing constraint (Type). Avg Viol. – Represents the average violation of all the violated elements for the specified manufacturing constraint (Type). Pct Viol. – Represents the percentage of the total number of elements in the design space for which the specified manufacturing constraint (Type) is violated. The Constraint Information columns are self-explanatory and may vary from one constraint type to the other.

Nonlinear Iteration Summary table for Nonlinear Analysis An example table is shown below:

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Where, Avg. U – Represents the average displacement of all elements for a particular iteration for a subcase EUI – Represents the relative error in displacements EPI – Represents the error in terms of loads EWI – Represents the error in terms of work Refer to the Nonlinear Convergence Criteria section of Nonlinear Quasi-Static Analysis in the User’s Guide for more information. Maximum Plststrn – Represents the Maximum Plastic Strain The Gap and Contact Element Status columns are self-explanatory. At the end of the file, the following information is provided: Resource usage information Compute time information

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.pch file The .pch file is a Nastran punch format results file. File Creation This file is created when the NASTRAN or PUNCH formats are chosen. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Acceleration

Acceleration results from frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option ACCELERATION.

Density

Density results from topology optimizations. Output is controlled by the I/O option DENSRES. Note: Density results are reported as von Mises Strains.

Displacement

Displacement results from static, frequency response, acoustic, and transient response analyses. Output is controlled by the I/O option DISPLACEMENT.

Eigenvector

Eigenvector results from normal modes analyses. Output is controlled by the I/O option DISPLACEMENT.

Element energy loss per cycle

Element energy loss per cycle and energy loss per cycle density output from frequency response analysis. Output is controlled by the I/O option EDE.

Element force

Element force results from static, frequency response, acoustic, and transient response analyses. Output is controlled by the I/O option FORCE (or ELFORCE).

Element kinetic energy

Element kinetic energy and kinetic energy density output from frequency response analysis.

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Result

Description Output is controlled by the I/O option EKE.

Element strain energy

Element strain energy and strain energy density results from static, normal modes and frequency response analyses. Output is controlled by the I/O option ESE.

Grid point stress

Grid point stress results for 3D elements from static analysis. Output is controlled by the I/O option GPSTRESS (or GSTRESS).

MPC force

Multi-point force of constraint results from static, frequency response, acoustic, and transient response analyses. Output is controlled by the I/O option MPCFORCE.

PSD acceleration

Power spectral density function of accelerations from random response analysis. (see comment 2) Output is controlled by the I/O options XYPEAK, XYPLOT, and XYPUNCH.

PSD displacement

Power spectral density function of displacements from random response analysis. (see comment 2) Output is controlled by the I/O options XYPEAK, XYPLOT, and XYPUNCH.

PSD velocity

Power spectral density function of velocities from random response analysis. (see comment 2) Output is controlled by the I/O options XYPEAK, XYPLOT, and XYPUNCH.

PSD element strain

Power spectral density function of element strains from random response analysis. (see comment 2) Output is controlled by the I/O options XYPEAK, XYPLOT, and XYPUNCH.

PSD element stress

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Power spectral density function of element stresses from random response analysis. (see comment 2)

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Result

Description Output is controlled by the I/O options XYPEAK, XYPLOT, and XYPUNCH.

RMS element strain

Root mean square value of element strains from random response analysis. Output is controlled by the I/O options XYPEAK, XYPLOT, and XYPUNCH.

RMS element stress

Root mean square value of element stresses from random response analysis. Output is controlled by the I/O options XYPEAK, XYPLOT, and XYPUNCH.

SPC force

Single-point force of constraint results from linear static analysis. Output is controlled by the I/O option SPCFORCE.

Strain

Strain results from static, frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option STRAIN.

Stress

Stress results from static, frequency response, acoustic, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option STRESS (or ELSTRESS).

Velocity

Velocity results from frequency response analyses, acoustic, transient response, and multi-body dynamics. Output is controlled by the I/O option VELOCITY.

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

2.

Multiple RANDOM subcase information entries with non-unique ID’s are allowed in a single model. Therefore, if the plot-type field on the XYPUNCH output request is set to PSDF, then the RANDOM ID will be added to the XYPUNCH headers in the corresponding result sections of the .pch file when multiple RANDOM entries are present in the same deck. If only one RANDOM entry is present, the RANDOM ID is not printed.

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.pcomp file The .pcomp file is an ASCII format result file. File Creation This file is created when OUTPUT,PCOMP is requested in composite sizing optimization. File Contents This file contains elements and PCOMPG property information for each STACK.

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.peak file The .peak file is an ASCII format results file. File Creation This file is created when XYPLOT, XYPEAK, or XYPUNCH is requested in random response analysis. File Contents This file contains the root mean square value, the number of positive crossings, and the peak power spectral density and responses.

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.pret file The .pret file is an OptiStruct ASCII format results file. File Creation Creation of this file is controlled by the PRETBOLT I/O Options Entry. File Contents Result

Description

Pretension force/ adjustment

Pretension force/adjustment values for pretension bolts in pretensioning and pretensioned subcases.

File Format The file is sorted by iteration. Output from each iteration starts in the following format: PRETENSION FORCE/ADJUSTMENT VALUES ON THE PRENTESION SECTIONS

ITERATION

Iteration_number

Where: ITERATION is a keyword denoting the beginning of a new iteration. Iteration_number is the iteration number.

Each iteration section contains the force/adjustment values for each pretension bolt in each static subcase. Each such subcase section is given the following header: Subcase

Subcase_id

Subcase_label

Where: Subcase is a keyword denoting the beginning of the current subcase section. Subcase_id is the user-defined subcase ID Subcase_label is the user-defined subcase label

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Pretension force/adjustment information is then provided, for each bolt, in the following format: Pretension section ID (PRETENS #)

Force-incr

Adjust-incr

Force-tot

Adjusttot

Where: Pretension section ID denotes the pretension section ID (SID of the PRETENS bulk data entry). Force-incr is the incremental pretension force value when compared to the previous subcase in the loading sequence. Adjust-incr is the incremental pretension adjustment value when compared to the previous subcase in the loading sequence. Force-tot is the total pretension force value. Adjust-tot is the total pretension adjustment value. Comments 1. The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

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.prop file The .prop file is an OptiStruct ASCII format result file. File Creation This file is output when sizing optimization is performed. Creation of this file is controlled by the PROPERTY I/O option. File Contents

Result

Description

Property definition

The property definitions, for those properties that were affected in the sizing optimization, used for the final iteration of the optimization.

File Format The format for the property output is the same as for the bulk data entries.

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.rand file The .rand file is an OptiStruct ASCII format results file. File Creation This file is only created for random response subcases. This file is only created if XYPLOT is defined in random response. File Contents

Result

Description

Random response results

Results from random response analyses.

Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _rand.mvw HyperView script file automatically creates plots for the results contained in this file.

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.res file The .res file is a HyperMesh binary results file. File Creation The .res file is created when either no format statement is given or when the HM, HYPER, or BOTH formats are chosen. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Acceleration

Acceleration results from frequency response, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option ACCELERATION.

Composite ply strain

Ply strain results for composite materials from static analyses. Output is controlled by the I/O option STRAIN and by the SOUTi field on the PCOMP definition.

Composite ply stress

Ply stress results for composite materials from static analyses. Output is controlled by the I/O option STRESS and by the SOUTi field on the PCOMP definition.

Composite failure indices

Failure indices for composite materials from static analyses. Output is controlled by the I/O option STRESS, by the SOUTi, SB and FT fields on the PCOMP definition, and by the related fields on the relevant material definition (see MAT1, MAT2, MAT8).

Density

Density results from topology optimizations. Output is controlled by the I/O option DENSITY.

Displacement

Displacement results from static, frequency response, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option DISPLACEMENT.

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Result

Description

Eigenvector

Eigenvector results from normal modes and linear buckling analyses. Output is controlled by the I/O option DISPLACEMENT.

Element strain energy

Element strain energy results from static and normal modes analyses. Output is controlled by the I/O option ESE.

Grid point stress

Grid point stress results for 3D elements from static analyses. Output is controlled by the I/O option GPSTRESS (or GSTRESS).

Shape

Shape results from topography or shape optimizations. Output is controlled by the I/O option SHAPE.

Single-point force of constraint

Single-point force of constraint results from static analyses. Output is controlled by the I/O option SPCFORCE.

Strain

Strain results from static, frequency response, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option STRAIN.

Stress

Stress results from static, frequency response, transient response, and multi-body dynamics analyses. Output is controlled by the I/O option STRESS (or ELSTRESS).

Thickness

Thickness results from size and topology optimizations. Output is controlled by the I/O option THICKNESS.

Velocity

Velocity results from frequency response analyses, transient response, and multi-body dynamics. Output is controlled by the I/O option VELOCITY.

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Comments 1.

If an optimization is terminated abruptly due to an error such as a full disk or power failure, the HyperMesh binary results file (*.res) may become corrupted. In this event, run the program "recover," included with OptiStruct, to clean up the results file.

2.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

3.

Grid point stresses are output for the entire model and for each individual component. This allows grid point stresses to be accurately obtained at the interface of two components referencing different material definitions.

4.

For dynamic analyses, like frequency response, transient response, and multi-body dynamics, it is recommended that sets be used to reduce the amount of model and results output data. The output file can become very large since results are output for each frequency or time step.

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.seplot file The .seplot file is an ASCII format output file. File Creation This file is created when the MODEL, PLOT, and PARAM, SEPLOT, YES options are presented and the CBN method is used to reach a Component Mode Synthesis solution. File Contents This file contains grid and plot element definitions. Comments 1.

By including this file in a residual run, the results of the superelement part will be recovered and post-processed.

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.sh file The .sh file is an OptiStruct ASCII format results file. File Creation This file is created when an optimization is performed. Output of this file is controlled by the I/O option SHRES. File Contents Contains information necessary to restart the optimization from the final iteration.

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.spcd file The .spcd file is an OptiStruct ASCII format results file. File Creation This file is created in a residual run when DMIG's are present in the model. The .spcd file contains displacement results at interface grid points. File Contents Result

Description

Displacement

Displacement results from a residual run. Output is controlled by the I/O option DISPLACEMENT.

File Format The .spcd file has the following format: For each iteration, the following header is used: SUBCASE

SID

SID

is the identification number of the corresponding subcase.

where:

Under each applicable subcase header, we have the following columns: SPC

####SID GRID ID

Component

Displacement

SID

is the identification number of the corresponding subcase.

GRID ID

is the identification number of the interface grid at which the displacement results are output.

Component

is the component in which the displacement result output.

where:

Displacement is the displacement result for a give grid in the corresponding component.

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Comments 1.

Only one .spcd file is created even if there are multiple DMIG’s in the model.

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.spcf file The .spcf file is an OptiStruct ASCII format results file. File Creation Creation of this file is controlled by the SPCFORCES I/O option. File Contents

Result

Description

Single-point force of constraint

Single-point force of constraints for linear static analysis.

File Format The SPC reaction force file has the following format: For each iteration, the following header is used: iter

Iteration

Numlds

iter

is a keyword denoting the beginning of a new iteration.

Iteration

is the iteration number.

Numlds

is the number of subcases for which this output is created.

where:

Each iteration section is divided up by subcase. Output for each subcase starts with a line in the following format: Id

Number_of_nodes

Frequency

SPCF:Spc_id(Datatype)

subcase_label

where: Id

Altair Engineering

is the output identification number for the subcase. This is not the same as the subcase ID used in the input data.

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Number_of_nodes

is the number of nodes for which this output is requested.

Frequency

is 1.0 for static analysis.

SPCF

is a keyword declaring SPC-force information.

Spc_id

is the SID for SPC's referenced by this subcase.

Datatype

is a keyword indicating the type of subcase involved. (LOAD) declares data is for a linear static subcase.

SPC-force information is then provided, for each node, in the following format: Node_id

x-force

y-force

z-force

x-moment

y-moment z-moment

where: Node_id

is the node identification number.

x-force

is the x-translational component of the force at the node.

y-force

is the y-translational component of the force at the node.

z-force

is the z-translational component of the force at the node.

x-moment

is the x-rotational component of the force at the node.

y-moment

is the y-rotational component of the force at the node.

z-moment

is the z-rotational component of the force at the node.

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an Optimization.

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.stat file The .stat file is an ASCII format results file. File Creation This file is always created. File Contents This file provides details on CPU and elapsed time for each solver module. File Format Information on CPU and elapsed time is provided in the following format: TOTAL TIME SPENT IN MODULE: module_name; CPU= cpu_time; WALL= wall_time where:

module_name is the name of the module. cpu_time

is the amount of CPU time spent in this module.

wall_time

is the total elapsed time spent in this module.

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.strn file The .strn file is an ASCII format results file. File Creation This file is created when OPTI, OS, or ASCII formats are chosen. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Strain

Strain results from linear static analysis. Output is controlled by the I/O option STRAIN.

File Format The strain file has the following format: For each iteration, the following header is used: iter

Iteration

Numlds

iter

is a keyword denoting the beginning of a new iteration.

Iteration

is the Iteration number.

Numlds

is the number of load cases for which this output is created.

where:

Each iteration section is divided up by subcase. Output for each subcase starts with a line in the following format: Id

Number_of_els

STRN:Spc_id

where: Id

is the output identification number for the subcase. This is not the same as the subcase ID used in the input data.

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Number_of_els

is the number of elements for which this output is requested.

STRN

is a fixed keyword.

Spc_id

is the SID for SPC's referenced by this subcase.

Datatype

is a keyword indicating the type of subcase involved. (LOAD) declares data is for a linear static subcase.

Strain information is then provided, for each element, in the following format: EID

Strain1

Strain2

Strain3

Strain4

Strain5

Strain6

Strain7

where: EID

is the element identification number.

Strain1

is von Mises strain for 2D and 3D elements, or Axial strain for 1D elements.

Strain2

is Normal X-strain at Z1 for 2D elements, Normal X-strain for 3D elements, or Axial strain for 1D elements.

Strain3

is Normal X-strain at Z2 for 2D elements, Normal Y-strain for 3D elements, or Axial strain for 1D elements.

