September 11, 2022 | Author: Anonymous | Category: N/A
ACP User's Guide
ANSYS, Inc. Southpointe 2600 ANSYS Drive Canonsburg, PA 15317
[email protected] http://www.ansys.com (T ) 724-746-33 724-746-3304 04 (F) 724-514-9494
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Table of Contents 1. Getting Started ....................................................................................................................................... 1
1.1. Overview .......................................................................................................................................... 1.1.1. Introduction ............................................................................................................................ 1.1.2. Supported Supported Platforms and Functional Add-ons ........................................................................... 1.1.3. Known Limitations ................................................................................................................... 1.1.4. First Steps ................................................................................................................................
1 1 3 3 5
1.2. The ANSYSUser Product Improvement Program Program ....................................................................................... 5 1.3. Graphical Interface .................................................................................................................... 9 1.3.1. Menus ................................................................................................................................... 10 1.3.1.1. File ................................................................................................................................ 11 1.3.1.1.1. Workbench ........................................................................................................... 12 1.3.1.1.2. Stand Alone .......................................................................................................... 12 1.3.1.2.View .............................................................................................................................. 13 1.3.1.2.1. Perspectives ......................................................................................................... 13 1.3.1.2.2.View Manager ....................................................................................................... 14 1.3.1.3. Tools ............................................................................................................................. 14 1.3.1.3.1. Logger Settings .................................................................................................... 14 1.3.1.3.2. Preferences ........................................................................................................... 15 1.3.1.3.2.1. Submenus .................................................................................................... 16 1.3.1.3.3. Scene ................................................................................................................... 17 1.3.1.3.3.1. Appearance ................................................................................................. 17 1.3.1.3.3.2. Screenshot ................................................................................................... 18 1.3.1.3.3.3. Interaction ................................................................................................... 18 1.3.1.4. Units ............................................................................................................................. 18 1.3.2. Tree Tree View ............................................................................................................................... 19 1.3.3. Scene ..................................................................................................................................... 22 1.3.3.1. Scene Manipulation ....................................................................................................... 22 1.3.4. Toolbar .................................................................................................................................. 23 1.3.4.1. Updates ........................................................................................................................ 23 1.3.4.2. Edit Entities with Excel ................................................................................................... 23 1.3.4.3. Mesh Appearance .......................................................................................................... 24 1.3.4.4. Orientation Visualization ................................................................................................ 25 1.3.4.5. Fiber Directions ............................................................................................................. 26 1.3.4.6. Draping ......................................................................................................................... 1.3.4.7. Other Features ............................................................................................................... 1.3.4.8. Postprocessing .............................................................................................................. 1.3.5.View Panes ............................................................................................................................. 1.4. Implementation in Workbench ........................................................................................................ 1.4.1. Basic Workflow ....................................................................................................................... 1.4.2. ACP Component Properties .................................................................................................... 1.4.3. Supported Analysis Types ....................................................................................................... 1.4.4. Multiple Multiple Load Cases and Analyses ........................................................................................... 1.4.5. Shared Composite Definition for Different Models .................................................................. 1.4.6. Solid Modeling ....................................................................................................................... 1.4.7. Assembly ............................................................................................................................... 1.5. Migrating ACP Projects from Previous Versions ................................................................................
28 31 33 33 35 35 39 41 42 42 43 45 47
1.6. 1.6.1. StandStarting Alone Operation ................................................................................................................... 48 ACP in Windows ........................................................................................................ 49 1.6.2. Starting ACP in Linux .............................................................................................................. 49
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ACP User's Guide 1.6.3. Command Command Line Options and Batch Mode ................................................................................ 1.6.4.Workflow in Stand Alone Operation ........................................................................................ 2. Usage Reference .................................................................................................................................... 2.1. Features ......................................................................................................................................... 2.1.1. Model .................................................................................................................................... 2.1.1.1. Model Properties Properties - General ............................................................................................ 2.1.1.1.1. ACP Model ............................................................................................................ 2.1.1.1.2. Reference Surface ................................................................................................. 2.1.1.1.3. Layup Computation .............................................................................................. 2.1.1.1.4. Model Summary ................................................................................................... 2.1.1.2. Solve ............................................................................................................................. 2.1.1.3. Import/Export Import/Export of ACP Composite Definitions File ........................................................... 2.1.1.4. Import From/Export to HDF5 Composite CAE File ........................................................... 2.1.1.5. Import Import Section Data from Legacy Model ........................................................................ 2.1.1.6. Element- vs. Node-based Thicknesses ............................................................................. 2.1.2. Material Data ......................................................................................................................... 2.1.2.1. Materials ....................................................................................................................... 2.1.2.1.1. Materials Context Menu ........................................................................................ 2.1.2.1.2.TTemperature Dependent and General Variable Material Properties ......................... 2.1.2.1.2. 2.1.2.1.3. Material Properties Dialog ..................................................................................... 2.1.2.1.4.Thermal Expansion Coefficients ............................................................................. 2.1.2.1.5. Fabric Fiber Angle .................................................................................................
49 50 53 53 54 55 57 57 58 59 59 59 60 60 61 64 64 64 65 65 67 68
2.1.2.1.6. Strain Limits .......................................................................................................... 2.1.2.1.7. Stress Limits .......................................................................................................... 2.1.2.1.8. Puck Constants ..................................................................................................... 2.1.2.1.9. Puck for Woven ..................................................................................................... 2.1.2.1.10.Tsai-W 2.1.2.1.10. Tsai-Wu u Constants ............................................................................................... 2.1.2.1.11. LaRC Constants ................................................................................................... 2.1.2.2. Fabric ............................................................................................................................ 2.1.2.2.1. General ................................................................................................................. 2.1.2.2.2. Polar Properties .................................................................................................... 2.1.2.2.3. Fabric Solid Model Options ................................................................................... 2.1.2.2.4. Draping ............................................................................................................... 2.1.2.3. Stackup ......................................................................................................................... 2.1.2.3.1.TTop-Down or Bottom-Up Sequence ....................................................................... 2.1.2.3.1.
69 70 71 72 73 73 74 74 74 75 76 77 78
2.1.2.3.2. Symmetries .......................................................................................................... 2.1.2.3.3. Analysis ................................................................................................................ 2.1.2.3.4. Stackup Stackup Solid Model Options ................................................................................ 2.1.2.3.5. Draping Options ................................................................................................... 2.1.2.4. Sublaminates ................................................................................................................ 2.1.3. Element Element and Edge Sets ........................................................................................................... 2.1.3.1. Element Sets ................................................................................................................. 2.1.3.1.1. Context Menu ....................................................................................................... 2.1.3.2. Edge Sets ...................................................................................................................... 2.1.4. Geometry .............................................................................................................................. 2.1.4.1. CAD Geometries ............................................................................................................ 2.1.4.1.1. Direct Import ........................................................................................................ 2.1.4.1.2.Workbench Geometry Link .................................................................................... Link .................................................................................... 2.1.4.2.Virtual Geometries ......................................................................................................... 2.1.5. Rosettes ................................................................................................................................. 2.1.5.1. Rosette Definition ..........................................................................................................
78 80 82 82 82 83 84 84 85 86 86 87 88 89 90 94
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ACP User's Guide 2.1.6. Look-Up Tables ....................................................................................................................... 94 2.1.6.1. 3D Look-Up Table With The Excel Link ............................................................................ Link ............................................................................ 95 2.1.6.2. 1D Look-Up Table with .CSV Files .................................................................................... 97 2.1.6.3. Look-Up Table with a Python Script .............................................................................. 100 2.1.6.4. 1-D Look-Up Table ....................................................................................................... 100 2.1.6.5. 3-D Look-Up Table ....................................................................................................... 101 2.1.6.6. Look-Up Table Column Properties ................................................................................ 102 2.1.7. Selection Rules ..................................................................................................................... 103 2.1.7.1. Basic Selection Rules .................................................................................................... 104 2.1.7.2. Tube Tube Selection Rule ..................................................................................................... 106 2.1.7.3. Cut-off Cut-off Selection Rules ................................................................................................. 106 2.1.7.3.1. Geometry Cut-off Selection Rule ......................................................................... 107 2.1.7.3.2.Tap 2.1.7.3.2. Taper er Cut-off Selection Rule ................................................................................ 109 2.1.7.3.3. Example Cut-off .................................................................................................. Cut-off .................................................................................................. 110 2.1.7.4. Geometrical Geometrical Selection Rule .......................................................................................... 111 2.1.7.5.Variable Offset Selection Rule ....................................................................................... 114 2.1.7.6. Boolean Selection Rules ............................................................................................... 117 2.1.8. Oriented Selection Sets (OSS) ............................................................................................... 118 2.1.8.1. Reference Direction ..................................................................................................... 120 2.1.8.2. Selection Rules ............................................................................................................ 122 2.1.8.3. Draping ....................................................................................................................... 123 2.1.9. Modeling Groups ................................................................................................................. 124 2.1.9.1. Modeling Group Structure ........................................................................................... 2.1.9.2. Modeling Group Tree Object Context Menu ................................................................. 2.1.9.3. Individual Individual Modeling Group Context Menu .................................................................... 2.1.9.4. Modeling Ply Properties ............................................................................................... 2.1.9.4.1. Draping .............................................................................................................. 2.1.9.4.2. Selection Rules .................................................................................................... 2.1.9.4.3.Thickness ............................................................................................................ 2.1.9.4.4. Modeling Ply Context Menu ................................................................................ 2.1.9.5. Interface Layer Properties ............................................................................................ 2.1.9.6. Butt Joint Sequence ..................................................................................................... 2.1.9.6.1. Butt Joint Sequence S equence Notes and Limitations .......................................................... 2.1.9.7. Production Ply ............................................................................................................. 2.1.9.8. Analysis Ply ..................................................................................................................
125 126 126 127 128 130 131 136 137 138 140 142 142
2.1.9.9. Import Import from / Export to CSV File ................................................................................... 2.1.9.9.1. Export ................................................................................................................ 2.1.9.9.2. Import ................................................................................................................ 2.1.9.10. Export Export Ply Geometry .................................................................................................. 2.1.10. Imported Modeling Group .................................................................................................. 2.1.10.1. Tree Tree Object Context Menu ......................................................................................... 2.1.10.2. Imported Modeling Ply .............................................................................................. 2.1.10.2.1. Imported Modeling Ply Properties ..................................................................... 2.1.10.3. Imported Production Ply ............................................................................................ 2.1.10.4. Imported Imported Analysis Ply ................................................................................................ 2.1.11. Field Definitions ................................................................................................................. 2.1.12. Sampling Points ................................................................................................................. 2.1.13. Section Cuts ....................................................................................................................... 2.1.13.1.Types of Extrusion ...................................................................................................... 2.1.13.2. Section Cut Notes ...................................................................................................... 2.1.13.3. Section Cut Export .....................................................................................................
143 143 143 144 145 146 146 147 150 150 151 154 156 159 161 161
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ACP User's Guide
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2.1.14. Sensors .............................................................................................................................. 2.1.15. Solid Models ...................................................................................................................... 2.1.15.1. Solid Model ............................................................................................................... 2.1.15.1.1. Properties ......................................................................................................... 2.1.15.1.1.1. General .................................................................................................... 2.1.15.1.1.2. Drop-offs .................................................................................................. 2.1.15.1.1.3. Export ...................................................................................................... 2.1.15.1.2. Export Solid Model ............................................................................................ 2.1.15.1.3. Extrusion Guides ............................................................................................... 2.1.15.1.3.1. Mesh Morphing ........................................................................................ 2.1.15.1.3.2. Extrusion Extrusion Guide Examples ........................................................................ 2.1.15.1.4. Snap-to Geometry ............................................................................................. 2.1.15.1.5. Cut-off Geometry .............................................................................................. 2.1.15.1.5.1. Defining Defining Cut-off Geometry ....................................................................... 2.1.15.1.5.2. Decomposition Decomposition of Degenerated Elements ................................................. 2.1.15.1.6. Material Handling for Different Extrusion Methods ............................................. 2.1.15.1.7. Save & Reload Solid Models ............................................................................... 2.1.15.1.8. Node-based Thicknesses ................................................................................... 2.1.15.2. Imported Imported Solid Model ................................................................................................ 2.1.16. Layup Plots ........................................................................................................................ 2.1.16.1. Interface Options ....................................................................................................... 2.1.16.2. Thickness Plots .......................................................................................................... 2.1.16.3. Angle Plot .................................................................................................................. 2.1.16.4. Draping Mesh Plot ..................................................................................................... 2.1.16.5. Look-Up Table Plot ..................................................................................................... 2.1.16.6. Field Definition Plot ................................................................................................... 2.1.16.7. Layup Mapping Plot ................................................................................................... 2.1.16.8. Material Plots ............................................................................................................. 2.1.16.9. User-Defined Plot ...................................................................................................... 2.1.17. Definitions ......................................................................................................................... 2.1.18. Solutions ............................................................................................................................ 2.1.18.1. Solution Object ......................................................................................................... 2.1.18.1.1. Solution Solution Context Menu ..................................................................................... 2.1.18.1.2. Solution Properties ........................................................................................... 2.1.18.2. Envelope Solution ......................................................................................................
162 163 164 164 164 168 171 175 176 179 180 182 185 186 187 188 188 189 189 196 197 200 201 201 203 205 205 206 207 207 208 209 209 210 213
2.1.18.3. Solution Plots ............................................................................................................ 2.1.18.3.1. Common Plot Settings ...................................................................................... 2.1.18.3.2.Visualization Mismatch ...................................................................................... 2.1.18.3.3. Deformation Plot .............................................................................................. 2.1.18.3.4. Strain Plot ......................................................................................................... 2.1.18.3.5. Stress Plot ......................................................................................................... 2.1.18.3.6. Failure Mode Plot .............................................................................................. 2.1.18.3.7. Temperature Plot .............................................................................................. 2.1.18.3.8. Progressive Damage Plot ................................................................................... 2.1.18.3.9. Material Plot ..................................................................................................... 2.1.18.3.10. User-Defined Plot ............................................................................................ 2.1.19. Scenes ............................................................................................................................... 2.1.20. 2.1. 20. Views ................................................................................................................................. 2.1.21. Ply Book ............................................................................................................................. Book ............................................................................................................................. 2.1.21.1. Ply Book Properties .................................................................................................... 2.1.21.2. Create Chapter ..........................................................................................................
214 215 215 216 216 216 217 218 218 219 221 227 228 228 228 229
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ACP User's Guide 2.1.21.3. Automatic Setup ........................................................................................................ 2.1.21.4. Generate the Ply Book ................................................................................................ Book ................................................................................................ 2.1.22. Parameters ......................................................................................................................... 2.1.22.1. Settings Settings for an Expression Output .............................................................................. 2.1.23. Material Databank .............................................................................................................. Databank .............................................................................................................. 2.2. Postprocessing ............................................................................................................................. 2.2.1. Failure Criteria ...................................................................................................................... 2.2.2. Failure Mode Measures ......................................................................................................... 2.2.3. Principal Principal Stresses and Strains ................................................................................................ 2.2.4. Linearization Linearization of Inverse Reserve Factors ................................................................................ 2.2.5. Postprocessing of a Composite Solid Model .......................................................................... 2.2.6. Postprocessing of Drop-off and Cut-off Elements .................................................................. 2.2.7. Evaluating Custom Failure Criteria ........................................................................................ 2.2.8. Limitations & Recommendations .......................................................................................... 2.3. Exchanging Exchanging Composite Definitions with Other Programs ............................................................... 2.3.1. HDF5 Composite CAE Format ............................................................................................... 2.3.1.1. Export ......................................................................................................................... 2.3.1.2. Import ......................................................................................................................... 2.3.1.2.1. Import Projection Types ...................................................................................... 2.3.1.2.2. Import Import Settings ................................................................................................... 2.3.2. Mechanical APDL File Format ................................................................................................ 2.3.3. Import Import of Legacy Mechanical APDL Composite Models ......................................................... 2.3.3.1. Special Cases ............................................................................................................... 2.3.3.2. Known Limitations ....................................................................................................... 2.3.4.TTabular Data Format for Excel ................................................................................................ 2.3.4. 2.3.5. CSV Format .......................................................................................................................... 2.3.6. ESAComp ............................................................................................................................. 2.3.6.1. Export ......................................................................................................................... 2.3.6.2. Import ......................................................................................................................... 2.3.7. LS-Dyna ............................................................................................................................... 2.3.8. BECAS .................................................................................................................................. 3. Composite Modeling Techniques ........................................................................................................ 3.1. T-Joint T-Joint .......................................................................................................................................... 3.2. Local Reinforcements .................................................................................................................... 3.3. Ply Tapering and Staggering ..........................................................................................................
229 229 230 231 233 233 233 234 235 235 235 237 237 240 240 241 241 242 242 243 246 249 251 251 252 253 254 254 254 254 255 257 257 267 269
3.3.1. Ply Tapering ......................................................................................................................... 3.3.1.1. Edge Tapering ............................................................................................................. 3.3.1.2. Class40 ....................................................................................................................... 3.3.1.3. Tutorial Tutorial 2 ..................................................................................................................... 3.3.1.4.TTapering of Multiple Plies ............................................................................................. 3.3.1.4. 3.3.2. Ply Staggering ...................................................................................................................... 3.4.Variable Core Thickness ................................................................................................................. 3.4.1. Solid CAD Geometry ............................................................................................................ 3.4.2. Look-Up Table ...................................................................................................................... 3.4.3. Geometry Geometry Cut-off Selection Rule ........................................................................................... 3.4.4. General Application .............................................................................................................. 3.5. Draping ........................................................................................................................................ 3.5.1. Internal Internal Draping Algorithm of ACP ........................................................................................
269 269 270 271 272 272 274 274 275 276 278 278 279
3.5.2. User-Defined......................................................................................................................... Draping ........................................................................................................... 281 3.5.3.Visualization 282 3.6. Ply Book ....................................................................................................................................... Book ....................................................................................................................................... 283
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ACP User's Guide 3.7. Guide to Solid Modeling ................................................................................................................ 3.7.1.When to Use a Solid Model ................................................................................................... 3.7.2. How to Use the Solid Model Feature ..................................................................................... 3.7.3. Principles Principles of Solid Model Generation .................................................................................... 3.7.4. Drop-off and Cut-off Elements .............................................................................................. 3.7.5. 3.7. 5. Workflow Workflow ............................................................................................................................. 3.7.6. Practical Tips ........................................................................................................................ 3.7.7. Known Limitations ............................................................................................................... 3.8. Guide to Composite Visualizations ................................................................................................. 3.8.1. Model Verification ................................................................................................................ 3.8.2. Postprocessing Visualizations ............................................................................................... 3.9. Guide to Composite Failure Criteria ............................................................................................... 3.10. Element Choice in ACP ................................................................................................................ 3.10.1. Introduction ....................................................................................................................... 3.10.2. Shell Elements .................................................................................................................... 3.10.3. Solid Elements .................................................................................................................... 3.10.4. Solid-shell Elements ........................................................................................................... 3.11.Variable Material Data in Composite Analyses .............................................................................. 3.11.1. Element- or Layer-wise Field Definition ............................................................................... 3.11.2. Draping Shear .................................................................................................................... 3.11.3. Degradation Factors ........................................................................................................... 3.11.3.1. Definition of the Degradation Factor Field .................................................................. 3.11.4. Definition of General User-Defined Fields in ACP-Pre ........................................................... 3.11.5.Variable Data Interpolation Settings .................................................................................... 4. Example Analyses ................................................................................................................................ 4.1. Analysis of a Composite Shell Model .............................................................................................. 4.1.1. Preprocessing ...................................................................................................................... 4.1.1.1. Workbench Integration Integration ................................................................................................ 4.1.1.2. Adding ACP Components to the Project ....................................................................... 4.1.1.3. Engineering Data ......................................................................................................... 4.1.1.4. Properties .................................................................................................................... 4.1.1.5. Geometry Geometry and Units ..................................................................................................... 4.1.1.6. Named Named Selections and Elements/Edge Sets .................................................................. 4.1.1.7. Starting and Running ACP ............................................................................................ 4.1.2. Workbench Analysis Analysis System .................................................................................................
285 285 286 286 287 287 289 289 290 290 292 298 299 299 300 300 300 300 301 301 302 302 303 303 305 305 306 306 306 307 307 309 309 309 310
4.1.2.1. Adding Adding an Analysis System to the Project ..................................................................... 4.1.3. Postprocessing ..................................................................................................................... 4.1.3.1. Adding an ACP (Post) Component to the Project .......................................................... 4.2. Analysis of a Composite Solid Model ............................................................................................. 4.2.1. Preprocessing ...................................................................................................................... 4.2.2. Workbench Analysis Analysis System ................................................................................................. 4.2.3. Postprocessing ..................................................................................................................... 4.3. Analysis Using Variable Material Data ............................................................................................. 4.3.1.Workbench 4.3.1. Workbench Engineering Data: Setup Variable Variable Data ................................................................ 4.3.2. ACP-Pre: Define Fields for Shear Angle, Degradation Factor, and User-Defined Field Variables ............................................................................................................................................ 4.3.3. Mechanical, Mechanical, Thermal Loading, and External Data ................................................................... 4.3.4. ACP-Post: Analysis Effect of Variable Data ..............................................................................
310 311 311 312 314 314 318 320 321 324 327 327
4.4. Analysis Analy of a Mapped Composite Model ................................................................................ 329 328 4.4.1. sis Import Import External Solid Mesh Solid ................................................................................................... 4.4.2. Layup Mapping .................................................................................................................... 332
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ACP User's Guide 4.4.3. Analysis of A Mapped Composite Model ............................................................................... 4.5. Shear Dependent Materials in Composite Analysis ......................................................................... 4.6. 3D Ply Workflow – Imported Plies .................................................................................................. 4.6.1. Inputs .................................................................................................................................. 4.6.2. Example of Use - HDF5 Composite CAE ................................................................................. 5. Theory Documentation ....................................................................................................................... 5.1. Draping Simulation ....................................................................................................................... 5.1.1. Introduction ......................................................................................................................... 5.1.2. Draping Procedure ............................................................................................................... 5.1.2.1. Propagation Strategy ................................................................................................... 5.1.2.2. Woven Woven Material Model ................................................................................................. 5.1.2.3. Unidirectional Unidirectional Material Model ...................................................................................... 5.1.2.4. Output Output of the Draping Simulation ................................................................................ 5.1.3. Thickness Correction ............................................................................................................ 5.1.4. Limitations Limitations of Draping Simulations ....................................................................................... 5.2. Interlaminar Stresses ..................................................................................................................... 5.2.1. Introduction ......................................................................................................................... 5.2.2. Interlaminar Interlaminar Normal Stresses ................................................................................................ 5.2.2.1. Reference Coordinates ................................................................................................. 5.2.2.2. Numeric Solution ......................................................................................................... 5.2.3. Transverse Transverse Shear Stresses ..................................................................................................... 5.3. Failure Analysis ............................................................................................................................. 5.3.1. Reserve Factor ...................................................................................................................... 5.3.2. Weighting Factors Factors ................................................................................................................ 5.3.3. Failure Criterion Function ..................................................................................................... 5.3.4. Failure Criteria for Reinforced Materials ................................................................................. 5.3.4.1. Maximum Strain Criterion ............................................................................................ 5.3.4.2. Maximum Stress Criterion ............................................................................................ 5.3.4.3. Quadratic Failure Criteria ............................................................................................. 5.3.4.3.1.Tsai-W 5.3.4.3.1. Tsai-Wu u Failure Criterion ...................................................................................... 5.3.4.3.2.Tsai-H 5.3.4.3.2. Tsai-Hill ill Failure Criterion ...................................................................................... 5.3.4.3.3. Hoffman Failure Criterion .................................................................................... 5.3.4.4. Hashin Failure Criterion ................................................................................................ 5.3.4.5. Puck Failure Criteria ..................................................................................................... 5.3.4.5.1. Simple Simple and Modified Puck Criterion .....................................................................
335 336 342 342 344 347 347 347 347 348 349 349 350 350 350 351 351 351 353 353 354 357 357 357 358 358 358 359 359 359 360 361 362 362 362
5.3.4.5.2. Puck's Puck's Action Plane Strength Criterion ................................................................. 5.3.4.5.2.1. Fiber Failure (FF) ......................................................................................... 5.3.4.5.2.2. Interfiber Failure (IFF) ................................................................................. 5.3.4.6. LaRC Failure Criterion ................................................................................................... 5.3.4.6.1. LaRC03/LaRC04 Constants ................................................................................... 5.3.4.6.2. General Expressions ............................................................................................ 5.3.4.6.3. Fiber Misalignment Frame ................................................................................... 5.3.4.6.4. LaRC03 (2-D) ....................................................................................................... 5.3.4.6.5. LaRC04 (3-D) ....................................................................................................... 5.3.4.7. Cuntze's Failure Criteria ................................................................................................ 5.3.4.7.1. 3-D Failures ......................................................................................................... 5.3.4.7.2. 2-D Failures ......................................................................................................... 5.3.5. Sandwich Failure ..................................................................................................................
363 363 364 367 368 368 369 371 372 373 375 376 377
5.3.5.1. Core Sheet FailureWrinkling ................................................................................................................. 5.3.5.2. Face .................................................................................................... 377 377 5.3.5.3. Shear Crimping Failure ................................................................................................. 379
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ACP User's Guide 5.3.6. Isotropic Material Failure ...................................................................................................... 5.3.7. Adhesive Failure (Beta Version) ............................................................................................. 5.3.7.1. Peel Stress Criterion ..................................................................................................... 5.3.7.2. Shear Stress Criterion ................................................................................................... 5.3.8. Failure Criteria vs. Ply Type Table ........................................................................................... 5.4. Classical Laminate Theory ............................................................................................................. 5.4.1. Overview ............................................................................................................................. 5.4.2. Analysis ................................................................................................................................ 5.4.2.1. Laminate Laminate Stiffness and Compliance Matrices ................................................................ 5.4.2.2. Normalized Normalized Laminate Stiffness and Compliance Matrices .............................................. 5.4.2.3. Laminate Engineering Constants .................................................................................. 5.4.2.4. Out-of-Plane Out-of-Plane Shear Moduli and Correction Factors ....................................................... 5.4.2.5. Polar Properties ........................................................................................................... 5.4.2.6. Analysis Options .......................................................................................................... 5.5. General Interpolation Library ........................................................................................................ 5.5.1. Algorithms ........................................................................................................................... 5.5.1.1. Nearest-Neighbor Interpolation ................................................................................... 5.5.1.2. Linear Multivariate Interpolation .................................................................................. 5.5.1.3. Radial-Basis Algorithm ................................................................................................. 5.5.2. Options ................................................................................................................................ 5.5.3. Extrapolations ...................................................................................................................... 5.6. Nomenclature ............................................................................................................................... 6. The ACP Pyt Python hon Scripting User Interface ............................................................................................ 6.1. Introduction to ACP Scripting ........................................................................................................ 6.2.The Python Object Tree ................................................................................................................. 6.3. DB Database ................................................................................................................................. 6.4. Material Classes ............................................................................................................................ 6.4.1. MaterialData ........................................................................................................................ 6.4.2. Material ............................................................................................................................... 6.4.2.1. PropertySet ................................................................................................................. 6.4.3. Fabric ................................................................................................................................... 6.4.4. Stackup ................................................................................................................................ 6.4.5. SubLaminate ........................................................................................................................ 6.5. Model Classes ............................................................................................................................... 6.5.1. Model ..................................................................................................................................
380 380 380 381 381 382 382 383 383 384 385 385 386 387 387 388 388 388 390 391 391 391 395 395 397 397 399 400 405 406 408 410 412 414 415
6.5.2. Rosette ................................................................................................................................ 6.5.3. LookUpTableBase ................................................................................................................. 6.5.4. LookUpTable1D .................................................................................................................... 6.5.5. LookUpTable3D .................................................................................................................... 6.5.6. LookUpTableColumn ............................................................................................................ 6.5.7. ElementSelectionRule Classes ............................................................................................... 6.5.7.1. ParallelSelectionRule ParallelSelectionRule ................................................................................................... 6.5.7.2. CylindricalSelectionRule .............................................................................................. 6.5.7.3. SphericalSelectionRule ................................................................................................ 6.5.7.4. TubeSelectionRule TubeSelectionRule ....................................................................................................... 6.5.7.5. CutoffSelectionRule ..................................................................................................... 6.5.7.6. GeometricalSelectionRule ............................................................................................ 6.5.7.7. VariableOffsetSelectionRule VariableOffsetSelectionRule .........................................................................................
443 445 446 446 447 447 448 449 449 450 450 451 452
6.5.8. EntitySet Classes .................................................................................................................. 452 6.5.8.1. ElementSet .................................................................................................................. 453 6.5.8.2. EdgeSet ....................................................................................................................... 454
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ACP User's Guide 6.5.9. Geometry Classes ................................................................................................................. 6.5.9.1. CADGeometry ............................................................................................................. 6.5.9.2. CADCompound ........................................................................................................... 6.5.9.3. CADSolid ..................................................................................................................... 6.5.9.4. CADShell ..................................................................................................................... 6.5.9.5. CADFace ...................................................................................................................... 6.5.9.6. VirtualGeometry .......................................................................................................... 6.5.9.7. CADReference ............................................................................................................. 6.5.10. OrientedSelectionSet ......................................................................................................... 6.5.11. ModelingGroup .................................................................................................................. 6.5.12. ModelingPly ....................................................................................................................... 6.5.13. ProductionPly .................................................................................................................... 6.5.14. AnalysisPly ......................................................................................................................... 6.5.15. InterfaceLayer .................................................................................................................... 6.5.16. ButtJointSequence ............................................................................................................. 6.5.17. FieldDefinition ................................................................................................................... 6.5.18. SamplingPoint ................................................................................................................... 6.5.19. SectionCut ......................................................................................................................... 6.5.20. Sensor ................................................................................................................................ 6.5.21. PlyBook .............................................................................................................................. PlyBook .............................................................................................................................. 6.5.21.1. PlyBook ..................................................................................................................... PlyBook ..................................................................................................................... 6.5.21.2. Chapter ..................................................................................................................... 6.6. Solid-model Classes ...................................................................................................................... 6.6.1. SolidModel ........................................................................................................................... 6.6.2. ExtrusionGuide .................................................................................................................... 6.6.3. SnapToGeometry ................................................................................................................. 6.6.4. CutOffGeometry .................................................................................................................. 6.6.5. ImportedSolidModel ............................................................................................................ 6.7. Solution Classes ............................................................................................................................ 6.7.1. Solution ............................................................................................................................... 6.7.2. EnvelopeSolution ................................................................................................................. 6.8. Scene Classes ................................................................................................................................ 6.8.1. Scene ................................................................................................................................... 6.8.2.View ..................................................................................................................................... 6.9. Postprocessing Definition Classes ..................................................................................................
455 455 456 457 457 457 457 459 459 461 466 469 471 472 473 473 474 476 478 479 479 480 480 481 483 484 484 485 486 486 490 490 491 492 493
6.9.1. CombinedFailureCriteria ....................................................................................................... 6.9.1.1. MaxStressCriterion ....................................................................................................... 6.9.1.2. MaxStrainCriterion ....................................................................................................... 6.9.1.3.TsaiWu ......................................................................................................................... 6.9.1.4.TsaiHill ......................................................................................................................... 6.9.1.5. Hashin ......................................................................................................................... 6.9.1.6. Hoffman ...................................................................................................................... 6.9.1.7. Puck ............................................................................................................................ Puck ............................................................................................................................ 6.9.1.8.Wrinkling ..................................................................................................................... 6.9.1.9. CoreShear ................................................................................................................... 6.9.1.10. Larc ........................................................................................................................... 6.9.1.11. Cuntze ....................................................................................................................... 6.9.1.12. VonMises ...................................................................................................................
493 494 495 496 496 497 497 497 499 499 500 500 501
6.9.1.13. .......................................................................................................... 502 6.10. Plot ClassesShearCrimping ................................................................................................................................. 502 6.10.1. PlotContainer Classes ......................................................................................................... 502
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ACP User's Guide 6.10.1.1. PlotDataDict Class ...................................................................................................... 6.10.1.2. LayupPlotDict Class ................................................................................................... 6.10.1.3. PostProcessingPlotDict Class ...................................................................................... 6.10.2. PlotData Classes ................................................................................................................. 6.10.2.1. PlotData .................................................................................................................... 6.10.2.2. ContourData .............................................................................................................. 6.10.2.3. AngleData ................................................................................................................. 6.10.2.4. ThicknessData ........................................................................................................... 6.10.2.5. ScalarFieldData .......................................................................................................... 6.10.2.6. DrapingData .............................................................................................................. 6.10.2.7. FieldDefinitionData .................................................................................................... 6.10.2.8. LayupMappingData ................................................................................................... 6.10.2.9. UserDefinedData ....................................................................................................... 6.10.2.10. DeformationContourData ........................................................................................ 6.10.2.11. StrainData ............................................................................................................... 6.10.2.12. StressData ............................................................................................................... 6.10.2.13. FailureData .............................................................................................................. 6.10.2.14.TTemperatureData 6.10.2.14. emperatureData ..................................................................................................... 6.10.2.15. ProgressiveDamageData .......................................................................................... Bibliography .............................................................................................................................................
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502 503 508 515 515 519 520 520 520 521 522 522 522 523 523 523 523 524 524 527
List of Figures 1.1. Oriented Selection Set Properties ............................................................................................................ 4 1.2. ANSYS Composite PrepPost GUI ............................................................................................................ 10 1.3. ANSYS Composite PrepPost Menu Options ............................................................................................ 11 1.4. File Menu for Workbench Integration .................................................................................................... 12 1.5. Stand Alone File Menu .......................................................................................................................... 13 1.6. View Menu Menu ........................................................................................................................................... 13 1.7. Perspective Submenu ........................................................................................................................... 14 1.8. Show View ............................................................................................................................................ 14 1.9. Logger Preferences ............................................................................................................................... 15 1.10. General ACP Preferences ..................................................................................................................... 16 1.11. Section Generation Preferences ........................................................................................................... 17 1.12. Scene Preferences ............................................................................................................................... 17 1.13. Units Menu ......................................................................................................................................... 19 1.14. Tree Tree View ............................................................................................................................................ 21 1.15. Locked Locked Rosettes and the Update Status ............................................................................................... 22 1.16. Excel Link Dialog ................................................................................................................................. 24 1.17. Orientation Visualizations in the Toolbar Toolbar .............................................................................................. 25 1.18.Visualization of the Element Normals ................................................................................................... 25 1.19.Visualization of the OSS Normal ........................................................................................................... 26 1.20.Visualization of the OSS Reference Direction ........................................................................................ 26 1.21. Fiber Directions in the Toolbar ............................................................................................................. 27 1.22.Visualization of the Fiber Direction ...................................................................................................... 27 1.23.Visualization 1.23. Visualization of the Transverse Ply Direction ......................................................................................... 28 1.24. Draping Directions in the Toolbar ........................................................................................................ 28 1.25. Fiber Directions (Defined and Draped) ................................................................................................. 29 1.26.Tr 1.26. Traverse averse Directions (Defined and Draped) ............................................................................................ 30 1.27. Material 1 Direction and Draped Fiber Direction for a Material with a 45° Fabric Fiber Angle .................. 31 1.28. Enclosed Box and Coordinate System .................................................................................................. 32 1.29. Distance Measure Tool ........................................................................................................................ 32 1.30. Properties Properties from Right-Click Context Menu ........................................................................................... 40 1.31. Properties Menu: Setup ....................................................................................................................... 40 1.32. Multiple Load Cases and Analyses ....................................................................................................... 42 1.33.Two Analyses Share the Same ACP (Pre) Setup ..................................................................................... 43 1.34. Import Import Volume Mesh from Mechanical Model (E4 to C5) ...................................................................... 44 1.35. Import Volume Mesh from Third Party Application ............................................................................... 44 1.36. Write Input Input File ................................................................................................................................... 50 1.37. Import Import ANSYS Model Using the Context Menu ..................................................................................... 51 1.38. Switch Between ACP Pre and Post ....................................................................................................... 52 2.1. Model Context Menu in Workbench Mode ............................................................................................. 54 2.2. Model Model Context Menu in Stand-Alone Mode ........................................................................................... 54 2.3. General Model Properties ...................................................................................................................... 56 2.4. Model Statistics .................................................................................................................................... 57 2.5. Solver Information (Solve.out) ............................................................................................................... 59 2.6. Export Composite Definitions Window .................................................................................................. 60 2.7. Import Composite Definitions Window .................................................................................................. 60 2.8. Element-based vs. Node-based Piercing ................................................................................................ 61 2.9. Ply Extension and Element-wise Thicknesses of a Tapered Tapered Ply with Element-based (left) and Node-based (right) Thicknesses ...................................................................................................................................... 62 2.10. Restriction for Node-based Thicknesses ............................................................................................... 62
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ACP User's Guide 2.11. Extrusion of a Tapered Tapered Ply without and with Node-based Thicknesses on the Left and Right, Respectively ........................................................................................................................................................... 63 2.12. Solid Model Extrusion of a Tapered Tapered Ply without and with Node-based Thicknesses ............................... 63 2.13. Cut-off Cut-off Selection Rule with Ply Tap Tapering ering Based on Element-based and Node-based Thicknesses ........... 63 2.14. Materials Materials Class Context Menu in Stand Alone Mode ............................................................................. 64 2.15. Example of Woven Material with a 45° Fabric Fiber Angle ..................................................................... 68 2.16. Fabric Properties - General .................................................................................................................. 74 2.17. Fabric Properties - Analysis .................................................................................................................. 75 2.18. Fabric Properties - Solid Model Options ............................................................................................... 76 2.19. Fabric Properties - Draping .................................................................................................................. 77 2.20. Stackup Properties Properties - General ............................................................................................................... 78 2.21. Stackup Sequence with Even Symmetry .............................................................................................. 79 2.22. Stackup Sequence with Odd Symmetry ............................................................................................... 80 2.23. Layup Information and Polar Properties ............................................................................................... 81 2.24. CLT Analysis - Laminate Engineering Constants .................................................................................... 82 2.25. Sub Laminate Properties - General Tab ................................................................................................ 83 2.26. Element Set Selection ......................................................................................................................... 84 2.27. Element Set Context Menu .................................................................................................................. 85 2.28. Edge Set Definition ............................................................................................................................. 85 2.29. CAD Geometry Assembly and Virtual Geometries in the Tree Tree View ....................................................... 86 2.30. Import Import External CAD Geometry ........................................................................................................... 87 2.31. Project Project Schematic with a CAD Geometry Import in ACP ....................................................................... 88 2.32. Create Create Virtual Geometry Directly from CAD Geometry Part .................................................................. 89 2.33. Create Virtual Geometry Through CAD Geometry Parts in Tree ............................................................. 89 2.34. Create Create Virtual Geometry Through Face Selection in the Scene .............................................................. 90 2.35. Rosette Properties Dialog .................................................................................................................... 91 2.36. Oriented Oriented Selection Set with a Radial R adial Rosette. ....................................................................................... 92 2.37. Oriented Oriented Selection Set with a Cylindrical Rosette ................................................................................. 93 2.38. Oriented Oriented Selection Set with a Spherical Rosette ................................................................................... 93 2.39. Edge Wise Rosette ............................................................................................................................... 94 2.40. Schematic of 1-D Look-Up Table Function ......................................................................................... 101 2.41. Look-Up Table Properties .................................................................................................................. 101 2.42. Look-Up Table Interpolation Parameters ............................................................................................ 102 2.43. Setting the Dimension in the Column Properties Dialog ..................................................................... 103 2.44. Selection Rules Context Menu ........................................................................................................... 103 2.45. Definition Definition of a Parallel Selection Rule ................................................................................................. 2.46. Example Example of a Parallel Selection Rule ................................................................................................... 2.47. Example of Tube Selection Rule ......................................................................................................... 2.48. Cut-off Selection Rule Properties ....................................................................................................... 2.49.Tr 2.49. Trailing ailing Edge with Cut-off Plies (Ply Tapering Tapering Activated) ...................................................................... 2.50. Section of the Cut-off Geometry ........................................................................................................ 2.51. Core Thickness Without Ply Tapering (Left) and With Ply Tapering (Right) ............................................ 2.52. Taper Cut-off Selection Rule Definition .............................................................................................. 2.53. Section with The Production Ply Option ............................................................................................. 2.54. Section with the Analysis Ply Option .................................................................................................. 2.55. Section with the Analysis Ply with Tapering Tapering Option ............................................................................ 2.56. Example Geometrical Selection Rule .................................................................................................. 2.57. Geometrical Selection Rule Properties ...............................................................................................
104 105 106 107 108 108 109 110 110 111 111 112 113
2.58. Capture ............................................................................................................................ 2.59. Look-UpTolerances Table Defines the Offset to Edge Set at a Given Length ......................................................... 114 115 2.60. Offset Correction ............................................................................................................................... 116
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ACP User's Guide 2.61. Offset Mapping Along a Direction Vector ........................................................................................... 2.62. Boolean Selection Rule ...................................................................................................................... 2.63. Boolean Operation Types .................................................................................................................. 2.64. Orientation Point Definition .............................................................................................................. 2.65. Definition ......................................................................................................................................... 2.66. Reference Reference Direction of a Bonding Laminate Defined by Two Rosettes and a Minimum Angle Selection Method .................................................................................................................................................... 2.67. Selection Rules .................................................................................................................................. 2.68. Draping ............................................................................................................................................ 2.69. Object Tree of a Layup Definition ....................................................................................................... 2.70. Context Menu of Modeling Groups .................................................................................................... 2.71. General Information .......................................................................................................................... 2.72. Internal Draping Definition ................................................................................................................ 2.73. Draping with Tabular Values Definition .............................................................................................. 2.74.Thickness Definition .......................................................................................................................... 2.75.Thickness Definition Options ............................................................................................................. 2.76. Core Geometry ................................................................................................................................. 2.77. Resulting Section Cut ........................................................................................................................ 2.78. Edge Tapering ................................................................................................................................... 2.79.Taper Edge Example .......................................................................................................................... 2.80. Right-Click Modeling Ply Menu .......................................................................................................... 2.81. Interface Layer Properties Properties - General ................................................................................................... 2.82. Interface Layer Properties - Open Area ............................................................................................... 2.83. Drop-Off Drop-Off Elements and a Butt Joint Between Two Cores ..................................................................... 2.84. Production Ply Context Menu ............................................................................................................ 2.85. Analysis Ply Context Menu ................................................................................................................ 2.86. CSV Import with Update Options ....................................................................................................... 2.87. Export Ply Geometry Window ............................................................................................................ 2.88. General Properties Options ............................................................................................................... 2.89. Draping Properties Options ............................................................................................................... 2.90. Thickness Properties Properties Options ............................................................................................................ 2.91. Imported Production Ply Dialog ........................................................................................................ 2.92. Imported Analysis Ply ........................................................................................................................ 2.93. Field Field Definitions Context Menu ......................................................................................................... 2.94. Field Definition Context Menu ...........................................................................................................
117 118 118 119 120 122 123 124 126 126 128 129 130 132 132 133 134 135 135 136 138 138 139 142 142 144 145 148 149 149 150 151 152 153
2.95. Field Definition Object Properties ...................................................................................................... 2.96. Sampling Point Properties - General Tab ............................................................................................ 2.97. Layup Sequence and Enhanced Postprocessing ................................................................................. 2.98. General Section Cut Properties .......................................................................................................... 2.99.Wire Frame Options ........................................................................................................................... 2.100. Surface Options .............................................................................................................................. 2.101. Element Normals ............................................................................................................................. 2.102. Surface Normal vs. Surface Sweep Based Extrusion ........................................................................... 2.103. Ply-Wise Angles on the Surface Section Cut ..................................................................................... 2.104. Supported Lay-up for T-Joints .......................................................................................................... 2.105. Export Export Surface Sur face Section Cut Options ................................................................................................. 2.106. Sensor Properties ............................................................................................................................ 2.107. Solid Model Folder with a Standard Solid Model and an Imported Solid Model .................................
154 155 156 157 158 158 160 160 161 161 162 162 163
2.108. Solid in the Tree View ................................................................................................ 164 2.109. Solid Model Model Feature Properties - General ...................................................................................................... 165 2.110. Illustration Illustration of Solid Model Extrusion Methods .................................................................................. 166
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ACP User's Guide 2.111. Extrusion Direction .......................................................................................................................... 167 2.112. Offset Direction ............................................................................................................................... 167 2.113. Solid Model Properties - Drop-Offs ................................................................................................... 169 2.114. Disable Drop-Offs ............................................................................................................................ 169 2.115. Connect Butt-Jointed Plies .............................................................................................................. 171 2.116. Solid Model Properties - Export ....................................................................................................... 172 2.117.Write Degenerated Elements ........................................................................................................... 172 2.118. Quadratic Tetrahedral Element on Top of a Hexahedral Element ....................................................... 173 2.119.Transferred Element Sets in Mechanical ........................................................................................... 174 2.120. Properties of the ACP-Pre Setup Cell in the Project Schematic .......................................................... 175 2.121. Extrusion Extrusion with and without an Edge Set Guide ................................................................................. 177 2.122. Extrusion Guide Properties .............................................................................................................. 178 2.123. Reordering Extrusion Guides ........................................................................................................... 179 2.124. Mesh Morphing Diagram ................................................................................................................. 180 2.125. Example Example of a Direction-type Extrusion Guide with Different Mesh Morphing Radii R adii ............................ 181 2.126. Example Example of a Geometry-type Extrusion Guide with Different Mesh Morphing Depths. ...................... 182 2.127. Extrusion without Snap Operation ................................................................................................... 183 2.128. Extrusion with Snap to Geometry G eometry at the Top (Shell Geometry also Displayed) ................................... 184 2.129. Extrusion with Snap to Geometry at the Top and Bottom (Shell Geometry also Displayed) ................ 185 2.130. Extruded Solid Model ...................................................................................................................... 185 2.131. Cut-off Cut-off Geometries Shown Alongside Extruded Solid Model ............................................................ 186 2.132. Solid Model with Cut-off Features .................................................................................................... 186 2.133. Cut-off Cut-off Geometry Normal Direction ................................................................................................. 187 2.134. A Degenerated Hexahedral Element (left) is Decomposed into Several TTetrahedral etrahedral Elements (right) .. . 188 2.135. Thickness Plot ................................................................................................................................. 200 2.136. Angle Plot ....................................................................................................................................... 201 2.137. Draping Mesh Plot Properties .......................................................................................................... 202 2.138. Draping Mesh ................................................................................................................................. 202 2.139. Draping Plot for a Hemisphere ......................................................................................................... 203 2.140. Flatwrap Flatwrap Surface of the Ply .............................................................................................................. 203 2.141. Look-Up Table Plot General Properties Tab ....................................................................................... 204 2.142. Look-Up Look-Up Table Table Plot of a 1-D Scalar Quantity with Supporting Points Shown as Circles ........................ 205 2.143. Layup Mapping General Properties Tab ............................................................................................ 206 2.144. Deviation Deviation of the Normal Direction between Shell Elements and Layered Solid Elements ................... 206 2.145. Failure Criteria Definition ................................................................................................................. 207 2.146. Puck Failure Criteria Configuration ................................................................................................... 2.147. Solutions Object in the Tree View ..................................................................................................... 2.148. Solution Solution Properties Window Showing Several Solution Sets in the Data tab ...................................... 2.149. Comparison Comparison of Imported and Recomputed Interlaminar Stresses ...................................................... 2.150. Envelope Solution Properties ........................................................................................................... 2.151. Scene with Failure Mode Plot Activated ........................................................................................... 2.152. Material Plot General Properties Tab ................................................................................................ 2.153. Script Field in the User-Defined Plot Properties ................................................................................ 2.154. Scene Properties ............................................................................................................................. 2.155. One Page of a Ply Book .................................................................................................................... Book .................................................................................................................... 2.156. Connection Connection of ACP and Workbench Parameter Interface .................................................................. 2.157. Parameter Properties ....................................................................................................................... 2.158. Material Databank ........................................................................................................................... Databank ...........................................................................................................................
208 209 211 213 214 218 220 222 228 229 230 230 233
2.159. Failure Failure Analysis Plot Dialog 236 2.160. of a........................................................................................................................... Solid Model. Show on Solids (left) and Show on Shells (right) ............................. 236 2.161. Export Export and Import Options in Model Context Menu ......................................................................... 241
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ACP User's Guide 2.162. HDF5 Composite Composite CAE File Export Settings ........................................................................................ 242 2.163. HDF5 HDF5 Composite CAE File Import Settings ....................................................................................... 244 2.164. Schematic of Tolerance Settings for a Single Element ....................................................................... 246 2.165. SHELL181 Keyopts ........................................................................................................................... 247 2.166. SHELL281 Keyopts ........................................................................................................................... 248 2.167. SOLID185 Keyopts ........................................................................................................................... 248 2.168. SOLID186 Keyopts ........................................................................................................................... 249 2.169. Configuration Configuration Overview .................................................................................................................. 250 2.170. Configuration Configuration Overview .................................................................................................................. 251 2.171. A Four Ply Mechanical APDL Lay-up Where a Ply Crosses the Reference Surface is Converted to a Five Ply ACP Lay-up .......................................................................................................................................... 251 2.172. ModelingGroup Tabular Format in Excel ........................................................................................... 252 2.173. Look-Up Table Tabular Format in Excel ............................................................................................. 253 3.1.T-Joint Lay-Up ..................................................................................................................................... 258 3.2. OSS for the Base Plate ......................................................................................................................... 259 3.3. OSS for the Stringer ............................................................................................................................. 260 3.4. OSS for Bonding Plies .......................................................................................................................... 261 3.5. Reference Direction ............................................................................................................................ 262 3.6. Laminate of the Base Plate .................................................................................................................. 263 3.7. Laminate Laminate of the Base Plate and Stringer ............................................................................................... 264 3.8. First Bonding Laminate ....................................................................................................................... 265 3.9. Second Bonding Laminate .................................................................................................................. 266 3.10. Cover Plies ........................................................................................................................................ 267 3.11.Tube Selection Rule ........................................................................................................................... 268 3.12. Rules Tab of the Modeling Ply Property Dialog ................................................................................... 268 3.13. Resulting Local Reinforcements Reinforcements ......................................................................................................... 269 3.14. Simple Edge Tapering ........................................................................................................................ 270 3.15.Tapered Edge .................................................................................................................................... 270 3.16. Tapering in Ply Definition .................................................................................................................. 271 3.17.Thickness 3.17. Thickness Distribution After Core Tapering Tapering ......................................................................................... 272 3.18. Superposition Superposition of Modeling Plies with Identical Taper Angles. Schematic (Middle) and Section View Illustration (Right) ........................................................................................................................................... 272 3.19.Thickness 3.19. Thickness Distribution of a Laminate with a Cutoff Selection Rule ....................................................... 273 3.20.Template Selection Rule Definition .................................................................................................... 273 3.21. Imported Core Geometry .................................................................................................................. 274 3.22. Modeling Ply Thickness Definition ..................................................................................................... 3.23. Section with Variable Core Thickness ................................................................................................. 3.24.Tab 3.24. Table le Definition ................................................................................................................................. 3.25.Thickness 3.25. Thickness Definition Through Tabular Tabular Values ...................................................................................... 3.26. Section Cut and Thickness Contour Plot ............................................................................................. 3.27. Imported Imported Cut-off Geometry ............................................................................................................... 3.28. Resulting Thickness Distribution (Ply Tapering Tapering Activated) ................................................................... 3.29. Flatwrap (Boundary) .......................................................................................................................... 3.30. Draping Draping Mesh with Shear Energy ....................................................................................................... 3.31. Draping Definition in OSS .................................................................................................................. 3.32.TTabular Values Definition of Draping .................................................................................................. 3.32. 3.33. Fiber and Draped Fiber Directions ..................................................................................................... 3.34.View 3.34. View Definition Definition .................................................................................................................................
275 275 276 276 277 277 278 279 280 281 282 283 283
3.35. Example Production Ply Representation ...................................................................................... 284 3.36. Analyzing Analy zingofa aSolid Model Alongside a Shell Model ............................................................................... 288 3.37. Solid Model Assembly Workflow ........................................................................................................ 289
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ACP User's Guide 3.38.T-Joint Section Cut ............................................................................................................................ 3.39. Class40 Section Cut ........................................................................................................................... 3.40. Activate Activate Deformed Geometry in the Solution Properties Visualizations ............................................... 3.41. Activate the Deformation Plot for Total Deformation .......................................................................... 3.42. Activate Activate the Failure Failure Criteria Plot with Failure Mode and Critical Ply Information .................................. 3.43. IRF Value and Text Plot for Each Element (Tutorial 1) ........................................................................... 3.44. Zoom Zoom on Critical Area (Class 40) ......................................................................................................... 3.45. Activate Activate the Ply-Wise Results in the Plot Properties ............................................................................ 3.46. Select an Analysis Ply in the Modeling Groups or Sampling Points ...................................................... 3.47. Ply-Wise Ply-Wise Stress (Tutorial 1) ................................................................................................................. 3.48. Stress Analysis for Selected Sampling Point ........................................................................................ 3.49. Field Definition Properties to Set Up a Degradation Factor Field ......................................................... 4.1. ACP Components ................................................................................................................................ 4.2. Engineering Data Sources ................................................................................................................... 4.3. Outline of Composite Materials ........................................................................................................... 4.4. Material Properties for ACP .................................................................................................................. 4.5. Context Menu of ACP (Pre) Setup ........................................................................................................ 4.6. Connecting Connecting a Static Structural Analysis to ACP (Pre) using a Drag and Drop Operation .......................... 4.7. Adding ACP (Post) by Drag and Drop Operation ................................................................................... 4.8. Linking a Solution with ACP (Post) ....................................................................................................... 4.9. Complete Composite Shell Analysis Model .......................................................................................... 4.10.Workbench 4.10. Workbench Workflow Workflow for Composite Solid Modeling with Mechanical ................................................ 4.11.Workbench 4.11. Workbench Workflow Workflow for Composite Solid Modeling with Mechanical APDL ....................................... 4.12. Analysis Analysis of a Composite Tube Tube with Metal Inserts Modeled with Mechanical ........................................ 4.13. Suppressed Suppressed Shell in Mechanical Model .............................................................................................. 4.14. Assembly Assembly of Composite and Metal Solids ........................................................................................... 4.15. Analysis Analysis of Composite Plate and T-joint Modeled with Mechanical APDL ............................................ 4.16. Add Reference File ............................................................................................................................ 4.17. List of Used Files and Their Order in Mechanical APDL ........................................................................ 4.18. Step 1: Drag and Drop an ACP (Post) System on to an ACP (Pre) System .............................................. 4.19. Step Step 2: Drag and Drop the Static Structural Solution Cell into the ACP (Post) Results Cell ..................... 4.20. Race Car Workbench Setup ................................................................................................................ 4.21. Predefined Predefined and User-Defined Field Variables Variables in Engineering Data ....................................................... 4.22. Assigning a Field Variable to Material Property ................................................................................... 4.23. Populating the Tabular Material using the CSV Interface .....................................................................
291 292 293 293 294 295 295 296 296 297 298 302 306 307 307 308 310 310 311 312 312 314 315 316 316 317 317 318 318 319 320 321 322 322 323
4.24. Setting Interpolation Options ............................................................................................................ 4.25. Draping Results ................................................................................................................................. 4.26. Curing Degree Plot ............................................................................................................................ 4.27. Activating a Look-up Table to Define Curing per Modeling Ply (layer-wise) .......................................... 4.28. Using External Data to Define Temperature Field ................................................................................ 4.29. Inverse Reserve Factor ...................................................................................................................... 4.30. Full Full Cross-Section Composite Spring ................................................................................................. 4.31. Complete Workbench Project Schematic ........................................................................................... 4.32. Layup of the Composite Spring ......................................................................................................... 4.33. Mesh Features Features and Solid Mesh with the Inflation Layers and Roving Cross Section .............................. 4.34. Selection of the ±45° and Core Plies ................................................................................................... 4.35. Filler Elements and Fiber Directions ................................................................................................... 4.36. Composite Composite Failure Analysis in Mechanical that Shows the Maximum Failure per Element ....................
324 325 326 326 327 328 329 330 331 331 334 335 336
4.37.Workbench Project Setup .................................................................................................................. 4.38.Woven 4.38. Woven RVE defined in Material Designer ............................................................................................ 336 337 4.39. Materials Materials in the Engineering Data Component of the ACP system ...................................................... 337
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ACP User's Guide 4.40. Shear Dependent Fabric Fiber Angle .................................................................................................. 4.41. Ply Definition .................................................................................................................................... 4.42. Fiber Fiber (Light Green),Transv Green), Transverse erse (Dark Green) and Material 1 (Red) Directions ....................................... 4.43. Draping Definition ............................................................................................................................ 4.44. ACP Draping Mesh ............................................................................................................................ 4.45. Shear Angle Plot ............................................................................................................................... 4.46. Draped Draped Fiber Direction (Light Blue), Draped Draped Transverse Transverse Direction (Blue) and Material 1 Direction (Red) ........................................................................................................................................................
337 338 338 339 339 340
4.47. Deformation Shear-Dependent Young's material Moduluson ................................................................................................... 4.48. Def ormation Plot (variable left, constant material on right) ............................................... 4.49. 3D Ply Workflow (Courtesy of 9T Labs) ............................................................................................... 4.50. HDF5 HDF5 Composite CAE Imported as 3D Plies (Imported Modeling Plies) ............................................... 4.51. 3D Printing with Endless Fiber Reinforcement and Final Part (Courtesy of 9T Labs) ..................... 4.52. Simulation Simulation of a 3D Printed Composite (Courtesy of 9T Labs) ............................................................... 4.53. Distribution Distribution of the Inverse Reserve Factors in the Mapped Composite Solid Model ............................. 5.1. Draping Scheme ................................................................................................................................ 5.2. Angle Notation for the Draping Energy Algorithm ............................................................................... 5.3. Deformation of the Draping Unit Cell .................................................................................................. 5.4. Doubly Curved FE Geometry ............................................................................................................... 5.5. Integration Scheme ............................................................................................................................ 5.6. Fracture Curve in σ2, τ21 Space for σ1 = 0 .............................................................................................. 5.7. UD Failure Modes ................................................................................................................................ 5.8. Relation Between ABD Matrix and the Coupling Between Laminate Forces Forces and Deformations .............. 5.9. Laminate Laminate Properties with Out-of-Plane Shear Stiffness and Shear Correction Factors ............................ 5.10. Linear Multivariate Algorithm ............................................................................................................
341 342 343 343 344 344 345 348 349 349 352 354 364 374 384 386 390
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List of Tables 1.1. Predefined Unit Systems ....................................................................................................................... 19 2.1. Key Differences Differences Between a Modeling Ply and Imported Modeling Ply ................................................... 146
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Chapter 1: Getting Started The following sections describe how to begin using ANSYS Composite PrepPost (ACP): 1.1. Overview 1.2.The 1.2. The ANSYS Product Improvement Program 1.3. Graphical User Interface 1.4. Implementation in Workbench 1.5. Migrating ACP Projects from Previous Versions 1.6. Stand Alone Operation
1.1. Overview The following sections provide an overview of ANSYS Composite PrepPost (ACP). 1.1.1. Introduction 1.1.2. Supported Supported Platforms and Functional Add-ons 1.1.3. Known Limitations 1.1.4. First Steps
1.1.1. Introduction Composite materials are created by combining two or more layered materials, each with different properties. These materials have become a standard for pr products oducts that are both light and strong. Composites provide enough flexibility so products with complex shapes, such as boat hulls and surfboards, can be easily manufactured. Engineering layered composites involves complex definitions that include numerous layers, materials, thicknesses and orientations. The engineering challenge is to predict how well the finished product will perform under real-world working conditions. This involves considering stresses and deformations as well as a range of failure criteria. ANSYS Composite PrepPost provides all necessary functionalities for the analysis of layered composite structures.
ACP Workflows ANSYS Composite PrepPost (ACP) is an add-in to ANSYS Workbench and is integrated with the standard analysis features. As a result, the entire workflow for a composite structure can be completed from design to final production information.
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Getting Started
The geometry of the tooling surfaces of a composite structure is the basis for analysis and production. Based on this geometry and a FE mesh, the boundary conditions and composite definitions are applied to the structure in the pre-processing stage. After a completed solution, the post-processing is used to evaluate the performance of the design and laminate. In the case of an insufficient design or material failure, the geometry or laminate has to be modified and the evaluation is repeated. ACP has a pre- and post-processing mode. In the pre-processing mode, all composite definitions can be created and are mapped to the geometry (FE mesh). These composite definitions are transferred to the FE model and the solver input file. In the post-processing mode, after a completed solution and the import of the result file(s), post-processing results (failure, safety, strains and stresses) can be evaluated and visualized.
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Overview
1.1.2. Supported Platforms and Functional Add-ons Supported Platfor Platforms ms ACP is supported on both Windows and Linux systems. For information about specific operating system versions and distributions, see the Platform Support section of the ANSYS Website. Website . ACP has additional library dependencies in Red Hat Enterprise Linux, for information on how to install Products in in the ANSYS, Inc. Linux Installation those libraries, see Post-Installation Procedures for Other Products Guide.. Guide
Functional Add-ons ACP provides functional add-ons for problem-specific functionality. These add-ons are not cconsidered onsidered appropriate for general use and should be used with caution. No standard documentation is provided for these features, but additional information is available on request. For more information, please contact
[email protected].
[email protected] . For information on how to activate these add-ons, see Submenus Submenus (p. (p. 16) 16)..
1.1.3. Known Limitations ACP has the following known limitations. Note that feature-specific limitations are often documented with the corresponding feature description throughout the ACP user's guide.
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Getting Started
Unicode ACP does not support Unicode characters.
Composite Failure Tool For Migrated ACP Projects The Composite Failure Tool in Mechanical can only be used in migrated projects once the ACP-Pre Setup cell has been updated.
Coordinate System Naming For Migrated ACP Projects In Version 2019 R2, naming is maintained when coordinate systems defined in Workbench are transferred to ACP as Rosettes. (See Rosettes Rosettes (p. (p. 90) 90).).) When migrating projects from previous versions, the Oriented Selection Set Properties may lose the Rosette link due to the renaming. This will require lay4).. up definitions to be updated manually as shown in Figure 1.1: Oriented Selection Set Properties (p. 4) For more information on migrating projects from previous versions, see Migrating ACP Projects from Previous Prev ious Versions Versions (p. 47) Figure 1.1: Oriented Selection Set Properties
Export System(s) and Import to Workbench The Export System(s) and Import of Workbench projects are not supported for ACP Systems. With this current limitation, the imported ACP systems cannot be updated correctly after import.
Parameters In ACP, Parameters, and how they are handled by the Parameter Manager, have certain limitations. Parameters ameters (p. (p. 230) 230) section section for additional information. See the Par
Options for Objects with the Same Name The application allows you to create objects with the same name. However, there are certain property specification and graphical selection limitations for this scenario. Based on the object type, you may
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The ANSYS Product Product Improvement Improvement Program Program not be able to define the properties to include objects with the same name. For example, you cannot define Sub Laminates using a Fabric and Stackup that have the same name.