Strain4

is Normal Y-strain at Z1 for 2D elements, Normal Z-strain for 3D elements, or Axial strain for 1D elements.

Strain5

is Normal Y-strain at Z2 for 2D elements, Shear XY-strain for 3D elements, or Axial strain for 1D elements.

Strain6

is Shear XY-strain at Z1 for 2D elements, Shear YZ-strain for 3D elements, or Axial strain for 1D elements.

Strain7

is Shear XY-strain at Z2 for 2D elements, Shear XZ-strain for 3D elements, or Axial strain for 1D elements.

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

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.strs file The .strs file is an OptiStruct ASCII format results file. File Creation This file is created when the OPTI, OS or BOTH formats are chosen. (See documentation for the I/O options FORMAT and OUTPUT). File Contents

Result

Description

Stress

Stress results from linear static analysis. Output is controlled by the I/O option STRESS (or ELSTRESS).

File Format The stress file has the following format: For each iteration, the following header is used: iter

Iteration

Numlds

iter

is a keyword denoting the beginning of a new iteration.

Iteration

is the Iteration number.

Numlds

is the number of load cases for which this output is created.

where:

Each iteration section is divided up by subcase. Output for each subcase starts with a line in the following format: Id

Number_of_els

STRS:Spc_id(Datatype)

where: Id

is the output identification number for the subcase. This is not the same as the subcase ID used in the input data.

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Number_of_els

is the number of elements for which this output is requested.

STRS

is a fixed keyword.

Spc_id

is the SID for SPC's referenced by this subcase.

Datatype

is a keyword indicating the type of subcase involved. (LOAD) declares data is for a linear static subcase.

Stress information is then provided, for each element, in the following format: EID

Stress1

S Stress3 t r e s s 2

S Stress5 t r e s s 4

Stress6

Stress7

Stress8

Stress9

where: EID

Element identification number.

Stress1

von Mises stress for 2D and 3D elements, Maximum Axial stress for 1D elements, or maximum stress in CWELD elements.

Stress2

Normal X-stress at Z1 for 2D elements, Normal X-stress for 3D elements, or Axial stress for 1D elements. For BAR/BEAM it is the stress at C at end A. Axial Stress for CWELD elements.

Stress3

Normal X-stress at Z2 for 2D elements, Normal Y-stress for 3D elements, or Axial stress for 1D elements. For BAR/BEAM it is the stress at D at end A. Maximum tensile stress at end A for CWELD elements.

Stress4

Normal Y-stress at Z1 for 2D elements, Normal Z-stress for 3D elements, or Axial stress for 1D elements. For BAR/BEAM it is the stress at E at end A. Minimum tensile stress at

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end A for CWELD elements. Stress5

Normal Y-stress at Z2 for 2D elements, Shear XY-stress for 3D elements, or Axial stress for 1D elements. For BAR/BEAM it is the stress at F at end A. Maximum tensile stress at end B for CWELD elements.

Stress6

Shear XY-stress at Z1 for 2D elements, Shear YZ-stress for 3D elements, or Axial stress for 1D elements. For BAR/BEAM it is the stress at C at end B. Minimum tensile stress at end B for CWELD elements.

Stress7

Shear XY-stress at Z2 for 2D elements, Shear XZ-stress for 3D elements, or Axial stress for 1D elements. For BAR/BEAM it is the stress at D at end B. Maximum shear stress for CWELD elements.

Stress8

Maximum shear stress for CWELD elements. For BAR/BEAM it is the stress at E at end B. Bearing stress for CWELD elements.

Stress9

Bearing stress for CWELD elements. For BAR/BEAM it is the stress at F at end B.

Comments 1.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

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_des.h3d file The _des.h3d file is a compressed binary file, containing both model and result data. It can be used to post-process results in HyperView or when using the HyperView Player. File Creation The _des.h3d file is created when the H3D format is chosen (see documentation for the I/O option FORMAT), and an optimization run is performed. File Contents The _des.h3d file contains node and element definitions in addition to the following results:

Result

Description

Density

Density results from topology optimizations. Output is controlled by the I/O option DENSRES.

Shape

Shape results from topography or shape optimizations. Output is controlled by the I/O option DENSRES.

Thickness

Thickness results from size and topology optimizations. Output is controlled by the I/O option DENSRES.

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_err.grid file The _err.grid file is an OptiStruct ASCII format results file. File Creation This file is automatically created when freeshape and topography (or shape) optimization runs are terminated due to mesh distortion. File Contents Result

Description

Nodal locations

It contains the nodal coordinates of the distorted mesh for freeshape and topography (or shape) optimization.

File Format The file uses the following format for each grid in the model: GRID

Id

Cp

X1

X2

X3

GRID

identifies this as a GRID card image.

Id

is the unique grid point identification number.

Cp

is blank.

Cd

Ps

where:

X1, X2, X3 provide the location of the grid point in the global coordinate system. Cd

is the identification number of the coordinate system in which the displacements, degrees-of-freedom, constraints, and solution vectors are defined at the grid point.

Ps

is the SPC associated with the grid.

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_frames.html file The _frames.html file is a HyperText Markup Language file. File Creation This file is output when the H3D FORMAT is chosen. File Contents The file contains two frames. The top frame opens one of the .h3d files using the HyperView Player browser plug-in. The .h3d file opened depends on the results selected for display in the bottom frame. The bottom frame opens the _menu.html file, which facilitates the selection of results to be displayed. Comments 1.

Requires HyperView Player plug-in to be installed.

2.

This file is linked to from the "Results summary" section of the .html file and is created primarily for this purpose.

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_freq.#.mvw file The _freq.#.mvw file is a HyperView session file. File Creation This file is created when frequency response optimization is performed and OUTPUT,HGFREQ is requested. Comments 1.

The # in the file name is the iteration number.

2.

This file may be opened from the File menu in HyperView or HyperGraph. It automatically creates plots for the results contained in the files: _s#_a.#.frf, _s#_d.#.frf, and _s#_v.#.frf.

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_freq.mvw file The _freq.mvw file is a HyperView session file. File Creation This file is only created when frequency response analysis is performed. Creation of this file is controlled by the I/O option OUTPUT. File Contents This file is a HyperView session file and may be opened from the File menu in HyperView or HyperGraph. The file automatically creates plots for each of the results contained in the files: _s#_a.frf, _s#_d.frf, and _s#_v.frf.

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_gauge.h3d file The _gauge.h3d file is a compressed binary file containing both model and result data. It can be used to post-process shell thickness (gauge) sensitivity in HyperView. File Creation This file is created when an optimization is performed. Creation of this file is controlled by the I/O option OUTPUT. File Contents The _gauge.h3d file contains node and element definitions in addition to the following results:

Result

Description

Sensitivity

Sensitivity of response vs. shell thickness (gauge) of PSHELL property. Output is controlled by the I/O option OUTPUT.

Comments 1.

The # in the file name is the iteration number.

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_gso.slk file The _gso.slk file is a Microsoft SLK Data Import format results file. File Creation This file is created when Global Search Option (GSO) is activated and executed using the DGLOBAL I/O entry and the DGLOBAL Bulk Data entry, respectively. This file outputs the results of Global Search Option (GSO). File Contents Result

Description

Optimized Designs

It contains the list of unique and similar optimized designs based on the Global Search Option (GSO) method. The designs in this resulting subset of the total design space are then sorted based on their rank (based on the number of convergences from unique starting points to result in a specific design).

File Format The file uses the following format for the designs optimized from specified starting points: Unique Designs Design Rank

Startin g Point

Times Found

Directo ry Name

Objecti ve Functio n

C onstr aint Violatio n

Max. Obj. Deviati on

Avg. Obj. Deviati on

Max. DV Deviati on

Avg. DV Deviati on

DV1

DVN

All Designs Design Rank

Starting Point

Unique Design

Directory Name

Objective Function

C onstraint DV1 Violation

DVN

Where, Design Rank

Denotes the rank of the design. This is assigned based initially on the values of Constraint Violation and then the Objective Function values.

Starting Point

Denotes the starting point of the optimization for a design in the design space.

Times Found

The number of times designs (from unique starting points) converge to the same design.

Directory Name

Name of the Directory where the output files associated with the specified design are stored.

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Objective Function

The value of the Objective Function for the current design.

Constraint Violation

The value of the Constraint Violation for the current design

Maximum Objective Deviation

The maximum deviation (of a design) from the objective function among designs from unique starting points that converged to this unique design.

Average Objective Deviation

The average deviation (of a design) from the objective function among designs from unique starting points that converged to this unique design.

Maximum DV Deviation

The maximum deviation between two design variables in the design space among designs from unique starting points that converged to this unique design.

Average DV Deviation

The average deviation between design variables in the design space among designs from unique starting points that converged to this unique design.

DV#

The various design variables values represented by DV1, DV2,….., DVN.

Unique Design This represents the Design Rank used in the UNIQUE DESIGN Table.

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_hist.mvw file The _hist.mvw file is a HyperView session file. File Creation This file is created when an optimization is performed. Creation of this file is controlled by the I/O option DESHIS. File Contents This file is a HyperView session file and may be opened from the File menu in HyperView or HyperGraph. The file automatically creates individual plots for each of the results contained in the .hist file. Each plot occupies its own page within HyperView (HyperGraph).

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_mass.#.mvw file The _mass.#.mvw file is a HyperView session file. File Creation This file is created when modal optimization is performed and OUTPUT,HGEFFMASS is requested. Comments 1.

The # in the file name is the iteration number.

2.

This file may be opened from the File menu in HyperView or HyperGraph. It automatically creates bar charts for the results contained in .#.mass file.

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_mass.mvw file The _mass.mvw file is a HyperView session file. File Creation This file is only created when modal analyses are performed. Creation of this file is controlled by the I/O option OUTPUT. File Contents This file is a HyperView session file and may be opened from the File menu in HyperView or HyperGraph. The file automatically creates plots for the results contained in the .mass file.

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_mbd.h3d file The _mbd.h3d file is a compressed binary file containing both model and result data from a multi-body dynamics analysis. It can be used to post-process results in HyperView. File Creation This file is created when a multi-body dynamics subcase is executed. File Contents The _mbd.h3d file contains node and element definitions in addition to the following results:

Result

Description

Displacement

Displacement results from static, frequency response, transient response, and multi-body dynamics analyses.

Deformation > Displacement

Deformations (deflections) of flexible bodies from multibody dynamics analyses in the body reference frame.

Deformation > Rotation

Deformation (rotations) of flexible bodies from multi-body dynamics analyses in the body reference frame.

Strain

Strain results of flexible bodies from a multi-body dynamics analysis.

Stress

Stress results of flexible bodies from a multi-body dynamics analysis.

Comments 1.

This file format is the most compressed animation output for multi-body dynamics analyses. It generates the smallest files compared to other formats.

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_mbd.log file The _mbd.log file is an ASCII format log file from a multi-body dynamics analysis. File Creation This file is created when a multi-body dynamics subcase is executed. It is a direct output file of MotionSolve. File Contents The file provides commentary on the multi-body dynamics solution progress.

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_mbd.mrf file The _mbd.mrf file is a Multi-body Results File. File Creation This file is created when a multi-body dynamics subcase is defined. The file contains time history data that can be used for 2D plotting in HyperGraph. Some data is written by default, and some needs to be requested. File Contents Data output by default.

Type

Component

Description

Rigid Body

X, Y, Z

Position

E0, E1, E2, E3

Orientation in Euler parameters.

VM, VX, VY, VZ

Magnitude and X, Y, Z components of velocity.

WM, WX, WY, WZ

Magnitude and X, Y, Z components of angular velocity.

ACCM, ACCX, ACCY, ACCZ

Magnitude and X, Y, X components of acceleration.

WDTM, WDTX, WDTY, WDTZ

Magnitude and X, Y, Z components of angular acceleration.

KE

Kinetic energy

Flex Body

All Rigid Body results Q/i, i = 1,2,…,n

Modal participation factors.

XD/i, i=1,2,…,N

Modal velocity.

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Type

Component

Description

System

KE

Kinetic energy

CPU Usage

Total CPU time used.

CPU/Sim. Time Ratio

The ration between the total CPU time used and the simulation time.

Stepsize

Actual step size used in the integration.

Integration Order

Order of the integrator used in the integration.

Data output by request. The request needs to be defined through a REQUEST I/O statement.

Type

Component

Description

Marker Displacement DM, DX, DY, DZ

Marker Velocity

Marker Acceleration

Altair Engineering

Magnitude and X, Y, Z components of displacement.

E0, E1, E2, E3

Orientation in Euler parameters.

VM, VX, VY, VZ

Magnitude and X, Y, Z components of velocity.

WM, WX, WY, WZ

Magnitude and X, Y, Z components of angular velocity.

ACCM, ACCX, ACCY, ACCZ

Magnitude and X, Y, Z components of acceleration.

WDTM, WDTX, WDTY, WDTZ

Magnitude and X, Y, Z components of angular acceleration.

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Type

Marker Force

Expressions

Component

Description

FM, FX, FY, FZ

Magnitude and X, Y, Z components of force.

TM, TX, TY, TZ

Magnitude and X, Y, Z components of torque.

F1, F2, …, F8

Vectors containing evaluated expressions.

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_mbd.mvw file The _mbd.mvw file is a HyperView session file. File Creation This file is only created when a multi-body dynamics analysis is performed. Creation of this file is controlled by the I/O option OUTPUT. File Contents This file is a HyperView session file and may be opened from the File menu in HyperView or HyperGraph. The file automatically creates plots for each of the results contained in the files: _s#_a.mbd, _s#_d.mbd, and _s#_v.mbd.

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_mbd.xml file The _mbd.xml file is a MotionSolve XML file from a multi-body dynamics analysis. File Creation This file is created when a multi-body dynamics subcase is executed. File Contents The file format is documented in the MotionSolve manual. The purpose is the communication between the OptiStruct core and the integrated MotionSolve. This file, together with the .h3d files, forms a full representation of the multi-body dynamics model which can be run separately in MotionSolve.