1.1.4. First Steps The best way to get to know ACP features is to attempt one of the tutorials. There are two tutorials that explain step-by-step how to define and analyze basic composite composite structures. The tutorials both start off with existing Workbench projects. These sample projects and more information can be found in section Introduction. Introduction. Knowledge of ANSYS Workbench is a prerequisite. For information on how to build a composite model from new, see Analysis of a Composite Shell Model Mod el (p. 305 305)). There are many ways to implement ACP in Workbench. The workflow for modeling composite solid Composite site Shell Model (p. (p. 305) 305).. Other examples are element models is described in Analysis Analysis of a Compo shown in Implementatio Implementation n in Workbench (p. 35) 35).. Composite Modeling Techniques (p. 257) 257) offers offers an insight into modeling approaches for common composite problems. (p. 53) 53).. Explanations and specific information of the ACP features can be found in Features Features (p. Background information on the underlying theory used in ACP is available in Theory Documentation (p. (p. 347 347)). This is especially of interest for the failure criteria.
1.2.The ANSYS Product Improvement Program This product is covered by the ANSYS Product Improvement Program, which enables ANSYS, Inc., to collect and analyze anonymous usage data reported by our software without affecting your work or product performance. Analyzing product usage data helps us to understand customer usage trends and patterns, interests, and quality or performance performan ce issues. The data enable us to develop or enhance product features that better address your needs.
How to Participate The program is voluntary. To participate, select Yes when the Product Improvement Program dialog appears. Only then will collection of data for this product begin.
How the Program Works After you agree to participate, participate, the product product collects anonymous usage data during each session. When you end the session, the collected data is sent to a secure server accessible only to authorized ANSYS employees. After ANSYS receives the data, various statistical measures such as distributions, counts, means, medians, modes, etc., are used to understand and analyze the data.
Data We Collect The data we collect under the ANSYS Product Improvement Program are limited. The types and amounts of collected data vary from product to product. Typically, Typically, the data fall into the categories listed here:
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Getting Started Hardware: Information about the hardware on which the product is running, such as the: • brand and type of CPU • number of processors available • amount of memory available • brand and type of graphics card
System: Configuration information about the system the product is running on, such as the: • operating system and version • country code • time zone • language used • values of environment variables used by the product
Session: Characteristics of the session, such as the: • interactive or batch setting • time duration • total CPU time used • product license and license settings being used • product version and build identifiers • command line options used • number of processors used • amount of memory used • errors and warnings issued
Session Actions: Counts of certain user actions during a session, such as the number of: • project saves • restarts • meshing, solving, postprocessing, etc., actions • times the Help system is used • times wizards are used • toolbar selections
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The ANSYS Product Product Improvement Improvement Program Program Model: Statistics of the model used in the simulation, such as the: • number and types of entities used, such as nodes, elements, cells, surfaces, primitives, etc. • number of material types, loading types, boundary conditions, species, etc. • number and types of coordinate systems used • system of units used • dimensionality (1-D, 2-D, 3-D)
Analysis: Characteristics of the analysis, such as the: • physics types used • linear and nonlinear behaviors • time and frequency domains (static, steady-state, transient, modal, harmonic, etc.) • analysis options used
Solution: Characteristics of the solution performed, including: • the choice of solvers and solver options • the solution controls used, such as convergence criteria, precision settings, and tuning options • solver statistics such as the number of equations, number of load steps, number of design points,
etc. Specialty: Special options or features used, such as: • user-provided plug-ins and routines • coupling of analyses with other ANSYS products
Data We Do Not Collect The Product Improvement Program does not collect collect any information that can identify you personally, your company, company, or your intellectual property. This includes, but is not limited to: • names, addresses, or usernames • file names, part names, or other user-supplied labels • geometry- or design-specific inputs, such as coordinate values or locations, thicknesses, or other di-
mensional values • actual values of material properties, loadings, or any other real-valued user-supplied data
In addition to collecting only anonymous data, data , we make no record of where we collect data from. We therefore cannot associate collected data with any specific customer, company, or location.
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Getting Started
Opting Out of the Program You may stop your participation in the program any time you wish. To do so, so, select ANSYS Product Improvement Program from the Help menu. A dialog appears and asks if you want to continue participating in the program. Select No and then click OK. Data will no longer be collected or sent.
The ANSYS, Inc., Privacy Policy All ANSYS products are covered by the ANSYS, Inc., Privacy Policy. Policy.
Frequently Asked Questions 1. Am I required to participate in this program? No, your participation is voluntary. We encourage you to participate, however, however, as it helps us create products that will better meet your future needs. 2. Am I automatically enrolled e nrolled in this program? No. You are not enrolled unless you explicitly agree to participate. Does participating in this program put my intellectual property at risk of being collected or discovered by
3. ANSYS?
No. We do not collect any project-specific, company-specific, or model-specific information. 4. Can I stop participating even after I agree to participate? Yes, you Yes, you can stop participating par ticipating at any time. To do so, select ANSYS Product Improvement Program from the Help menu. A dialog appears and asks if you want to continue participating in the program. Select No and then click OK. Data will no longer be collected or sent. 5. Will participation in the program slow the performance of the product? No, the data collection does not affect the t he product performance in any significant way. The amount of data collected is very small. 6. How frequently is data collected and sent to ANSYS servers? The data is collected during each use session of the product. The collected data is sent to a secure server once per session, when you exit the product. 7. Is this program available in all ANSYS products? Not at this time, although we are adding it to more of our products at each release. The program is available in a product only if this ANSYS Product Improvement Program description appears in the product documentation, as it does here for this product. 8. If I enroll in the program for this product, am I automatically enrolled in the program for the other ANSYS products I use on the same machine?
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Graphical User Interface Yes. Your enrollment choice applies to all ANSYS products you use on the same mach machine. ine. Similarly, if you end your enrollment in the program for one product, you end your enrollment for all ANSYS products on that machine. 9. How is enrollment in the Product Improvement Program determined if I use ANSYS products in a cluster? In a cluster configuration, the Product Improvement Program enrollment is determined by the host machine setting. 10. Can I easily opt out of the Product Improvement Program for all clients in my network installation? Yes. Perform the following steps on the file server: a. Naviga Navigate te to to the installa installatio tion n direct directory: ory: [Drive:]\v202\commonfiles\globalsettings b. Open Open th the e fil file e ANSYSProductImprovementProgram.txt. c. Change Change the value value from from "on" "on" to to "off" "off" and save save the the file. file.
1.3. Graphical User Interface The user interface is split into the following parts: 1.3.1. Menus 1.3.2.Tre 1.3.2. Tree e View 1.3.3. Scene 1.3.4.Toolbar 1.3.5.View Panes The interface also contains View P Panes anes (p. (p. 33) 33) that that show how individual elements within the ACP interface can be rearranged.
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Getting Started Figure 1.2: ANSYS Composite PrepPost GUI
1.3.1. Menus ACP (Pre) provides the following menu options: Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information
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Graphical User Interface 1.3.1.1. File 1.3.1.2.View 1.3.1.3.Tools 1.3.1.4. Units Figure 1.3: ANSYS Composite PrepPost Menu Options
1.3.1.1. File The File menu differs between Workbench and Stand Alone mode. 1.3.1.1.1.Workbench
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Getting Started 1.3.1.1.2. Stand Alone
1.3.1.1.1.Workbench When you launch ACP (Pre) from Workbench, the File menu contains the following options: Save Project: If the project was not already saved, specify the project name and location.
Saves the entire Workbench project. Refresh All Data: Reloads the Model in ACP. If the model is not up-to-date in the Workbench schematic, changes on the model (mesh, named selections) are not transferred to ACP. If you have made changes to the model, close ACP and update the model in Workbench. Run Script: Select a Python script to execute. Exit: Exit from ANSYS Composite PrepPost. Any newly defined ACP features are not de-
leted. Figure 1.4: File Menu for Workbench Integration
1.3.1.1.2. Stand Alone When you open the application in stand alone mode (via the Start menu), the File menu contains the following options: Open: Open an existing database. Save: Save the active database. Save As: Save the active database, select location and file name. Save All: Save all open databases. Close: Close the active database. Close All: Close all open databases. Import Model: Import an ANSYS model. Run Script: Select a Python script to execute. Exit: Exit from ANSYS Composite PrepPost. Any newly defined ACP Features are not de-
leted.
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Graphical User Interface Figure 1.5: Stand Alone File Menu
1.3.1.2.View The layout of the GUI is managed through the View menu. 1.3.1.2.1. Perspectives 1.3.1.2.2.View Manager Figure Figur e 1.6: View Menu Menu
1.3.1.2.1. Perspectives The Perspectives submenu allows you to manage different interface layouts: Perspective:
Activate named Perspective. Available perspectives appear in a list in the drop down menu. New Perspective: Create a new perspective. Save Perspective As: Save the current interface layout into a new perspective. Rename Perspective: Modify the name of the active perspective. Delete Perspective: Delete the active perspective. Reset Perspective: Reset the active perspective to an empty perspective. Reset All Perspectives: Reset all defined perspectives.
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Getting Started Figure 1.7: Perspective Submenu
1.3.1.2.2.View Manager Interface elements can be added or removed from a perspective by clicking Other... to bring up the View Manager. To activate a view, view, select it in the View Manager and click OK. The selected view appears in the View menu for the selected perspective. Views present in the perspective perspective can be activated or deactivated through the View menu. when migrating Workbench archives from previous version Figure 1.8: Show View
1.3.1.3.Tools The Tools menu enables you to change global settings: 1.3.1.3.1. Logger Settings 1.3.1.3.2. Preferences 1.3.1.3.3. Scene
1.3.1.3.1. Logger Settings The logger settings allow you to set the severity level of messages displayed in the log window. The levels are:
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Graphical User Interface
Debug: Log everything, including debugging information. Info (default): Log everything, except debugging information. Warning: Log errors and warnings. Error: Log errors only. Critical: Not used. Figure 1.9: Logger Preferences
1.3.1.3.2. Preferences In the main ACP heading, the following options are available: ANSYS Executable Path: Path to the ansys.exe file (solver). If empty, ACP uses the default
path from the installation. ANSYS License: Defines which license used to solve the model. For more information on licenses, see the ANSYS Product to License Feature Mapping table located on InThe Feature Name (from the ANSYS stallation and Licensing page of the ANSYS Help. The
Product to License Feature Mapping Table) should be typed in this field. For example, enter ane3fl for an ANSYS Multiphysics License. By default, the ANSYS License field is empty, in which case ACP uses the order of licenses defined in the LM Center. Center. Number of Threads to Use in Parallel: Specifies the number of cores/threads used for computation. ACP uses all available cores when the option is zero (default). H5 Compression Level: Specify the GZip compression level of HDF5 (storage format of
ACP). The default setting is 2. This setting pro provides vides good compression compression at an overhead of about 35% when compared to no compression (setting of 0). The highest available setting is 9. Note that processing requirements increase based on this setting. You will notice an increase in processing times with a setting of 4 and above. above. You need to evaluate the benefits of increased processing time versus file size reduction.
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Getting Started Figure 1.10: General ACP Preferences
1.3.1.3.2.1. Submenus The following submenus allow you to change global defaults: Units: Define solver units. Material Database: Define the path to the material database (.acpMdb file).
(p. 3) 3).. add-ons (p. Add-Ons: Activate or deactivate the available add-ons Section Generation: Define default tolerance values for the generation of sections
and the minimum analysis ply thickness. For more information see Layup Computation tio n (p. (p. 58) 58).. ANSYS Product Improvement Program: Here you can opt to participate in the ANSYS
Product Improvement Program. Refer to the section ANSYS Product Improvement Program Prog ram (p. (p. 5) 5) for for complete information. The option applies only to workflows in ACP standalone operation. For Workbench workflows, you must opt into the ANSYS Product Improvement Program using the Workbench settings.
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Graphical User Interface Figure 1.11: Section Generation Preferences
1.3.1.3.3. Scene In the Scene heading, some graphical properties of the model display can be modified. These properties are grouped in three parts: 1.3.1.3.3.1. Appearance 1.3.1.3.3.2. Screenshot 1.3.1.3.3.3. Interaction Figure 1.12: Scene Preferences
1.3.1.3.3.1. Appearance Background color of the scene window can be defined as uniform or as a gradient from bottom to top. To obtain a uniform background, Background Color and Background Color 2 should have the same color definition. When defining a top to bottom gradient, Background Color is the bottom color and Background Color 2 is the top color. To modify these colors click Edit.
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Getting Started
1.3.1.3.3.2. Screenshot By default, the size of the image captured by the snapshot utility has the same size as the scene size. The size of the captured captured image can be fixed to a certain dimensio dimension. n. This option shou should ld be used carefully. By default, the Anti-Aliasing option is active. On some hardware, this option may slow down image creation. If you are experiencing difficulty taking screenshots, turn the Anti-Aliasing option off.
1.3.1.3.3.3. Interaction Two mouse interaction styles are available in ACP. ACP. The default style (ANSYS) is the same as the interaction in ANSYS Workbench. Workbench. The two interaction styles are described in the table below: Interaction Style Action
ANSYS
Mouse Only
Pan
Ctrl+MB drag
MB drag
Dolly-Zoom
Wheel/Shift+MB drag
MB drag+RB click/MB drag+LB click
Box-Dolly-Zoom
RB drag
Rotate Spin
MB drag
MB+RB MB+RB/MB+LB drag close to border
Pick
LB click
LB click/RB click
Box-Pick
LB drag
LB drag/RB drag
Rotation Point
MB click/Shift + LB click
MB click
Reset • (L,M,R)B denotes left, middle, and right mouse button respectively • + denotes concurrent execution
1.3.1.4. Units You use the Units menu to change the active unit system.
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Graphical User Interface Figure 1.13: Units Menu
The unit system can only be altered in preprocessing, it is locked in shared mode and postprocessing. When changing from a predefined unit system to Undefined, or vice versa, no conversions take place. The unit system of the active model is displayed in the status bar at the bottom of the ACP window. Table 1.1: Predefined Unit Systems Name
BFT
2
Length Mass
ft
Time Length*Mass/Time Temperature Currency
slug
s
lbf
F
USD
2
BIN
in
1/in*lbf/s s
lbf
F
USD
CGS
cm
g
s
dyn
C
USD
MKS
m
kg
s
N
K
USD
MPA MP A
mm
t
s
N
C
USD
SI
m
kg
s
N
K
USD
UMKS
µm
kg
s
µN
C
USD
-
-
-
-
-
Undefined -
1.3.2. Tree View 1.3.2.T The underlying Python Object TTree ree (p. 397) 397) is is mapped into the graphical tree view. It provides an easy way of selecting objects or viewing/modifying the state of an object. An explanation on how to modify specific objects in the tree is provided in the Usage Referenc Reference e (p. 53) 53).. Most tree objects are associated with a context menu, which can be displayed by right-clicking the object. Double-clicking a tree object directly opens the Properties dialog for that object - providing a shortcut from opening the context menu. The tree view is accompanied with a toolbar that is located at the top of the tree view. The following functions are available:
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Getting Started • Search allows you to search for tree objects which have a name matching the search string. • The collapse button folds the tree back into its original state.
Note: The search is case-insensitive and requires an exact match. Special characters are not treated as wild cards and are not ignored in the search and object name strings. For example, a search for "test object 1" will not return a match for an object named test_ob ject_1. Similarly, a search for "test_object_*" will not return a match for and object named test_object_1.
Caution: Care should be taken when defining objects while tree filtering is active. The object selection must be consistent with what is displayed in the filtered tree. It is recommended that you clear any tree filters while defining new objects.
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Graphical User Interface Figure Figur e 1.14: Tree View
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Getting Started A status symbol appears for each item. Figure 1.15: Locked Rosettes and the Update Status
: Rosette is locked and up-to-date. : Rosette is locked but not up-to-date. : Rosette is updated. : Rosette is hidden. : Rosette is not updated. It can be updated with the general update in the toolbar or context menu. The symbol indicates that this object is defined, but inactive and therefore not considered in any evaluation. Modeling Plies, Solid Models and Analysis Plies can be inactive. You can can move through the tree using the arrow keys. The sub-trees are automatically reduced and expanded. e (p. 53) 53)).). Special shortcuts exist for the Modeling Group. For more information, see Usage Referenc Reference
1.3.3. Scene The scene contains a 3D graphical representation of the model and all defined entities. There is no limit to the number of scenes that can be created, and changing from one scene to another can be done with a single click. You can navigate through the scene by mouse or keyboard input. For For more information, see Scene Mani Manipulatio pulation n (p. 22) 22).. (p. 18) 18).. For more information on mouse interactions, see Interaction Interaction (p.
1.3.3.1. Scene Manipulation The view of the scene can be manipulated using several buttons on the toolbar: : Standard views along each axis. : Zoom to fit the model. : View full-scre full-screen. en. : Active or deactivate perspective. : Capture screenshot.
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Graphical User Interface
1.3.4.Toolbar The toolbar interacts with the scene by modifying modi fying camera views or displaying or hiding elements: 1.3.4.1. Updates 1.3.4.2. Edit Entities with Excel 1.3.4.3. Mesh Appearance 1.3.4.4. Orientation Visualization 1.3.4.5. Fiber Directions 1.3.4.6. Draping 1.3.4.7. Other Features 1.3.4.8. Postprocessing
1.3.4.1. Updates After some operations (for example, reloading the model, modification of one or more plies, or activat acti vating ing postpr postproce ocessin ssing), g), an upda update te (
) of the scene scene is is neces necessary sary..
1.3.4.2. Edit Entities with Excel : Create, edit, or save the entities such as Look-up Tables or Modeling Plies with Excel. The Excel Link interface allows you to define, modify, or save s ave the layup definition in an Excel spreadsheet. The layup can be transferred to to a spreadsheet using the push function or a layup which has been defined in a spreadsheet can be imported into ACP using the pull function. By default, all layup data is synchronized between Excel and ACP. Alternatively, you can select specific modeling groups for which the layup is synchronized. In addition, Pull Mode controls how the layup is transferred to ACP. ACP. The layup can be linked to a new spreadsheet or to an existing one. The latter functionality gives you the ability to restore a layup from pre-defined data.
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Getting Started Figure 1.16: Excel Link Dialog
The main functions of the Excel Link are: • Open Excel: Open an existing Excel file if specified. If no path is specified, a new worksheet is opened
and filled with the current layup information. • Push to: Sync layup definition data from ACP to Excel. • Pull from: Read definition data from Excel and update the definition in ACP. • Close All: Close Excel and the ACP Dialog Box
The following options are available for Pull Mode: • Update Entities: During a Pull from operation, definitions are updated, additional plies are generated
and deleted according to Excel data. • Update Properties Only: During a Pull from operation, definitions are updated with properties given. • Recreate Entities: During a Pull from operation, existing lay-up is deleted and generated from scratch.
The ACP tree order corresponds to the Excel spreadsheet order.
1.3.4.3. Mesh Appearance Appearance of the mesh can be modified using several buttons on the toolbar: : Show or hide element edges. : Activate or deactivate shaded view. : Highlight elements. : Change highlighted elements between solid and shell elements. : Highlight silhouette of selected elements even if it is hidden by mesh.
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Graphical User Interface
: Display probe values when hovering over model.
1.3.4.4. Orientation Visualization You can display the surface orientations using the orientation buttons on the toolbar. Figure 1.17: Orientation Visualizations in the Toolbar
: Display element normals or normal direction of CAD geometry parts. Figure Figur e 1.18: Visualization Visualization of the Element Normals
: Display orientation of an Oriented Selection Set (OSS).
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Getting Started Figure Figur e 1.19: Visualization Visualization of the OSS Normal
: Display reference direction of an Oriented Selection Set (OSS). Figure 1.20: Visualization of the OSS Reference Direction
1.3.4.5. Fiber Directions The ply angles can be visualized with the fiber direction buttons on the toolbar.
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Graphical User Interface Figure 1.21: Fiber Directions in the Toolbar
: Display the fiber direction of the selected ply. Figure Figur e 1.22: Visualization Visualization of the Fiber Direction
: Display the transverse ply direction.
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Getting Started Figure 1.23: Visualization of the Transverse Transverse Ply Direction
1.3.4.6. Draping You can highlight the draping effect by comparing the fiber direction (see Fiber Fiber Directions Directions (p. 26) 26))) with the draped fiber direction as well as the transverse fiber direction with the transverse draped (p. 68) 68) property property is active, its effect can be visufiber direction. Moreover, if the Fabric Fabric Fiber Angle (p. alized by plotting the Material 1 Direction of the selected analysis ply. Figure 1.24: Draping Directions in the Toolbar
: Plot Draped Fiber Directions.
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Graphical User Interface Figure 1.25: Fiber Directions (Defined and Draped)
: Plot Draped Transverse Fiber Directions.
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Getting Started Figure 1.26: Traverse Traverse Directions (Defined and Draped)
: Plot Material 1 Directions.
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Graphical User Interface Figure 1.27: Material 1 Direction and Draped Fiber Direction for a Material with a 45° Fabric Fiber Angle
1.3.4.7. Other Features The toolbar displays the following additional features: •
: Display or hide the coordinate system axis. A coordinate system axis is displayed by default in the bottom left corner of the graphics window for a better 3-D orientation.
•
: Plot box with coordinate system.
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Getting Started Figure 1.28: Enclosed Box and Coordinate System
•
: Distance measure tool. Select two points of the mesh and the distance and point coordinates will be displayed in the bottom left. Figure 1.29: Distance Measure Tool
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Graphical User Interface
1.3.4.8. Postprocessing Some features of the toolbar are only available during postprocessing: : Display or hide the legend. : Display or hide the failure criteria text. : Display or hide the plot description.
1.3.5.View Panes The view panes displayed at the bottom of the interface contain specific information about the processes performed. You can rearrange the views using drag and drop. A red highlight displays the new (drop) position for placing the view. Each view is described below.
Shell View All commands performed through GUI interactions are executed by the internal Python interpreter. The same commands can be entered manually in the Shell View V iew window. The Shell View window also provides standard text editing features such as copy and paste, history, and tab completing. A detailed overview about scripting in ACP and a command reference can be found in ACP Python Scripting Scripti ng User Interface Interface (p. 395) 395).. Code Completing and Help
The period (".") activates the code completing. Use the Up Arrow, Down Arrow, or the mouse to navigate through the drop-down menu. [TAB], [ENTER] or double-clicking inserts the selected command.
Enter an opening parentheses "(" to get help on the selected method. Press [ENTER] to insert the function header.
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Getting Started
The context menu of the Shell View V iew windows is accessible by a right-click and it allows you to copy and paste commands. Use "Paste and Run" to execute multi-line or multiple statements.
Hot Keys
Here is the list of hot keys of the Shell View window that allow you to access the history, copy and paste commands, etc. Selection Hot Key Home
Description
End
Go to the end of the line.
Shift+Home
Select back to the beginning of the command or line.
Shift+End
Select to the end of the line.
Go to the beginning of the command or line.
Copy and Paste Hot Key
Description
Ctrl+C
Copy selected text, removing prompts.
Ctrl+Shift+C
Copy selected text, retaining prompts.
Ctrl+V Ctrl+Shift+V
Paste from clipboard. Paste and run multiple commands from clipboard.
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Implementation in Workbench History Hot Key
Description
Ctrl+Up+Arrow
Retrieve previous history item.
Ctrl+Down+Arrow
Retrieve next history item.
Shift+Up+Arrow
Insert previous history item.
Shift+Down+Arrow
Insert next history item.
Font Size Hot Key
Description
Ctrl+]
Increase font size.
Ctrl+[
Decrease font size.
Ctrl+Wheel
Edit font size.
Ctrl+=
Default font size.
Logger The information saved in the file %APP_DATA%\Ansys\v202\acp\ACP.log is shown in this View. Logger er Settings Settings (p. 14) 14).. The severity level of the logged events is defined in Logg
History View All commands processed during the existing session are stored in the Python command history. history. They can be inspected in the History View window, where each text line refers to an executed command. The command history is also available in the Shell View V iew by using the Ctrl+Up/Ctrl+Down keys.
1.4. Implementation in Workbench In Workbench, the ACP analysis component can be used from basic analysis to complex load cases and analyses. The following sections contain some examples of common use of the ACP analysis system. 1.4.1. Basic Workflow 1.4.2. ACP Component Properties 1.4.3. Supported Analysis Types 1.4.4. Multiple Multiple Load Cases and Analyses 1.4.5. Shared Composite Definition for Different Models 1.4.6. Solid Modeling 1.4.7. Assembly
1.4.1. Basic Workflow A composite shell defined using ACP be imported Mechanical for aanalysis by importing mesh and composite definitions fromcan an upstream ACPinto system. To import composite shell fromthe ACP into Mechanical, use the following procedure:
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Getting Started 1. From th the Component Systems list, drag and drop an ACP (Pre) system into the Project Schematic. Fore more information on Component Properties available in Workbench, see ACP Component Properties erti es (p. (p. 39) 39).. 2. Se Sellect the Geometry cell and specify your geometry. Make sure that you properly define your mesh, Named Selections, etc. before opening the geometry in ACP. Note that ACP only uses a linear or quadratic shell mesh. Setup cell 3. needed, Se Sellect the of theModel ACP system. Right-click the cell and select the Properties activate the Load Properties optionon contained in the Geometry category option. of the As Properties of Schematic. Selecting this property makes your geometry available in ACP's CAD Geometries (p (p.. 86 86)) object.
4. Pe Perfor rform m all of the the steps steps to fully fully define define your your ACP (Pre) system. 5. Return to the the Workbench Workbench.. Drag and drop drop a supported supported Mechanical Mechanical system system into the Project Schematic. 6. Drag Drag an and d dro drop p the the ACP (Pre) Setup cell onto the Mechanical system Model cell to create a transfer of the model. A pop-up gives you to options Transfer Solid Composite Data or Transfer Shell Composite Data. The connection enables the transfer of Mesh, Geometry, Engineering Data, and composite definitions from ACP to Mechanical. When you create this link, the Geometry and Engineering Data cells no longer display for the Mechanical system. ACP provides this system data.
7. Doub Double le-c -cli lick ck the the Model cell of the Mechanical system. In the Mechanical application, an Imported Plies object is already inserted. Analysis Ply objects, corresponding to the Analysis Plies in ACP, are created under the Imported Plies object. The Analysis Ply objects are grouped in Production Plies, and Production Plies are further grouped into Modeling Plies to mimic the ply structure defined in ACP:
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Implementation in Workbench
8. Perform Perform all the steps to to fully define and solve the the Mechanical Mechanical system. system. The following should be noted when performing an analysis with imported ACP data: d ata: • Since the mesh is imported from an upstream ACP system, any operations that affect the mesh state
are blocked inside Mechanical. • It is recommended that you do not edit the mesh inside Mechanical; however, the Clear Generated
Data option is available on the Mesh object and performs the action of cleaning up the imported mesh. mes h. The Generate Mesh /Update operation restores the imported mesh that was previously
modified. • Since the material is assigned to elements/bodies through the upstream ACP system, the Material Assignment field is read-only and set to Composite Material. • If the Setup cell of the upstream ACP system is modified, refreshing the downstream Model re-imports
the meshes and resynthesizes the geometry. geometry. This action has the following effects: – Any properties set on the bodies imported from the ACP system are reset to default. – For solids, any scoping to geometry (bodies/faces/edges/vertices) is lost and any loads/boundary
conditions scoping to geometry are lost.
Tip: Any criterion-based Named Selections defined in the downstream Mechanical system are updated on refresh after any modification in the upstream ACP system. Since criterion-based Named Selections are automatically updated, and any direct scoping is lost, you should create criterion-based Named Selections and then scope any loads or
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Getting Started
boundary conditions to these Named Selections. This will result in p persistence ersistence of scoping during modify/refresh operations.
9. Review the results. results. Layered Layered results can be reviewed reviewed in Mechanical or in ACP-Post. ACP-Post. For postproc postprocessing essing in Mechanical, see Surface Body Results (including Layered Shell Results) and Results) and the Composite Failure Tool T ool.. To utilize additional postprocessing capabilities within the ACP application, drag an ACP (Post) system the ACP (Pre) the ACPonto (Post) Results cell.Model cell, and connect the Solution cell of the Mechanical system onto
Analyses that require upstream results from also supported and can be transferred from Eigenvalue the solution.Buckling or Pre-Stress Modal analyses are
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Implementation in Workbench
1.4.2. ACP Component Properties The following section describes properties of an ACP Component in Workbench. Properties can be accessed through the right-click context menu over each component cell, as shown below in Figure 1.30: Properties Properties from Right-Click Context Menu (p. 40) 40)..
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Getting Started Figure 1.30: Properties from Right-Click Context Menu
Properties operties Menu: Menu : Setup (p. 40) 40),, the From the Setup Properties Menu, shown below in Figure 1.31: Pr following options are available. Figure 1.31: Properties Menu: Setup
• Load Model Geometry: Imports the geometry from ACP's Mechanical model.
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Implementation in Workbench • Editor Startup Timeout (s): Timeout to catch an ACP start-up error. (Example: No license is available.)
You can increase this value to account for license server delays. • Batch Mode: Specifies the Batch Mode of ACP between True Batch Mode and GUI Without Window.
By default, ACP runs in True Batch Mode so it can support cluster environments (Windows or Linux) where no graphics support is present. Note that ACP Snapshot functionality is only supported in the GUI Without Window option. If your analysis is generating snapshots and is run by mistake in True Batch Mode, the analysis will still run to completion. Notice that the Editor Startup Timeout and Batch Mode options are also available in the ACP Post properties.
1.4.3. Supported Analysis Types The ACP (Pre) system can be linked with the following Mechanical analysis systems: • Static Structural • Transient Structural Struc tural • Steady-State Thermal • Transient Thermal • Modal • Harmonic Response • Random Vibration • Response Spectrum • Eigenvalue Buckling • Explicit (LS-DYNA)
ACPsystems: (Post) system cannot post-process all analysis types. It supports the following Mechanical The analysis • Static Structural • Transient Structural Struc tural • Steady-State Thermal • Transient Thermal
Note: • Although both Structural and Thermal layer modeling are available, the particular degrees
of freedom results on corresponding layers could behave differently in structural and thermal environments. For more information, see the Element Reference for the specific elements, particularly SOLID185 SOLID185 and and SOLID278. SOLID278.
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Getting Started
• Steady-State Thermal and Transient Thermal analysis systems are fully supported by the solid
workflow (p. workflow (p. 43) only. For the shell workflow, the number of layers per element is limited to 31 for a linear temperature distribution through-the-thickness and 15 for a quadratic distribution.
1.4.4. Multiple Load Cases and Analyses Complex workflows with multiple load cases and/or analyses are defined in the same way as standard analyses. In most of the cases, the links to share the data are set automatically by Workbench. Some links must be manually added. In the following example, the links from the Solution cells of analyses B and C to the ACP (Post) system have been added manually. Figure 1.32: Multiple Load Cases and Analyses
1.4.5. Shared Composite Definition for Different Models The ACP (Pre) ( Pre) Setup cell can be shared across multiple models. This means the same composite layup can be applied to models of different geometries and meshes. This functionality can be used in design studies where the composite definition remains the same but different geometries are evaluated. Submodeling another situation this functionality can isbedragged used. Inon a scenario where two models are to isshare the same ACPwhere (Pre) Setup, one setup cell to the other. ACP maps as much information onto the second model as possible. It is advised to use common Named Selections
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Implementation in Workbench as well as the same Engineering Data. The figure below shows an example of a shared ACP (Pre) setup. Figure 1.33: Two Two Analyses Share the Same ACP (Pre) Setup
1.4.6. Solid Modeling Similar to composite shells, composite solids defined using ACP can be imported into Mechanical for analysis by importing the mesh from upstream ACP systems and synthesizing the geometry from the imported meshes. The import of a composite solid from A ACP CP into Mechanical follows the same procedure for shells except that the transfer option Transfer Solid Composite Data must be selected as shown below.
ACP distinguishes between two different approaches: the first approach is an extrusion algorithm that generates a solid mesh based on the Composite Definitions and the shell reference surface. This Solid Model (p. 163) (p. 163). In this scenario theModeling solid mesh completely generated feature simply Model refer Guide of Solid deling (p. is (p. 285) and 285) and the Analysis of by ACP is (Pre). For called more information, to .the Mo a Composite Composite Solid Model (p. (p. 312) 312) sections sections of the Help.
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Getting Started In the second approach, the Composite Definitions are mapped onto an external solid mesh that is loaded in ACP. ACP. This feature is called Imported Imported Solid Model (p. (p. 189) 189)..
Load an External Solid Mesh in ACP (Pre) External solid meshes can be transferred to ACP (Pre) by linking a Mechanical Model component to ACP Setup as shown in the Figure Figure below. This allows to map the composite definitions onto the Imported Solid Solid Model. (p. (p. 189) Figure 1.34: Import Volume Mesh from Mechanical Model (E4 to C5)
Solid meshes from third party applications can also be loaded into ACP (Pre). In that scenario the mesh is loaded via External Model and Mechanical Model as shown in the next figure. Figure 1.35: Import Volume Mesh from Third Party Application
Note: • The internal link between Mechanical Model and ACP Setup within an ACP (Pre) system C4
to C5 in the figure above always transfers the shell mesh only.
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Implementation in Workbench
• Imported solid models can only be post-processed in Mechanical via the Composite Failure
Tool.. Tool
1.4.7. Assembly Meshes can be imported into Mechanical from multiple systems. It is possible to combine composite shell, composite solid, and non-layered shell and solid meshes to perform mixed analysis. Mechanical does not allow overlap of node/element number from multiple systems; therefore the import fails if the meshes from different systems are overlapping in node/element numbers. Meshes from upstream to downstream Mechanical Models are renumbered automatically to avoid any overlap. For every analysis system (mesh), you have the choice between automatic renumbering (default) and manual configuration. If automatic renumbering is disabled, you must ensure that the element/node numbering is unique for each mesh.
The Properties menu of the Mechanical Model allows you to turn automatic renumbering on or off and also to change the transfer type of ACP (Pre) systems from shell to solid.
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Getting Started
To create a mixed assembly: 1. From From the Analysis Systems Systems panel panel,, drag drag and drop an ACP (Pre) (Pre) analysis analysis system into the the project schemschematic. 2. Drag and drop drop a supported supported Mechanical Mechanical system system into the the project project schematic schematic and create create a link from the ACP (Pre) Setup cell to the Mechanical Model cell. 3. Add other other ACP ACP (Pre) (Pre) syst systems ems as as needed needed.. 4. Drag and drop drop a Mechanical Mechanical Model Model component component into into the project project schematic schematic for the the non-layered non-layered parts. parts. Create a transfer link from the Model cell of the upstream system to the Model cell of any downstream systems. 5. Double Double-cl -click ick the downstr downstream eam Model cell to edit the model. For every upstream mesh, a Geometry , Imported Plies, and Named Selections folder are inserted in the tree view of Mechanical.
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Migrating ACP Projects from Previous Versions
6. Perform Perform all the steps to to fully define and solve the the Mechanical Mechanical analysis analysis system. system.
Limitations A connection from an upstream ACP (Pre) Setup or Mechanical Model cell is only possible if the Engineering Data cell of the intended downstream Mechanical system is not modified. If the Engineering Data cell of the downstream system is modified by creating/modifying an existing material in the Engineering Data interface, a data transfer cannot be created.
1.5. Migrating ACP Projects from Previous Versions Versions General Updates In Version Version 2019 R2, the coordinate system naming is maintained between Mechanical and ACP. ACP. When migrating Workbench archives from previous versions, minor manual input may be required to maintain Rosette reference links. See Known Limitation Limitationss (p. 3) 3) for for more information. A new serialization format for ACP was introduced in Version 2019 R1 in order to improve performance and usability. Therefore, any ACP database created with version version 19.2 or older must upgraded. The sections below describe how to upgrade ACP projects from previous versions:
ACP into Workbench When opening ACP projects generated in a previous version, you should do a Clear Generated Data on the ACP (Pre) Setup cell. Upgrading Projects from Version 17.1 or Older
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Getting Started Projects older then version 17.2 should be opened and saved in any version from 17.2 to 19.2 to ensure a robust upgrade to the current release. Please ensure that every ACP-Pre, -Shared, and -Post system is completely updated and saved. This intermediate upgrade is supported starting from version 14.0. Upgrading Projects from Versions 17.2 to 19.2 to the Current Release
If you open or restore a Workbench project that has been created with any version from 17.2 to 19.2, then the ACP systems turn to a `refresh `refresh required` state. This ensures that the upgrade happens automatically on refresh or update of thebefore ACP systems. ACP This also leads to the situation ACP-Post and Shared systems cannot be launched the corresponding (upstream) ACP-Prethat system has been updated. Once the upgrade is done, up-to-date status, etc. are maintained. Miscellaneous
Version 17.0 introduced a new workflow for ACP (composites). (composites). The existing workflow from previous versions is still valid. If you wish to upgrade your projects from previous versions to the new composite workflow, please contact your technical support representative.
ACP Standalone Upgrading ACP Databases from Version 17.1 or Older
ACP databases older then version 17.2 should be opened and saved in any version from 17.2 to 19.2 to ensure a robust upgrade to the current release. Upgrading ACP Databases from Versions 17.2 to 19.2 to the Current Release
ACP models that have been generated with any version from 17.2 to 19.2 can be upgraded easily. Open the *.acp file in the current release and perform a `Save As` in order to generate the new *.acph5 database file.
Python UI Version 18.0 changed the material scripting interface for ACP. A material's properties (for example engineering constants and stress and strain limits) are no longer members of the Material class, but each property forms its own class instance of the type PropertySet. This is to better reflect the individually closed data basis for data interpolation in case the properties depend on user-defined field variables Composite Analyses (p. 300) 300)).). The PropertySet PropertySet instances can be accessed (see Variable Material Data in Composite by their string key on the Material class. ACP scripts using materials must be updated to be compatible with the new material properties. In 2019 R1, The model attribute attribute create_cad_selection_rule() has been replaced with create_geometrical_selection_rule(geometrical_rule_type='geometry') . Scripts that used the CAD Selection Rule in previous versions need to be adapted accordingly for this release.
1.6. Stand Alone Operation ACP can be used as a Stand Alone application. This section describes how ACP can be operated in Stand Alone mode. It is important to know that the Stand Alone mode does not support all features that are available within Workbench (For instance, the user fields and variable materials are not supported.)
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Stand Alone Operation Version 2019 R1 introduced a new serialization format. This changes the handling of external sources (shell input mesh or CAD geometries) when ACP is run in standalone mode. Modifications of the input files are no longer automatically detected by ACP and are not considered on update or open. Therefore, you must refresh the inputs explicitly: • Reference Surface (shell): perform a Reload of the model (Model> Reload) • CAD Geometry: press Refresh button in the property dialog of the object • Imported Solid Model (solid mesh): press Refresh button in the property dialog of the object
1.6.1. Starting ACP in Windows 1.6.2. Starting ACP in Linux 1.6.3. Command Command Line Options and Batch Mode 1.6.4.Workflow 1.6.4. Workflow in Stand Alone Operation Operation
1.6.1. Starting ACP in Windows To start ACP in Stand Alone mode in Windows, Wi ndows, use the shortcut in the Start Menu. The shortcut can be found in Programs\ANSYS 2020 R2\ACP
1.6.2. Starting ACP in Linux On a standard installation, ACP can then be started by entering the following command into the command prompt: /ansys_inc/v202/ACP/ACP
(p. 49) 49) are are also valid in Command line options listed in Command Command Line Options and Batch Mode (p. Linux.
1.6.3. Command Line Options and Batch Mode ACP can also be used on a command command line level. The general usage of the ACP start script is: ACP.exe [options] [FILE]
The supported command line options are: Long Form
Short Form
Display the program’s version number and exit.
--version --help
Description
-h
--batch=BATCH_MODE -b
Display the program’s command line options and exit. Run ACP in Batch Mode.
BATCH_MODE
0 - Batch Mode disabled. 1 - True Batch Mode. (No GUI supported.) will be created. Snapshot functionality is not
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Getting Started Long Form
Short Form
Description
2 - Batch Mode with GUI toolkit but hidden window. (Snapshot functionality is supported.) --debug
-d
Enable debug output.
--num-t threads=NUM_THREADS NUM_THREADS
Number of threads to be used. 0 for max available threads.
--logfile=LOGFILE --mode=MODE
-o LOGFILE -m MODE
Specify file to be used for log messages. Application starts up in the specified mode (‘pre’, ‘shared’, or ‘post’).
--workbench
-w
Run ACP in Workbench mode.
--port=PORT
-p PORT
Specify port number for remote access server.
[FILE]
[FILE]
If the specified file is an ACP project, it is opened. If it is a Python script it is executed.
1.6.4. 1.6.4.W Workflow in Stand Alone Operation The difference between Stand Alone operation and WB Integration is that the several steps or operations have to be performed manually. The following is an overview of these steps: 1. Generate Generate the ANSYS input input file in Workbench Workbench or Mechanical Mechanical APDL, APDL, including including the loads and boundary boundary conditions (*.inp, *.dat or *.cdb). From Workbench:
In the Mechanical application, select the analysis and select Tools > Write Input File to write a *.dat or a *.inp file. Figure Figu re 1.36: Write Write Input File
Alternatively, in the project schematic, you can update the Setup status. A ds.dat file is written in the project folder SYS-X/MECH. This file can also be used as Pre-processing Model in ACP ACP.. From Mechanical APDL:
In Mechanical APDL, use the command CDWRITE to write a .cdb file, which can be used as a preprocessing model in ACP. cdwrite,db,file,cdb
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Stand Alone Operation 2. Start ACP 3. Import Import the the ANSYS ANSYS Model Model in ACP. ACP supports the .dat, .inp and .cdb file formats. Import the model into ACP by selecting File > Import Model or by right-clicking the Models object in the tree view and selecting Import Model. Figure 1.37: Import ANSYS Model Using the Context Menu
4. Define the the Materials, Materials, or copy copy the materials materials from the the ACP Material Material Databank. Databank. For more information on defining materials, see Materia Materiall Data (p. (p. 64) 64).. For more information on using the Material Databank, see Material Material Databank (p. (p. 233) 233).. 5. Crea Create te lamin laminat ate e seque sequenc nces es.. Reference erence (p. (p. 53) 53) and and Composite Modeling Techniques (p. 257) 257) for for detailed information. See Usage Ref 6. Update Update the model after after any change change in the ACP ACP definition definition (layup (layup definitions) definitions) or change change of the input input model. After any modification in the input model, the input file must be reloaded (see Mod Model el (p. (p. 54) 54)).). After any change in the ACP definition, the database must be updated. Use the Update (p. 23) button in the toolbar. 7. Send the mode modell to the ANSY ANSYSS solver solver (Solve Current Model) or export the new analysis file ( Save (p. 54) 54).. Analysis Model). For more information, see Model Model (p. 8. Switch Switch betw between een ACP ACP Pre Pre and and ACP Po Post. st. Click on the parent object in the tree view to switch between ACP Pre and ACP Post. You may also right click the parent object to call up the contextual menu and select ACP Post.
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Getting Started Figure 1.38: Switch Between ACP Pre and Post
9. Im Impo port rt the the res resul ults ts.. In the ACP Post mode, solutions can be imported to evaluate the strength of the composite structure. In the tree view, import the result files by right clicking the Solution object. See Solutions tio ns (p. 208 208)) for more details. 10. Perform Perform composite composite postprocessing. postprocessing. Use definitions definitions (p. (p. 207) 207) to to define which results are evaluated in postprocessing. Plot these values 227) for for representation on the geometry or use sampling points points (p. (p. 154) 154) for for represin the scene scene (p. 227) entation through the lay-up. 11. Save the composite composite definitions. definitions. Use the File menu or right-click the Models object in the tree view to use the contextual menu.
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Chapter 2: Usage Reference This chapter consists of the following sections: 2.1. Features 2.2. Postprocessing 2.3. Exchanging Exchanging Composite Definitions with Other Progr Programs ams
2.1. Features The features described are in the following sections: 2.1.1. Model 2.1.2. Material Data 2.1.3. Element Element and Edge Sets 2.1.4. Geometry 2.1.5. Rosettes 2.1.6. Look-Up Tables 2.1.7. Selection Rules 2.1.8. Oriented Oriented Selection Sets (OSS) 2.1.9. Modeling Groups 2.1.10. Imported Modeling Group 2.1.11. Field Definitions 2.1.12. Sampling Points 2.1.13. Section Cuts 2.1.14. Sensors 2.1.15. Solid Models 2.1.16. Layup Plots 2.1.17. Definitions 2.1.18. Solutions 2.1.19. Scenes 2.1.20.Views 2.1.21. Ply Book 2.1.22. Parameters 2.1.23. Material Databank
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Usage Reference
2.1.1. Model The right-click context menu of the model gives you access a ccess to model properties, save options, and import/export interface inter face options. The context menu options are different when A ACP CP is run in W Workbench orkbench compared to stand-alone mode. In Workbench mode, these options are: Figure 2.1: Model Context Menu in Workbench Mode
In stand-alone mode, the options are: Figure 2.2: Model Context Menu in Stand-Alone Mode
This is an overview of the items in the model context menu. Selected items are explained in more detail below. • Properties : Display the Model Properties dialog where information about the model, input file, tolerances
and unit system can be found and modified (see Model Pr Properties operties - General (p. (p. 55) 55))) • Update: Update the entire model. • Clear Generated Data: Delete all results of the previous update and remove the serialized cached data.
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Features • Save (Stand Alone only): Save the selected model. • Reload (Stand Alone only): Reload the input file into the database (return to the last saved state). • Close (Stand Alone only): Close the selected model. • Save Analysis Model (Stand Alone only): Save the ANSYS input file including the layup defined in ACP. • Save APDL Commands (Stand Alone only): Save the layup definition as APDL Command Macro, modifies
the model from isotropic material monolithic elements to orthotropic layered composite elements with some adjustments on results save. • Solve Current Model (Stand Alone only): Submit the ANSYS input file including the composite layup
definition to the ANSYS solver. • Export Composite Definitions to ACP File: Export the layup definitions to a different ACP file (see
File (p. 59) 59)).). Import/Export of ACP Composite Definitions File • Import Composite Definitions from ACP File: Import the layup definitions from an other ACP file (see
Import/Export of ACP Composite Definitions File File (p. 59) 59)).). • Export to HDF5 Composite CAE File : Export the mesh with the composite definitions to a .HDF5 file
(see Import From/Export to HDF5 HDF5 Composite CAE File File (p. 60) 60)).). • Import from HDF5 Composite CAE File : Import a mesh with composite definitions from a .HDF5 file
File (p. 60) 60)).). (see Import From/Export to HDF5 HDF5 Composite CAE File • Import Section Data from Legacy Model : Import section data from a Mechanical APDL legacy model
Dataa from Legacy Model Model (p. 60) 60)).). (see Import Section Dat
2.1.1.1. Model Properties - General The following figures show the Model Properties dialog window in both Workbench and Stand Alone mode.
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Usage Reference Figure 2.3: General Model Properties
In stand-alone mode, the Format, Input File Path, and Input File Unit System properties become editable and they are used to import the shell ref reference erence surface (shell mesh). The Model Statisticstab gives an overview of model statistics including number of materials, stack-ups, etc. The full list of 57) below. below. Model Statistics are shown in Figure 2.4: Model Statistics (p. 57)
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Features Figure 2.4: Model Statistics
2.1.1.1.1. ACP Model The ACP Model section of the Model Properties dialog displays the path to the ACP model file. The unit system of the ACP model is also displayed. This unit system can be changed in the Uni Units ts (p. (p. 18) 18) menu. menu. The selected unit system is displayed in the status bar at the bottom of the ACP window. The property Cache Update Results controls whether the update results (i.e ply extents, analysis plies, solid models) are stored as well. This allows the reopening of the most recently used layup model state and improves the application's application's performance. You can disable this feature in order to reduce the size of the .ACPH5results file. Note, if the feature is disabled, you will be prompted for a model update whenever the ACP Model is reopened.
2.1.1.1.2. Reference Surface The file path to the input file of the reference sur face is set in the Reference Surface section of the Model Properties dialog. In Workbench, the reference surface is automatically transferred to ACP in the ANSYS HDF format. In this case, the reference surface unit system is fixed. In Stand Alone mode, the input file path for the reference surface is set here. The input file can be a .DAT (generated by Workbench), .INP, or .CDB (generated by Mechanical APDL with CDWRITE). The unit system for the reference reference surface can be set if it is not defined in the input file. The unit system must be defined in Stand Alone mode when importing or exporting a model in .HDF5 format and also when exchanging material data with the database or ESAComp. The bounding box describes des cribes the dimensions of the reference sur face in xyz-space.
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Usage Reference
2.1.1.1.3. Layup Computation The options defined in this section are described below: Angle and Relative Thickness Tolerance
ACP transfers the composite definitions into Section Data so that they can be interpreted by ANSYS Mechanical. In the case of curved surfaces or draped laminates, sections may change continuously with every element as their orientations change. This generates a large amount of information which can reduce the performance of data transfers tran sfers and solvers. To avoid this, ACP ACP groups section data of multiple elements together within a certain tolerance range. The Angle Tolerance field sets the allowable ply angle tolerance between the same layers of neighboring neighb oring elements. The Relative Thickness Tolerance field applies to the individual layer thickness as well as the global layup thickness. For two elements to be included in the same section definition, the difference of the angle and the relative thickness of every single ply must be within the defined tolerance. Core materials are typically thicker than a laminate by a factor of 10 or more. As such, the thickness tolerance is defined as a relative rather than an absolute value. The default tolerance values values are very small compared with the manufacturing tolerances of composites. The loss of accuracy accuracy is negligible. Minimum Analysis Ply Thickness
Cutting operations used in ACP can cut an analysis ply to a thickness thinner than the specified ply thickness. For example, if a cut-off geometry intersects a ply at its vertical mid-point it will slice the ply in half. When the intersection occurs at ply boundaries, an extremely thin layer can appear as the result of geometric tolerances of CAD files. These extremely thin layers are of the order of magnitude of 109 and are purely purely the results of numerical imprecision. The Minimum Analysis Ply Thickness field sets a thickness threshold below which no such plies can arise. The global default values for the above mentioned tolerances and thickness are set in the section Submenus (p. 16) 16) but but can be overridden in the Model Properties dialog. Submenus (p. Use Nodal Thicknesses
variable e thickness (p. (p. 274) 274) and and ply tapering tapering (p. (p. 269) 269).. By default, the thicknesses ACP supports ply with variabl are evaluated at the element centers, but for ply tapering and cut-off operations it can be worthwhile to evaluate them on a per-node basis. This additional data further refines the layup representation in ACP and is used in shell and solid model analysis. The option Use Nodal Thicknesses enables the node-based thicknesses evaluation. For more information, see Elementvs. Node-base Node-based d Thicknesses (p. 61) 61).. Use Draping Offset Correction
By default, during draping simulation, the application lays the draping mesh on the reference surface of the model independently of the layup thickness. However, for thick laminates, such as sandwich structures, with ply tapering and drop-offs, this approach can lead to inaccurate results. If you enable the Use Draping Offset Correction option, the draping mesh follows the bottom offset (relative to the reference surface orientation) of the selected ply. This allows the application to account for the layup thickness and as a result provides a more accurate draping simulation. Enabling offset correction for thick and curved laminates also improves the precision of the boundary and area for the flat wrap of the ply.
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Features
2.1.1.1.4. Model Summary Global information about the model is displayed in this section of the dialog. The Number of Elements field includes both layered shell and layered solid elements.
2.1.1.2. Solve In Stand Alone mode the Model Properties dialog has a second tab: Solve. On it, you can define the file path of the analysis model and the working directory used by the solver. solver. The Solver Status and the Output File information are also located on the Solver tab. In the case of an incomplete run, warning and error massages from the solver can be found here. Figure 2.5: Solver Information (Solve.out)
2.1.1.3. Import/Export of ACP Composite Definitions File The ACP Composite Definitions file contains all the information stored in an ACP model. mod el. The model is defined in the ACP file in the ACP Python scripting language. During import, you will be asked specify how ACP should handle objects having the same name.
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Usage Reference Figure 2.6: Export Composite Definitions Window
Figure 2.7: Import Composite Definitions Window
2.1.1.4. Import From/Export to HDF5 Composite CAE File You can exchange composite models across different CAE and CAD platforms using the HDF5 Composite CAE specification. For more information, see HDF5 Composite Composite CAE Format (p. 241) 241)..
2.1.1.5. Import Section Data from Legacy Model The Import Section Data from Legacy Model menu option automatically loads the section data from a legacy Mechanical APDL layered shell model. It converts the data into standard ACP composite definitions. definitions. The conversion conversion is based on the element label labels. s. That means that the meshes of the legacy and ACP model have to be equal. See the Import of Legacy Mechanical APDL Composite Models (p. 249) 249) section section for a detailed explanation for importing legacy models.
Parameters The parameters for the menu include: the legacy file. • Path: This is the file path to the
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Features The Workbench framework does not allow ACP to add materials to the Workbench project during the import process. Therefore, the materials have to be created and/or imported in an upstream Engineering Data system before you can import the legacy model into ACP. This makes sure that a full transfer of the section-based lay-up of the legacy model is performed. forme d. The External Model component enables you to import materials easily (see Import (p. 249) 249)).). However, the material IDs get conof Legacy Mechanical APDL Composite Models (p. verted following a certain pattern. The Material ID pre- and suffix pr property operty of the import options allows you to define this pattern. The mapping is case independent. • Materials Mapping Mask : This area of the dialog provides the following entries: – Prefix: A text-based string displayed before the legacy material ID in Workbench. – Suffix: A text-based string displayed after the legacy material ID in Workbench.
2.1.1.6. Element- vs. Node-based Thicknesses By default, ACP stores the thicknesses per ply and element, in other words, the ply's thickness is constant per element. This representation is consistent with the solver capabilities of layered shells, since they do not support varying ply thickness within one element. Therefore, geometry features (for example thickness by geometry or taper edge) calculate the ply thickness at the element centers (element-based thicknesses). ACP also supports node-based thicknesses. When node-based thickness evaluation is enabled, thicknesses are evaluated supplementary to the element-based thicknesses. This involves some performance losses but gives benefits when working with tapered plies (see 131) and and Cut-off Cut-off Selection Rules (p. (p. 106) 106)).). Thickness (p. 131) Shell Layup
The differences between element- and node-based thicknesses are best explained with a tapered ply. The nominal ply covers the entire plate plate and a cut-off geometry defines the tapering as shown in the figure below. below. The figure on the left shows the element-based piercing where the ccomputed omputed ply thickness at the element centers is negative for the upper two elements (red arrows). The right image shoes the node-based piercing that brings a more precise resolution. In that specific case, all elements have at least one node with a positive (valid) thickness. Figure 2.8: Element-based vs. Node-based Piercing
The final result for both optiomns is shown in the following figure. The ply is cropped if the thicknesses are only evaluated at the element corners since two elements have a negative thickness. In
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Usage Reference contrast, the ply covers the entire plate if the thicknesses are evaluated for each node because at least one node of each element has a valid ply thickness. If the node-based piercing determines that only some nodes of an element have a valid piercing but not the element center, then the thickness at the element center becomes the average node-based thickness. Figure 2.9: Ply Extension and Element-wise Thicknesses of a Tapered Ply with Element-based (left) and Node-based (right) Thicknesses
In summary, node-based thicknesses bring some benefit for shell models but also bring certain restrictions. Node-based thicknesses cannot be evaluated if a ply covers more than two components, as shown in the figure below. In other words, a ply is not allowed to cover three elements that share one edge. Figure 2.10: Restriction for Node-based Thicknesses
Solid Extrusion
The usage of node-based thicknesses brings more benefits if you perform a solid model analysis when compared to a shell analysis because the extrusion of the solid model is performed on a pernode basis. Additionally, layered solid elements support plies with variable thickness. The figure below shows the solid model from an example discussed in a previous section. As for the shell model, the solid model with element-based thicknesses does not cover the entire reference surface. In contrast, the node-based extrusion represents the ply extension more precisely. Additionally, it also captures the variable ply thickness over one element and therefore reproduces the taper much better.
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Features Figure 2.11: Extrusion of a Tapered Ply without and with Node-based Thicknesses on the Left and Right, Respectively
There are two additional examples where you can ca n benefit from node-based thicknesses: • Tapered edge: Only nodal thicknesses can represent tapers with 0 thickness correctly.
Figure 2.12: Solid Model Extrusion of a Tapered Ply without and with Node-based Thicknesses
• Cut-off selection rules with ply tapering: By default, tapering evaluated at the element centers can
cause ripples in the extrusion. Node-based thicknesses result in a smoother shape and more accurate ply representation. In this specific case, it even allows you to proceed without a snap-to operation, since the surface is of good quality. Figure 2.13: Cut-off Selection Rule with Ply Tapering Based on Element-based and Node-based Thicknesses
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Usage Reference
2.1.2. Material Data ACP differentiates between four material classes: Materials Materials (p. 64) 64),, Fabrics Fabrics (p. (p. 74) 74),, Stackups Stackups (p. 77) and Sublaminates Sublaminates (p. 82) 82).. Materials ls (p. (p. 64) 64) class class is the material database in ACP. • The Materia 74) class class is where Materials can be associated with a ply of a set thicknesses. • The Fabric Fabric (p. 74) 77) class class is used to combine fabrics into a non-crimp fabric, such as a [0 45 90] combin• The Stackup (p. 77) ation. (p. 82) 82) class class is used to group fabrics and stackups together for frequently used lay• The Sublaminate Sublaminate (p. ups. A Stackup or a Sublaminate can only be defined if a fabric and material have been defined previously.
2.1.2.1. Materials The Materials database is only editable within ACP in Stand Alone mode. Otherwise it draws all material properties from Engineering Data within Workbench. In this case, the material properties can only be viewed but not altered in ACP.
2.1.2.1.1. Materials Context Menu The context menu of the Materials class has the following options: • Create Material (Stand Alone only): Open a Material Properties dialog for creating a new material. • Paste (Stand Alone only): Paste a copied material into the material database. • Sort: Sort the list of materials alphabetically. • Export: Export the material database into a .CSV file, ESAComp XML file, or an ANSYS Workbench
XML file. • Import (Stand Alone only): Import materials from a .CSV file or ESAComp XML file.
ESAComp mp (p. (p. 254) 254).. More information on the import and export of ESAComp XML file can be found in ESACo Stackups and Sublaminates can also be exported to an ESAComp XML file format but are converted to laminates in the process. Figure 2.14: Materials Class Context Menu in Stand Alone Mode
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Features
2.1.2.1.2.Temperature Dependent and General Variable Material Properties Engineering constants, density, fabric fiber angle, as well as stress and strain limits, can be set to depend on scalar field variables, including Temperature, Shear Angle, and Degradation Factor. Other properties can only depend on temperature. The material properties are always shown at the reference point in the Materials object. Variable material data can be edited in Workbench Engineering Data. In ACP, ACP, variable material data are considered in ACP-Post when evaluating failure criteria criteria.. Temperature-dependence comes into effect if the solution contains a temperature data block. Shearing of plies is considered if the material is dependent on the Shear Angle variable and at least one ply is draped. All other dependencies require the respective field variable to be defined by means of Look-Up Tables. For more information, see Analysis Using Variable Material Dataa (p. 320 Dat 320)). Within the Workbench workflow, variable data are passed to and from ACP. In Stand-Alone mode, temperature-dependent data are passed to and from ACP if the import and export is in an ANSYS file format, such as .CDB. General variable material properties are read only from the Workbench Engineering Data ( .ENGD) file. Export and import of material data within the Materials object via .CSV or .XML file formats does not support general variable material data.
2.1.2.1.3. Material Properties Dialog Here is the Material Properties dialog.
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Usage Reference
In the Material Properties dialog, the following preprocessing data is required: • Name: Name of the material. •
ρ:
Density of the material.
• Ply Type: Defines the material type and controls which failure criteria evaluates the safety of a
certain material (see Failure Criteria vs. Ply Type Type Table Table (p. 381) 381)).). Depending on the extrusion method (e.g. sandwich-wise extrusion) in the Solid Model, it also affects the volume mesh of the solid model . – Adhesive: Materials of this type are post-processed with specific failure criteria. An adhesive has
isotropic mechanical properties. – Honeycomb Core: Sandwich core material with a honeycomb pattern. – Isotropic: Isotropic material and post-processed with the von Mises criterion. – Isotropic Homogeneous Core: Sandwich core material, such as foam, with isotropic elasticity.
Note that orthotropic strength limits have to be defined for post-processing (failure criteria evaluation). – Orthotropic Homogeneous Core: Sandwich core material, such as balsa, with an orthotropic
material characteristic.
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Features – Regular (uni-directional): Uni-directional reinforced material. – Undefined: If the material type is not known or not defined, then the ply type becomes undefined.
This material type is not post-processed. Weave material. material. – Woven: Weave
• Orthotropic Young's Modulus: – E1: In-plane, in fiber direction (fiber direction is corresponding to angle 0 for the ply's definition) – E2: In-plane, orthogonal to fiber direction – E3: Out of plane direction • Orthotropic Poisson's Ratio: – ν12: In-plane – ν13: Out of plane, in fiber direction – ν23: Out of plane, normal to fiber direction • Orthotropic Shear Modulus: – G12: In-plane – G13: Out of plane, in fiber direction – G23: Out of plane, normal to fiber direction
Further failure properties can be activated. Depending on the Ply Type some properties are deactivated automatically.
Note: Engineering Data can only be modified in preprocessing. Once postprocessing has been initiated the data is frozen.
2.1.2.1.4.Thermal Expansion Coefficients For thermal stress analyses, the thermal expansion coefficients of the material and the reference temperature must be given:
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Usage Reference
Temperature at which strain in the design does not result from thermal • Reference Temperature: Temperature expansion or contraction • alpha X: In-plane, in fiber direction (fiber direction is corresponding to angle 0 for the ply's definition) • alpha Y: In-plane, orthogonal to fiber direction • alpha Z: Out of plane direction
2.1.2.1.5. Fabric Fiber Angle
The Fabric Fiber Angle represents the angle between the Material 1 Direction and the Draped Fiber Direction. When no draping is specified, the Draped FFiber iber Direction coincides with the Fiber Direction. By default, the Fabric Fiber Angle is set to zero so that the Material 1 Direction coincides with the (draped) fiber direction. Figure 2.15: Example of Woven Material with a 45° Fabric Fiber Angle
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Features When the Fabric Fiber Angle property is active and nonzero, you need to specify the Material Properties, Thermal Expansion Coefficients, Strain Limits and Stress Limits with respect to the material directions rather than the fiber directions. For instance, E1 and E2 would represent the Young’s moduli in the material 1 and 2 directions, respectively. However, the fiber direction is still the nominal modeling direction in ACP. For more information, see the Shear Dependent Materials Materi als in Composite Analysis (p. (p. 336) 336) example example and the Material Designer User's Guide. Guide. You can highlight the effect of the Fabric Fiber Angle by plotting the draped fiber direction and the material 1 direction of a selected analysis ply (see Drapi Draping ng (p. (p. 28) 28)).).
2.1.2.1.6. Strain Limits The Strain Limits are used to calculate the IRF if the Max Strain criteria is selected in the failure criteria criter ia definition definition (p. 207) 207).. Compressive strain limits must be negative.