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_menu.html file The _menu.html file is a HyperText Markup Language file. File Creation This file is output when the H3D FORMAT is chosen. File Contents This file facilitates the selection of the appropriate .h3d file, for the HyperView Player browser plug-in in the top frame of the _frames.html file, based on chosen results. Comments 1.

This file serves no purpose on its own.

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_modal.#.mvw file The _modal.#.mvw file is a HyperView session file. File Creation This file is only created for frequency response and transient analyses. Creation of this file is controlled by the I/O option OUTPUT (with the HGMODFAC keyword). File Contents This file is a HyperView session file and may be opened from the File menu in HyperView or HyperGraph3D. The file contains HyperGraph3D plots of modal participation factors. The plots display the mode number on the x-axis, the frequency (for frequency response analyses) or time (for transient analyses) on the y-axis, and the modal participation factor on the z-axis. In HyperGraph3D, it is possible to define cross-sections to generate 2D plots of either: Modal participation factor vs. frequency or time for a given mode number Modal participation factor vs. mode number at a given frequency or time For frequency response analyses, plots are generated for the real part, the imaginary part and the magnitude of the participation factors. Magnitude plot is visible by default, while real and imaginary plots are hidden by default. Comments 1.

The # in the file name is the iteration number.

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_modal.mvw file The _modal.mvw file is a HyperView session file. File Creation This file is only created for frequency response and transient analyses. Creation of this file is controlled by the I/O option OUTPUT (with the HGMODFAC keyword). File Contents This file is a HyperView session file and may be opened from the File menu in HyperView or HyperGraph3D. The file contains HyperGraph3D plots of modal participation factors. The plots display the mode number on the x-axis, the frequency (for frequency response analyses) or time (for transient analyses) on the y-axis, and the modal participation factor on the z-axis. In HyperGraph3D, it is possible to define cross-sections to generate 2D plots of either: Modal participation factor vs. frequency or time for a given mode number Modal participation factor vs. mode number at a given frequency or time For frequency response analyses, plots are generated for the real part, the imaginary part and the magnitude of the participation factors. Magnitude plot is visible by default, while real and imaginary plots are hidden by default. Comments 1.

This file is generated for an analysis-only run; the _modal.#.mvw is generated for optimization runs where # is the iteration number.

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_rand.mvw file The _rand.mvw file is a HyperView session file. File Creation This file is only created when random response analysis is performed. This file is only created if XYPLOT is defined in random response. File Contents This file is a HyperView session file and may be opened from the File menu in HyperView or HyperGraph. The file automatically creates plots for each of the results contained in .rand files.

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_s#.h3d file The _s#.h3d file is a compressed binary file, containing both model and result data. It can be used to post-process results in HyperView or using the HyperView Player. File Creation The _s#.h3d file is created when the H3D format is chosen (See documentation for the I/O option FORMAT), and an optimization is performed containing a linear static subcase. A similar file is created for each static subcase. File Contents The _s#.h3d file contains node and element definitions in addition to the following results:

Result

Description

Displacement

Displacement results from linear static analysis. Output is controlled by the I/O option DISPLACEMENT.

Element strain energy

Element strain energy results from linear static analysis. Output is controlled by the I/O option ESE.

Stress

Stress results from linear static analysis. Output is controlled by the I/O option STRESS (or ELSTRESS).

Density

Density results from topology optimization. Output is controlled by the I/O option DENSITY.

Shape

Shape results from topography, shape, and free shape optimization. Output is controlled by the I/O option SHAPE.

Comments 1.

The # in the file name is the user-defined subcase ID.

2.

The I/O option RESULTS controls the frequency of output for analytical results during an optimization.

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_s#_a.#.frf file The _s#_a.#.frf file is an OptiStruct ASCII format results file. File Creation This file is only created for frequency response optimization. Output is controlled by the I/O option ACCELERATION and OUTPUT,HGFREQ. File Contents This file contains the acceleration results from frequency response optimization. File Format If the real and imaginary format was selected on the ACCELERATION card, the file starts with the following header: Frequency "REA | X Trans"IMA | X Trans"REA | Y Trans"IMA | Y Trans"REA | Z Trans"IMA | Z Trans If the phase and magnitude format was selected on the DISPLACEMENT card, the file starts with the following header: Frequency"PHA | X Trans"MAG | X Trans"PHA | Y Trans"MAG | Y Trans"PHA | Z Trans"MAG | Z Trans In either case, the results are grouped by node with results for different nodes separated by a blank line. The format of each line after the header is as follows: Frequency

X-rl/ph

X-im/mag

Y-rl/ph

Y-im/mag

Z-rl/ph

Z-im/mag

where: Frequency

is the frequency at which results are calculated.

X-rl/ph

is either the real component in the x-direction or the phase angle in the x-direction component.

X-im/mag

is either the imaginary component in the x-direction or the magnitude in the x-direction component.

Y-rl/ph

is either the real component in the y-direction or the phase angle in the y-direction component.

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Y-im/mag

is either the imaginary component in the y-direction or the magnitude in the y-direction component.

Z-rl/ph

is either the real component in the z-direction or the phase angle in the z-direction component.

Z-im/mag

is either the imaginary component in the z-direction or the magnitude in the z-direction component.

Comments 1.

The first # in the file name is the user-defined subcase ID.

2.

The second # in the file name is the iteration number.

3.

The_freq.#.mvw HyperView script file automatically creates plots for the results contained in this file.

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_s#_a.frf file The _s#_a.frf file is an OptiStruct ASCII format results file. File Creation This file is only created for frequency response subcases. Creation of this file is controlled by the I/O option OUTPUT. File Contents

Result

Description

Acceleration

Acceleration results from frequency response analyses. Output is controlled by the I/O option ACCELERATION.

File Format If the real and imaginary format was selected on the ACCELERATION card, the file starts with the following header: Frequency"REA | X Trans"IMA | X Trans"REA | Y Trans"IMA | Y Trans"REA | Z Trans"IMA | Z Trans

If the phase and magnitude format was selected on the ACCELERATION card, the file starts with the following header: Frequency"PHA | X Trans"MAG | X Trans"PHA | Y Trans"MAG | Y Trans"PHA | Z Trans"MAG | Z Trans In either case the results are grouped by node with results for different nodes separated by a blank line. The format of each line after the header is as follows: Frequency

X-rl/ph

X-im/mag

Y-rl/ph

Y-im/mag

Z-rl/ph

Z-im/mag

where: Frequency

is the frequency at which results are calculated.

X-rl/ph

is either the real component in the x-direction or the phase angle

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in the x-direction component. X-im/mag

is either the imaginary component in the x-direction or the magnitude in the x-direction component.

Y-rl/ph

is either the real component in the y-direction or the phase angle in the y-direction component.

Y-im/mag

is either the imaginary component in the y-direction or the magnitude in the y-direction component.

Z-rl/ph

is either the real component in the z-direction or the phase angle in the z-direction component.

Z-im/mag

is either the imaginary component in the z-direction or the magnitude in the z-direction component.

Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _freq.mvw HyperView script file automatically creates plots for the results contained in this file.

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_s#_a.mbd file The _s#_a.mbd file is an OptiStruct ASCII format results file. File Creation This file is only created for Multi-Body Dynamics subcases. Creation of this file is controlled by the I/O option OUTPUT. File Contents

Result

Description

Acceleration

Acceleration results from multi-body dynamics analyses. Output is controlled by the I/O option ACCELERATION.

File Format Time"X Trans"Y Trans"Z Trans Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _mbd.mvw HyperView script file automatically creates plots for the results contained in this file.

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_s#_a.trn file The _s#_a.trn file is an OptiStruct ASCII format results file. File Creation This file is only created for transient response subcases. Creation of this file is controlled by the I/O option OUTPUT. File Contents

Result

Description

Acceleration

Acceleration results from frequency response analyses. Output is controlled by the I/O option ACCELERATION.

File Format Time"X Trans"Y Trans"Z Trans

Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _tran.mvw HyperView script file automatically creates plots for the results contained in this file.

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_s#_d.#.frf file The _s#_d.#.frf file is an OptiStruct ASCII format results file. File Creation This file is only created for frequency response optimization. Output is controlled by the I/O option DISPLACEMENT and OUTPUT,HGFREQ. File Contents This file contains the displacement results from frequency response optimization. File Format If the real and imaginary format was selected on the DISPLACEMENT card, the file starts with the following header: Frequency"REA | X Trans"IMA | X Trans"REA | Y Trans"IMA | Y Trans"REA | Z Trans"IMA | Z Trans If the phase and magnitude format was selected on the DISPLACEMENT card, the file starts with the following header: Frequency"PHA | X Trans"MAG | X Trans"PHA | Y Trans"MAG | Y Trans"PHA | Z Trans"MAG | Z Trans In either case, the results are grouped by node with results for different nodes separated by a blank line. The format of each line after the header is as follows: Frequency

X-rl/ph

X-im/mag

Y-rl/ph

Y-im/mag

Z-rl/ph

Z-im/mag

where: Frequency

is the frequency at which results are calculated.

X-rl/ph

is either the real component in the x-direction or the phase angle in the x-direction component.

X-im/mag

is either the imaginary component in the x-direction or the magnitude in the x-direction component.

Y-rl/ph

is either the real component in the y-direction or the phase angle in the y-direction component.

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Y-im/mag

is either the imaginary component in the y-direction or the magnitude in the y-direction component.

Z-rl/ph

is either the real component in the z-direction or the phase angle in the z-direction component.

Z-im/mag

is either the imaginary component in the z-direction or the magnitude in the z-direction component.

Comments 1.

The first # in the file name is the user-defined subcase ID.

2.

The second # in the file name is the iteration number.

3.

The _freq.#.mvw HyperView script file automatically creates plots for the results contained in this file.

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_s#_d.frf file The _s#_d.frf file is an OptiStruct ASCII format results file. File Creation This file is only created for frequency response subcases. Creation of this file is controlled by the I/O option OUTPUT. File Contents

Result

Description

Displacement

Displacement results from frequency response analyses. Output is controlled by the I/O option DISPLACEMENT.

File Format If the real and imaginary format was selected on the DISPLACEMENT card, the file starts with the following header: Frequency"REA | X Trans"IMA | X Trans"REA | Y Trans"IMA | Y Trans"REA | Z Trans"IMA | Z Trans

If the phase and magnitude format was selected on the DISPLACEMENT card, the file starts with the following header: Frequency"PHA | X Trans"MAG | X Trans"PHA | Y Trans"MAG | Y Trans"PHA | Z Trans"MAG | Z Trans In either case, the results are grouped by node with results for different nodes separated by a blank line. The format of each line after the header is as follows: Frequency

X-rl/ph

X-im/mag

Y-rl/ph

Y-im/mag

Z-rl/ph

Z-im/mag

where: Frequency

is the frequency at which results are calculated.

X-rl/ph

is either the real component in the x-direction or the phase angle

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in the x-direction component. X-im/mag

is either the imaginary component in the x-direction or the magnitude in the x-direction component.

Y-rl/ph

is either the real component in the y-direction or the phase angle in the y-direction component.

Y-im/mag

is either the imaginary component in the y-direction or the magnitude in the y-direction component.

Z-rl/ph

is either the real component in the z-direction or the phase angle in the z-direction component.

Z-im/mag

is either the imaginary component in the z-direction or the magnitude in the z-direction component.

Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _freq.mvw HyperView script file automatically creates plots for the results contained in this file.

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_s#_d.mbd file The _s#_d.mbd file is an OptiStruct ASCII format results file. File Creation This file is only created for Multi-Body Dynamics subcases. Creation of this file is controlled by the I/O option OUTPUT. File Contents

Result

Description

Displacement

Displacement results from multi-body dynamics analyses. Output is controlled by the I/O option DISPLACEMENT.

File Format Time"X Trans"Y Trans"Z Trans Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _mbd.mvw HyperView script file automatically creates plots for the results contained in this file.

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_s#_d.trn file The _s#_d.trn file is an OptiStruct ASCII format results file. File Creation This file is only created for transient response subcases. Creation of this file is controlled by the I/O option OUTPUT. File Contents

Result

Description

Displacement

Displacement results from frequency response analyses. Output is controlled by the I/O option DISPLACEMENT.

File Format Time"X Trans"Y Trans"Z Trans

Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _tran.mvw HyperView script file automatically creates plots for the results contained in this file.

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OptiStruct 13.0 Reference Guide 2333 Proprietary Information of Altair Engineering

_s#_v.#.frf file The _s#_v.#.frf file is an OptiStruct ASCII format results file. File Creation This file is only created for frequency response optimization. Output is controlled by the I/O option VELOCITY and OUTPUT,HGFREQ. File Contents This file contains the velocity results from frequency response optimization. File Format If the real and imaginary format was selected on the VELOCITY card, the file starts with the following header: Frequency "REA | X Trans"IMA | X Trans"REA | Y Trans"IMA | Y Trans"REA | Z Trans"IMA | Z Trans If the phase and magnitude format was selected on the DISPLACEMENT card, the file starts with the following header: Frequency"PHA | X Trans"MAG | X Trans"PHA | Y Trans"MAG | Y Trans"PHA | Z Trans"MAG | Z Trans In either case, the results are grouped by node with results for different nodes separated by a blank line. The format of each line after the header is as follows: Frequency

X-rl/ph

X-im/mag

Y-rl/ph

Y-im/mag

Z-rl/ph

Z-im/mag

where: Frequency

is the frequency at which results are calculated.

X-rl/ph

is either the real component in the x-direction or the phase angle in the x-direction component.

X-im/mag

is either the imaginary component in the x-direction or the magnitude in the x-direction component.

Y-rl/ph

is either the real component in the y-direction or the phase angle in the y-direction component.

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Y-im/mag

is either the imaginary component in the y-direction or the magnitude in the y-direction component.

Z-rl/ph

is either the real component in the z-direction or the phase angle in the z-direction component.

Z-im/mag

is either the imaginary component in the z-direction or the magnitude in the z-direction component.

Comments 1.

The first # in the file name is the user-defined subcase ID.

2.

The second # in the file name is the iteration number.

3.

The _freq.#.mvw HyperView script file automatically creates plots for the results contained in this file.

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OptiStruct 13.0 Reference Guide 2335 Proprietary Information of Altair Engineering

_s#_v.frf file The _s#_v.frf file is an OptiStruct ASCII format results file. File Creation This file is only created for frequency response subcases. Creation of this file is controlled by the I/O option OUTPUT. File Contents

Result

Description

Velocity

Velocity results from frequency response analyses. Output is controlled by the I/O option VELOCITY.

File Format If the real and imaginary format was selected on the VELOCITY card, the file starts with the following header: Frequency"REA | X Trans"IMA | X Trans"REA | Y Trans"IMA | Y Trans"REA | Z Trans"IMA | Z Trans If the phase and magnitude format was selected on the VELOCITY card, the file starts with the following header: Frequency"PHA | X Trans"MAG | X Trans"PHA | Y Trans"MAG | Y Trans"PHA | Z Trans"MAG | Z Trans In either case, the results are grouped by node with results for different nodes separated by a blank line. The format of each line after the header is as follows: Frequency

X-rl/ph

X-im/mag

Y-rl/ph

Y-im/mag

Z-rl/ph

Z-im/mag

where: Frequency

is the frequency at which results are calculated.

X-rl/ph

is either the real component in the x-direction or the phase angle in the x-direction component.

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X-im/mag

is either the imaginary component in the x-direction or the magnitude in the x-direction component.

Y-rl/ph

is either the real component in the y-direction or the phase angle in the y-direction component.

Y-im/mag

is either the imaginary component in the y-direction or the magnitude in the y-direction component.

Z-rl/ph

is either the real component in the z-direction or the phase angle in the z-direction component.

Z-im/mag

is either the imaginary component in the z-direction or the magnitude in the z-direction component.

Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _freq.mvw HyperView script file automatically creates plots for the results contained in this file.

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OptiStruct 13.0 Reference Guide 2337 Proprietary Information of Altair Engineering

_s#_v.mbd file The _s#_v.mbd file is an OptiStruct ASCII format results file. File Creation This file is only created for multi-body dynamics subcases. Creation of this file is controlled by the I/O option OUTPUT. File Contents

Result

Description

Velocity

Velocity results from multi-body dynamics analyses. Output is controlled by the I/O option VELOCITY.

File Format Time"X Trans"Y Trans"Z Trans Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _mbd.mvw HyperView script file automatically creates plots for the results contained in this file.

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Altair Engineering

_s#_v.trn file The _s#_v.trn file is an OptiStruct ASCII format results file. File Creation This file is only created for transient response subcases. Creation of this file is controlled by the I/O option OUTPUT. File Contents

Result

Description

Velocity

Velocity results from frequency response analyses. Output is controlled by the I/O option VELOCITY.

File Format Time"X Trans"Y Trans"Z Trans

Comments 1.

The # in the file name is the user-defined subcase ID from which these results are obtained.

2.

The _tran.mvw HyperView script file automatically creates plots for the results contained in this file.

Altair Engineering

OptiStruct 13.0 Reference Guide 2339 Proprietary Information of Altair Engineering

_sens.#.mvw file The _sens.#.mvw file is a HyperView session file. File Creation This file is created when an optimization is performed. Creation of this file is controlled by the I/O option OUTPUT. File Contents This file is a HyperView session file and may be opened from the File menu in HyperView or HyperGraph. The file automatically creates a histogram for each of the results contained in the .#.sens file. The plots are grouped so that design variable sensitivities for different responses are given on separate pages. Comments 1.

The # in the file name is the iteration number.

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Altair Engineering

_shuffling.#.fem file The _shuffling.#.fem file is an ASCII format file. File Creation This file is created when OUTPUT, SZTOSH (sizing to shuffling) is requested during the plybased sizing optimization phase. File Contents This file is a ply-based stacking optimization input deck. It contains the updated PLY and STACK cards describing the stacking model, as well as a DSHUFFLE card defining shuffling design variables. Comments 1.

The # in the file name is the number of the last iteration.

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OptiStruct 13.0 Reference Guide 2341 Proprietary Information of Altair Engineering

_sizing.#.fem file The _sizing.#.fem file is an ASCII format file. File Creation This file is created when OUTPUT, FSTOSZ (free-sizing to sizing) is requested during the freesizing optimization phase. File Contents This file is a ply-based sizing optimization input deck. It contains PCOMPP, STACK, PLY, and SET cards describing the ply-based composite model, as well as DCOMP, DESVAR, and DVPREL cards defining the optimization data. Comments 1.

The # in the file name is the number of the last iteration.

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_topol.h3d file The _topol.h3d file is a compressed binary file containing both model and result data. It can be used to post-process topology (density) sensitivity in HyperView. File Creation This file is created when an optimization is performed. Creation of this file is controlled by the I/O option OUTPUT. File Contents The _topol.h3d file contains node and element definitions in addition to the following results:

Result

Description

Sensitivity Sensitivity of response vs. element density from topology optimization. Output is controlled by the I/O option OUTPUT.

Comments 1.

The # in the file name is the iteration number.

Altair Engineering

OptiStruct 13.0 Reference Guide 2343 Proprietary Information of Altair Engineering

_tran.mvw file The _tran.mvw file is a HyperView session file. File Creation This file is only created when a transient response analysis is performed. Creation of this file is controlled by the I/O option OUTPUT. File Contents This file is a HyperView session file and may be opened from the File menu in HyperView or HyperGraph. The file automatically creates plots for each of the results contained in the files _s#_a.trn, _s#_d.trn, and _s#_v.trn.

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.h3d file The .h3d file is a compressed binary file from a multi-body dynamics analysis that uses flexible bodies defined through a PFBODY bulk data entry. File Creation This file is created when a multi-body dynamics subcase is executed. One file for each PFBODY entry is generated. BODY_NAME is taken directly from PFBODY, BODY_NAME. If no BODY_NAME is given, the default is OUTFILE_body_.h3d. By default, the flexible body is only generated once; and if a file already exists in the execution directory, the flexible body generation is not repeated. The default can be changed by the parameter PARAM, FLEXH3D. File Contents This file contains the modal representation of the flexible body for direct use in the multi-body dynamics solution sequence or in MotionSolve. It is generated using a Component Mode Synthesis. Each flexible body is written to a separate file.

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OptiStruct 13.0 Reference Guide 2345 Proprietary Information of Altair Engineering

Results Output by OptiStruct The tables in this section summarize the results output for different analysis types. They show the formats available for each result and the I/O option entry that controls the output of the result. The columns in the tables represent the major output streams: H3D

– Hyper3D format (.h3d file)

HM

– HyperMesh format (.res file)

OP2

– Nastran Output2 format (.op2 file)

PCH

– Nastran Punch format (.pch file)

OPT

– OptiStruct ASCII format (multiple files)

PAT

– Patran and Alternative-Patran formats (multiple files)

H3D (MBD)

– Hyper3D format for body results (_mbd.h3d)

MRF

– Multi-body results file (_mbd.mrf)

Results for Linear Static Analysis and Nonlinear Quasi-Static Analysis

H3D

HM

OP2

PCH

OPT

PAT

Nodal Displacements

Controlling I/O Option DISPLACEMENT

Element Strain Energy

ESE

Element Stresses *

STRESS

Element Strains *

STRAIN

Ply Stresses

CSTRESS

Composite Failure Indices

CSTRESS

Ply Strains

CSTRAIN

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H3D

HM

OP2

PCH

OPT

PAT

Controlling I/O Option

Element Forces

FORCE

Grid Point Stresses

GPSTRESS

SPC Forces

SPCFORCE

MPC Forces

MPCFORCE

Grid Point Forces

GPFORCE

Applied Loads

OLOAD

Results for Linear Steady-state Heat Transfer Analysis H3D

OP2

PCH

Controlling I/O Option

Nodal Temperatures

THERMAL

Element Fluxes and Gradients

FLUX

Results for Linear Transient Heat Transfer Analysis H3D Nodal Temperatures

Altair Engineering

OP2

PCH

Controlling I/O Option THERMAL

OptiStruct 13.0 Reference Guide 2347 Proprietary Information of Altair Engineering

Results for Normal Modes Analysis

H3D

HM

OP2

PCH

OPT

PAT

Eigenvectors

Controlling I/O Option DISPLACEMENT

Element Kinetic Energy

EKE

Element Strain Energy

ESE

Grid Point Energy

GPKE

Grid Point Stress

GPSTRESS

Element Stresses *

STRESS

SPC Forces

SPCFORCE

MPC Forces

MPCFORCE

Grid Point Forces

GPFORCE

Nodal Pressures (Fluid)

PRESSURE

Ply Stresses

CSTRESS

Ply Strains

CSTRAIN

Results for Complex Eigenvalue Analysis

H3D

OP2

Eigenvectors

PCH

Controlling I/O Option DISPLACEMENT

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Results for Linear Buckling Analysis

H3D

HM

OP2

PCH

OPT

Eigenvectors

Controlling I/O Option DISPLACEMENT

Results for Frequency Response Analysis

H3D HM OP2 PCH OPT

XYPUNCH

Nodal Displacements

Controlling I/O Option DISPLACEMENT

Modal Participation Displacements

SDISPLACEMENT

Element Energy Loss Per Cycle

EDE

Element Kinetic Energy

EKE

Element Strain Energy

ESE

Nodal Velocities

VELOCITY

Modal Participation Velocities

SVELOCITY

Nodal Accelerations

ACCELERATION

Modal Participation Accelerations

SACCELERATION

Element Stresses *

STRESS

Element Strains *

STRAIN

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OptiStruct 13.0 Reference Guide 2349 Proprietary Information of Altair Engineering

H3D HM OP2 PCH OPT

Controlling I/O Option

XYPUNCH

Element Forces

FORCE

SPC Forces

SPCFORCE

MPC Forces

MPCFORCE

Grid Point Forces

GPFORCE

Power Flow Field

POWERFLOW

Ply Stresses

CSTRESS

Ply Strains

CSTRAIN

Sound Power

SPOWER

Sound Intensity

SINTENS

Sound Pressure Level

SPL

Applied Load Vectors

OLOAD

Results for Coupled Frequency Response Analysis of Fluid-structural Models (Acoustic Analysis) H3D OP2 PCH Nodal Displacements

Controlling I/O Option DISPLACEMENT

Modal Participation Displacements

SDISPLACEMENT

Nodal Velocities

VELOCITY

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H3D OP2 PCH Modal Participation Velocities

Controlling I/O Option SVELOCITY

Nodal Accelerations

ACCELERATION

Modal Participation Accelerations

SACCELERATION

Nodal Pressures (Fluid)

PRESSURE

Element Stresses *

STRESS

Element Strains *

STRAIN

Element Forces

FORCE

SPC Forces

SPCFORCE

MPC Forces

MPCFORCE

Grid Point Forces

GPFORCE

Power Flow Field

POWERFLOW

Ply Stress

CSTRESS

Ply Strain

CSTRAIN

Results for Transient Analysis H3D

Nodal Displacements

Altair Engineering

HM

OP2 PCH OPTI

Controlling I/O Option DISPLACEMENT

OptiStruct 13.0 Reference Guide 2351 Proprietary Information of Altair Engineering

H3D

HM

OP2 PCH OPTI

Modal Participation Displacements

Controlling I/O Option SDISPLACEMENT

Nodal Velocities

VELOCITY

Modal Participation Velocities

SVELOCITY

Nodal Accelerations

ACCELERATION

Modal Participation Accelerations

SACCELERATION

Element Stresses *

STRESS

Element Strains *

STRAIN

Element Forces

FORCE

MPC Forces

MPCFORCE

Ply Stresses

CSTRESS

Ply Strains

CSTRAIN

Composite Failure Indices

CSTRESS

Applied Load Vectors

OLOAD

Results for Random Response Analysis (PSDF Request)

XYPUNCH

XYPLOT PUNCH (HyperGraph)

OP2

H3D

DISP / VELO / ACCE

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XYPUNCH

XYPLOT PUNCH (HyperGraph)

OP2

H3D

Shell Stress Shell Strain Solid Stress Solid Strain CBUSH Force CELAS / CDAMP / CVISC Forces

Results for Random Response Analysis OP2 PCH

H3D

Controlling I/O Option

Displacement PSD and RMS

DISP, XYPEAK, XYPLOT, XYPUNCH

Velocity PSD and RMS

VELO, XYPEAK, XYPLOT, XYPUNCH

Acceleration PSD and RMS

ACCEL, XYPEAK, XYPLOT, XYPUNCH

PSD Element Force and RMS

FORCE, XYPEAK, XYPLOT, XYPUNCH

PSD Element Stress

STRESS, XYPEAK, XYPLOT, XYPUNCH

PSD Element Strain

STRAIN, XYPEAK, XYPLOT, XYPUNCH

RMS Element Stress

STRESS

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OptiStruct 13.0 Reference Guide 2353 Proprietary Information of Altair Engineering

STRAIN

RMS Element Strain

Results for Multi-body Dynamics Analysis H3D

HM

OP2

H3D (MBD)

MRF

Nodal Displacements

Controlling I/O Option DISPLACEMENT

Nodal Velocities

VELOCITY

Nodal Accelerations

ACCELERATION

Element Stresses *

STRESS

Element Strains *

STRAIN

Body time history System time history Marker time history

REQUEST

Results for Fatigue Analysis H3D

Controlling I/O Option

Element Life

LIFE

Element Damage

DAMAGE

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Results for Geometric Nonlinear Analysis (ANALYSIS=NLGEOM, IMPDYN or EXPDYN) Controlling I/O Option

Controlling I/O Option (Block Format)