For orthotropic materials, 9 strain limits (5 in-plane and 4 out-of-plane strains) can be entered: • eXc: Normal strain, in-plane, in fiber direction, compression limit • eXt: Normal strain, in-plane, in fiber direction, tension limit • eYc: Normal strain, in-plane, orthogonal to fiber direction, compression limit • eYt: Normal strain, in-plane, orthogonal to fiber direction, tension limit • eZc: Normal strain, out of plane, compression limit • eZt: Normal strain, out of plane, tension limit • eSxy: In-plane shear strain • eSxz: Transverse (interlaminar) shear strain, plane in fiber direction • eSyz: Transverse (interlaminar) shear strain, plane normal to fiber direction
If the material is defined as isotropic, the von Mises Strain Limit can be entered:
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Usage Reference
2.1.2.1.7. Stress Limits All the other Failure Criteria definitions are based on values defined in the Stress Limits dialog. Compressive stress limits must be negative.
For orthotropic materials, 9 stress limits (5 in-plane and 4 out-of-plane strains) can be entered: • Xc: Normal stress, in-plane, in fiber direction, compression limit • Xt: Normal stress, in-plane, in fiber direction, tension limit • Yc: Normal stress, in-plane, orthogonal to fiber direction, compression limit • Yt: Normal stress, in-plane, orthogonal to fiber direction, tension limit • Zc: Normal stress, out of plane, compression limit • Zt: Normal stress, out of plane, tension limit • Sxy: In-plane stress strain • Sxz: Transverse (interlaminar) shear stress, plane in fiber direction • Syz: Transverse (interlaminar) shear stress, plane normal to fiber direction
If the material is defined as isotropic the von Mises Stress Limit can be entered (equivalent to Tensile Yield Strength in Engineering Data):
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Features
2.1.2.1.8. Puck Constants The Puck failure criterion requires internal parameters, which depend on the material. The Material Classification drop-down menu offers a selection of pre-defined constants and also allows for the definition of custom constants. The menu has the following options: • Carbon: Sets pre-defined Puck constants for carbon fiber materials. • Glass: Sets pre-defined Puck constants for glass fiber materials. • Material-specific : Allows you to set your own Puck constants. • Ignore Puck Criterion: No constants are set.
inclination XZ • p21(+): Tensile inclination • p21(-): Compressive inclination XZ
inclination YZ • p22(+): Tensile inclination • p22(-): Compressive inclination YZ • s and M: Degradation parameters
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Usage Reference • Interface Weakening Factor: Scales the interlaminar normal strength
2.1.2.1.9. Puck for Woven Woven The Puck for Woven functionality of ACP allows to evaluate the Puck failure criterion for woven materials. Two UD plies plies can be specified representing the woven ply. During the failure evaluation, ACP evaluates the stresses for theses plies and computes the Puck failures. The relative ply angles, engineering constants, stress limits and Puck constants must be defined for both plies.
Note: This specification does not affect the analysis model and is only considered in the failure analysis for the Puck criterion.
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Features
2.1.2.1.10. Tsai-Wu Constants 2.1.2.1.10. The Tsai-Wu constants are constants used into the interaction coefficient of the quadratic failure criteria for Tsai-Wu formulation. Refer to Tsai-Wu Failure Criterion (p. 359) 359) for for more details.
In ACP the Tsai-Wu constants correspond to: • 2 F12 = XY, default -1 • 2 F13 = XZ, default -1 • 2 F23 = YZ, default -1
2.1.2.1.11. LaRC Constants The LaRC failure criteria requires the following parameters to evaluate the failure in matrix and fiber:
• Fracture Angle Under Compression: The value for
α0 used in the LaRC fiber and matrix failure.
Default value is 53°. to mode II fracture toughness, which is used • Fracture Toughness Ratio: The ratio of the mode I to in the fiber failure criteria. • Fracture Toughness Mode I • Fracture Toughness Mode II • Thin Ply Thickness Limit (set to 0.7 mm in Workbench mode)
For more information, see LaRC03/LaRC04 LaRC03/LaRC04 Constants Constants (p. 368) 368)..
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Usage Reference
2.1.2.2. Fabric The settings for the t he Fabric Properties dialog are described in the sections below:
2.1.2.2.1. General Figure 2.16: Fabric Properties - General
• Material: Material of the fabric • Thickness: Ply thickness
more e information, • Price/Area: The surface price can be given to provide global information. For mor see Sensors (p. 162) 162).. density. y. • Weight/Area: The weight per unit area is calculated based on the thickness and material densit • Ignore for Post-Processing: If active, all the analysis plies with this fabric are not considered in the
failure criteria analysis during postprocessing. This does not affect the analysis model.
2.1.2.2.2. Polar Properties The Polar Properties (Classical Laminate Laminate Theory Theory (p. 382) 382))) of the fabric can be plotted as graphical information.
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Features Figure 2.17: Fabric Properties - Analysis
This plot can be exported as a picture (
) or in a .CSV fi file ( )
2.1.2.2.3. Fabric Solid Model Options Solid model options set which material is used for diminished (drop-off and cut-off) elements during solid model generation. Material handling is determined by the settings in every Fabric/Stackup definition, as well as the global drop-off/cut-off material handling setting, and the extrusion method in the Solid Model definition. For more information, see Material Handling for Different Diffe rent Extrusion Extrusion Methods (p. 188) 188)..
Note: The Solid Model Options tab is the same for both Fabrics and Stackups.
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Usage Reference Figure 2.18: Fabric Properties - Solid Model Options
• Drop-off Material Handling:
global drop-off material material in the Solid Model Properties is used. (default) – Global: The global – Custom: Select a material from the Drop-off Material drop-down menu. • Drop-off Material: The list becomes becomes active when when Drop-off Material Handling is set to Custom. • Cut-off Material Handling:
Fabric/Stackup material is used for analysis ply-wise extrusion. Otherwise, the – Computed: The Fabric/Stackup global material is used and a warning is generated that computed materials for cut-offs are currently not supported if the element points to more than one Analysis Ply. (default) global drop-off material material in the Solid Model Properties is used. – Global: The global – Custom: Select a material from the Cut-off Material drop-down menu.
becomes active when when Cut-off Material Handling is set to Custom. • Cut-off Material: The list becomes
2.1.2.2.4. Draping The Draping settings are used if draping is activated in the Modeling Ply definition. For more Simulation (p. 347) 347).. details about the draping calculation, see Draping Draping Simulation
Note: The Draping tab is the same for both Fabrics and Stackups.
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Features Figure 2.19: Fabric Properties - Draping
• Material Model:The material model used in the draping simulation, either Woven (default) or
Unidirectional . Note that the draping material model can be set independently of the Ply Type of
the fabric’s material. • UD Coefficient: A parameter between 0 and 1 which controls the amount of deformation in the
transverse draping direction. This property is active only when Material Model is set to Unidirectional.
2.1.2.3. Stackup A stackup is a non-crimp fabric with a defined stacking sequence. From a production point of view, it is considered as one ply, which is applied on the form. For the analysis, all plies forming the stackup are considered. For every ply of the stackup, the fabric and its orientation must be given:
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Usage Reference Figure 2.20: Stackup Properties - General
These stackups have different Price/Area and solid model options than a laminate of single plies. For this reason, Price/Area can be entered again. Stackups can be exported to an ESAComp XML file format and are converted to laminates in the process.
2.1.2.3.1.Top-Do 2.1.2.3.1.Top-Down wn or Bottom-Up Sequence The definition of the stackup can be given in both directions (Bottom-Up and Top-Down). In the Top-Down sequence, the first defined ply (the first one in the list) is placed first on the mold and is the bottom stackup. Thethe other are placed over During During analysis, the sequence can be checked. In of thethe above figure, ply plies -45 direction is on topit.(see Figure 2.23: Layup Information and Polar Polar Properties Properties (p. 81) 81)).).
2.1.2.3.2. Symmetries For a quicker definition, the stackup can be defined with symmetries. The Even Symmetry option defines the symmetry axis on the top of the sequence, and uses all plies.
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Features Figure 2.21: Stackup Sequence with Even Symmetry
In the Odd Symmetry option, the ply on the top is not used for the symmetry. So the middle of the top ply is the symmetry axis of the final sequence.
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Usage Reference Figure 2.22: Stackup Sequence with Odd Symmetry
2.1.2.3.3. Analysis Analysis The tab provides evaluation of the laminate properties of the stackup, which can be plotted as graphical information.
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Features Figure 2.23: Layup Information and Polar Properties
This plot can be exported as a picture (
) or as a .CSV file file (
). It is possi possibl ble e to ttra ransl nslat ate e and and
zoom into the lay-up distribution with the mouse button. To come back to a fit view, click . In addition, laminate properties (stiffness matrix or flexural stiffness), which are based on Classical Laminate Laminat e Theory Theory (p. 382) 382) (CLT), (CLT), can be calculated. The following results based on Classical Lamina Laminate te Theory Theory (p. 382) 382) can can be calculated by selecting them from the CLT Analysis drop-down: • Laminate Stiffness and Compliance Matrices
• Normalized Laminate Stiffness and Compliance Matrices
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Usage Reference • Laminate Engineering Constants
Figure 2.24: CLT Analysis - Laminate Engineering Constants
2.1.2.3.4. Stackup Solid Model Options The material handling settings for Solid Models are identical for Fabrics and Stacks. For more information, see Fabric Fabric Solid Model Options Options (p. 75) 75)..
2.1.2.3.5. Draping Options The Draping settings are identical for Fabrics and Stacks. For more information, see Draping (p.. 76 (p 76)).
2.1.2.4. Sublaminates A sublaminate is a sequence of plies defined by fabrics and stackups with relative angles. This sublaminate can be used later in the lay-up definition. As with stackups, the sequence direction 78) for for more information. Sublaminates can and symmetry can be chosen. Refer to Symmetries Symmetries (p. 78) be exported to an ESAComp XML file format and are converted to laminates in the process.
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Features Figure 2.25: Sub Laminate Properties - General Tab
The Analysis tab is exactly the same as for a stackup. Refer to Analysis (p. 80) 80) for for information on the content of this tab.
Important: If stackups and symmetry are used in the sublaminate definition, the stackup is not reversed in the ply sequence. For example, for a stackup S1 defined as [45,-45,0], and a sub-laminate defined with even symmetry and the stackup ([S1]s), the sub-laminate sequence is [45,-45,0,45,-45,0], not [45,-45,0,0,-45,45].
2.1.3. Element and Edge Sets Named selections defined in Mechanical or components defined Mechanical APDL can be imported into ACP. ACP. These selections are imported with wit h the same names. FFaces aces (element components in Mech(p. 84) 84) and and edges (node components in Mechanical APDL) anical APDL) are imported as Element Sets (p. as Edge Sets (p. (p. 85) 85)..
Important: After the definition of a new Named Selection in Mechanical, the model must be updated.
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Usage Reference
2.1.3.1. Element Sets New Element Sets can be manually defined by selecting individual elements. Element Sets store the element labels and are therefore not associated with the geometry. If the mesh changes, the element numbering changes and the element set must be redefined to avoid erroneous layups. Figure 2.26: Element Set Selection
• Middle Offset: If the mesh is generated at the mid-plane surface, activate this option so that the
section definition is translated to where the middle of the section corresponds to the element. The lay-up definition - in particular the definition of Oriented Selection Sets - is not influenced. Solid Model extrusion and Draping Offset Correction do not support the Middle Offset setting. To verify Cut ut (p. (p. 156) 156) or Sampling Point Point (p. (p. 154) 154).. a lay-up with Middle Offset, use a Section C • Operation: Add or Remove elements in the list. • Mode: Define the selection mode by dragging the mouse from one corner to the other. – Box on Surface: Only visible elements are selected. – Box Prism: All elements included in the box are selected, depth included. – Point: Element at the picking location is selected.
2.1.3.1.1. Context Menu Several options are available in the element set context menu: • Properties: Open the element set property window. • Update: Update any changes into the database • Hide /Show: Hide or show this Element Set. The elements of the hidden Element Sets are no longer
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Features • Copy: Copy the selected Element Set to the clipboard. • Paste: Paste an Element Set from the clipboard. • Delete: Delete the selected Element Set • Export Boundaries: Export the boundaries of the Element Set to a STEP or an IGES file • Partition: Create partitioned Element Sets for any Element Set that can be divided in different
zones, due to a geometrical separation (for example, three elements share the same edge).
Figure 2.27: Element Set Context Menu
2.1.3.2. Edge Sets Named Selections of connected edges in Mechanical are transferred to ACP as Edge Sets. New Edge Sets can also be defined manually in ACP-Pre: Figure 2.28: Edge Set Definition
• Edge Set Type: How the Edge Set is defined: – By Reference: Defined the Edge Set using an existing Element Set (activates the following options): →
→
Element Set: The Element Element Set of which the Edge Set is part. Limit Angle: The Edge Set is extended from the origin in both directions until the angle between two elements is bigger than the Limit Angle. If the Limit Angle is set to a negative value, the
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Usage Reference
→
Origin: Origin to determine the closest boundary.
• By Reference: An existing Element Set is used to define a new Edge Set through one boundary limited
by an angle diffusion. • By Nodes: Manually select the nodes to define the Edge Set.
2.1.4. Geometry Geometries can be used to build complex lay-ups during preprocessing in ACP. For example, core of variable thickness can be modeled as a ply whose thickness is set by an imported geometry of the core. Cut-off Rules can be based on geometry, thus controlling the lay-up by a CAD surface or at a pre-defined offset to a CAD surface. The use of geometries is particularly helpful in the generation of solid models where geometry-based extrusion guides, snap-to and cut-off operations can create intricate shapes. For more information on the use of geometries in a lay-up definition, see the following sections: (p. 131) 131) in in Modeling Groups definition (p. • Ply thickness definition Geometry-based based Cut-off Cut-off Selection Rule (p. 107) • GeometryGuides uides (p. (p. 176) 176),, Snap-to (p. 182) 182) and and Cut-off Cut-off Geometries (p. (p. 185) 185) in Solid Mo Models dels (p. (p. 164) • Extrusion G CAD geometries are incorporated in an ACP model by creating a link to a Geometry in the Workbench Project Schematic or by directly importing an external geometry (IGES or STP format). These CAD geometries may be surfaces, bodies, or assemblies of parts. The concept of virtual geometries allows you to select and group specific regions or bodies of the imported CAD geometry and use them for subsequent modeling operations. All geometry-based operations are based on virtual geometries. Virtual geometries act as a reference to one of more faces or bodies of one CAD geometry. Figure 2.29: CAD Geometry Assembly and Virtual Geometries in the Tree View
2.1.4.1. CAD Geometries There are two ways to import an external geometry into ACP: ACP. This option directly imports copies the C CAD AD file into the user_files • Directly through ACP. directory in the Workbench file structure. Any further changes to the original file are not trans-
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Features • By selecting the Setup cell of your ACP system and then selecting the Load Model Properties
option (Geometry category of the Properties of Schematic) in Workbench. Workbench. The advantage advantage of this option is that the CAD geometry can be refreshed inside DesignModeler or SpaceClaim. For either case, the geometry remains intact when a project is archived and restored.
Note: For CAD geometries imported from SpaceClaim, the entire geometry from SpaceClaim is imported into ACP. In addition, bodies with the Suppress for Physics option activated are imported. The parts included in an imported CAD geometry are displayed once the CAD geometry is up-todate. If the imported CAD geometry is an assembly of parts, multiple parts are shown in the tree underneath the CAD geometry. ACP makes the distinction between four different types of parts: • Face ( ): Sing Single le face face
Single surfac surface e bod bodyy • Surface ( ): Single • Solid (
): Si Sing ngle le vol olum ume e bod bodyy
• Compound (
): Combina Combinatio tion n of multipl multiple e connect connected ed surface surfacess and/or and/or bodies bodies
2.1.4.1.1. Direct Import Geometry import has the following options: Figure 2.30: Import External CAD Geometry
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Usage Reference • Name: Name of geometry for use in the database. • External Path: Location of the geometry file to be imported. • Refresh: Reload the file from the external path. The file is automatically copied to the Workbench
project folders. • Scale Factor: Scale the geometry in the global coordinate system (useful for change of units). • Precision: Precision of the imported geometry. This value is used to evaluate intersections and
other geometrical operations. • Offset: Sets the default capture tolerance value associated with the CAD geometry for operations
such as the Geometrical Geometrical Selection Rule (p. (p. 111) 111).. • Use Default Offset: Boolean which sets the offset to 10% of the average element size. • Visualization Color: Color in which the imported geometry is displayed. • Transparency: Transparency of the imported geometry (value between 0 and 1).
Assemblies should be imported as a single .STP file rather than individual ones containing links.
2.1.4.1.2.Workbench Geometry Link The geometry component in Workbench can be used to link CAD geometries with ACP-Pre. The linked geometry is scaled automatically if its units do not match those of the project. The required steps for geometry import are: 1. Add a Geometry component to the project. 2. In the the con conte text xt menu menu of the Geometry select Import Geometry 3. Link the Geometry cell to the ACP (Pre) Setup cell The imported geometry appears under CAD Geometries in ACP. Figure 2.31: Project Schematic with a CAD Geometry Import in ACP
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Features
2.1.4.2.Virtual Geometries Virtual Geometries group together subshapes of CAD geometry parts. The subshapes are referenced referenced by linking to features of CAD geometry parts. There are three ways to define virtual geometries: • Directly from CAD parts through the CAD part context menu.
Figure 2.32: Create Virtual Geometry Directly from CAD Geometry Part
• By selecting multiple CAD parts from the tree when the Virtual Geometry Properties dialog is open.
Figure 2.33: Create Virtual Geometry Through CAD Geometry Parts in Tree
• Through face selection in the scene.
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Usage Reference Figure 2.34: Create Virtual Geometry Through Face Selection in the Scene
Note: Virtual geometries can only reference parts from one CAD geometry.
2.1.5. Rosettes Rosettes are coordinate systems used to set the Reference Direction of Oriented Selection Sets. Rosettes define the 0° direction for the composite lay-up. Coordinate systems defined in Mechanical are imported by default and the naming is maintained between Mechanical and ACP. Additional Rosettes can be defined in ACP. ACP. There are 5 different types of Rosettes. The origin and directions of Rosettes are given in the global coordinate system. Rosettes are independent of the mesh, even if you select nodes and elements to define their properties. One or more Rosettes can be used to set the Reference Direction for elements in an Oriented Selected Set (OSS). (OSS). The Selection Method in the OSS definition controls which Rosette determines the Reference Direction for the elements. The the Reference Direction a singletypes element is determined by athe projection of the applicable Rosette onto element. DifferentforRosette can be used to define Reference Direction.
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Features Figure 2.35: Rosette Properties Dialog
• Flip Buttons: Reverse the direction • Shuffle Axes: Rotate coordinate system to exchange the X , Y, and Z axis. • Swap 1 and 2 Direction : Exchange direction 1 with 2.
Rosette Types byy the Rosette's • Parallel: Analogous to a Cartesian coordinate system. The Reference Direction is given b X direction. radial Rosette is perpendicular to the Z direction. The Z direction • Radial: the Reference Direction for a radial lies orthogonal to Direction 1 and Direction 2 in the Rosette properties. The Reference Direction Direction for an individual element is defined by the vector of Rosette origin to element center which is projected onto the element. If the direction vector cannot be projected the alternate Direction 1 is chosen.
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Usage Reference Figure 2.36: Oriented Selection Set with a Radial Rosette.
• Cylindrical: Based on a cylindrical coordinate system. The Reference Direction runs circumferentially
around the Rosette's Z direction according to the right hand rule. The Z direction is defined by the X and Y direction vectors. Flip the Z direction to reverse the Reference Direction.
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Features Figure 2.37: Oriented Selection Set with a Cylindrical Rosette
circumferentially entially around • Spherical: Based on a spherical coordinate system. The Reference Direction runs circumfer the Z axis of the Rosette. Figure 2.38: Oriented Selection Set with a Spherical Rosette
• Edge Wise: Requires the selection of an Edge Set in addition to the usual Rosette definition. The Reference
Direction is given by a projection of the Rosette's X direction and the path of the Edge Set. The X direction
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Usage Reference of the Rosette. This determines Reference Direction along the Edge Set. The Reference Direction is reversed by switching the coordinates of the Rosette's X direction. An element within an Oriented Selection Set gets its Reference Direction from the direction of the point on the edge that is closest to the element centroid. Figure 2.39: Edge Wise Rosette
2.1.5.1. Rosette Definition Each Rosette is defined by an origin and two vectors. Enter the origin by clicking on an element or a node, or by typing the coordinates. When selecting an element, the coordinates of the center of the element are used. If a direction field is selected in the dialog, the selection of an element returns the normal direction of the element. By pushing down the Ctrl key and clicking on a second element, you can select the direction defined by the two element centers.
2.1.6. Look-Up Tables Several features in ACP can be defined as tabular values. Look-up tables can be used for thickness definition definiti on of plies (p. (p. 131) 131),, selectio selection n rules (p. (p. 114) 114),, draping an angles gles (p. (p. 128) 128),, and field definitions definitions (p. (p. 151) 151).. In such cases, the Look-up Table contains values (scalars) or direction (vectors) at specified points in 3-D space or along a single direction. Look-Up Tables require at least a Location column (1 or 3 components, one for each coordinate). Table can be edited Direction columns (3 columns) and/or Scalar columns can be added. The Look-Up Table
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Features efficiently by exporting and importing an .xls(x) file (see Edit Entities Entities with Excel Excel (p. 23) 23))) or a .csv file.(see CSV FFormat ormat (p. (p. 253) 253)).).
Note: Look-up Table Table rows cannot be directly added or removed in the ACP GUI. The values in existing cells can only be modified.
Populating Look-Up Tables The easiest way is to populate Look-up Tables is i s with the help of the Edit Entiti Entities es with Excel Excel (p. 23) on Windows. Windows. The set-up with exporting exporting and importing a .csv file is similar and ideal for Linux. Data can also be entered into Look-up Tables using The using The ACP Python Scripting User Interface (p. 395) 395).. There are three approaches to populating a Look-Up table. This can be done with: Li nk (p. 95) • The Excel Link Filess (p. 97) • Exporting/Importing .csv File • A Python Sc Script ript (p. (p. 100)
2.1.6.1. 3D Look-Up Table With The Excel Link The set-up of a 3D Look-up Table is demonstrated in the figures below: From the right-click context menu, select Create a 3D Look-Up Table (p. (p. ?) ?) .
An empty 3D Look-Up Table (p. ?) ?) is is created with XYZ-location columns.
Direction ection Columns Columns (p. ?) ?) from from the right-click context menu of the new Look-Up Table. Create Dir
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Usage Reference
The empty Look-u Look-up p Table Table (p. ?) ?) now now has three additional columns for three directional components of the vector.
Populate the table in Excel with your values. Ensure the data set is followed by the END DATA ?) in in Excel is shown below. and END TABLE rows. An example of a populated Look-Up Table (p. ?)
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Features
Use the Excel Link (p. (p. ?) ?) to to import and export the data from Excel to ACP.
2.1.6.2. 1D Look-Up Table with .CSV Files The Look-up Table definition defi nition with a .CSV file follows the same process as the Excel Excel Link (p. (p. 95) 95):: create Look-Up table, add desired columns, export data to Excel, populate the Excel data and reimport. imp ort. The .CSV file approach for setting up a 1D look-up table is demonstrated with the figures below. From the right-click context Look-Up Table menu in the Outline, select Create 1D Look-Up
Table (p. ?) ?)..
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Usage Reference
An empty 1D Look-Up table is created with a single column. Specify the origin and direction of the table as shown below.
From the right-click context menu of the new Look-Up Table, select Create Scalar Scalar Column Column (p. ?) .
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Features Export the empty Look-Up Table to a .csvfile using the right-click context menu.
Open the exported .csv fil file e (p. (p. ?) ?) in in an editor or spreadsheet program.
Add the entries and save the CSV file. Note that you may need to verify the deliminator type if your regional settings use a comma as a decimal separator.
In ACP, re-import the CSV File by selecting Import from from CSV File File (p. ?) ?)..
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Usage Reference
2.1.6.3. Look-Up Table with a Python Script The set-up of a 1D Look-Up Table with a script: table = db.active_model.create_lookup_table1d(name='LookUpTable1D.1') table.origin=(0.0, 0.0, 0.0) table.direction=(1.0, 0.0, 0.0) table.create_column(name='Value', type='scalar') table.dimensions=['length', 'dimensionless'] table.columns['Location'].values = [0., 1., 2., 3.] table.columns['Value'].values = [0., 1., 2., 3.]
2.1.6.4. 1-D Look-Up Table A 1-D Look-Up Table can be used to create a distribution of a scalars or vectors in one direction. Such a distribution can be used in: (p. 118) 118) Reference Reference Direction. • the definition of an Oriented Oriented Selection Set (p. • the definition of the drapin draping g angle (p. (p. 278) 278)..
thickness (p. (p. 131) 131).. • the definition of the ply thickness A 1-D Look-Up Table is defined by an origin, a direction vector, and a column of at least one quantity varying along the direction vector. Location points can be defined in an arbitrary order. They are automatically sorted and duplicate location points are permitted for the definition of step functions. The values of the defined quantity are linearly interpolated to the element centers in the mesh. The 1-D Look-Up Table uses a scalar product to project the vector between origin and element center on to the Look-Up Table direction vector and look-up the desired value at that point.
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Features Figure 2.40: Schematic of 1-D Look-Up Table Function
2.1.6.5. 3-D Look-Up Table A 3-D Look-Up Table can be used in: (p. 118) 118) Reference Reference Direction. • the definition of an Oriented Oriented Selection Set (p. draping g angle (p. (p. 278) 278).. • the definition of the drapin thickness (p. (p. 131) 131).. • the definition of the ply thickness Figure 2.41: Look-Up Table Properties
The values in the Look-Up Table are inter- or extrapolated to the model elements position. The interpolation uses the Shepard's method (3-D inverse distance weighted interpolation). The Interpolation tab allows to enter two parameters. By default, ACP evaluates a reasonable search radius and the number of interpolation points is 1.
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Usage Reference Figure 2.42: Look-Up Table Interpolation Parameters
• Search Radius: Only the element centers which are included in this radius are used in the interpolation. • Min. Number of Interpolation Points : If there are of no element centers (or not enough if > 1) in
the radius, the Search Radius is increased until the pinball includes at least the minimum number of interpolation points (element centers) defined in this value.
Note: If a 3-D Look-Up Table contains points without real numbers (i.e. nan or blank), these values are automatically computed on update by interpolating the valid results.
2.1.6.6. Look-Up Table Column Properties The dimension of the data columns must be set for unit conversion to work correctly. The column properties can be accessed through the context menu of the column in the tree view.
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Features Figure 2.43: Setting the Dimension in the Column Properties Dialog
2.1.7. Selection Rules Selection Rules enable you to select elements through geometrical operations. These selections can (p. 122) 122))) or Modeling P Plies lies (p. (p. 127) be combined with Oriented Selection Sets (see OSS Selection Selection Rules (p. to define plies of arbitrary shape. The final extension of the ply is the combination of the Selection Rules and the selected Oriented Selection Sets. This feature can be used to define local reinforcements (patches) or staggering. You can select between different selection rule types which are explained in the sections below. It is also possible to combine different rules and to define boolean operations between rules. Figure 2.44: Selection Rules Context Menu
The .CSV file interface of ACP offers the ability to create or modify selection rules externally or share
them with other ACP users working on the same model or even on a different project. Limitation: The Variable Cutoff Selection Rule and Boolean Selection Rule are not supported by the t he CSV interface Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Usage Reference
2.1.7.1. Basic Selection Rules Figure 2.45: Definition of a Parallel Selection Rule
Parallel, Cylindrical, and Spherical Selection Rules are simple shapes which can be defined by a
few parameters: • Parallel: Defined by two parallel planes. The planes are defined by an origin, a normal vector and
two distances (offsets of the planes from the origin along the normal vector). • Cylindrical: The cylinder is defined by an origin and the vector of the axial direction and the radius.
The cylinder has infinite height. • Spherical: The sphere is defined by the center center and the radius.
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Features Figure 2.46: Example of a Parallel Selection Rule
Selection Rule based on Rosettes Parallel, Cylindrical, and Spherical Selection Rules can be defined in terms of the coordinate relative to a specific Rosette. To choose choose a Rosette, uncheck "Use global Coordinate System" and select a Rosette from the drop-down menu. If a Rosette is selected, Origin and Direction are in the Rosette's reference frame. Note that only parallel Rosettes can be used to define Selection Rules.
Relative Selection Rule It is possible to define a Selection Rule as relative. In this case the Selection Rule parameters define the ratios of the selection rule relative to the Modeling Ply dimensions. Take care that the Plotted Selection rule is evaluated from the global geometry dimensions and that this plot does not represent the final shape of the Selection Rule which depends on the Modeling Ply. Select the ply and check the highlighted elements which represent the final shape of the ply.
Include Selection Rule The Include Selection Rule Type option can be used to select the elements inside the geometry or outside. the option is active shown in Figure 2.46: Example a Parallel Rule Rul e (p. 105 105)By )). Ifdefault the option is inactive, the (as inverse selection takes effect. Plies of with a hole Selection can be
created through a Cylindrical Selection Rule and disabled Include Selection Rule Type option. This option applies to all geometrical rules as well as the Tube Selection Rule.
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Usage Reference
2.1.7.2. 2.1.7.2.T Tube Selection Rule A Tube Selection Rule is a cylindrical selection rule of variable axial direction. The longitudinal direction is defined by the Edge Set and the radius defines the diameter of the cylinder. Figure 2.47: Example of Tube Selection Rule
2.1.7.3. Cut-off Selection Rules A Cut-off Selection Rule acts as a cutting operation on the composite layup. In contrast to other Selection Rules that affect the in-plane directions of the ply, a Cut-off Selection Rule also considers the laminate thickness. A Cut-off Selection Rule can be defined by a geometry or a taper. Using a Geometry Cut-off Selection Rule, the ply is cut at the intersection with a CAD Geometry, taking into account the thickness of the laminate. An example of this is a skew-whiff surface being used to define the tapering near a trailing edge of a blade. A Taper Cutoff Selection Rule cuts plies based on an edge and a taper angle. Only Analysis Plies are cut off as a result of the selection rule. Modeling and Production Plies are not affected. affected. The Cut-off Selection Rule is similar to a milling operation on built-up structure. In that sense, the full size Modeling and Production Plies are required before the machining operation. The Analysis Plies are the only decisive plies for any structural computation.
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Features Figure 2.48: Cut-off Selection Rule Properties
Cut-off Selection Rule settings are: • Name: Name of the Selection Rule. • Cut-off Geometry: The CAD geometry defining the cut-off. • Offset: CAD / taper surface offset. The intersection of the CAD Geometry/taper edge and the lay-up
can be moved by an offset. The direction and orientation of the offset is defined by the normal direction of the Oriented Selection Set. • Edge Set: Selection of an Edge Set (Taper).
(Taper). • Angle: Taper angle (Taper). • Ply Cutoff Type: Either the complete production ply is cut off or individual analysis plies are cut off.
Ply tapering can only be activated in the latter case. Cut-off ut-off (p. (p. 110) • Example C • Ply Tapering: Control of the cut-off resolution.
2.1.7.3.1. Geometry Cut-off Selection Rule For each element, ACP determines the position of the ply (including its offset) in relation to the imported surface. There are two possibilities of how the model geometry is cut by a CAD geometry - one cutting operation follows the geometry contour, the other divides the ply into either its maximum thickness or zero thickness. This is controlled b byy the Ply Tapering option in the Cutoff Selection Rule Properties dialog.
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Usage Reference Figure 2.49: Trailing Edge with Cut-off Plies (Ply Tapering Activated) Activated)
In the first method, the ply is cropped cropped if it intersects with th the e geometry. The ply is cut to match the external geometry. In the second method, the ply is cut at a discrete point. The ply cannot have a varying thickness - it is either at its maximum thickness or it has been entirely cut-off. The ply is cut if the intersection of CAD geometry and ply is less than half of the ply's thickness. The following figures are taken from Tutorial from Tutorial 2 and 2 and are presented to explain the concept further. In the tutorial, a Geometry Cut-off Selection Rule is applied to the core. A section view of the Cut-off Geometry, applied to two edges, is shown in the figure below. The cut-off has a nominal thickness of approximately two thirds of the core thickness and, towards the outside, it has a multi radii edge. The dashed yellow line in the figure denotes the ply's centerline. Figure 2.50: Section of the Cut-off Geometry
Ply Tapering
When is activated, the core is cropped tothe match the Cut-off Contour,isasatshown the right figure below. If Ply Tapering is deactivated, resulting core thickness its fullin thickness everywhere the intersection of the geometry is above the core centerline. Everywhere else, the core is completely cut-off.