Nodal Displacements

DISPLACEMENT

/ANIM/VECT/DISP /ANIM/VECT/DROT

Nodal Velocities

VELOCITY

/ANIM/VECT/VEL

Nodal Accelerations

ACCELERATION

/ANIM/VECT/ACC

STRESS

/ANIM/BRICK/TENS/ STRESS /ANIM/SHELL/TENS/ STRESS/UPPER /ANIM/SHELL/TENS/ STRESS/LOWER /ANIM/BEAM/VONM /ANIM/TRUSS/SIGX

STRAIN

/ANIM/BRICK/TENS/ STRAIN /ANIM/SHELL/TENS/ STRAIN/UPPER /ANIM/SHELL/TENS/ STRAIN/LOWER

Ply Stresses

CSTRESS

/ANIM/SHELL/TENS/ STRESS/N /ANIM/SHELL/TENS/ STRESS/ALL

Ply Strains

CSTRAIN

/ANIM/SHELL/TENS/ STRAIN/ALL

Composite Failure Indices

CSTRESS

N/A

Element Forces

FORCE

/ANIM/Eltyp/FORC

Grid Point Stresses

GPSTRESS

/ANIM/GPS1/TENS /ANIM/GPS1/SHELL/

H3D OP2 PCH

Element Stresses*

Element Strains*

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OptiStruct 13.0 Reference Guide 2355 Proprietary Information of Altair Engineering

Controlling I/O Option

H3D OP2 PCH

Controlling I/O Option (Block Format) UPPER /ANIM/GPS1/SHELL/ LOWER

SPC Forces

SPCFORCE

/ANIM/VECT/FREAC /ANIM/VECT/MREAC

MPC Forces

MPCFORCE

/ANIM/VECT/FINT

Applied Loads

OLOAD

/ANIM/VECT/FEXT

Plastic Strain

STRAIN (PLASTIC)

/ANIM/ELEM/EPSP /ANIM/SHELL/EPSP/ UPPER /ANIM/SHELL/EPSP/ LOWER

Contact Force and Pressure

CONTF

/ANIM/VECT/CONT /ANIM/VECT/PCONT

Element Thinning and Thickness

THIN

/ANIM/ELEM/THIC /ANIM/SHELL/THIN

Element Energy

ENERGY

/ANIM/ELEM/ENER /ANIM/ELEM/HOURG

Optimization Results

H3D

HM

OP2

PCH

OPT

PAT

Element Density

Controlling I/O Option DENSITY

Element Thickness

THICKNESS

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H3D

HM

OP2

PCH

OPT

PAT

Controlling I/O Option

Ply Thickness

THICKNESS

% Thickness

THICKNESS

Shape

SHAPE

* The element stress and strain results written to the various output streams are not always the same. Refer to the following pages for more details on the stress results available in the different output streams: Strain Results Written in HyperView .h3d Format Strain Results Written in Nastran .op2 and .pch Formats Strain Results Written in HyperMesh .res Format Stress Results Written in HyperView .h3d Format Stress Results Written in Nastran .op2 and .pch Format Stress Results Written in HyperMesh .res Format

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OptiStruct 13.0 Reference Guide 2357 Proprietary Information of Altair Engineering

Strain Results Written in HyperView .h3d Format 1D Elements ALL, DIRECT and TENSOR options Von Mises Strain CELAS Strain CROD Axial Strain CBAR Longitudinal Strain SAC CBAR Longitudinal Strain SAD CBAR Longitudinal Strain SAE CBAR Longitudinal Strain SAF CBAR Longitudinal Strain SAMIN CBAR Longitudinal Strain SAMAX CBAR Longitudinal Strain SBC CBAR Longitudinal Strain SBD CBAR Longitudinal Strain SBE CBAR Longitudinal Strain SBF CBAR Longitudinal Strain SBMIN CBAR Longitudinal Strain SBMAX CWELD Axial Strain CWELD Maximum Strain A CWELD Minimum Strain A CWELD Maximum Strain B CWELD Minimum Strain B CWELD Maximum Shear Strain VON and PRINC options Von Mises Strain 1D Elements (CBAR/CBEAM via PBARL/PBEAML) The following strain results are output for CBAR/CBEAM elements defined via PBARL/PBEAML property entries. The Result type: HyperView is CBAR/CBEAM Strains (), where the entry is based on the selected cross-section (TYPE/NAME field) on the PBARL/PBEAML entries. The element strain results can be reviewed for each cross-section type, corresponding evaluation point, at element ends (A or B). The maximum normal/shear/von Mises strains can also be reviewed. Syntax -

CBAR/CBEAM Strains () (A/B)

Where, = BAR, BOX, BOX1, CHAN, CHAN1, CHAN2, CROSS, H, HAT, I, I1, ROD, T, T1, T2, TUBE, Z. = normal, shear, and von Mises = evaluation point of the element

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Examples -

CBAR/CBEAM Strains(BAR) Normal S1N(A) Normal S1N(B) Shear S4S(A) Shear S4S(B) von Mises S8V(A) von Mises S8V(B)

Example descriptions Normal S3N(B): normal strain at the 3rd evaluation point of the beam element (end B); Shear S6S(A): shear strain at the 6th evaluation point of the beam element (end A); von Mises S5V(B): von Mises strain at the 5th evaluation point of the beam element (end B). Review evaluation points via: DRESP1 - Static Strain Item Codes for Bar Elements using PBARL, PBEAML Properties The von Mises strains for all CBEAM/CBAR elements with PBARL/PBEAML properties at the same time can be output using the Result type: CBAR/CBEAM vonMises Strains. Syntax -

CBAR/CBEAM vonMises Strains

Where, = Von Mises

2D Elements ALL and TENSOR options Results are calculated by HyperView.

DIRECT option Von Mises Strain Maximum Principal Strain Von Mises Strain (Z1) Von Mises Strain (Z2) Von Mises Strain (mid) P1 (major) Strain (Z1) P1 (major) Strain (Z2) P1 (major) Strain (mid)

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OptiStruct 13.0 Reference Guide 2359 Proprietary Information of Altair Engineering

P3 (minor) Strain (Z1) P3 (minor) Strain (Z2) P3 (minor) Strain (mid) Normal X Strain (Z1) Normal X Strain (Z2) Normal X Strain (mid) Normal Y Strain (Z1) Normal Y Strain (Z2) Normal Y Strain (mid) Shear XY Strain (Z1) Shear XY Strain (Z2) Shear XY Strain (mid) Principal Strain Angle (Z1) Principal Strain Angle (Z2) Principal Strain Angle (mid)

VON option Von Mises Strain - This is equal to max[Von Mises Strain (Z1), Von Mises Strain (Z2)] PRINC option Von Mises Strain Maximum Principal Strain

3D Elements ALL and TENSOR options Results are calculated by HyperView.

DIRECT option Von Mises Strain Signed Von Mises Strain P1 (major) Strain (solid) P2 (mid) Strain (solid) P3 (minor) Strain (solid) Normal X Strain (solid) Normal Y Strain (solid) Normal Z Strain (solid) Shear XY Strain (solid) Shear YZ Strain (solid) Shear XZ Strain (solid) VON option Von Mises Strain PRINC option

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Von Mises Strain Maximum Principal Strain Comments 1.

In the TENSOR mode, pass tensor components to HyperView which then calculates derived results on-the-fly.

2.

For frequency response loadcases, only the TENSOR mode is available.

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OptiStruct 13.0 Reference Guide 2361 Proprietary Information of Altair Engineering

Strain Results Written in Nastran .op2 and .pch Formats Static, Transient and Multi-body Loadcases 1D elements CROD Axial Strain CELAS Strain CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM

SA1 SA2 SA3 SA4 Axial SA-maximum SA-minimum SB1 SB2 SB3 SB4 SB-maximum SB-minimum Long Strain at Point Long Strain at Point Long Strain at Point Long Strain at Point Maximum Strain1 Minimum Strain1 Long Strain at Point Long Strain at Point Long Strain at Point Long Strain at Point Maximum Strain2 Minimum Strain2

C1 D1 E1 F1

C2 D2 E2 F2

2D elements Fibre Distance (Z1) Normal XX Strain (Z1) Normal YY Strain (Z1) Shear XY Strain (Z1) Principal Strain Angle (Z1) Major Principal Strain (Z1) Minor Principal Strain (Z1) Von Mises Strain (Z1) Fibre Distance (Z2) Normal XX Strain (Z2) Normal YY Strain (Z2) Shear XY Strain (Z2)

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Principal Strain Angle (Z2) Major Principal Strain (Z2) Minor Principal Strain (Z2) Von Mises Strain (Z2) 3D elements Normal XX Strain Shear XY Strain Major Principal Strain Major Principal X Cosine Mid Principal X Cosine Minor Principal X Cosine Mean Strain Von Mises Strain Normal YY Strain Shear YZ Strain Mid Principal Strain Major Principal Y Cosine Mid Principal Y Cosine Minor Principal Y Cosine Normal ZZ Strain Shear XZ Strain Minor principal Strain Major Principal Y Cosine Mid Principal Y Cosine Minor Principal Y Cosine

Eigenvalue Loadcases 1D elements None. 2D elements Fibre Distance (Z1) Normal XX Strain (Z1) Normal YY Strain (Z1) Shear XY Strain (Z1) Principal Strain Angle Major Principal Strain Minor Principal Strain Von Mises Strain (Z1) Fibre Distance (Z2) Normal XX Strain (Z2) Normal YY Strain (Z2) Shear XY Strain (Z2) Principal Strain Angle Major Principal Strain Minor Principal Strain

Altair Engineering

(Z1) (Z1) (Z1)

(Z2) (Z2) (Z2)

OptiStruct 13.0 Reference Guide 2363 Proprietary Information of Altair Engineering

Von Mises Strain (Z2) 3D elements Normal XX Strain Shear XY Strain Major Principal Strain Major Principal X Cosine Mid Principal X Cosine Minor Principal X Cosine Mean Strain Von Mises Strain Normal YY Strain Shear YZ Strain Mid Principal Strain Major Principal Y Cosine Mid Principal Y Cosine Minor Principal Y Cosine Normal ZZ Strain Shear XZ Strain Minor principal Strain Major Principal Y Cosine Mid Principal Y Cosine Minor Principal Y Cosine

Frequency Response Loadcases 1D elements CROD Axial Strain CELAS Strain CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBEAM CBEAM CBEAM CBEAM

SA1 SA2 SA3 SA4 Axial SA-maximum SA-minimum SB1 SB2 SB3 SB4 SB-maximum SB-minimum Long Long Long Long

Strain Strain Strain Strain

at at at at

Point Point Point Point

C1 D1 E1 F1

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CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM

Maximum Strain1 Minimum Strain1 Long Strain at Point Long Strain at Point Long Strain at Point Long Strain at Point Maximum Strain2 Minimum Strain2

2D elements Fibre Distance (Z1) Normal XX Strain (real) Normal XX Strain (imag) Normal YY Strain (real) Normal YY Strain (imag) Shear XY Strain (real) Shear XY Strain (imag) Fibre Distance (Z2) Normal XX Strain (real) Normal XX Strain (imag) Normal YY Strain (real) Normal YY Strain (imag) Shear XY Strain (real) Shear XY Strain (imag) 3D elements Normal XX Strain Normal YY Strain Normal ZZ Strain Shear XY Strain Shear YZ Strain Shear XZ Strain Normal XX Strain Normal YY Strain Normal ZZ Strain Shear XY Strain Shear YZ Strain Shear XZ Strain

C2 D2 E2 F2

(Z1) (Z1) (Z1) (Z1) (Z1) (Z1) (Z2) (Z2) (Z2) (Z2) (Z2) (Z2)

(real) (real) (real) (real) (real) (real) (imag) (imag) (imag) (imag) (imag) (imag)

Comments 1.

The order above reflects the contents of the OP2 file, but post-processors such as HyperView may display results in a different manner.

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Strain Results Written in HyperMesh .res Format Static, Eigenvalue, Transient and Multi-body Loadcases ALL, DIRECT and TENSOR options Von Mises Strain Maximum Principal Strain Von Mises Strain (Z1) Von Mises Strain (Z2) Von Mises Strain (mid) P1 (major) Strain (Z1) P1 (major) Strain (Z2) P1 (major) Strain (mid) P1 (major) Strain (max) P3 (minor) Strain (Z1) P3 (minor) Strain (Z2) P3 (minor) Strain (mid) P3 (minor) Strain (min) Normal X Strain (Z1) Normal X Strain (Z2) Normal X Strain (mid) Normal Y Strain (Z1) Normal Y Strain (Z2) Normal Y Strain (mid) Shear XY Strain (Z1) Shear XY Strain (Z2) Shear XY Strain (mid) Principal Strain Angle (Z1) Principal Strain Angle (Z2) Principal Strain Angle (mid) Signed Von Mises Strain (solid) P1 (major) Strain (solid) P2 ( mid ) Strain (solid) P3 (minor) Strain (solid) Normal X Strain (solid) Normal Y Strain (solid) Normal Z Strain (solid) Shear XY Strain (solid) Shear YZ Strain (solid) Shear XZ Strain (solid) VON option Von Mises Strain PRINC option Von Mises Strain Maximum Principal Strain

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Frequency Response Loadcases Normal X Normal X Normal Y Normal Y Shear XY Shear XY Normal X Normal Y Normal Z Shear XY Shear YZ Shear XZ

Strain Strain Strain Strain Strain Strain Strain Strain Strain Strain Strain Strain

(Z1) (comp) (Z2) (comp) (Z1) (comp) (Z2) (comp) (Z1) (comp) (Z2) (comp) (solid) (comp) (solid) (comp) (solid) (comp) (solid) (comp) (solid) (comp) (solid) (comp)

Comments 1. "von Mises Strain" and "Maximum Principal Strain" apply to 1D, 2D, and 3D elements simultaneously. Other results apply to 2D or 3D elements exclusively. There are no specific results for 1D elements. 2. For frequency response loadcases, (comp) may be replaced by (real) (imag) (magn) and/or (phas), depending on the complex format request. 3. "Maximum Principal Strain" is the maximum absolute principal strain: max(abs(P1(Z1)),abs(P1(Z2)),abs(P3(Z1)),abs(P3(Z2))) max(abs(P1),abs(P2),abs(P3))

for shells. for solids.

4. "P1 (major) Strain (max)" is the maximum major principal strain: max(P1(Z1),P1(Z2)). 5. "P3 (minor) Strain (min)" is the minimum minor principal strain: min(P3(Z1),P3(Z2)). 6. "Signed von Mises Strain" is the von Mises strain with traction/compression sign: sign(P1+P2+P3) * VonMises.

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Stress Results Written in HyperView .h3d Format 1D Elements ALL, DIRECT and TENSOR options Von Mises Stress CELAS Stress CROD Axial Stress CBAR Longitudinal Stress SAC CBAR Longitudinal Stress SAD CBAR Longitudinal Stress SAE CBAR Longitudinal Stress SAF CBAR Longitudinal Stress SAMIN CBAR Longitudinal Stress SAMAX CBAR Longitudinal Stress SBC CBAR Longitudinal Stress SBD CBAR Longitudinal Stress SBE CBAR Longitudinal Stress SBF CBAR Longitudinal Stress SBMIN CBAR Longitudinal Stress SBMAX CWELD Axial Stress CWELD Maximum Stress A CWELD Minimum Stress A CWELD Maximum Stress B CWELD Minimum Stress B CWELD Maximum Shear Stress CWELD Bearing Stress VON and PRINC options Von Mises Stress 1D Elements (CBAR/CBEAM via PBARL/PBEAML) The following stress results are output for CBAR/CBEAM elements defined via PBARL/PBEAML property entries. The Result type: HyperView is CBAR/CBEAM Stresses (), where the entry is based on the selected cross-section (TYPE/NAME field) on the PBARL/PBEAML entries. The element stress results can be reviewed for each cross-section type, corresponding evaluation point, at element ends (A or B). The maximum normal/shear/von Mises stresses can also be reviewed. Syntax -

CBAR/CBEAM Stresses () (A/B)

Where, = BAR, BOX, BOX1, CHAN, CHAN1, CHAN2, CROSS, H, HAT, I, I1, ROD, T, T1, T2, TUBE, Z.

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= normal, shear, and von Mises = evaluation point of the element Examples -

CBAR/CBEAM Stresses(BAR) Normal S1N(A) Normal S1N(B) Shear S4S(A) Shear S4S(B) von Mises S8V(A) von Mises S8V(B)

Example descriptions Normal S3N(B): normal stress at the 3rd evaluation point of the beam element (end B); Shear S6S(A): shear stress at the 6th evaluation point of the beam element (end A); von Mises S5V(B): von Mises stress at the 5th evaluation point of the beam element (end B). Review evaluation points via: DRESP1 - Static Stress Item Codes for Bar Elements using PBARL, PBEAML Properties The von Mises stresses for all CBEAM/CBAR elements with PBARL/PBEAML properties at the same time can be output using the Result type: CBAR/CBEAM vonMises Stresses. Syntax -

CBAR/CBEAM vonMises Stresses

Where, = Von Mises

2D Elements ALL and TENSOR options Results are calculated by HyperView.

DIRECT option Von Mises Stress Maximum Principal Stress Von Mises Stress (Z1) Von Mises Stress (Z2)

Altair Engineering

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Von Mises Stress (mid) P1 (major) Stress (Z1) P1 (major) Stress (Z2) P1 (major) Stress (mid) P3 (minor) Stress (Z1) P3 (minor) Stress (Z2) P3 (minor) Stress (mid) Normal X Stress (Z1) Normal X Stress (Z2) Normal X Stress (mid) Normal Y Stress (Z1) Normal Y Stress (Z2) Normal Y Stress (mid) Shear XY Stress (Z1) Shear XY Stress (Z2) Shear XY Stress (mid) Principal Stress Angle (Z1) Principal Stress Angle (Z2) Principal Stress Angle (mid) VON option - This is equal to max[Von Mises Stress (Z1), Von Mises Stress (Z2)] PRINC option Von Mises Stress Maximum Principal Stress

3D Elements ALL and TENSOR options Results are calculated by HyperView.

DIRECT option Von Mises Stress Signed Von Mises Stress P1 (major) Stress (solid) P2 (mid) Stress (solid) P3 (minor) Stress (solid) Normal X Stress (solid) Normal Y Stress (solid) Normal Z Stress (solid) Shear XY Stress (solid) Shear YZ Stress (solid) Shear XZ Stress (solid) VON option Von Mises Stress

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PRINC option Von Mises Stress Maximum Principal Stress Comments 1.

In the TENSOR mode, pass tensor components to HyperView, which then calculates derived results on-the-fly.

2.

For frequency response loadcases, only the TENSOR mode is available.

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Stress Results Written in Nastran .op2 and .pch Formats Static, Transient and Multi-body Loadcases 1D elements CROD Axial Stress CELAS Stress CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM

SA1 SA2 SA3 SA4 Axial SA-maximum SA-minimum SB1 SB2 SB3 SB4 SB-maximum SB-minimum Long Stress at Point Long Stress at Point Long Stress at Point Long Stress at Point Maximum Stress1 Minimum Stress1 Long Stress at Point Long Stress at Point Long Stress at Point Long Stress at Point Maximum Stress2

C1 D1 E1 F1

C2 D2 E2 F2

CBEAM Minimum Stress2

2D elements Fibre Distance (Z1) Normal XX Stress (Z1) Normal YY Stress (Z1) Shear XY Stress (Z1) Principal Stress Angle (Z1) Major Principal Stress (Z1) Minor Principal Stress (Z1) Von Mises Stress (Z1) Fibre Distance (Z2) Normal XX Stress (Z2) Normal YY Stress (Z2)

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Shear XY Stress (Z2) Principal Stress Angle (Z2) Major Principal Stress (Z2) Minor Principal Stress (Z2) Von Mises Stress (Z2)

3D elements Normal XX Stress Shear XY Stress Major Principal Stress Major Principal X Cosine Mid Principal X Cosine Minor Principal X Cosine Mean Stress Von Mises Stress Normal YY Stress Shear YZ Stress Mid Principal Stress Major Principal Y Cosine Mid Principal Y Cosine Minor Principal Y Cosine Normal ZZ Stress Shear XZ Stress Minor principal Stress Major Principal Y Cosine Mid Principal Y Cosine Minor Principal Y Cosine

Eigenvalue Loadcases 1D elements None 2D elements Fibre Distance (Z1) Normal XX Stress (Z1) Normal YY Stress (Z1) Shear XY Stress (Z1) Principal Stress Angle Major Principal Stress Minor Principal Stress Von Mises Stress (Z1) Fibre Distance (Z2) Normal XX Stress (Z2) Normal YY Stress (Z2) Shear XY Stress (Z2) Principal Stress Angle Major Principal Stress Minor Principal Stress

Altair Engineering

(Z1) (Z1) (Z1)

(Z2) (Z2) (Z2)

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Von Mises Stress (Z2) 3D elements Normal XX Stress Shear XY Stress Major Principal Stress Major Principal X Cosine Mid Principal X Cosine Minor Principal X Cosine Mean Stress Von Mises Stress Normal YY Stress Shear YZ Stress Mid Principal Stress Major Principal Y Cosine Mid Principal Y Cosine Minor Principal Y Cosine Normal ZZ Stress Shear XZ Stress Minor principal Stress Major Principal Y Cosine Mid Principal Y Cosine Minor Principal Y Cosine

Frequency Response Loadcases 1D elements CROD Axial Stress CELAS Stress CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBAR CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM

SA1 SA2 SA3 SA4 Axial SA-maximum SA-minimum SB1 SB2 SB3 SB4 SB-maximum SB-minimum Long Stress at Point Long Stress at Point Long Stress at Point Long Stress at Point Maximum Stress1 Minimum Stress1

C1 D1 E1 F1

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CBEAM CBEAM CBEAM CBEAM CBEAM CBEAM

Long Stress at Point Long Stress at Point Long Stress at Point Long Stress at Point Maximum Stress2 Minimum Stress2

2D elements Fibre Distance (Z1) Normal XX Stress (real) Normal XX Stress (imag) Normal YY Stress (real) Normal YY Stress (imag) Shear XY Stress (real) Shear XY Stress (imag) Fibre Distance (Z2) Normal XX Stress (real) Normal XX Stress (imag) Normal YY Stress (real) Normal YY Stress (imag) Shear XY Stress (real) Shear XY Stress (imag) 3D elements Normal XX Stress Normal YY Stress Normal ZZ Stress Shear XY Stress Shear YZ Stress Shear XZ Stress Normal XX Stress Normal YY Stress Normal ZZ Stress Shear XY Stress Shear YZ Stress Shear XZ Stress

C2 D2 E2 F2

(Z1) (Z1) (Z1) (Z1) (Z1) (Z1) (Z2) (Z2) (Z2) (Z2) (Z2) (Z2)

(real) (real) (real) (real) (real) (real) (imag) (imag) (imag) (imag) (imag) (imag)

Comments 1.

The order above reflects the contents of the OP2 file, but post-processors such as HyperView may display results in a different manner.

2.

For 2D elements, results are printed at the center of the element, followed by results at each grid when corner stresses are requested.

3.

For 3D elements, results are printed at the center of the element, followed by results at each grid when corner stresses are requested. In the OP2 format, regardless of the corner stress request, results are printed at each grid by duplicating results at the center.

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Stress Results Written in HyperMesh .res Format Static, Eigenvalue, Transient and Multi-body Loadcases ALL, DIRECT and TENSOR options Von Mises Stress Maximum Principal Stress Von Mises Stress (Z1) Von Mises Stress (Z2) Von Mises Stress (mid) P1 (major) Stress (Z1) P1 (major) Stress (Z2) P1 (major) Stress (mid) P1 (major) Stress (max) P3 (minor) Stress (Z1) P3 (minor) Stress (Z2) P3 (minor) Stress (mid) P3 (minor) Stress (min) Normal X Stress (Z1) Normal X Stress (Z2) Normal X Stress (mid) Normal Y Stress (Z1) Normal Y Stress (Z2) Normal Y Stress (mid) Shear XY Stress (Z1) Shear XY Stress (Z2) Shear XY Stress (mid) Principal Stress Angle (Z1) Principal Stress Angle (Z2) Principal Stress Angle (mid) Signed Von Mises Stress (solid) P1 (major) Stress (solid) P2 ( mid ) Stress (solid) P3 (minor) Stress (solid) Normal X Stress (solid) Normal Y Stress (solid) Normal Z Stress (solid) Shear XY Stress (solid) Shear YZ Stress (solid) Shear XZ Stress (solid) VON option Von Mises Stress PRINC option Von Mises Stress Maximum Principal Stress

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Frequency response loadcases Normal X Stress (Z1) (comp) Normal X Stress (Z2) (comp) Normal Y Stress (Z1) (comp) Normal Y Stress (Z2) (comp) Shear XY Stress (Z1) (comp) Shear XY Stress (Z2) (comp) Normal X Stress (solid) (comp) Normal Y Stress (solid) (comp) Normal Z Stress (solid) (comp) Shear XY Stress (solid) (comp) Shear YZ Stress (solid) (comp) Shear XZ Stress (solid) (comp) Comments 1. "von Mises Stress" and "Maximum Principal Stress" apply to 1D, 2D, and 3D elements simultaneously. Other results apply to 2D or 3D elements exclusively. There are no specific results for 1D elements. 2. For frequency response loadcases, (comp) may be replaced by (real) (imag) (magn) and/or (phas), depending on the complex format request. 3. "Maximum Principal Stress" is the maximum absolute principal stress: max(abs(P1(Z1)),abs(P1(Z2)),abs(P3(Z1)),abs(P3(Z2))) for shells. max(abs(P1),abs(P2),abs(P3)) for solids. 4. "P1 (major) Stress (max)" is the maximum major principal stress: max(P1(Z1),P1(Z2)). 5. "P3 (minor) Stress (min)" is the minimum minor principal stress: min(P3(Z1),P3(Z2)). 6. "Signed von Mises Stress" is the von Mises stress with traction/compression sign: sign(P1+P2+P3) * VonMises.

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Legacy Data Previous (OS3.5) Input Format Setting Up Decks in OptiStruct 5.0 and higher with OptiStruct 3.5 Objectives and Constraints Previously Supported Input

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Previous (OS3.5) Input Format OptiStruct will continue to support the old input format from version 3.5. The new optimization capabilities will not be available if the old format is used for the set up of the optimization problem, that is, if matfrac, mini, maxi, ubcon or lbcon are present. This section is intended to be used for the purpose of debugging or re-running older decks. OptiStruct Version 3.5 Parameters: Checkerboard

0,1,2, or blank (default = 0, if card not in deck) (Default = 1, if blank)

Controls checkerboarding. Use 0 for no checkerboard control. Use 1 or blank for global averaging over the entire design domain. This option generally yields a large number of semidense elements around fully dense elements. To reduce the number of semi-dense elements in the solution, restart the final iteration with checkerboard control off and run for 10-20 iterations. This may reintroduce some local checkerboarding. This method is used with plate/shell and solid design elements and is highly recommended for tetra elements. Nodal densities are output to the .res file if this option is used. Use 2 for averaging at local areas identified as checkerboarded. Since averaging is only applied locally, a much smaller number of semi-dense elements are found in the final iteration compared to the global averaging method. This method applies only to plate/shell design elements. If used in models with solid design elements, checkerboard control is not applied to solid elements. OptiStruct errors out if this parameter is repeated on DOPTPRM in the bulk data section.

Discrete

default = 1.0

Discreteness parameter. Influences the tendency for elements to converge to a material density of 0 or 1. Higher values decrease the number of elements that remain between 0 and 1. Recommended bounds are 0.0 and 2.0. OptiStruct errors out if this parameter is repeated on DOPTPRM in the bulk data section.

Dcomp



Altair Engineering

Shell elements with PCOMP PID given on this card will be placed in the topology design domain. This card overrides declarations in the bulk data deck.

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Dshell

no defdef=0.0

Shell elements with PSHELL PID given in first field of DSHELL card will be placed into the topology design domain with T0 given in the second field. This card overrides declarations in the bulk data deck.

Dsolid



Solid elements with PSOLID PID given on this card will be placed into the topology design domain. This card overrides declarations in bulk data deck.

Matinit

def. = 0.9 or constraint val.

This card declares the initial material fraction. For runs with mass as the objective, default is 0.9. For runs with constrained mass, default is reset to constraint value. OptiStruct errors out if this parameter is repeated on DOPTPRM in the bulk data section.