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Features Figure 2.51: Core Thickness Without Ply Tapering (Left) and With Ply Tapering (Right)
2.1.7.3.2.Taper Cut-off Selection Rule The second way of using the Cut-off Selection Rule is to define a taper with an Edge Set and a tapering angle. The area close to the edge has to be sufficiently meshed for the taper cutoff to (p. 107) 107),, the ply is cut-off in the taper zone. Only if Ply work. Similar to the Geometry Cut-off Cut-off (p. Tapering is selected will there a be a gradual taper over thickness. The Taper Taper Cut-off Selection Rule allows the same definition as the Taper Edges feature for modeling plies. For a detailed 269).. explanation of taper angle and offset, see Edge Tapering Tapering (p. 269) By default, ACP analyzes the cut-off selection rule at the element centers. Each element is cropped from the ply if the ply thickness at the element center is negative. This binary representation may not be sufficiently accurate in certain cases. If the Use Nodal Thicknes Thicknesss (p. 58) 58) is is enabled, the cut-off and ply tapering (if enabled) will be refined, which in turn results in a more accurate Thicknesses (p. 61) 61).. model. For more information, see Element- vs. Node-based Thicknesses
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Usage Reference Figure 2.52: Taper Cut-off Selection Rule Definition
2.1.7.3.3. Example Cut-off Consider a Stackup of three Fabrics for this example. In the pictures below, a laminate of one Stackup is shown marked with the green lines. The blue lines highlight the Analysis Plies of the Stackup. The black lines represents the mesh and the red line indicates the final laminate resulting from the Cut-off Selection Rule. Figure 2.53: Section with The Production Ply Option
The Cut-off Selection Rule with the Analysis Ply Cutoff option option will result in a smoother section
as each Analysis Ply of the Stackup is cut individually.
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Features Figure 2.54: Section with the Analysis Ply Option
The Cut-off Selection Rule with Ply Tapering will result in an even smoother section. The ratio between the area of the section cut by the CAD Geometry and the uncut section is calculated. The same ratio is applied to the ply thickness for the considered element. Figure 2.55: Section with the Analysis Ply with Tapering Option
2.1.7.4. Geometrical Selection Rule The Geometrical Selection Rule allows you to define the extent of a modeling ply or OSS based on a CAD surface or solid geometry. Elements are selected if they lie within the enclosure of a defined volume. The volume is set by the size of the CAD solid geometry or the CAD surface geometry in combination with specified Capture Tolerances. Tolerances. This means that a flat CAD surface geometry can be used to define a ply on a curved mesh surface. Figure 2.56: Example Geometrical Selection Rule (p. 112 Rule 112)) shows a selection inside a curved mesh enclosed by a flat surface with relatively high
negative and positive capture tolerances.
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Usage Reference Figure 2.56: Example Geometrical Selection Rule
Geometrical Selection Rules have the following settings:
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Features Figure 2.57: Geometrical Selection Rule Properties
• Rule Type: Define whether the rule extent is defined by a geometry of element sets. The value can
be geometry or element_sets. The default default is setting is is geometry . Geometr y defining the basic selection (only relevant for Rule Type: Geometry). • Geometry : Virtual Geometry • Element Sets: Preselection of elements in the form of an element set where the rule is applied on
(only relevant for Rule Type: Element Sets). Multiple element sets can be parsed as input by holding the [Ctrl] button while making your selections. • Include Rule Type (p (p.. 10 105) 5)
Capture tolerances are only used for non-solid geometries (surfaces). Negative values are supported. • Use Defaults: Defines if the default value is used. The default value is the Offset property of the CAD
geometry geomet ry (p. 86) 86).. • In-plane: Increase the in-plane extension by this value. • Negative: Capture tolerance reverse the surface normal. • Positive: Capture tolerance along the surface normal.
Negative values are also supported.
Note:
In principle, the in-plane tolerance is used to extend to the boundary of the geometry. It is also used to fill gaps between adjacent surfaces that may cause sampling issues.
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Usage Reference
Therefore, it is recommended to use an In-plane tolerance > 0 when the selection is missing some elements inside the capturing geometry. Figure 2.58: Capture Tolerances
2.1.7.5.Va Variable riable Offset Selection Rule 2.1.7.5. The Variable Offset Selection Rule is defined on the basis of an Edge Set and a 1-D Look-Up Table containing a list of offsets at different locations. Elements adjacent to the Edge Set are selected if their centroids lie within the specified offset at the given locations. The offsets are linearly interpolated between locations. In this way, the rule behaves like an advanced Tube Selection Rule for which the outer radius can be varied. There are two different ways in which the Look-Up Table data can be interpreted. The location of each offset can be mapped on to a direction vector (default) or on to the length of the Edge Set. The reason the rule is not called the variable radii rule is due to the ability to deifine the offset over a curved surface defined by an Element Set. The offsets are initially evaluated as a radius at each element adjacent to the Edge Set. The Offset Correction then adjusts the offset so that the offset is measured over the curvature of the surface. The template rule functionality is not available for the Variable Offset Selection Rule, however there is a way to accommodate ply staggering with this rule. In addition to the offsets, varying ply taper angles can also be defined in the form of a 1-D Look-Up Table. Ply tapering can be used when multiple Modeling Plies share the same Variable Offset Selection Rule. In such cases, the first Modeling Ply will cover the area defined by the offset definition. The subsequent plies will be tapered
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Features based on the angle definition. The tapering is applied not on the Edge Set side but on the offset side, away from the Edge set.
Note: The angle definition can be used to decrease, fix, or increase the covered areas of the subsequent Modeling Plies. Complex patch shapes can be realized with the help of this selection rule. Figure 2.59: Look-Up Table Defines the Offset to Edge Set at a Given Length
Parameters • Edge Set: The offsets offsets are measured along this Edge Edge Set. • Offsets: 1-D Look-Up Table with a list of offsets at different locations. • Angles: (optional) 1-D Look-Up Table with a list of angles at different locations. Only active when
same rule is applied to multiple Modeling Plies. Does not affect the first Modeling Ply. Depending on the local angle, the covered area of the subsequent plies is changed.
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Usage Reference – Angle equals 90 deg: Plies are not changed. – Angle less than 90 deg: Ply coverage decreases with number of modeling plies. – Angle greater than 90 deg: Ply coverage increases with number of modeling plies.
option. • Include Rule Type: The selection envelope can be inverted with this option. Offset Correction Figure 2.60: Offset Correction
• Use Offset Correction: The offset is measured along the surface curvature of the selected Element
Set in a segmented arc when this option is active. • Element Set: The offset correctio correction n is calculated on the curvature curvature of this Element Set. The selection selection
rule can be applied to other Element Sets also, but retains the offset correction.
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Features Table Properties Figure 2.61: Offset Mapping Along a Direction Vector
Look-Up Table Table definition. • Origin: This replaces the origin in the 1-D Look-Up • Direction: This replaces the direction in the 1-D Look-Up Table definition.
Look-Up TTable able data is mapped along the distance dist ance • Distance Along Edge: When active, the 1-D Look-Up of the Edge Set. In this case, the origin is used to determine the start and the end of the Edge Set. The mapping will start at the corner of the edge which is closest to the origin. The zero location in the Look-Up Table coincides with the start of the selection rule.
2.1.7.6. Boolean Selection Rules The Boolean Selection Rule enables you to combine rules based on boolean operations. Supported are Intersect, Add, and Remove. The rules are processed processed as sequential filters and the boolean operation is always applied onto the previous intermediate result. So the order of the rules matters. The first rule is always applied to all shell elements and therefore a first rule with the operation type Add will have no effect.
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Usage Reference Figure 2.62: Boolean Selection Rule
Figure 2.63: Boolean Operation Types
Note the following limitations: • Cutoff Selection and other Boolean Rules cannot be used within a Boolean Selection Rule. • The CSV interface does not support Boolean Selection Rules.
2.1.8. Oriented Selection Sets (OSS)
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Oriented Selection Sets (OSS) are a key concept in ACP.
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Features The OSS define the basis for the lay-up definition. Plies are applied on Oriented Selection Sets and not on Element Sets. The OSS give you an independence from your finite element model and its element normals. OSS combine the following important entities for your composite layup: • The area that plies are applied to. • The orientation, or side of the shell mesh on which the plies are applied. • The reference direction defining the 0° fiber direction. All ply angles are relative to this direction.
The area of an OSS can be controlled further with the help of Selection Rules defined in the Rules tab. You may also use the draping algorithm, in the Draping tab, to define the reference direction on the OSS. The following figure shows an example of an Orientation Point selected sel ected on the mesh and pointing outwards. The section cut indicates that the lay-out is built in the outwards direction. Figure 2.64: Orientation Point Definition
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Usage Reference Figure 2.65: Definition
An Oriented Selection Set is defined by: • Name: Name of the OSS. • Element Sets: Underlying elements for the OSS definition • Orientation Point: Offset direction is defined at this point. The point should be inside and close to the
reference surface, otherwise the mapping of the offset direction can result in wrong results. • Orientation Directions: Vector defining the offset (normal) direction at the Orientation Point. • Reference Direction: Defines the 0° direction of the OSS. – Selection Method: Defines the mapping algorithm for the Rosettes if more than one Rosette is used.
Reference nce Direction Direction (p. 120) 120).. For more information, see Refere – Rosettes: One or more Rosettes defining the Reference Direction for each element through the selected
method. – Reference Direction Field: Defines the direction column of a 3-D Look-Up Table. Only applicable to
the tabular values method. Use the Flip button to reverse the offset direction.
2.1.8.1. Reference Direction
The Reference Direction can be defined by Rosettes R osettes or from tabular values. A single Rosette is sufficient for the definition of the Reference Direction. Multiple Rosettes can be selected for one Oriented Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Features Selection Set to obtain complex Reference Direction definition. In this case, a Selection Method must be used to determine which Rosette is applicable to what part part of the Element Set. The Selection Method offers several interpolation algorithms listed below:
• Ansys Classic: Coordinate system is projected on the elements as defined in ANSYS (see Coordinate
Systems).). Systems • Maximum Angle: Coordinate system in which the Z direction has the maximum angle with the element
orientation defines the Reference Direction of the Oriented Selection Set. • Maximum Angle Superposed: Same as Maximum Angle but all the chosen coordinate systems are
considered and weighted by the maximum difference angle direction. • Minimum Angle: Coordinate system in which the Z direction has the minimum angle with the element
orientation defines the Reference Direction of the Oriented Selection Set. (default) • Minimum Angle Superposed: Same as Minimum Angle but all the chosen coordinate systems are
considered and weighted by the minimum difference angle direction.
• Minimum Distance: Nearest coordinate system of the element defines the Reference Direction of the
Oriented Selection Set • Minimum Distance Superposed: Same as Minimum Distance but all the chosen coordinate systems
are considered and weighted by the distance to the element. Look-Up Up Table Table (p. 94) 94).. The table table must include include • Tabular Values: Interpolated from the values put in a Lookthe location values and a direction column.
Note: If the determination of an element's Reference Direction fails, an alternate computation method is used and a warning is issued. In this case, it is recommended to verify the Reference Directions of the affected Oriented Selection Set. example are a case where a Minimum Angle Selection The bonding laminates of the T-Joint the T-Joint example Method is suitable.
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Usage Reference Figure 2.66: Reference Direction of a Bonding Laminate Defined by Two Rosettes and a Minimum Angle Selection Method
2.1.8.2. Selection Rules The OSS can be intersected with one or several Selection Rules. The intersection of all selected
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entities (Element (Element Sets (p. (p. 84) 84) and and Selection Rule (p. (p. 103) 103))) defines to new extension of the OSS.
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Features Figure 2.67: Selection Rules
Note: Rules (p. 106) 106) use use the lay-up definition to calculate the Although the Cut-off Selection Selection Rules cut location, this Selection Rule has no influence in this case.
2.1.8.3. Draping If the Draping option is activated, the reference direction of the Oriented Selection Set is adjusted and all associated modeling plies use this draped reference direction. Note that the model property Use Draping Offset Correction doesn’t have any effect on the OSS draping. For more information about draping, see Drapi Draping ng (p. (p. 278) 278) and and Draping Draping Simulation (p. (p. 347) 347)..
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Usage Reference Figure 2.68: Draping
The following parameters control the Internal Draping of the OSS: • Seed Point: Starting point of the draping process. • Auto Draping Direction: Uses the reference direction of the oriented selection set. • Draping Direction: Sets the primary draping direction for the draping scheme. The secondary direction
is always orthogonal to the primary. • Mesh Size: Defines the draping mesh size. If this mesh size is defined as negative, ACP uses the default
mesh size. • Material Model: The material model used in the draping simulation, either Woven (default) or Uni-
directional
• UD Coefficient: A parameter between 0 and 1 that controls the amount of deformation in the trans-
verse draping direction. This property is active only when Material Model is set to Unidirectional .
2.1.9. Modeling Groups Modeling Groups define composite lay-ups. Before working with a Modeling Group, it is necessary to specify an Oriented Selection Set and a Material (Fabric, Stackup, or Sublaminate). The ply definition can be organized into Modeling Groups. These Ply Groups have no influence on the ply-ordering and definition but help to group the composite definitions. It make sense to define one Ply Group for each substructure (for example, hull, deck, bulkhead for a boat).
Within a Modeling Group, plies can be created. created. The lay-up is defined as it would be in production. The first ply is also first in the stacking sequence. The lay-up can be tailored by specifying the Orientation, Layering, geometrical Selection Rules, Draping Settings and Edge Tapering for each ply.
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Features A lay-up can also include an Interface Layer for carrying out a fracture analysis of a composite solid model in Mechanical. The interface layer is a separation layer in the stacking sequence. It can be used to analyze the crack growth of existing existing cracks. The crack topology is defined with an interface layer in ACP while all other fracture settings are specified in Mechanical. The interface layers are exported INTER204 or INTER205 INTER205 elements elements and can be used to set up a Cohesive Zone Model (CZM) or a as INTER204 Virtual Crack Closure Technique Technique (VCCT ) analysis. They can also be be used to define contacts zones Debonding in in the between two layers. For more information, see Interface Delamination and Contact Debonding Mechanical User's Guide.
(p. 23) 23).. Changes can also be Lay-ups can also be defined or changed using the Excel Excel Link interface (p. made by importing or exporting the lay-up as a .CSV file (p. (p. 253 253)).
2.1.9.1. Modeling Group Structure The Modeling Group node has three sub-levels: lay-up is defined at this level. The other two levels levels are built automatically automatically • Modeling Ply (MP): The ACP lay-up from information defined in this level. • Production Ply (PP): Production Plies are generated derived from the Modeling Ply definition (Ma-
terial and Number of Layers). A Fabric and Stackup is one Production Ply. A Sublaminate typically contains more than one Production Ply. In addition the Number of Layers option is also propagated
to this level. • Analysis Ply (AP): The analysis plies describe the plies used in the section definition for the ANSYS
solver. A Fabric results in one Analysis Ply. A Production Ply without an Analysis Ply indicates that the resulting Analysis Ply contains no elements and is therefore not generated. In the example below, there are three different MP separated by one interface layer: • ModelingPly 1: Defined with a single Fabric • ModelingPly 2: Defined with a Stackup of two Fabrics • ModelingPly 3: Defined with a Sublaminate containing three production plies (Stackup, Fabric,
Stackup), which results in five analysis plies. The interface layer lies between the second and third modeling plies.
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Usage Reference Figure 2.69: Object Tree of a Layup Definition
Shortcuts exist to easily navigate through the ply definition. Use the square brackets keys ( [ and ] ) to move up and down through the plies.
2.1.9.2. Modeling Group Tree Object Context Menu The context menu of Modeling Group in the top level of the object tree contains the following options: • Create Modeling Group: Create a Ply Group with the default name. • Create Imported Modeling Group: Create an Imported Ply Group with the default name. • Export to CSV file: Export all plies with all modeling ply definitions to a .CSV file (see Import from
/ Export to CSV File (p. 143) 143)).). • Import from CSV file: Import plies from a .CSV file (see Import fro from m / Export to CSV File (p. (p. 143) 143)))
Figure 2.70: Context Menu of Modeling Groups
2.1.9.3. Individual Modeling Group Context Menu The context menu of an individual Modeling Group has these options:
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Features
• Properties : Display the Modeling Ply Properties dialog. • Create Ply: Create and define a new ply. • Create Interface Layer: Create and define an interface layer for fracture analysis. • Create Butt Joint Sequence : Create and define a new butt joint sequence. • Update: Update the model until all Modeling Plies of this group are up-to-date. • Paste: Paste a ply from the clipboard. • Delete: Delete the selected Modeling Group. • Export to CSV file: Export the whole modeling group with all modeling ply definitions to a .CSV file
(p. 143) 143)).). (see Import from from / Export to CSV File (p. • Import from CSV file: Import a modeling group from .CSV file (see Import from / Export to CSV
File Fi le (p. 143 143))). • Export Plies: Export the ply offset geometry as a .STP, .IGES, or STL file (see Export Ply Geo-
metry met ry (p. 144 144))).
2.1.9.4. Modeling Ply Properties The following properties are needed for a Modeling Ply definition:
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Usage Reference Figure 2.71: General Information
• Name: Name of the Modeling Ply. • Oriented Selection Sets: Defines the offset and material direction. • Material: Modeling Ply Material (Fabric, Stackup or Sublaminate). • Ply Angle: The design angle between the reference direction and the ply fiber direction. • Number of Layers: Number of times the plies are generated. • Active: Active plies are considered in an analysis, inactive plies are present but not considered. • Global Ply Nr: Defines the global ply order. Per default a new Modeling Ply is added after the last
Modeling Ply of the Modeling Group The order of the Modeling Plies in the Modeling Groups is equal to this value.
2.1.9.4.1. Draping It is possible to consider the draping effects which occur during the production process in the lay-up definition. The draping approach approach can be specified in the Draping tab of the Modeling Ply Properties dialog. The following types of draping are available: • No Draping (default) • Internal Draping: The draped fiber directions are determined by the internal ACP draping algorithm.
• Tabular Values: Draped fiber directions are interpolated from a Look-Up Table.
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Features The parameters for Internal Draping and Tabular Values are explained below.
Note: Draping can also be assigned to an Oriented Oriented Selection Set (OSS) (p. (p. 123) 123).. In that case, the Reference Direction of the OSS is adjusted. All associated modeling plies use this draped reference direction. This avoids running multiple draping draping simulations on the same surface. If Internal Draping is applied to a modeling ply associated with a draped OSS, then an independent draping simulation is started for the Modeling Ply.
Internal Draping The following parameters control the Internal Draping: • Seed Point: Starting point of the draping process. • Draping Direction: Sets the primary draping direction for the draping scheme. The secondary dir-
ection is always orthogonal to the primary. – Auto Draping Direction: Uses fiber direction of the production ply. – User-Defined Direction: Uses the defined vector. • Mesh Size: Defines the draping mesh size. If this mesh size is defined as negative, ACP uses the
default mesh size. • Thickness Correction: The thickness of the draped ply is corrected based on the shearing (see
Thickness Correction (p. 350) 350)).). Figure 2.72: Internal Draping Definition
Tabular Values
The tabular value draping options lets you choose the draped fiber directions from vectors in a Look-Up Table:
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Usage Reference • Correction Angle 1: Sets the draped fiber direction. • Correction Angle 2: Sets the draped transverse direction.
Figure 2.73: Draping with Tabular Values Definition
2.1.9.4.2. Selection Rules Like in the definition of an Oriented Selection Set, a Modeling Ply can have one or more Selection Rules Rul es (p. 103 103)). The combinatio combination n of all Element Sets (p. (p. 84) 84) and and active Selection R Rules ules (p. (p. 103) 103) defines defines the extension of the Modeling Ply. Each rule has its own boolean operator (intersect, add, or remove) which allows you to define arbitrary combinations of rules (see Boolean Operation Types (p. 118) 118)).).
Template Rules In addition, the Selection Rule parameters can be redefined in the Modeling Ply definition. This prevents the same Selection Rule from being defined multiple times and allows staggering to be defined with a single Selection Rule. In the Rules tab, activate Template as True for those selection rules that have to be treated as template rule and set the values.
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Features
The template parameters for each selection rule type are given in the table below: Rule Type
Parameter 1
Parameter 2
Parallel Selection Rule
Lower Limit
Upper Limit
Tube Selection Rule
Outer Radius
Inner Radius
Cylindrical Selection Rule
Radius
-
Spherical Selection Rule
Radius
-
Cutoff Selection Rule
-
-
Geometrical Selection Rule (Geometry) In-plane capture
tolerance
-
Variable Offset Rule
-
-
Boolean Selection Rule
-
-
2.1.9.4.3.Thickness The thickness of the ply is defined by default defa ult by the thickness of the ply material.
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Usage Reference Figure Figu re 2.74: Thickness Thickness Definition
For Fabrics Fabrics the ply thickness can ca n also be defined by a CAD Geometry or Tabular Values. The thickness options are: Thickness definition method. method. • Type: Thickness Figure Figu re 2.75: Thickness Thickness Definition Options
– Nominal: The thickness defined in Fabrics Fabrics is used for the thickness definition.
(p. 86) 86).. In the case of a thickness is calculated from from a CAD Geometry Geometry (p. – From Geometry: The thickness complex core ply, it can be helpful to work with a CAD Geometry defining the thickness distribution of the core. ACP samples through the CAD Geometry for each element and maps the thickness. The thickness is evaluated in the element normal direction.
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Features Figure 2.76: Core Geometry
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Usage Reference Figure 2.77: Resulting Section Cut
– From Table: The thickness is evaluated from a data field. ACP inter- or extrapolates the thicknesses
for each element. One data point contains the global coordinates and the thickness values. The Tables (p. 94) 94) for values in the table can be used as absolute or relative thickness. See Look-Up Look-Up Tables more information on how to define this table. • Core Geometry: Thickness Thickness of the CAD geometry is mapped to the mesh. • Thickness Field: Thickness is determined by mapping a value field to the mesh. • Thickness Field Type: – Absolute Values: Values in the Look-Up Table define the thickness. – Relative Scaling Values: Values in the Look-Up Table are scaling factors. • Taper Edges: adds an edge tapering to the selected Edge Set.
It is common that core plies are tapered along the boundary. The Taper Edges option allows you to define a taper angle and a taper offset for each edge. The figure below shows a 15 degree tapering along the edge on the left. The thickness is 0 at the selected edge and grows with the specified specified angle. The Taper Edges option is intended for applying a taper angle to a single
ply, for example a core material. When applied to multiple Modeling Plies the thickness distri 269) and butions of all plies are superposed. For more information, see Edge Tapering Tapering (p. 269) Tapering of Multiple Plies (p. 272) Tapering 272)..
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Features Figure 2.78: Edge Tapering
Figure Figu re 2.79: Taper Edge Example
By default, ACP analyzes ply tapering at the element centers. Each element is cropped from the ply if the ply thickness at the element center is negative. This binary representation may Thicknesss (p. 58) 58) is is enabled, the not be sufficiently accurate in certain cases. If the Use Nodal Thicknes
ply tapering will be refined, which results in a more accurate model. For more information, see Element- vs. Node-based Thicknesses Thicknesses (p. 61) 61)..
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Usage Reference
2.1.9.4.4. Modeling Ply Context Menu The context menu for Modeling Ply has the following options: Figure 2.80: Right-Click Modeling Ply Menu
• Properties: Display the Modeling Ply Properties dialog. • Update: Updates the selected Modeling Ply. • Active/Inactive: Activate or deactivate the selected Modeling Ply. Inactive plies are defined in the
database but not considered in the analysis. • Create Ply Before: Create a new ply before the selected one. • Create Ply After: Create a new ply after the selected one. • Reorder: Move the selected Modeling Ply (or plies if several are selected) before or after another
defined ply.
• Copy: Copy the selected Modeling Ply to the clipboard. • Paste: Paste a Modeling Ply from the clipboard. • Paste Before: Paste a Modeling Ply from the clipboard before the selected one.
• Paste After: Paste a Modeling Ply from the clipboard after the selected one. • Delete: Delete the selected Modeling Ply.
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Features Ply ly (p. (p. 144) • Export P
2.1.9.5. Interface Layer Properties The Interface Layer is i s defined by two t wo sets of surfaces: • The first set is the total surface of the open interface. This is the surface along which a crack can
propagate. It is defined by an Oriented Selection Set in Interface Layer Properties dialog under the General tab.
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Usage Reference Figure 2.81: Interface Layer Properties - General
an n Oriented Selection Set in Inter• The second set is the surface of the open interface. It is defined by a face Layer Properties dialog under the Open Area tab. Figure 2.82: Interface Layer Properties - Open Area
The Interface Layer can ca n be activated or deactivated with a check box. You can also change the global number of an Interface Layer (Global Ply Number). Interface Layers are only taken into consideration in solid model generation and further processes. All shell based analyses ignore any Interface Layers.
2.1.9.6. Butt Joint Sequence The Butt Joint Sequence allows you to define butt joints between Modeling Plies. A butt joint
consists of sequences (master and slave plies) which specify the lay up on both sides of a butt joint. The Butt Joint Sequence object automatically detects where the selected plies join and generates butt joints instead of drop-offs.
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Features Figure 2.83: Drop-Off Elements and a Butt Joint Between Two Cores
The Butt Joint Sequence Properties window contains the following options:
• Active: Active plies are considered in an analysis, inactive plies are present but not considered. • Global Ply Number: Defines the global ply order. By default, a new Sequence is added after the last
one in the Modeling Group. The order of the Plies Plies in the Modeling Groups is equal to this value.
• Master Plies: Sequences which pass their thickness on to the other plies of a Butt Joint Sequence. A
Master Ply can be a Modeling Ply or a Modeling Group. The Level column specifies which sequence defines the thickness at a butt joint. The sequence with the lower level is dominant where the other Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Usage Reference sequence inherits the thickness. Potential differences in the thickness between the sequences are graduated over one element within the sequence with the higher level (the transition zone in the following image).
• Slave Plies: Slave plies inherit the thickness from Master Plies but do not pass it further. This means
that drop-offs are generated where two slave plies join.
In most cases, you can define a Butt Joint Sequence without the use of slave plies. An example where slave plies may be necessary would be a butt joint on a cylinder where you need dropoffs:
2.1.9.6.1. Butt Joint Sequence Notes and Limitations
The following is a list of notes limitations of the Butt Joint Sequence: • A Modeling Ply can only be used in one Butt Joint Sequence
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Features Cuts uts (p. (p. 156) • Butt Joint Sequences do not affect shell models. They are only considered in Section C modell extrusion (p. (p. 163) 163) does does not consider butt joints • Solid mode • A Butt Joint Sequence can only be linked to Modeling Plies with a lower Global Ply Number. • The butt joint can not be updated if a ply sequenced between the first and last ply of the butt joint
covers the node where the plies join, shown in the following diagram:
Modeling g groups (p. (p. 124) 124) may may be easier to work with if a butt joint consists of a large number of • Modelin plies
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Usage Reference
2.1.9.7. Production Ply The context menu of the Production Ply has the following options: Figure 2.84: Production Ply Context Menu
• Properties : Display the Production Ply Properties dialog. These properties cannot be edited, but
can be viewed or printed for informational purposes.
production or design. The • Export Flat Wrap: Export the flat wrap as a .DXF, .IGES, or .STP file for production draping option must be activated to obtain a flat wrap. Refer to Drapin Draping g (p. (p. 278) 278) for for more information on draping and flat wrap. (p. 144) Ply (p. • Export Ply
2.1.9.8. Analysis Ply The context menu of the Analysis Ply has the following options: Figure 2.85: Analysis Ply Context Menu
• Properties : Display the Analysis Ply Properties dialog. These properties cannot be edited, but can
be viewed or printed for informational purposes.
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Features
• Export P Ply ly (p. (p. 144)
2.1.9.9. Import from / Export to CSV File The CSV interface allows you to create a comma separated value file to be edited in a spreadsheet program such as Excel or OpenOffice. This can be efficient if you wish to edit the parameters of many plies. For additional information on the format, see CSV Format Format (p. (p. 253) 253)..
2.1.9.9.1. Export All the information are exported to a .CSV file. This file can be used to give the lay-up information back to a CAD System or can be modified and imported.
2.1.9.9.2. Import The modified .CSV file can be imported. There are three different import options to handle the update of the lay-up: • Update Lay-up: During the import operation, definitions are updated, additional plies are generated and deleted according to the .CSV file. • Update Properties Only: During the import operation, definitions are updated with properties
given. • Recreate Lay-up: During the import operation, existing lay-up is deleted and generated from
scratch.
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Usage Reference Figure 2.86: CSV Import with Update Options
2.1.9.10. Export Ply Geometry The ply geometry and fiber directions can be exported to a CAD file format. Using this feature, you can check geometry clashes in CAD assemblies. Other uses may include using the data for CNC programming or for the projection of orientation vectors of the fibers onto tooling surfaces. It is possible to export the surfaces or boundaries with an offset. This gives you full control over surfaces to be exported. The Export Ply Geometry feature has the following settings: (STEP, IGES or STL). The STL format only supports the ply surfaces. • Format: The geometry file format (STEP, Directions and boundaries can only be exported in the STEP or IGES format. • Path: Specify the file name and file path. • Ply Level (only available for Export Ply Geometry at Modeling Group level): – Modeling Ply Wise: Every Modeling Ply is exported. – Production Ply Wise: Every Production Ply is exported. – Analysis Ply Wise: Every Analysis Ply is exported. • Offset Type: – No Offset: Ply geometry is exported with no offset to the reference surface (Oriented Selection
Set). – Bottom Offset: Bottom surface of the ply relative to the direction of the reference surface is exported. – Middle Offset: Middle surface of the ply is exported. (default)
reference ence surface is exported. – Top Offset: Top surface of the ply relative to the direction of the refer • Export Ply Surface: Ply surface is exported as a shell surface.
• Export Ply Contour: Outlining contour of the ply surface is exported as perimeter lines. • Export Fiber Directions: Fiber orientations are exported as orientation vectors.
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Features – Export Draped Fiber Direction: Include the draped fiber direction (the fiber direction is included
if draping is not enabled). – Export Draped Transverse Direction: Include the draped transverse direction (the transverse dir-
ection is included if draping is not enabled). – Arrow Type: Choose between No Arrow (line without an arrowhead), Standard Arrow and Half
Arrow. – Arrow Length: Specify the arrow length.
Figure 2.87: Export Ply Geometry Window
2.1.10. Imported Modeling Group Imported Modeling Groups organize plies that are independent of the shell reference surface. It is important to understand that Imported Modeling Groups and the attached Imported Plies do not
contribute to the standard lay-up that is defined by the Modeling Plies applied to a shell reference surface. The table below, below, Table Table 2.1: Key Differences Between a Modeling Ply and Imported Modeling Ply (p. (p. 146 146)), lists the major differences when compared to a Standard Standard Modeling Ply (p. (p. 127) 127)..
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Usage Reference The structure of the Imported Modeling Group follows the pattern of the standard Modeling Group and is described in the section above, Modeling Modeling Group Structure Structure (p. 124) 124).. The equivalent equivalent to Modeling Modeling Ply, Production Ply and Analysis Ply are Imported Modeling Ply, Imported Production Ply and Imported Analysis Ply, respectively. Workflow - Imported Plies (p. 342) 342).. An example workflow is available in Chapter 4: 3D Ply Workflow
2.1.10.1. 2.1.10.1.T Tree Object Context Menu The context menu of the Imported Modeling Group contains the following options: • Properties: Show the dialog window. • Update: Update the model until all Imported Modeling Plies of this group are up to date. • Create Imported Ply: Add a new Imported Modeling Ply. • Paste: Create a new Imported Modeling Ply by copying the object on the clipboard. • Delete: Remove all attached Imported Modeling Plies. Then remove the group object itself.
2.1.10.2. Imported Modeling Ply An Imported Modeling Ply represents a single ply that has a 3D surface mesh which is independent of the reference surface. That allows you to model thick and/or comp complex lex 3D laminates in ACP based on separate ply geometries. It can be used in combination with an Imported Solid Model (lay-up mapping). mappin g). The section 3D Ply Workflow - Imported Plies (p. 342) 342) in in chapter four provides a sample workflow and instructions on how to work with Imported Plies. The table below lists the key differences between a standard Modeling Ply and an Imported Modeling Ply: Table 2.1: Key Differences Between a Modeling Ply and Imported Modeling Ply
Mesh and Extension
Modeling Ply
Imported Modeling Ply
Scoped to the shell reference surface
Holds its own imported mesh (surface) that is independent of the reference surface
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The lay-up orientation is defined by Oriented Selection Sets
Orientation
The orientation is defined by the element normals of the imported mesh and the offset type (bottom, middle, or top).
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Features Reference Direction
The reference directions d irections of the ply are defined by Oriented Selection Sets.
Supports the same features as an Oriented Selection Set, but the definition is part of the Imported Modeling Ply object.
Material
Supports Fabrics, Stackups and Sub-Laminates
Supports Fabrics only
Shell Model / Analysis
Contributes to the shell lay-up
Is ignored in any shell analysis
Solid Model Extrusion
Considered in the standard Solid Model feature
The standard solid model extrusion ignores imported plies.
Imported Solid Model / Lay-Up Mapping
Considered in the lay-up mapping of the Imported Solid Model if the scope is set to Element Sets
Considered in the lay-up mapping of the Imported Solid Model if the scope is set to Use Imported Plies.
The context menu of an Imported Modeling Ply contains these actions: • Properties : Display the ply properties dialog. • Update: Update the model until this ply is up-to-date. • Active/Inactive: Choose whether an Imported Ply is active or suppressed in all subsequent analyses. • Copy: Copy into the clipboard. • Paste: Create a new Imported Modeling Ply by copying the object in the clipboard. • Delete: Delete the selected ply.
2.1.10.2.1. Imported Modeling Ply Properties Standard features in ACP are used to define the thickness distribution, reference and fiber directions. An Imported Modeling Ply contains the properties listed below. Since the meaning is often identical if compared with an Oriented Selection Set or Modeling Ply, the same wording is used here.
General Properties Refer to the figure below, General Properties Options. • Offset: Determines if the surface mesh defines the bottom, mid or top surface of the ply. • Mesh Input: Indicates whether the mesh was imported from a HDF5 Composite CAE or from a CAD
geometry. This is automatically set by the application based on the input source and is therefore read-only. • CAD Surface: If the Mesh Input is From Geometry, then the selected Virtual Geometry defines the
surface of the ply.
• Selection Method: Defines the mapping algorithm for the Rosettes if more than one Rosette is
used. For more information, see Reference Direction in the section above, Oriented Selection Sets (p. (p. 118 118)).
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Usage Reference Rosettes (p. (p. 90) 90) will will define the Reference Direction • Rosettes: Select which method one or more Rosettes for each element. • Reference Direction Field: Defines the direction column of a 3-D Look-Up Table. Only applicable
to the tabular values method. • Ply Material: Select the Fabric that defines the material of the ply and nominal thickness. • Ply Angle: Set the design angle between the reference direction and the ply fiber direction.
Figure 2.88: General Properties Options
Draping Properties Refer to the figure below, Draping Properties Options. • Type: Specifies the type of draping – No draping: Constant thickness defined by the Fabric – Tabular values: Variable thickness by mapping a LookUp Table field • Correction Angle 1: Sets the draped fiber direction • Correction Angle 2: Sets the draped transverse direction
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Features Figure 2.89: Draping Properties Options
Thickness Properties Refer to the figure below, Thickness Properties Options. • Type: Thickness Thickness definition method method – Nominal: The thickness defined in Fabrics Fabrics is used for the thickness definition. – From Table: The thickness is evaluated from a data field. ACP interpolates or extrapolates the
thicknesses for each element. • Thickness Field: Thickness is determined by mapping the selected LookUp Table Column to the
mesh. • Thickness Field Type: – Absolute Values: Values in the Look-Up Table define the thickness. – Relative Scaling Values: Values in the Look-Up Table are scaling factors.
Figure Figu re 2.90: Thickness Thickness Properties Options
Limitations • StackUps and Sublaminates are not supported as ply material.
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Usage Reference • The thicknesses and angles can only be visualized on the Imported Solid once the mapping is done.
su rface and at least one ply, even if they are not used in • The ACP model always needs a reference surface the lay-up mapping (Imported Solid Model) workflow in combination with Imported Plies. • The CAD geometry must be a surface. Solid geometries are not supported. • Export Composite Definitions to ACP File … does not support Imported Ply objects • The Excel Interface cannot be used in combination with Imported Plies.
do not take Imported Plies into account. • The features Sensor and Ply Book do • The variable material workflow is not supported. That includes the field definitions and material
plots. • The HDF5 Composite CAE Export does not support Imported Plies.
2.1.10.3. Imported Production Ply An Imported Production Ply is the output of an Imported Modeling Ply update. The context menu contains the following option: Properties: Display the Imported Production Production Ply Properties Properties dialog. These properties cannot be
edited but can be viewed or printed for informational purposes. Figure 2.91: Imported Production Ply Dialog
Note, to see the mesh and ply data, select the parent Imported Modeling Ply.
2.1.10.4. Imported Analysis Ply An Imported Analysis Ply is the result of an Imported Modeling Ply update. update. The context menu contains the following option: Properties : Display the Imported Analysis Ply Properties dialog. These properties cannot be
edited but can be viewed or printed for informational purposes.
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Features Figure 2.92: Imported Analysis Ply
Note, to see the mesh and ply data, select the parent Imported Modeling Ply.
2.1.11. Field Definitions During the Vari Variable able Material Material Data (p. 300) 300) workflow, workflow, the variation of the scalar variables controlling the local state of the material properties over the finite element model can be defined using Field Definition objects. You can scope Field Definition objects to Element Sets, Oriented Selection Sets, and Modeling Plies. If your field definition is based on Elements Sets or Oriented Selection Sets, all of the layers within your scoping are affected. When scoping to Modeling Plies, only the associated Analysis Plies are affected. Therefore, it is possible implement both a “layer-wise” as well as a “element-wise” application of field definitions in your finite element model. Parts of the finite element model not covered by Field Definition Objects assume default values of the field variables. In order to understand the effect of a Field Definition Object, contour plots of the field variables are Field d Definition Plot Plot (p. 205) 205) topic topic of the Layup Plots (p. (p. 196) 196) section. available Fiel
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Usage Reference Figure 2.93: Field Definitions Context Menu
As illustrated below, once you create a Field Definition object, you use the context menu to define its features. Menu options include: • Properties : Display the properties window of the selected Field Definition. • Update: Update the selected Field Definition. • Active/Inactive: Toggle field definition object active or inactive • Copy: Copy the selected Field Definition to the clipboard. • Paste: Paste a table Field Definition from the clipboard. • Delete: Delete the selected Field Definition.
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Features Figure 2.94: Field Definition Context Menu
Field Definition Object Properties Field Definition objects can be used for element-wise and layer-wise specification of the variation of a scalar variable controlling Variable Variable Material Data on subparts of your finite element model. You can scope layer-wise specifications to specific Modeling Plies. The properties dialog is illustrated below. Properties include: • Name: Name of the Field Definition. This field is initially populated with an default name.
your • Active: This selection indicates that the application processes the Field Definitions during your analysis. Inactive definitions are ignored. Variables as as defined • Field Variable Name: This drop-down menu provides provides a list of available Field Variables in the in the Engineering Data Workspace. • Scope Entities: Entry field to define the applicable element-wise field definitions. You can use a
combination of Element Sets and Oriented Selection Sets in order to scope the definition to subparts of your model. For layer-wise field definitions you can use a combination of Modeling Plies to scope
the definition toModeling subparts of your model; the Field Definition will be applied only to Analysis Plies attached to the Plies. • Look-Up Table Column: Select the scalar Look-Up Table column from which the state of the field
variable is interpolated from.
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Usage Reference • Include Shell Offset: Specify whether or not to include the shell offset of each analysis ply for the
interpolation process. The default is to interpolate the state of the field variables variables at the shell element centroid. For solid elements the actual position of each analysis ply is automatically considered and this behavior cannot be changed. Figure 2.95: Field Definition Object Properties Element-Wise Field Definition
Layer-Wise Field Definition
2.1.12. Sampling Points Sampling Points can be used in postprocessing mode to access to ply-wise results. In addition the Sampling Point functionality provides Layup Plots, through-the-thickness postprocessing plots, and laminate engineering constants. ACP samples through the element near the given coordinates. After the update all plies (Modeling Ply, Production Ply, and Analysis Ply) are listed and can be selected for postprocessing. In the General tab of the Sampling Point Properties dialog the sampling point and direction can be defined.
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Features Figure 2.96: Sampling Point Properties - General Tab
• Sampling Point: The sampling sampling point in global coordinates coordinates.. The nearest element element to the point is the
sample. • Sampling Direction: Normal direction of the sampling point. The ply sequence will be given in this
direction. • Element ID (Label): Element number closest to the defined sampling point. (informational only)
A detailed description of the options Offset is Middle and Consider Coupling Effect can be found (p. 387) 387).. in Analysis Analysis Options (p. Use the [ and ] buttons to navigate easily through the ply definition. The Analysis tab of the Sampling Point Properties dialog provides extended postprocessing functionality. The lay-up can be visualized and analyzed by evaluating the polar properties and equivalent laminate stiffnesses based on the classical laminate theory. The distributions of the postprocessing postprocessing results (strains, stresses, and failure criteria) are shown in 2-D plots. The view postprocessing results, the solution, and the set of interest must be selected. The lay-up visualization can be set to display Modeling, Production, and Analysis Plies present in the
Sampling Point. The Material, Thickness, and Angle can be displayed additionally as text labels for every ply in the plot. The angle displayed for Modeling and P Production roduction Plies always matches the design angle in the Modeling Ply and Material definitions. Note that the angle for the Analysis Ply is always given in relation to the reference reference direction of the Sampling Point. This reference direction is
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Usage Reference indicated by a yellow arrow at the Sampling Point in the scene. You can can change the reference direction in the General tab if desired.
Note: Classical Laminate Theory is described in Classical Lami Laminate nate Theory Theory (p. 382) 382).. Figure 2.97: Layup Sequence and Enhanced Postprocessing
Stresses and strains shown in the 2-D plot are the values at the element center (interpolated) at the top and bottom of the layer. The 2-D failure plot shows the worst IRF IRF,, RF or MoS factor of all failure criteria, failure modes evaluated, and integration point level.
2.1.13. Section Cuts Section Cuts enable a visual verification of the lay-up definition on an arbitrary section plane through the model. The lay-up definition at the section cut can be exported to Mechanical APDL or BECAS (p. (p. 255 255)). The Section Cut Properties dialog contains the following options:
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Features Figure 2.98: General Section Cut Properties
• Name: Name of the Section Cut. • Interactive Plane: If active, modify the section plane directly in the Scene. If inactive, the following
options are required: – Origin: Origin of the section plane. – Normal: Normal direction of the section plane. – Reference Direction 1: First in-plane reference direction (x-axis). • Show Plane: Plot the section plane. • Type: Mode of extrusion extrusion (p. (p. 159) 159).. • Scale Factor: Scale the offsets of all plies.
factor. • Core Scale Factor: Thickness of the core plies are scaled by this factor. • Section Cut Type: Select which ply type is plotted: – Modeling Ply Wise: Modeling Plies are plotted. – Production Ply Wise: Production Plies are plotted.
– Analysis Ply Wise: Analysis plies are plotted.
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Usage Reference Figure Figur e 2.99: Wire Frame Frame Options
• Interaction Type: Define the intersection of the section plane and the model: – Normal to Surface: Plies are plotted as normal to the intersected elements. – In Plane: Plies are plotted in the section plane.
Figure 2.100: Surface Options
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• Use Default Tolerance: Use the default tolerance (0.1% of the average element size). If unselected, you
should specify the Tolerance: – Tolerance: Defines the minimum edge length. Edges smaller than this length are merged.
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Features Sweep based extrusion: • Use Default Interpolation Settings: Use default interpolation settings. If unselected, you must
specify Search Radius and Number of Interpolation Points. For more information, see 3-D LookUp Table Table (p. 101) 101)..
2.1.13.1. Types of Extrusion 2.1.13.1.T The following extrusion types are available: investigate the lay-up lay-up of shell elements. The mid-surface mid-surface • Wire Frame: This type can be used to investigate of the plies are represented by lines, as shown below.
• Surface Section Cut: For this type, the plies are shown as surface elements. A surface section
cut generates a continuous mesh that can be used for 2D analyses. Therefore, drop-off elements are generated by default at the ply boundaries (like the solid model extrusion). If this does not represent the real structural behavior, then you can use the Butt Joint Sequence Sequence (p. (p. 138) 138) to to control the connectivity of the adjacent plies and drop-off behavior behavior.. The surface section cut supports two types of extrusion: follows the element normals of the reference reference surface. The offset – Surface Normal: The extrusion follows direction does not change during the extrusion. – Surface Sweep Based: The offset direction follows the interpolated element normals (potential
Table (p. 94) 94) that that field defined by the shell normals). The interpolation is based on a Look-Up Look-Up Table specifies the Search Radius and Number of Interpolation Points. In general, the sweep-based algorithm is more robust in sharp corners with thick laminates; however,, the extrusion of t-joints may be less accurate. however a ccurate. The sharp corner in Figure 2.99 illustrates the difference between the extrusion algorithms. • Surface Normal: The plies are illustrated illustrated by surface elements. The extrusion extrusion follows the element
normals.
elements. The offset offset direction follows follows the • Surface Sweep Based: The plies are shown as surface elements. interpolated element normals (potential field defined by the shell normals).
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Usage Reference Figure 2.101: Element Normals
The interpolation is based on a Look-Up Look-Up Table Table (p. 101) 101) which which specifies the Search Radius and Number of Interpolation Points. Figure 2.102: Surface Normal vs. Surface Sweep Based Extrusion
angles es (p. 196 196)). For more information, Section Cuts can also be used to plot ply-wise properties such as angl (p. 196) 196).. see Layup Plots Plots (p.
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Features Figure 2.103: Ply-Wise Angles on the Surface Section Cut
2.1.13.2. Section Cut Notes • The line segments are locally enlarged (if necessary) to improve the t he quality of the surface elements. • Plies covering more than 3 components cannot be extruded (see figure below):
Figure 2.104: Supported Lay-up for T-Joints
2.1.13.3. Section Cut Export The Section Cut can be exported in two formats:
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Usage Reference Figure 2.105: Export Surface Section Cut Options
• The becas.in format includes the 2-D mesh, material properties, and element orientations. • The mapdl.cdb format supports only the 2-D mesh and the named selections (top and bottom node
sets derived from the element sets of the shell mesh). This can be useful to fill the Section Cut with a core material (for example).
2.1.14. Sensors A Sensor provides the evaluation of global results like price, weight, or area. Results can be evaluated for specific parts, materials or plies. Figure 2.106: Sensor Properties
The Sensor Properties dialog contains the following options:
• Name: Name of the Sensor. • Sensor Type: Define the evaluation type. – Sensor by Area: Select one or several Element Sets or Oriented Selection Sets.
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Features – Sensor by Material: Select Fabric(s), Stackup(s) and/or Sublaminates. If a Fabric is selected, the plies
in the Sublaminates are also considered in the evaluation; plies in a Stackup are not. – Sensor by Modeling Ply: Select one or more plies. – Sensor by Solid Model: Select one or more solid models. For a solid model sensor type, only weight
and center of gravity are computed. • Entities: Select the corresponding entities by clicking them in the tree. • Measure: Display results of different quantities. – Weight: Mass of the selected entity. – Covered Area: Surface area of a selected Element Set, Oriented Selection Set, or tooling surface area
that is covered by the composite lay-up of the selected Material or Modeling Ply. – Modeling Ply Area: Surface area of all Modeling Plies of the selected entity. – Production Ply Area: Surface area of all Production Plies of the selected entity.
Price rice for the composite lay-up of the selected entity. The price per area is set under Material – Price: P Data > Fabrics or Material Data > Stackups. – Center of Gravity: Center of gravity of the selected entity in the global coordinate system.
2.1.15. Solid Models ACP knows two different types of solid models: the first type is simply called Solid Model and is based on an extrusion algorithm that generates a volume mesh from the shell mesh and its Composite Definitions. The second type is named Imported Solid Model and maps the Composite Definitions onto an external (imported) solid mesh. Figure 2.107: Solid Model Folder with a Standard Solid Model and an Imported Solid Model
The context menu of the Solid Models object contains these actions: • Create Solid Model: creates a new solid model object
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Usage Reference • Paste: adds a new solid model object from the clipboard
Note: The Imported Solid Models can only be created via the Workbench Project Schematic. See the Solid Mo Modeling deling (p. (p. 43) 43) workflow workflow section.
2.1.15.1. Solid Model The Solid Model feature creates a layered solid s olid element model from a composite shell model. The solid element model can be integrated into a Workbench workflow or exported for use outside of Workbench. Analysis Analysis of a Compo Composite site Solid Model (p. (p. 312) 312) explains explains the Solid Model workflow in Modeling deling (p. (p. 285) 285) provides provides general information on solid modeling. Workbench, and Guide to Solid Mo The settings for the t he solid model generation are adjusted under the Solid Model context menu item Properties . The The Solid Model Properties Properties (p. (p. 164) 164) dialog dialog covers what element sets are extruded, the extrusion method, drop-off elements handling and numbering offsets among other things. Extrusion Guides, Snap To, and Cut-off Geometries can be used to shape the Solid Model in a desired Model way. are specified in the Analysis respective subfolders in the Solid tree view. The Analysis view. PliesThey sub-folder shows which Plies are incorporated in the Solid Model. Figure 2.108: Solid Model Feature in the Tree View
2.1.15.1.1. Properties The Solid Model Properties dialog is divided into the following tabs: 2.1.15.1.1.1. General 2.1.15.1.1.2. Drop-offs 2.1.15.1.1.3. Export
2.1.15.1.1.1. General The General tab has the following properties:
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Features Figure 2.109: Solid Model Properties - General
Element Sets
Starting with a shell model and the lay-up definition, the shell elements are extruded to a layered solid element model. Select an Element Set to define the region of the extrusion.
Important: The mid-offset option of Element Sets is not supported for Solid Model extrusion. The ply definition must be defined without this option to obtain the correct solid model position. Extrusion Properties
The lay-up extrusion can be organized in different ways to merge plies with different criteria:
• Extrusion Method: – Analysis Ply Wise: Extrude each Analysis Ply as one solid element layer.
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Usage Reference – Material Wise: All sequential plies containing the same material are grouped in one solid
element layer. A maximum element thickness can be specified that will subdivide the single element layers if necessary. – Modeling Ply Wise: Extrude each Modeling Ply as one solid element layer (for example,
every Stackup or Sublaminate is extruded as one solid element layer). – Monolithic : Extrude the whole lay-up in one solid element layer. – Production Ply Wise: Extrude each Production Ply as one solid element layer if possible.
Depending on the model topology, monolithic modeling groups may be split in order to ensure the cohesion of the resulting solid model. – Specify Thickness: Plies are grouped by iterating through the laminate from the inside
out.. – User Defined: Plies are grouped by iterating through the laminate from the inside out. – Sandwich Wise: Plies on either side of a core material are grouped into single element
layers. The core material is extruded as one element lay layer. er. Figure 2.110: Illustration of Solid Model Extrusion Methods
For extrusion methods other than analysis ply-wise, see Material Handling for Different Extrusion Extrusio n Methods (p. (p. 188) 188).. • Max Element Thickness: Thickness at which a new modeling group will be introduced. If a
single ply is thicker than this value it is split into layers of equal thickness no thicker than this value.
• Start Ply Groups at: A new modeling group is introduced each time the iteration meets one
of the plies specified in this option (User Defined Extrusion Method only)
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Features • Offset Direction: With the Surface Normal option, the extrusion direction is re-evaluated
after each row of solid elements. elements. With Shell Normal option, the extrusion direction stays defined as shell normal. Figure 2.111: Extrusion Direction
An example of both options is shown in the following figure: Figure 2.112: Offset Direction
Solid Model with Surface Normal Direction
Solid Model with Shell Normal Direction
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Usage Reference
Drop-Offs and Cut-Offs The Drop-Offs and Cut-Offs section controls the global material handling for drop-off and cut-
off elements in the solid model. The following options are available: • Global Drop-Off Material: This setting is used when the material handling settings for fabrics
and stackups are set to Global. • Global Cut-Off Material: This setting is used when the material handling settings for fabrics
and stackups are set to Global. Element Quality
ACP performs a shape check during the solid model generation. The checks are similar to Element Shape Testing in Testing in Mechanical APDL. The Solid Model feature has the option to delete elements if they violate the shape checking. Warping is not the only element shape check that is carried out but the warping factor can be adjusted.
2.1.15.1.1.2. Drop-offs The Drop-Offs Tab has the following properties:
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Features Figure 2.113: Solid Model Properties - Drop-Offs
• Drop-Off Method: Define the ply's drop-off before or after the edge.
• Disable Drop-Offs on Top Surface: Deactivates drop-off elements on the top face sheet of the
laminate for the selected (oriented) element sets. • Disable Drop-Offs on Bottom Surface: Deactivates drop-off elements on the bottom face sheet of the laminate for the selected (oriented) element sets. Figure 2.114: Disable Drop-Offs
Disable Drop-Offs option deactivated
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Usage Reference
Disable Drop-Offs option activated
• Connect Butt-Joined Plies: If a composite layer ends away from a mesh boundary it tails off with
a drop-off element. These drop-off elements are degenerated brick elements that are reduced reduced from bricks into prisms. This option can prevent an element drop-off of two adjacent, sequential plies in the same modeling group. By default it is active.
The feature is limited to plies that appear sequentially in the same modeling group. It is not possible to connect all butt-jointed plies that are arranged in a circle. This is a known limitation.
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Features An example of a sandwich structure with divided core material is shown below to demonstrate the use of a ply connection. Figure 2.115: Connect Butt-Jointed Plies Connect Butt-Joined Plies activated
Connect Butt-Joined Plies deactivated
2.1.15.1.1.3. Export The Export Tab has the following properties:
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Usage Reference Figure 2.116: Solid Model Properties - Export
Global Options • Write Degenerated Elements: Include drop-off elements and cut-off elements in the solid
model export. Deactivating this option can lead to holes in the mesh and prevent import into Mechanical. Deactivating this option is not advised during a Workbench workflow. Figure 2.117: Write Degenerated Elements
Export with Drop-off Elements
Export without Drop-off Elements
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Features
(SOLSH190).). • Use SOLSH Elements: Create the model with Solid-Shell elements (SOLSH190 • Drop Hanging Nodes: Remove hanging nodes from model before solve. (default on)
Hanging nodes are nodes which are not connected to all the neighboring elements. Hanging nodes can occur when quadratic hexahedral, tetrahedral, and prism elements are connected together. Hanging nodes can lead to discontinuous deformation fields and are therefore not desirable. When this option is active, element edges containing a hanging node are described as a linear shape function. The following figure shows a quadratic tetrahedral element on top of a quadratic hexahedra element. There is a hanging node on the tet element, highlighted by the red square: Figure 2.118: Quadratic Tetrahedral Element on Top of a Hexahedral Element
• Use Solid Model Prefix: This option makes element components begin with the name of the defined solid model. For example, if the solid model is BULKHEAD, the elements are grouped
into components in the following way: CMBLOCK,BULKHEAD_P9L1_Plies_Top,ELEM, 600! users element component definition
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Usage Reference Transferred Sets • Transfer All Sets: All Edge and Element Sets are transferred. • Transferred Element Sets: Specify Element Sets for transfer. Element Sets become two separate element components with the designation _TOP and _BOT. One element component
coincided with the original element set and the other one lies at the end of the extrusion path. • Transferred Edge Sets: Specify Edge Sets for transfer. Edge Sets are extruded to form surfaces
(an Edge Set transfers to a surface element component). Figure 2.119: Transferred Element Sets in Mechanical
Numbering Offset
Entity numbering is performed automatically in ACP within your Workbench project. Entities of multiple solid models in one ACP setup are automatically renumbered to avoid overlap. The automatic renumbering also takes place when different ACP or Mechanical models are combined in a single analysis system.
The automatic renumbering is activated by default and can be deactivated in the properties of the downstream Mechanical Model cell (see Renumber Mesh Nodes and Elements Automatically). The entity numbering offset can also be controlled manually. Deactivate the Default option to define the offset manually for each of the entities (elements, nodes, materials, sections, coordinate systems). The numbering starts at the defined index and is incremented b byy one
at a time.
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Features Figure 2.120: Properties of the ACP-Pre Setup Cell in the Project Schematic
2.1.15.1.2. Export Solid Model The context menu of Solid Model and Imported Solid Model enables you to export the solid mesh itself or the skin (envelope) of the mesh in different formats.
The skin of the solid model can be exported as STEP, STEP, IGES, STL, or Mechanical APDL (CDB). These representations can be used for instance to construct the geometry of adjacent structures to the solid model or to construct the geometry of filling material in an airfoil structure. Please note Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Usage Reference that the STEP and IGES geometries are build from a mesh based tessellation of the skin. Therefore it might be worth to work with the STL format and the usage of reverse engineering tools (for instance in SpaceClaim) to construct a proper geometrical representation. The CDB format brings the benefit to that you work without a geometry. The analysis solid model itself can be exported as a CDB file. Element shape checking is deactivated in the exported file. You need to check that the material properties are consistent with the mesh units of the CDB file.
Midside Nodes: If available and active, the tessellation of the mesh includes the midside nodes
of the quadratic elements. If not, only the corner nodes are considered. This option is only available for the formats skin:stp, skin:igs and skin:stl.
2.1.15.1.3. Extrusion Guides Solid Model generation for curved geometries and thick layups can lead to boundary edges being extruded in undesirable directions. For example, the extrusion of a dome with a hole at the top results in a solid model with a hole that is not cylindrical. The Extrusion Guide feature allows you to control the extrusion direction of the edges in order to rectify this. The edge of the hole can be used as an Extrusion Guide in the vertical direction to create a cylindrical hole.
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Features Figure 2.121: Extrusion with and without an Edge Set Guide
Multiple Extrusion Guides can be used for one Solid Model. The extrusion itself is controlled with an edge set and a direction vector or with a geometry. geometry. The Extrusion Guide feature also contains a Curvature Control. Control. The Extrusion Guide Properties dialog has the following options:
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Usage Reference Figure 2.122: Extrusion Guide Properties
• Edge Set: Define the Edge Set along which the Extrusion Guide acts.
Extrusion Guide. Guide. • Type: The type of Extrusion – Direction : Defines a direction vector of the extrusion direction of the Edge Set. →
Orientation Direction: By default, the normal direction of the Edge Set is calculated and
defined when an Edge Set is selected. It can also be entered manually. – Geometry: CAD file of a boundary surface is used to define the extrusion path. →
CAD Geometry: Select a previously imported CAD geometry
– Free: No extrusion path is defined but a curvature correction can be activated independently. • Radius: Controls the sphere of influence for mesh morphing. • Depth: controls the bias of the mesh morphing.
Use Curvature Correction: Apply a curvature correction during the solid model extrusion which
results in a smoother extruded surface. Under certain circumstances, deactivating curvature correction can lead to better extrusion results.
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Features You can change the order of Extrusion Guides using us ing the context menu from the tree view. The order in which the Extrusion Guides appear in the tree is their order of execution, which has significant effects when Extrusion Guides intersect. Figure 2.123: Reordering Extrusion Guides
2.1.15.1.3.1. Mesh Morphing The generation of a solid model is by extrusion ex trusion of a shell mesh. By default, extrusion is in the direction of the shell normal direction. The 2-D shell mesh is used as a base for the 3-D solid element mesh, which can have one or more element layers depending on the ply thickness and extrusion method. The Extrusion Guide only affects the extrusion of the element edges that are part of the guided Edge Set. It is either defined by an Edge Set and direction vector or by an Edge Set and a CAD geometry. While the CAD geometry already is a surface, the Edge Set and direction vector are used to define a surface. In both cases, these surfaces serve as target surfaces in the extrusion. The guided edge is initially extruded in the normal direction and then the nodes on the resulting
free surface are moved to coincide with the target surface of the extrusion guide. Mesh morphing is a way to control the propagation of the Extrusion Guide effect through the entire mesh.
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Usage Reference Mesh morphing is governed by the morphing law, shown in Equation Equation 2.1 (p. (p. 180) 180).. It relates the displacement of internal nodes to the displacement of a node of the guided free surface. It can be controlled with the two parameters: • Radius: All elements within the defined Radius from the Edge Set are extruded with a mesh
morphing correction. • Depth: Defines the bias of the mesh morphing (linear with 1, quadratic with 2,...).
(2.1) where: m0 is the distance a node on the free surface has to move in-plane to coincide with the extrusion guide. mi is the distance the inward node of the i th shell element moves in-plane as a result of the mesh morphing. di is the distance between the node in the guided Edge Set and the inward node of the ith shell element. Figure 2.124: Mesh Morphing Diagram
2.1.15.1.3.2. Extrusion Guide Examples The following is an example of a direction-type Extrusion Guide with different mesh morphing radii. The location of the edge set is indicated by the circle in the bottom left corner. corner. The mesh
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Features morphing is only applied to nodes on the shell surface whose distance to the Edge Set is smaller than the radius. Figure 2.125: Example of a Direction-type Extrusion Guide with Different Mesh Morphing Radii
The following is an example of a geometry-type Extrusion Guide with different mesh morphing depths:
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Usage Reference Figure 2.126: Example of a Geometry-type Extrusion Guide with Different Mesh Morphing Depths.
2.1.15.1.4. Snap-to Geometry The Snap-to Geometry feature can alter an extruded Solid Model to align with an imported CAD geometry. The layered Solid Model is locally stretched or compressed so that its selected faces coincide with the CAD geometry. Multiple Snap-to Geometries can be assigned to one Solid Model. The adaptation occurs at the first intersection that is found.
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The feature is only applied to the selected Oriented Selection Set and its selected face (top or bottom). Which face is top or bottom is defined by the normal orientation of the Oriented Selection Set. The height of all the elements through the thickness is altered to an even distribution.
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Features
In the following example, the first picture shows the extrusion without any Snap-to Geometry operation. The lay-up is defined from two Oriented Selection Sets which point in opposite directions. In the second figure, the first Modeling Ply (oriented to the top) is defined to be extruded to a CAD Geometry. Only the nodes which meet the surface are extruded until the surface. The other nodes are extruded normally. The second Modeling Ply is extruded to another CAD Geometry in the last figure. For both cases, the orientation of the Snap-to Geometry operation must be top as the Oriented Selection Sets both point outward. Figure 2.127: Extrusion without Snap Operation
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Usage Reference Figure 2.128: Extrusion with Snap to Geometry at the Top (Shell Geometry also Displayed)
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Features Figure 2.129: Extrusion with Snap to Geometry at the Top and Bottom (Shell Geometry also Displayed)
Caution: The Snap to Geometry operation operation occurs after the Extrusion Guide operations. It is possible that the nodes moved during the Extrusion Guide operations are translated again, and do not match with the previous Extrusion Guide definition.