Maxiter

default = 30 Maximum number of iterations. Sets an upper limit on the number of iterations OptiStruct can perform before completion. If maxiter = 0, baseline analysis is conducted after initializing material fractions of all design elements at the matfrac value. If check is present, it overrides maxiter = 0. If analysis is present, it overrides maxiter = 0. OptiStruct errors out if this parameter is repeated on DOPTPRM in the bulk data section.

Mindens

default = 0.01

Minimum element material density. Sets a lower limit on the amount of material that can be assigned to any design element. Extremely low values for this parameter can result in an illconditioned stiffness matrix. OptiStruct errors out if this parameter is repeated on DOPTPRM in the bulk data section.

Minmember

no default default= 2

Specifies the minimum diameter of members formed by OptiStruct. This also eliminates checkerboard results. This command is used to eliminate small members. Method is either 1 or 2. Method 2 is set as default since it achieves more discrete solutions for most examples. OptiStruct errors out if this parameter is repeated on DOPTPRM in the bulk data section.

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Mmcheck

No input

The use of this card will ensure a checkerboard free solution, although with the undesired side effect of achieving a solution that involves a large number of semi-dense elements, similar to the result of using CHECKER=1. Therefore, use this card only when it is necessary. OptiStruct errors out if this parameter is repeated on DOPTPRM in the bulk data section.

Objtol

default = 0.005 Tolerance in objective function. If the fractional change in objective function is below this quantity for two consecutive iterations, the optimization is considered converged and is stopped. OptiStruct errors out if this parameter is repeated on DOPTPRM in the bulk data section.

Smooth

default = 0.7071

Solution smoothness. Influences the step size of the optimization iterations if the optimality criteria method is used for topology optimization. Changing this parameter generally results in changes in the solution topology. Larger values of this parameter create smoother topologies for shell element models. Leave this parameter at the default value, unless a different solution topology is desired. Recommended bounds are 0.5 and 0.9.

OptiStruct Version 3.5 Subcase Information: lbcon

no defaults

Mass



Altair Engineering

Sets a lower bound constraint of value given in the first field of this card for the response given in the second field of the card. Supported responses are: volume, mass, disp, comp, freq, wcomp, wfreq, and comb. Global responses (volume, mass, wcomp, wfreq, and comb) must be located outside of all subcase declarations. Local responses (comp, freq, and disp) must be located within a subcase declaration. The third field is used for mode number declarations for freq responses or grid number declarations for disp responses. The fourth field is used for grid component declarations for disp responses. Mass of total model. If present, the matfrac parameter is not used. Input the total target

OptiStruct 13.0 Reference Guide 2381 Proprietary Information of Altair Engineering

no default

mass for the part and OptiStruct calculates the material fraction automatically. If the computed material fraction is below 0.0 or above 1.0, OptiStruct returns an error. Not available if using multiple material types in the design domain.

Matfrac

default = 0.30 range = 0.0-1.0

Material fraction. Defines the amount of material to be distributed within the design domain as a fraction of the design domain. For shell elements, design volume is equal to (T - T0) * area. For solid elements, design volume is equal to the sum of the volume of the elements designated as design space. The design volume multiplied by the material fraction is the total amount of design material available. Material fractions for all design elements in the design space are initialized to matfrac value.

maxi

Sets objective function to maximize a no default response. Supported responses are: volume, mass, disp, comp, freq, wcomp, wfreq, and comb. Global responses (volume, mass, wcomp, wfreq, and comb) must be located outside of all subcase declarations. Local responses (comp, freq, and disp) must be located within a subcase declaration. The second field is used for mode number declarations for freq responses or grid number declarations for disp responses. The fourth field is used for grid component declarations for disp responses.

mini

Sets objective function to minimize a no default response. Supported responses are: volume, mass, disp, comp, freq, wcomp, wfreq, and comb. Global responses (volume, mass, wcomp, wfreq, and comb) must be located outside of all subcase declarations. Local responses (comp, freq, and disp) must be located within a subcase declaration. The second field is used for mode number declarations for freq responses or grid number declarations for disp responses. The fourth field is used for grid component declarations for disp responses.

Primary

default= lowest mode with highest weight if eigen. Subcase no default if static. ubcon

no defaults

Altair Engineering

angles. Primary mode declaration only applies to runs without static analyses and must be placed in the subcase declaration. If the card is placed in a static subcase, only that subcase is used to determine material orientation angle - no fields are necessary.

Sets an upper bound constraint of value given in the first field of this card for the response given in the second field of the card. Supported responses are: volume, mass, disp, comp, freq, wcomp, wfreq, and comb. Global responses (volume, mass, wcomp, wfreq, and comb) must be located outside of all subcase declarations. Local responses (comp, freq, and disp) must be located within a subcase declaration. The third field is used for mode number declarations for freq responses or grid number declarations for disp responses. The fourth field is used for grid component declarations for disp responses.

OptiStruct 13.0 Reference Guide 2383 Proprietary Information of Altair Engineering

Setting Up Decks in OptiStruct 5.0 with OptiStruct 3.5 Objectives and Constraints Setting up an optimization was simpler in OptiStruct 3.5, but it was also very limited. Starting with OptiStruct 5.0, a lot more flexibility has been added to the way objectives and constraints are set up, but the problem setup is more complex. Although versions of OptiStruct (including and beyond 5.0) will execute OptiStruct 3.5 decks flawlessly, users are urged to create decks using the new optimization format. This section demonstrates how objectives and constraints in OptiStruct 3.5 (such as comp, freq, wcomp, wfreq, and comb) can be set up in OptiStruct 5.0 and higher. The new optimization capabilities of OptiStruct 5.0 and higher will not be available if the old format is used for the setup of the optimization problem (if matfrac, mini, maxi, ubcon, or lbcon are present in the setup). Minimize Compliance for Constrained Mass Fraction In OptiStruct 3.5, two cards were used to do this kind of optimization: mini, comp and ubcon, 0.3, volume. The new setup is as follows: mini, comp is replaced by DESOBJ(MIN) = 1 and ubcon, 0.3, volume is replaced by DESGLB = 101. Three cards (two DRESP1s and one DCONSTR) defining the responses and constraint values referenced in the header are added after the BEGIN BULK statement as shown below: $ DESGLB = 101 $ SUBCASE 1 LOAD = 2 SPC = 1 DESOBJ(MIN) = 1 $ BEGIN BULK $ DRESP1, 1, comp, COMP DRESP1, 100, massf, MASSFRAC DCONSTR, 101, 100, , 0.300 $ Minimize Mass for Constrained Displacement The deck setup for this problem is similar to the previous one. Since the objective is global (mass), the DESOBJ statement goes outside of the load case definition. The constraint on displacement is only active for the first load case; thus a DESSUB statement is used within that load case. $ DESOBJ(MIN) = 1 $ SUBCASE 1 LOAD = 2 SPC = 1 DESSUB = 101

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$ BEGIN BULK $ DRESP1, 1, weight, MASS $ DRESP1, 100, disp, DISP, , , 7, , 1202 DCONSTR, 101, 100, , 1.4e-6 $

Minimize Weighted Compliance for Constrained Mass OptiStruct provides the response type WCOMP, weighted DRESP1 card. In addition, you need to define the weight in the weighted compliance function. Note that both the quantities (not specific to any single load case) and thus occur before the load case declarations.

compliance, to be defined on the factors for each load case included objective and constraint are global the DESOBJ and DESGLB statements

$ DESOBJ = 50 DESGLB = 101 $ SUBCASE 1 LOAD = 2 SPC = 1 WEIGHT = 2.0 $ SUBCASE 2 LOAD = 3 SPC = 1 WEIGHT = 1.0 $ BEGIN BULK $ DRESP1, 50, wcomp, WCOMP $ DRESP1, 100, weight, MASS DCONSTR, 101, 100, , 1.560 $ Maximize Frequency for Constrained Volume The setup for this deck is similar to that for the first two decks except that, starting with OptiStruct 5.0, the volume response now refers to the actual volume (not the volume fraction). $ DESGLB = 101 $ SUBCASE 1 METHOD = 2 SPC = 1 DESOBJ(MAX) = 1 $

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BEGIN BULK $ DRESP1, 1, freq1, FREQ, , , 1 $ DRESP1, 100, vol, VOLUME DCONSTR, 101, 100, , 20000.0 $

Maximize Weighted Frequencies for Constrained Volume In OptiStruct 3.5, the weighted frequency response (wfreq), was minimized since the inverse of the eigenvalues was being summed together. This was done so that increasing the frequencies of the lower modes would have a larger effect on the objective function than increasing the frequencies of the higher modes. If the frequencies of all modes are simply added together, OptiStruct will put more effort into increasing the higher modes than the lower modes. Note that the DESOBJ statement goes above the first load case since wfreq is a global response. To duplicate the frequency weighting and summing in OptiStruct 3.5, use the following approach: $ DESGLB = 101 $ DESOBJ(MIN) = 11 SUBCASE 1 METHOD = 2 SPC = 1 MODEWEIGHT, 1, 1.0 MODEWEIGHT, 2, 1.0 $ BEGIN BULK $ DRESP1, 11, wfreq, WFREQ $ DRESP1, 100, vol, VOLUME DCONSTR, 101, 100, , 20000.0 $

Minimize Combined Compliance and Frequencies for Constrained Volume Fraction In OptiStruct 3.5, the combined reciprocal frequency and compliance response (comb) required a normalization factor in order to properly add frequency values and compliance. The equivalent setup for OptiStruct 5.0 and higher is shown below. If no NORM is given, OptiStruct will evaluate the frequencies and compliances in the initial iteration step to automatically select a NORM factor. $ DESOBJ(MIN) = 50 DESGLB = 101 $ NORM = 1000.0 $ SUBCASE 1

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LOAD = 2 SPC = 1 WEIGHT = 1.0 $ SUBCASE 2 LOAD = 3 SPC = 1 WEIGHT = 1.0 $ SUBCASE 3 METHOD = 10 SPC = 1 MODEWEIGHT, 1, 1.5 MODEWEIGHT, 2, 1.0 $ BEGIN BULK $ DRESP1, 50, comp, COMB $ DRESP1, 100, volf, VOLFRAC DCONSTR, 101, 100, , 0.300 $

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Previously Supported Input BEAD (Not Supported in 8.0 or Later Versions) MASSTOH3D (Not Supported in 8.0 or Later Versions) ROTATION (Not Supported in 8.0 or Later Versions) DOPTPRM, MINMETH (Not Supported in 8.0 or Later Versions) PARAM, PRTRENUM (Not Supported in 9.0 or Later Versions) INFILE (Not Supported in 10.0 or Later Versions) PARAM, GAPOFFST (Not Supported in 10.0 or Later Versions) SET/PSET (Not Recommended for use in 10.0 or Later Versions) DENSRES (Not Recommended for use in 10.0 or Later Versions) SHRES (Not Recommended for use in 10.0 or Later Versions) FLSPOUT (Not Supported in 11.0 or Later Versions) PARAM, INRGAP (Not Supported in 11.0 or Later Versions) MODELMPC (Not Supported in 12.0 or Later Versions) PARAM, AMLSASPC (Not Supported in 12.0 or Later Versions) UPDATE (Not Supported in 12.0 or Later Versions)

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BEAD (Not Supported in 8.0 or Later Versions) Bulk Data Entry BEAD – Topography Design Variables Description Defines parameters for the generation of topography design variables. Format (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

BEAD

BID

MW

ANG

BF

HGT

norm/ XD

YD

ZD

SKIP

FID/XF

YF

ZF

AID/XA

YA

ZA

LB

UB

TYP

SID/XS

YS

ZS

UC YC

Example (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

(9)

(10)

BEAD

1

3.0

60.0

yes

5.0

norm

both

0.0

1.0

0.0

0.0

25.0

0.0

50

1.0

0.0

0.0

3

Field

Contents

BID

PID or DID (Integer > 0; no default). This field can contain the PSHELL or PCOMP property ID of the elements or the desvar number of any set of DVGRIDs present in the deck to be optimized for topography. If field 6 contains data, OptiStruct will assume that the BEAD card references a property, otherwise it assumes that the card references a DESVAR and its corresponding DVGRIDs.

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Field

Contents

MW

Bead minimum width (Real > 0.0; no default). This parameter controls the width of the beads in the model [recommended value between 1.5 and 2.5 times the average element width]. See comment 1.

ANG

Draw angle in degrees (1.0 < Real < 89.0; no default). This parameter controls the angle of the sides of the beads [recommended value between 60 and 75 degrees]. See comment 1.

BF

Buffer zone (‘yes’ or ‘no’; default = ‘yes’). This parameter will establish a buffer zone between elements in the design domain and elements outside the design domain.

HGT

Draw height: (Real > 0.0; no default). This parameter sets the maximum height of the beads to be drawn. This field is only valid if a PID is declared in field 2.

norm/XD,YD,ZD Draw direction (‘norm’ in field 7 or Real in all three fields; default = ‘norm’). If field 7 is ‘norm’, the shape variables will be created in the normal directions of the elements. If all the fields are real, the shape variable will be created in the direction specified by the xyz vector defined by fields 7, 8, and 9. The X, Y, and Z values are in the basic coordinate system. This field is only valid if a PID is declared in field 2. SKIP

Boundary skip (‘both’, ‘bc’, ‘spc’, ‘load’, or ‘none’; default = ‘both’). This parameter tells OptiStruct to leave certain nodes out of the design domain. If ‘none’, all nodes attached to elements whose PID was specified in field 2 will be a part of the shape variables. If ‘bc’ or ‘spc’, any nodes which have SPC or SPC1 declarations are omitted from the design domain. If ‘load’, any nodes which have FORCE, FORCE1, MOMENT, MOMENT1, or SPCD declarations are omitted from the design domain. If ‘both’, nodes with either ‘spc’ or ‘load’ declarations are omitted from the design domain. This field is only valid if a PID is declared in field 2.

FID/XF,YF,ZF

Direction of first vector for variable pattern grouping (Real in all three fields or Integer in field 12; default = blank). These fields define an xyz vector which determines how grids are grouped into variables. The X, Y, and Z values are in the global coordinate system. You may put a grid ID in field 12 to define the first vector. This vector goes from the anchor point to this grid. If all fields are blank and field 20 is not blank or zero, OptiStruct gives an error.

AID/XA,YA,ZA

Variable grouping pattern anchor point (Real in all three fields or integer in field 15; default = blank). These fields define a point which

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Field

Contents determines how grids are grouped into variables. The X, Y, and Z values are in the global coordinate system. You may put a grid ID in field 15 to define the anchor point.

LB

Lower bound on variables controlling grid movement (Real < UB, default = 0.0). This sets the lower bound on grid movement equal to LB*HGT.

UB

Upper bound on variables controlling grid movement (Real > LB, default = 1.0). This sets the upper bound on grid movement equal to UB*HGT.

TYP

Type of variable grouping pattern. (Integer > 0, default = 0) Required if any symmetry or variable pattern grouping is desired. If zero or blank, anchor node, first vector, and second vector definitions are ignored. If less than 20, second vector definition is ignored.

SID/XS,YS,ZS

Direction used to determine second vector for variable pattern grouping (Real in all three fields or Integer in field 22; default = blank). These fields define an xyz vector which, when combined with the first vector, form a plane. The second vector is calculated to lie in that plane and is perpendicular to the first vector. The second vector is sometimes required to determine how grids are grouped into variables. The X, Y, and Z values are in the global coordinate system. You may put a grid ID in field 22 to define the second vector. This vector goes from the anchor point to this grid. If all fields are blank and field 20 contains a value of 20 or higher, OptiStruct gives an error.

UCYC

Number of cyclical repetitions for cyclical symmetry (Integer > 0 or blank; default = 0). This field defines the number of radial "wedges" for cyclical symmetry. The angle of each wedge is computed as 360.0 / UCYC.

Comments 1. The BEAD bulk data entry will no longer be supported for the definition of topography optimization. All definitions must be provided using the DTPG bulk data entry. HyperMesh will continue to read BEAD entries, but will convert them into DTPG entries.

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DOPTPRM, MINMETH (Not Supported in 8.0 or Later Versions) Parameter

Values

Description

MINMETH

Integer = 1,2 Default = 2

Specifies the method of minimum member size control. Method 2 is set as default since it achieves more discrete solutions for most examples.

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MASSTOH3D (Not Supported in 8.0 or Later Versions) I/O Options Entry MASSTOH3D - Output Request Description The MASSTOH3D command can be used in the I/O Options section to request the output of the mass matrix to the .h3d file. Format MASSTOH3D = option

Argument Options

Description

option

YES, ALL, blank: Mass matrix is output to .h3d file.

Default = ALL

Mass matrix is not output.

NO, NONE:

Comments 1.

Mass matrix is not output if this card is not present.

2.

This option is only for use with MotionView's MBD Flexbody utility.

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ROTATION (Not Supported in 8.0 or Later Versions) I/O Options Entry ROTATION - Output Request Description The ROTATION command can be used in the I/O Options or Subcase Information sections to request the output of rotation information for all subcases or individual subcases respectively. Format ROTATION (format, form) = option

Argument

Options

Description

format



HM:

Results are output in HyperMesh results format (.res file).

H3D:

Results are output in Hyper3D format (.h3d file).

OPTI:

Results are output in OptiStruct results format (.disp file).

PUNCH:

Results are output in Nastran punch results format (.pch file).

OUTPUT2:

Results are output in Nastran output2 format (.op2 file).

PATRAN:

Results are output in Patran format (multiple files).

APATRAN:

Results are output in Alternative Patran format (multiple files).

blank:

Results are output in all active formats for which the result is available.

Default = blank

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Argument

Options

Description

form



COMPLEX, blank: Provides a combined magnitude/ phase form of complex output to the .res file if HM output format is chosen. The REAL form of complex output is used for other formats, if they are not specifically defined. (Phase output is in degrees).

Default = COMPLEX

option

REAL, IMAG:

Provides rectangular format (real and imaginary) of complex output.

PHASE:

Provides polar format (magnitude and phase) of complex output. Phase output is in degrees.

BOTH:

Provides both polar and rectangular formats of complex output.



YES, ALL, blank: Rotations are output for all nodes.

Default = ALL

NO, NONE:

Rotations are not output.

SID:

If a set ID is given, rotations are output only for nodes listed in that set.

Comments 1. When a ROTATION command is not present, rotations are not output. 2. The form argument is only applicable for frequency response analysis. It is ignored for other analysis types. 3. The form BOTH does not apply to the .frf output files. Results are output to these files using the rectangular form of complex output when BOTH is the chosen form. 4. Multiple formats are allowed on the same entry; these should be comma separated. If no format is specified, then this output control applies to all formats defined by OUTPUT or FORMAT commands for which the result is available. See Results Output for information on which results are available in which formats.

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5. Multiple instances of this card are allowed; if instances are conflicting, the last instance dominates. 6. For optimization, the frequency of output to a given format is controlled by the I/O option OUTPUT. In previous versions of OptiStruct, a combination of the I/O options FORMAT and RESULTS were used; this method is still supported, but not recommended as it does not allow different frequencies for different formats.

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FLSPOUT (Not Supported in 11.0 or Later Versions) I/O Options and Subcase Information Entry FLSPOUT – Output Request Description The FLSPOUT command can be used in the I/O Options section to control output of modal participation factors for coupled fluid-structure models. Format FLSPOUT(argument = option, argument = option, ...)

Argument

Options

Description

FLUIDMP



Requests fluid participation calculation of fluid response on selected fluid points.

Default = NONE

GRIDFMP

ALL:

Requests that all the fluid modes extracted be used.

NONE:

Requests no participation calculation.

Requests inclusion or exclusion of specific fluid grids to be used in all the requested types of participation calculations.

No default

SID:

FEPS



Set identification number - Results are output only for fluid grids listed in the selected set.

Filter Threshold for fluid participation.

Default = 1.0e-11

ARF



Acceptance ratio for fluid participation.

Default = 1.0e-11

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Argument

Options

Description

STRUCTMP



Requests structural, load, and panel participation calculations on the selected fluid points.

Default = NONE

PANELMP

Default = ALL

ALL:

Requests that all the structural modes extracted be used.

NONE:

Requests no participation calculation.

Requests inclusion or exclusion of panel participation calculations on the selected fluid points. ALL:

SEPS



Requests that all the panels defined be included in the participation calculations on the selected fluid points.

Filter Threshold for structural participation.

Default = 1.0e-11

ARS



Acceptance ratio for structural participation.

Default = 1.0e-11

PSORT



Requests type of sort.

Default = ABSOLUTE Comments 1.

GRIDFMP is required for all FLSPOUT statements.

2.

FLUIDMP and STRUCTMP are required when PANELMP is defined.

3.

The output file name for modal participation is *.modal.

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MODELMPC (Not Supported in 12.0 or Later Versions) Subcase Information Entry MODELMPC – Description MODELMPC command can be used in the Subcase Information section while including h3d DMIG in residual runs. This card converts interior DOFs of the DMIG to exterior DOFs. Format MODELMPC = setdof Examples MODELMPC = 100 SET,100,GRIDC, +,10643,T1,10643,T2,10643,T3

Argument

Option

Description

setdof

< SID >

Interior DOF of h3d DMIG to be converted into exterior DOF. SID refers to the ID of a SET of type GRIDC.

Comments 1.

After the conversion with MODELMPC, these DOFs are part of the analysis DOFs and can be used as connection points, load DOFs, response DOFs during optimization.

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PARAM, AMLSASPC (Not Supported in 12.0 or Later Versions) Parameter AMLSASPC

Values

Description

0, 1 Default = 0

This parameter is used to indicate when to automatically constrain degrees-of-freedom with no stiffness for AMLS run. If 0, then the constraints are applied before constraint reduction. If 1, then the constraints are applied after constraint reduction.

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PARAM, GAPOFFST (Not Supported in 10.0 or Later Versions) Parameter

Values

Description

GAPOFFST

YES, NO Default = YES

If YES, frictional offset for nonlinear gap analysis is active. If NO, frictional offset for nonlinear gap analysis in inactive. For more details, refer to the PGAP description.

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PARAM, INRGAP (Not Supported in 11.0 or Later Versions) Parameter

Values

Description

INRGAP

Default = NO

PARAM, INRGAP can be used during nonlinear gap analysis to improve the performance for some models. In this method, an internal super element which includes all of the gap elements is created automatically, and the nonlinear iterations are only processed in this super element. If the degrees-of-freedom associated with gap elements make up less than 3% of the total degrees-offreedom and the gap elements are concentrated in one area of the model, this approach may be beneficial. However, a performance gain is not guaranteed.

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PARAM, PRTRENUM (Not Supported in 9.0 or Later Versions) Parameter

Values

Description

PRTRENUM

Default = YES

If YES, prints a warning message when element nodes have been renumbered, including the number of such elements. (Renumbering is applied to elements that have node sequence reversed with respect to the standard numbering as described on respective bulk data cards). If NO, no such message is printed. If LIST, the warning message is printed for every element where renumbering was necessary. The message includes the node list before and after renumbering.

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UPDATE (Not Supported in 12.0 or Later Versions) I/O Options and Subcase Information Entry UPDATE – Input Definition Description The UPDATE command controls the behavior of ASSIGN,UPDATE,. Format UPDATE option Option

Description

off

Disable update.

permissive

Allow all cards and repeat IDs.

quiet

Less output [default].

strict

Do not allow non-supported cards in update deck [default].

unique

Each ID only once.

verbose

More output including old and new values.

Example UPDATE verbose,unique Comments 1.

Choose only one option: verbose or quiet.

2.

Choose only one option: unique, strict, permissive, or off.

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INFILE (Not Supported in 10.0 or Later Versions) I/O Options Entry INFILE - File Selection Description The INFILE command is used in the I/O Options section to identify the file containing the bulk data entries. Format INFILE = option

Argument

Option

Description

option



file prefix: The path to and prefix of the .fem file containing the bulk data entries.

Default = passed in from the command line. Comments 1. This card is used in the obsolete two-file setup; the one-file or multiple-file setups are recommended (see The Input File for more information). 2. Prefixes specified on the INFILE card can be arbitrary file prefixes with optional paths appropriate to the operating system (Windows or UNIX). They may be enclosed in quotes (double or single quotes can be used), and either forward slash (/) or back slash (\) characters can be used to separate parts of the path name. The following rules are used to locate a file referenced on the INFILE card: When the argument contains the absolute path of the file (if it starts with "/" on UNIX or a drive letter, such as "D:", on Windows, for example), the file at the given location is used. When only the file prefix is given (without the path), the file has to be located in the same directory as the file containing the INFILE command. When the argument contains a relative path (../filename or sub/filename, for example), it is located in the directory relative to the file containing the INFILE command and is NOT relative to the directory in which the solver was executed, or to the directory where the main file is located. 3. The total length of information on this card is limited to 200 characters (including the card name and spaces between arguments). This data can be on a single line or span multiple continuation lines. See Guidelines for I/O Options and Subcase Information Entries for an example showing how to enter long file names on multiple lines.

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SET/PSET (Not Recommended for use in 10.0 or Later Versions) I/O Options and Subcase Information Entry SET - Set Definition PSET - Set Definition Description The SET and PSET commands can be used in the I/O Options or Subcase Information section input deck to define sets of grids, elements, properties, or frequencies. Format SET n = i1, i2, …, in

Integer sets are used for sets of grids, elements, modes, and design variables.

SET n = r1, r2, …, rn

Real value sets are used for frequencies or times.

SET n = i1, c1, i2, c2, …, in, cn

Sets of Gird/Component pairs are used for PFMODE data. Example: SET 24 = 12, T1, 15, R2, 128, T3 (alternatively 12/T1, 15/R2, 128/T3 is acceptable, see Guidelines for I/O Options and Subcase Information Entries).

PSET n = PID1, PID2, …, PIDn

Property identification numbers are used for property set definition.

Comments 1.

Every SET must have a unique identification number, n, regardless of whether the SET is defined within a subcase or in the I/O Options section. Also, a SET cannot have the same ID as a PSET or the bulk data entries SET, SET1, or SURF.

2.

From 10.0 onwards, it is recommended to use the SET bulk data entry for set definitions.

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DENSRES (Not Recommended for use in 10.0 or Later Versions) I/O Options Entry DENSRES - Output Control Description The DENSRES command can be used in the I/O Options section to control the frequency of output of design results (density, shape, or thickness). Format DENSRES = frequency

Argument Options

Description

frequency

FIRST:

Optimization results are output for the first iteration only.

LAST:

Optimization results are output for the final iteration only.

FL:

Optimization results are output for the first and last iterations only.

ALL, blank:

Optimization results are output for all iterations.

N:

Optimization results are output for the first and last iterations and every Nth iteration. If N = 5, output occurs for iterations 0, 5, 10, 15, 20, and so on, and the final iteration.

Default = ALL

Comments 1.

This output control is ignored if OUTPUT, DESIGN is present.

2.

When the DENSRES command is not present, results are output for all iterations.

3.

From 10.0 onwards, it is recommended to use the OUTPUT I/O Option entry to control this output.

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SHRES (Not Recommended for use in 10.0 or Later Versions) I/O Options Entry SHRES - Output Control Description The SHRES command can be used in the I/O Options section to control the frequency of output of the state files (.sh file and the .grid file). Format SHRES = frequency

Argument

Options

Description

frequency



FIRST:

The files are output for the first iteration only.

LAST, blank:

The files are output for the final iteration only.

FL:

The files are output for both the first and last iterations.

ALL:

The files are output for all iterations.

NONE:

The files are not output.

N:

The files are output for the first and last iterations and for every Nth iteration. If N = 5, output occurs for iterations 0, 5, 10, 15, 20, and so on, and the final iteration. All equation and combination responses are output.

Default = LAST

Comments 1.

When a SHRES command is not present, state files are output for the final iteration only.

2.

The .grid file is only output for shape, topography, and free-shape optimization.

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3.

For all .sh and .grid output files bar the last one, the files are named .sh(.grid). The last one is just named .sh(.grid).

4.

The .grid file output may also be controlled by the GRID keyword on the OUTPUT card.

5.

From 10.0 onwards, it is recommended to use the OUTPUT I/O Option entry to control this output.

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