2.1.15.1.5. Cut-off Geometry The Cut-off Geometry isfeature uses to CAD geometries to shape the cutting cutGuide ting off ments. The operation analogous machining a composite partSolid afterModel curing.by See to eleSolid Modeling Modeling (p. (p. 285) 285) for more more information. The Cut-off Geometry feature is illustrated in the following figures: Figure 2.130: Extruded Solid Model
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Usage Reference Figure 2.131: Cut-off Geometries Shown Alongside Extruded Solid Model
Figure 2.132: Solid Model with Cut-off Features
2.1.15.1.5.1. Defining Cut-off Geometry A Cut-off Geometry is added by selecting Create CutOffGeometry in the context menu of the Cut-off Geometry folder. The cut-off operation can be defined with either a CAD surface geometry of CAD body geometry. The orientation flag specifies on which side of the surface or the body the elements are cut off. The up orientation specifies that elements in the reverse normal direction of the geometry are cut off. A visualization of the surface normal direction of a CAD body geometry can be displayed with the Show Normals button in the toolbar. Multiple Cut-Off Geometries can be used for one solid model. The cut offs are applied sequentially in the order of creation of the Cut-Off Geometries. The following properties must be defined in the Cut-Off Geometry Properties dialog:
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Features
Cut-off Geometry Properties
• CAD Geometry: CAD geometry for surface or body geometry. • Orientation: Determines the cutting orientation of a surface/body geometry.
Figure 2.133: Cut-off Geometry Normal Direction
• Relative Merge Tolerance: Set the merging tolerance for neighboring nodes relative to the ele-
ment size. If two nodes fall within this tolerance they are merged, thus avoiding very small element edges.
2.1.15.1.5.2. Decomposition of Degenerated Elements The cutting operation can reshape elements in such a way that they are no longer able to be handled by the solver. solver. The cut-off elements are therefore decomposed into homogenous prism
and tetrahedral elements following the cut off operation. An example of such a decomposition is shown in the figure below. below. The decomposition takes place automatically during Solid Model generation.
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Usage Reference Figure 2.134: A Degenerated Hexahedral Element (left) is Decomposed into Several Tetrahedral Elements (right)
2.1.15.1.6. Material Handling for Different Extrusion Methods The material handling for an analysis ply-wise extrusion follows the rules outlined in Fabric Solid Model Options Options (p. (p. 75) 75).. The following additional rules apply for other extrusion methods where plies of different materials are grouped together in one solid element layer.
Non-Analysis-Ply-Wise Extrusions Drop-Off Material Handling in Non-Analysis-Ply-Wise • If the material handling option of at least one ply is set to Global, the global Solid Model drop-off
material is used. • If all ply material handling options are set to Custom and refer to the same custom material, the
custom drop-off material is used. • In all other cases (for example, a multi-layered solid with material handling options Custom and
Global), the global Solid Model drop-off material is used.
Non-Analysis-Ply-Wise -Ply-Wise Extrusions Cut-Off Material Handling in Non-Analysis • If the material handling option of at least one ply is set to Global, the global Solid Model cut-off
material is used. • If all ply material handling options are set to Custom and refer to the same custom material, the
custom cut-off material is used. • In all other cases, the global Solid Model cut-off material is used.
2.1.15.1.7. Save & Reload Solid Models ACP Solid Models are saved as .H5 files. An update of ACP (Pre) component initiates a check of the current and previous laminate layup. While the laminate layup does not change no new solid model is generated.
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Features
2.1.15.1.8. Node-based Thicknesses By default, the solid model extrusion and the 3D layup representation used for the layup mapping within the Imported Solid Model are based on the ply thicknesses at the element center. On the basis of those, the average ply thickness per node is evaluated. If the Use Nodal Thickness is on ion (p. 58) 58)),), the solid model extrusion and 3D layup representation directly (see Layup Computat Computation consume the node-based thicknesses, which can improve the accuracy. For more information, see the Element- vs. Node-based Thicknesses Thicknesses (p. 61) 61) section.
2.1.15.2. Imported Solid Model The Imported Solid Model feature enables you to map the Composite Definitions of ACP (Pre) onto the mesh of an external (imported) solid model. This approach can be used if the standard solid model approach, that is based on an extrusion algorithm and post operations, fails or produces a mesh of poor quality. In that case, it is more robust to mesh the final composite solid structure first, independent of the layup data and, in a second step, to map the Composite Definitions. See (p. 285) 285) section section for solid model workflows as well as tips used when the Guide to Solid Modeling Modeling (p. working with a solid model. Currently, the mapping algorithm supports structured elements (linear and quadratic prism and hexa) which are automatically aligned according to the layup normal direction. Degenerated elements (tetra, pyramid, pyramid, etc.) can be filled with a homogeneous material. The imported solid mesh with th the e mapped layup data is exported for downstream analyses using the standard solid model workflow flo w (p. (p. 43) 43) in in Workbench. Structured elements are exported as layered solid or slosh, and homogeneous elements are oriented according according the material direction of the orthotropic material. The component sets (nodal and element) that are defined in the external solid mesh are exposed as Named Selections in the downstream analyses and can be used to maintain associativity. See the Analysis of a Mapped Composite Composite Solid Model Model (p. 328) 328) section section for an example analysis. Cut-off Geometries can be used to shape the Imported Solid Model in a desired way. way. They are specified in the respective subfolders in the Imported Solid Model tree view. The cut-off feature behaves in the same way for the Imported Solid Model as it does for the standard Solid Model. It eometry (p. 185) (p. 185).. The Analysis Plies sub-folder shows which Analysis Plies is in Cut-off Glay-up aredescribed incorporated in theGeometry mapping. This cut-off feature allows you to shape the imported solid mesh after the lay-up mapping. It gives you further control of geometry and mesh. You can add details and geometrical features to the Imported Solid Model. Therefore, the generation of a structured mesh will be easier and more robust for many cases.
Imported Solid Model Properties The settings for the t he imported solid model are adjusted under the Imported Solid Model context menu item Properties. The properties dialog covers what element sets and plies are taken into account for the mapping.
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Usage Reference
General Tab
Property Description
Format
This property specifies the format of the input file. Within a Workbench project, solid meshes are imported via Mechanical Mechanical Model (p. (p. 43) 43).. The import automatically automatically completes completes
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the Format, Unit System, and File Path properties and as a result, these properties are read-only. If you are running ACP in standalone, you can directly import ANSYS CDB files in ACP Pre. For this scenario, you need to specify the Unit System of the volume mesh.
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Features Property Description
Unit System
This property specifys the unit system of the external solid mesh.
File Path
This property specifys the location of the geometry file to be imported.
Use enabled,Plies. Imported Plies are mapped onto the solid mesh instead of the standard Imported If Modeling Plies Element Starting with a shell model and the lay-up definition, the 3D representation of the Sets laminate is mapped onto the imported solid mesh. Select one or several Element Set(s) to define the region of interest.
Note: The mid-offset option of Element Sets is not supported. The ply definition must be defined without this option to obtain an accurate mapping.
All Plies
By default, this property of the selected shell for mesh the solid mesh. Uncheck this boolean to maps select all anplies user-defined set of plies theonto mapping.
User This property enables you to select a set of Modeling Plies and/or Modeling Groups Defined to specify the plies to be mapped onto the solid mesh. Set Scale Plies
The thickness of the mapped layup and the geometrical thickness of layered elements el ements can differ due to various reasons (drop-offs, numerical differences etc.). If this boolean is checked, the thickness of the mapped laminate is scaled to match the element as shown below. Note that the scaling is done element-wise and not on a global scope. Side view of a layered solid with void space and scaled plies is illustrated below.
Global Void Material
Instead of scaling the laminate, fill the void space with a specific material. For that, un-check the option Scale Plies and define a void material. Since the in-plane material
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Usage Reference Property Description
orientation cannot be set, it is recommended you specify a material with isotropic characteristic.
Note: The elements with void material can be accessed through the analysis ply `void_` within the Analysis Plies folder of the Imported Solid Model. There are as many void layers in the analysis plies folder of the imported solid model as the maximum number of void layers in a layered element. For instance, there are two in the illustration below. Void space in a layered solid element is illustrated below.
Minimum Void Material Thickness
Void space as shown above can be caused for instance by drop-offs or differences between the shell and solid mesh, especially in curved areas. The void handling can be further refined by specifying an adequate `minimum void material thickness` value as shown in the figure below. If the thickness of the void space is below this value, the void space is not filled. In that case the regular layers are scaled to fill the void space. Scaled layers and filled void space is illustrated below.
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At a glance, it may seem wrong to scale the layers since the option Scale Plies has been disabled. But as the solver automatically scales the laminate if the total laminate thickness does not correspond with the element height, the scaling is done already by ACP. ACP. That allows you to visualize visuali ze and numerically quote the effect already in ACP ACP..
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Features Materials Tab
The handling of lost (filled) and cut-off elements can be specified in this window. If the layup representation does not intersect with all imported solid elements or the solid mesh contains degenerated elements, solid elements remain without layup data. These elements can either be removed or filled with a homogeneous material. The material handling of the elements that are shaped by a cut-off geometry can also be specified. More details about the cut-off feature and material handling can be found in Cut-off Geometry met ry (p. 185 185)).
Property
Description
Delete
This boolean is used to control whether the solid elements without mapped
Lost Eleme Element ntss
layup data are removed or kept. Note that unstructured elements such as tets or pyra pyrami mids ds ar are e iigno gnore red d in in the the mappi mapping ng algori algorithm thm and treat treated ed as lost lost e ele leme ment ntss (elements without data).
Global Filler Mate Ma teri rial al
If the property Delete Lost Elements is disabled a filler material has to be assigned to the solid elements without mapped layup data. Note that lost elements are ha hand ndle led d as non non-l -lay ayer ered ed (ho (homo moge gene neou ous) s) ele eleme ment nts. s. The The char charac acte teri rist stic ic of of the the fill filler er material can be of type isotropic or anisotropic. Note: The homogeneous elements with filler material can be accessed through the analysis ply `filler_` within the Analysis Plies folder of the Imported Solid Model.
Orientation
Select one or several rosettes to orient the lost elements. Note that the rosettes
are used to evaluate the fiber directions (local x-axis) and the normal directions (local z-axis) of the elements. This is slightly different if compared with the Oriented Selection Sets where the rosettes are used to apply the reference directions only.
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Usage Reference Property
Description
Selection Method
Supported options include Minimum Distance and Minimum Distance Superposed Direction (p. 120) 120) section. as described in Oriented Selection Set - Reference Reference Direction
Export Tab
164)) topic The export tab options are a limited set of the standard solid model. See the Export Export (p. 164 in the Solid Model Properties section of the Help. Mapping Statistics
The mapping statistics tab includes basic information of the result of the layup mapping such as total mass, volume, volume, resin resin volume content etc. The Ply-Wise Data table shows the volume per analysis ply and the difference to the layup definition based on the shell mesh. The ply volume in the solid mesh is greater if the difference is positive, else it is smaller.
Quality Check The application offers several options to verify the quality of the mapped layup.
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• You can examine the fiber directions and element normals using the Orientation Visualizations
options on the Toolbar.
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Features Make sure that the solid elements option is enabled.
196) to to display the ply-wise thicknesses on the solid elements. • You can use the Thickness Plot (p. 196) You can also select the Component option Relative Thickness Correction to plot the ply-wise scaling factors. (p. 196) 196) enables enables you to plot ply-wise volume contents and the deviation of • Layup Mapping Mapping Plot (p. the normal direction between the shell mesh and solid mesh. • You can get a coarse overview using the mapping statistics.
Miscellaneous The global model property 'minimum analysis ply thickness' also counts for the layup mapping. A layer is only added to an element if the mapped layer thickness is greater than this value. The layup representation that is evaluated for the t he mapping always follows the surface normal of the shell mesh. Since the imported solid model does not support the feature Extrusion Guide (p. (p. 176) 176),, that might cause special handling of free edges in curved areas. The layup representation (shell) is ignorant to the concept of drop-off elements (solid) and this can lead to 'voids' if you have steps in the layup as shown in the figure below. If the drops are low, this can be neglected, if they are high you might have to refine the tapering or adjust the void handling of the imported solid model.
The mapping algorithm itself is based on a 3D representation of the Composite Definitions and it consist 3 main parts: firstly, the structured solid elements are aligned according to the local offset direction of the 3D representation. Secondly, the ply-wise intersections between the solid elements and plies are evaluated. Of course it also detects if a ply is completely within a ply. The output of this operation is the element-wise ply thicknesses and orientations. And finally, this data is stored for downstream analyses. Note that the intersection is evaluated at the element center of the solid elements. This means that the ply thicknesses are constant within one element. In general, the mapping is mesh independent and the shell and solid mesh do not have to be coincident. However, However, too big of a difference in the meshes might cause inaccurate results. Therefore we recommend to work with meshes with similar element sizes, especially in curved regions.
The shape functions of the shell and solid elements can differ. For For instance a Composite Definition of a linear shell mesh can be mapped onto a quadratic solid mesh. Use Filler Option only: You can also just assign a material and orient the elements of an external mesh without mapping any layer. For that, uncheck `All Plies`, leave the `User Defined Set` empty and complete the Filler options as shown below Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
Usage Reference
Full cross-sections: The mapping might does not work as exp expected ected for plies that shrink into a very small tube as pictured below on the left hand side. In that case it is more robust to have several plies of moderate thickness instead of one thick ply as shown by the right picture.
Limitations The projection of the failure results to the reference surface s urface is not supported. Either do ply-wise analyses or use the Section Cut feature in Mechanical to investigate results inside the solid. Laminate failure criteria such as Wrinkling and Shear Crimping are not supported since the reconstruction of the stacking sequence of the laminate is not possible for mapped lay-up data.
2.1.16. Layup Plots Layup Plots enable you to verify and visualize element and ply-wise data, such as thickness and angle, of the Composite Definition in ACP (Pre). Available Layup Plots include:
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• Thickness Plot (p. 200)
Angle le Plot (p. (p. 201) • Ply Ang Draping g Mesh Plot (p. (p. 201) • Drapin • Look-Up Table Plot (p. 203)
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Features Definition inition Plot (p. (p. 205) • Field Def Mapping pping (p. (p. 205) • Layup Ma • Material P Plots lots (p. (p. 206)
User-Defined efined Plot (p. (p. 207) • User-D
2.1.16.1. Interface Options The right-click context menu for the Layup Plots object provides the following options: • Create Thickness: plot thicknesses per element or ply-wise • Create Layup Angle: plot ply-wise angles (fiber, shear angle etc.) • Create Draping Mesh and Flatwrap: plot draping mesh and flatwrap • Create Scalar Look-up Table: plot scalar look-up tables and interpolations • Create Field Definition: plot field definition data • Create Layup Mapping: plot layup mapping data • Create User-Defined: plot a custom set of data on the mesh • Paste: paste a layup plot from the clipboard.
The context menu for each individual Layup Plot option includes the following selections: • Properties : Display the Plot Properties dialog. • Update: Update the selected plot. • Copy: Copy the selected plot definition to the clipboard. • Paste: Paste a lay-up plot from the clipboard. • Delete: Delete the selected plot. • Hide: Hide the selected plot. • Show: Show the selected plot.
All plots can display the information for all or a selection of elements through the data scope. A thickness and angle plot for all element sets is predefined by default. The plot definition for layup plots follows the same definition as solution plots.
The properties for plots, such as Thickness Thick ness properties illustrated below, have two tabs: General and Legend. You use the General tab to configure the plot's basic settings. Once you you deselect the Use Default check box, the Legend tab enables you to specify minimum and maximum values as well as changing the legend title, range, and color display.
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Usage Reference General Tab
Legend Tab
The following general settings can be found in most of the plots:
Property descriptions include: • Use Defaults: Uncheck this option to manually
• Name: Name of the plot.
configure the color bar. Otherwise, the default s
• Entire Model: If enabled, the scope of the plot is the
are used.
entire shell- or all the solid elements of the model if Show on Solids is active. Otherwise you can define the scope through the Data Scope property. By default, Entire Model is enabled. • Data Scope: Determines what scope is used in the
plot. Element sets, OSS, Modeling Plies & Sampling Points can be selected in the data scope. scope. The data scope of a sampling point covers all plies that are intersected by the sampling point.
• Min Value: Defines the value of the first label. D
Auto to set a user-defined value.
• Max Value: Defines the value of the last label. D
Auto to specify a user-defined value. • Use as Threshold: If enabled, the min and max
become the second and second-to-last labels in color bar, respectively. • Grey Below Value: Grey is inserted in the color
• Ply-Wise: Activates a ply-wise plot display. Thickness
and angle only shownset if atoply is selected. Angle plotsplot areare automatically ply-wise. The plies can be selected from the modeling groups, sampling points or solid model analysis plies.
All values below the min label are then shown i Use as Threshold If is onand also,the then the min becomes the third label, second andlab fir evaluated accordingly.
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Features General Tab
Legend Tab
• Show on Solids: Shows plot data on solid elements
appended to the the • Violet Above Value: Violet is appended
and for solid elements only. • Component: Allows you to select different
components the results of a ply-wise ply-wise plot on • Ply Offsets: Visualize the the selected plies at their true or scaled offset from the reference surface (Angle Plot only).
bar. All values above the max label are then sho violet. If Use as Threshold is checked as well, th the max label becomes the third-last label, and second-last and last are evaluated accordingly. • Legend Title: Specifies the title that is shown a
the color bar. By default, the name of the plot is
• Number of Colors: Sets the number of colors fo
color bar. • Color Scheme: Chooses one of the preconfigur
schemes. • Fixed Color Bar Range: Activates the Fixed Col
Range option to prevent the color bar from cha
when you switch from one ply to another. If ena the overall min and maximum values of the sco set as color bar min and max labels. If ply-wise i enabled as well, the global min and max are us
Note: Only a subset of the plots support Imported Plies. Currently, these are Thickness Plot, Angle Plot and Lay-up Mapping Plot. To plot plot data on Imported Plies, the Entire Model and Ply-Wise options must be enabled.
Thickness plot with "Use as Threshold" on for both the Min and Max Value.
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Usage Reference
Thickness plot with "Grey Below Value" and "Violet Above Value" on.
2.1.16.2.Thickness Plots The Thickness Thicknes s Plot shows the thickness distribution for an entire layup or single plies. The Angle Plot is purely a ply-wise plot and shows the orientation angle a ngle of a selected ply. The Look-Up Table Table Plot enables you to explore the interpolation result of scalar columns. Scalar columns can be used to define thickness, angle, or degradation fields. Figure Figur e 2.135: Thickness Thickness Plot
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Components
The component of the plot include: • Thickness: show the element thickness or ply-wise thickness
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Features • Relative Thickness Correction: show the thickness scaling due to draping or layup mapping
2.1.16.3. Angle Plot The Angle Plot is purely a ply-wise plot and shows the orientation angle of a selected ply. FFor or example, an Angle Plot showing the shear angle of a draped ply is illustrated below. Figure 2.136: Angle Plot
Components
The component of the plot include: between the Reference Reference Direction Direction and the Fiber Direction. Direction. This is the • Design Angle: The angle between angle between the element lay-up reference defined through the Oriented Selection Set and the user-set Ply Angle. Direction and the Draped Fiber Direction. • Draped Fiber Angle: The angle between the Reference Direction This is the angle between the lay-up reference defined defi ned through the Oriented Selection Set and the effective fiber direction due to draping. • Draped Shear Angle: The local ply shear value due to draping. • Draped Transverse Fiber Angle: The angle between the Reference Direction and the Draped
Transverse Direction. This is the angle between the lay-up reference defined de fined through the Oriented Selection Set and the effective transverse fiber direction due to draping.
2.1.16.4. Draping Mesh Plot The Draping Mesh Plot enables you to control if the Draping Mesh or the Flatwrap of a draping
simulation are shown in the active scene. You need to select a Production or Analysis Ply in order to show the draping mesh and/or the flatwrap.
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Usage Reference Figure 2.137: Draping Mesh Plot Properties
For this plot type, specific options of the General tab include: • Show Draping Mesh: Shows the Draping Mesh Plot. The worst distortion is located in red areas
of the draping mesh. If the model property Use Draping Draping Offset Correction Correction (p. 58) 58) is is active, the draping mesh is displayed at the bottom offset (relative to the reference surface orientation) of the selected ply. • Show Flatwrap: Shows the Flatwrap surface that is a result of the draping in ACP.
The Draping Plot shows the average shear (distortion) angle of each element. The angles are given in degrees and they are the average absolute values of the corner angles differing from 90 degrees. Therefore no distortion is equal to zero degrees. More information on draping can be found in the (p. 278) 278).. section Composite Modeling Techniques under Draping Draping (p. The following illustrations show examples of Draping Mesh, Draping Plot for a Hemisphere, and Flatwrap Surface of the Ply. Figure 2.138: Draping Mesh
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Features Figure 2.139: Draping Plot for a Hemisphere
Figure 2.140: Flatwrap Surface of the Ply
2.1.16.5. Look-Up Table Plot The Look-Up Table Plot enables you to explore the interpolation result of scalar columns. Scalar columns can be used to define thickness, angle, or degradation fields for instance.
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Usage Reference Figure 2.141: Look-Up Table Plot General Properties Tab
For this plot type, specific options of the General tab include: • Look-up Table Column: Select the Look-up Table column data that is to be plotted. • Supporting Points: – Show Points: Visualize the location of the supporting points of the plotted look-up table data. – Show Labels: Show labels indicating the row index in the respective look-up table. – Scale Factor: Scale the size of the supporting points. • Show Labels: Show labels indicating the row index in the respective look-up table.
supporting points can be scaled in size. • Scale Factor: The supporting
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Features Figure 2.142: Look-Up Table Plot of a 1-D Scalar Quantity with Supporting Points Shown as Circles
2.1.16.6. Field Definition Plot The Field Definition plot enables you to visualize and investigate the effect of a Field Definition tio n (p. 151 151)). This plot is only available available ply-wise ply-wise.. For this plot type, the specific option of the General tab is the Field Variable Name. You select the field variable to be plotted from this drop-down menu.
2.1.16.7. Layup Mapping Plot The purpose of the layup mapping plot is to show the result of the layup mapping (mapped Composite Definitions onto a solid mesh). It also allows to check the quality of the mapping result. Therefore the scope only accepts Imported Solid Models and the property `Show on Solids` is always checked. For this plot type, the specific option of the General tab is the Data Scope option. Using this entry field, you specify one or more Imported Solid Models.
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Usage Reference Figure 2.143: Layup Mapping General Properties Tab
Components
The component options for this plot include: • Volume Content: show the ply-wise volume contents • Deviation in Normal Direction: show the difference between the shell normal and layered solid
normal direction. If ply-wise is disabled, the average normal deviation of the element is shown. Figure 2.144: Deviation of the Normal Direction between Shell Elements and Layered Solid Elements
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2.1.16.8. Material Plots The Material Plot (p. (p. 219) 219) enables enables you to visualize ply-wise variable material p propertie ropertiess (p. 300) 300).. You must select an Analysis Ply to display the distribution of the material properties.
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Features For additional information, see the Material Plot topic in the Solution P Plots lots (p. (p. 214) 214) section section of the User Guide.
2.1.16.9. User-Defined Plot The User-Defined Plot allows you a specify arbitrary scalar quantities for plotting. For ad additional ditional information, see the User-Defined User-Defined Plot (p. (p. 221) 221) topic topic in the Solution Plots section of the User Guide.
2.1.17. Definitions Failure criteria are used to evaluate the strength of a composite structure. Several failure criteria can be defined, combined and configured in the Definitions object. Failure criteria definitions can be used for failure plots and sampling points. The critical failure mode for an element shown in failure plots and sampling points is the one with the lowest reserve factor. ssing (p. 233) 233).. A list of implemented failure criteria and the associated failure types is shown in Postproce Postprocessing More detailed theory information about failure criteria is provided in Failure Failure Analysis Analysis (p. 357) 357).. New failure criteria definitions can be added by selecting the Create Failure Criteria option. In the Failure Criteria context menu of the object. Failure criteria definition is configured in the Definition dialog thatDefinitions distinguishes between failure criteria for reinforced (UD and woven) materials,
sandwich structure, and isotropic materials. Figure 2.145: Failure Criteria Definition
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Usage Reference Each failure criteria definition can be a selection of any failure criteria. Different failure modes are activated via the check-boxes and can be set up in the failure criteria configuration. Individual failure modes for each failure criterion can be activated and be associated with a weighting factor. The weighting factors can be used to define differ different ent factors of safety for certain failure criteria or specific failure modes. Some criteria also have different levels of complexity. For example, the Puck criterion can be used in its simplified, 2-D, or 3-D option. Figure 2.146: Puck Failure Criteria Configuration
2.1.18. Solutions The Solutions object is only available in postprocessing mode. The individual items under Solutions
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objects are used to import and read the solution results into ACP. All postprocessing plots (for example, deformation, failure, stress, strain, temperature plots) are linked to individual solutions. Several solutions can be combined into one envelope solution to visualize an overlay of failure results. One solution holds all the results for each analysis system that is linked to ACP-Post in the Workbench schematic. The solution has to be up-to-date and the results need to match the mesh before any a ny postprocessing can be done.
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Features Figure 2.147: Solutions Object in the Tree View
Details on how to configure the results import, create an envelope solution, and plot results are explained in the following sections: 2.1.18.1. Solution Object 2.1.18.2. Envelope Solution 2.1.18.3. Solution Plots
2.1.18.1. Solution Object The solution object controls how results are imported into ACP-Post. Each solution links to a .RST results file. The import settings can be configured in the Solution Properties dialog. Solution Plots can be created in connection with a solution object. The solution set (for instance, load step) is specified for each plot object individually. Solution Context Menu 2.1.18.1.1. Solution 2.1.18.1.2. Solution Properties In Workbench mode, a solution is created in ACP-Post for every solution component that is linked to the ACP-Post cell in the project schematic. A solution can also be added by selecting Import Results in the context menu of the Solutions object in the tree view. Doing so creates an individual solution and displays the Solution Properties dialog.
2.1.18.1.1. Solution Context Menu The context menu of every solution has the following options: • Properties: Display the Solution Properties dialog. • Update: Update the specific solution and reload result if changed. • Reload: Reload the results file. • Delete: Delete the selected solution.
• Delete Postprocessing Results: Delete all deformations, stresses and strains, computed. • Export Results: Exports result (deformation, stress, strain, failure results, progressive damage) as a .CSV file for selected element sets, oriented selection sets, and modeling plies for both shell and
solid elements.
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Usage Reference Plots (p. (p. 214) • Create Deformation: Create a deformation plot for the selected solution. (see Solution Plots for more information on all plots) • Create Strain: Create a strain plot. • Create Stress: Create a stress plot. • Create Failure: Create a failure plot based on a failure definition. • Create Temperature: Create a temperature plot if data is available. • Create Progressive Damage: Create a progressive damage plot if data is available. • Paste: Paste a plot from the clipboard.
2.1.18.1.2. Solution Properties Import settings and load step selection can be configured in the Data tab of the Solution Properties dialog. The following properties can be set in the Data tab of the Solution Properties dialog:
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Features Figure 2.148: Solution Properties Window Showing Several Solution Sets in the Data tab
Note that in the previous figure, the solution sets are greyed out; the solution set selection happens at the plot level. • Name: The name of the solution, used in postprocessing.
be imported. • Format: The format of the solution file to be – Import an .RST result file from the ANSYS solver. All solution information is contained in this
file. – Import deformation and rotational result file. These files are generated by Mechanical APDL with
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Usage Reference importing a .RST file, the path to that file. When importing individual deformation • File Path: When importing and rotational result files, the path to the deformation results. • Rotation Path: When importing individual deformation and rotational result files, the path to the
rotational results (inactive otherwise). • Automatic Reload: When active, ACP checks for changes to result files and reads new results
automatically. • Read Strains and Stresses: When importing a .RST file, import stresses and strains calculated by
the solver by default. default. When this option is inactive and the Use ACP to Compute Strains and Stresses option is active, ACP calculates stresses and strains from deformation and rotation information present in the file. When several load steps or substeps are present, you are prompted prompted to select which set is to be imported. Having ACP calculate stresses and strains can increase the computational load and time for postprocessing and is only recommended for linear analyses. Interlaminar stresses and strains cannot be calculated for linear triangular elements in ACP. • Temperature Data Available: When active, this option indicates that the results file to be imported
contains a temperature field. When imported, temperature temperature data can be visualized, and temperature dependent material data can be used in stress and strain analysis. • Use Solid Results if Available: If this option is active and results for solid elements are present in the .RST file, the results are mapped onto the reference shell elements. Mapped results are visible
when Solid Models are hidden. Postprocessing can be done on both layered shell and solid elements. • Recompute ISS of Solids: When active, ACP recalculates interlaminar shear stresses for solid models.
The recomputation algorithm takes the following two steps: 1. Summatio Summation n of all shear shear forces forces per per solid solid stack. stack. 2. Calculation Calculation of interlami interlaminar nar shear stress stress by by laminate-base laminate-based d approach approach (see Transverse (see Transverse Shear Stressess (p. Stresse (p. 354) 354)).).
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Features Figure 2.149: Comparison of Imported and Recomputed Interlaminar Stresses
Non-zero boundary conditions are not considered in this recomputation process. The recomputed stresses take the place of the imported ones. The results file itself is not altered and the recomputation can be reversed by un-checking the option and updating the solution.
2.1.18.2. Envelope Solution The Envelope Solution feature can be used to combine and compare multiple load cases in failure plots. In this way, the critical load case for a structure can be determined. An Envelope Solution can be added by selecting Create Envelope Solution from the context menu of the Solutions object. Existing solutions can be added to the Envelope Solution in the Envelope Solution Properties dialog. Plot (p. 217) 217) for for more details on visualizing failure plots using Envelope Solutions. See Failure Failure Mode Plot
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Usage Reference Figure 2.150: Envelope Solution Properties
In the Envelope Solution Properties dialog, you can set the Name of the Envelope Solution and add any results set for the available solutions for the failure analysis comparison.
2.1.18.3. Solution Plots This section examines available solution plots and their functionality. Refer to the Guide to Composite Visualizations for the practical application of solution plots (Post ( Postproc processing essing Visualizations Visualizations (p. 292) 292)).). All analysis results can be visualized as solution plots in ACP-Post. Solution plots are attached to individual solutions. 2.1.18.3.1. Common Plot Settings 2.1.18.3.2.Visualization Mismatch 2.1.18.3.3. Deformation Plot 2.1.18.3.4. Strain Plot 2.1.18.3.5. Stress Plot 2.1.18.3.6. Failure Mode Plot
2.1.18.3.7.Temperature 2.1.18.3.7.Temperatu re Plot 2.1.18.3.8. Progressive Damage Plot 2.1.18.3.9. Material Plot 2.1.18.3.10. User-Defined Plot
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Features
2.1.18.3.1. Common Plot Settings Plot settings are largely similar for all plot types. Each plot can be configured through the Plot Properties dialog has two tabs, General and Legend. The The General Properties dialog. The Plot Properties tab is where the results component and geometry scope are defined. It possible to configure a plot to display only a particular section of a component. component. The Legend tab controls the format of the plot legend. Specific to solution plots is the selection of the solution set of interest. The General T Tab ab has the following properties: • Name: Name of the plot. • Data Scope: Determines what scope is used in the plot. Element sets, OSS, Modeling Plies & Sampling
Points can be selected in the data scope. scope. The data scope of a sampling point ccovers overs all plies that are intersected by the sampling point. display. Thickness and angle plot are only shown if a ply is selected. • Ply-wise: Activates a ply-wise plot display. Angle plots are automatically set to ply-wise. The plies can be selected from the modeling group groups, s, sampling points or solid model analysis plies. • Show on Solids: Shows plot data on solid elements and for solid elements only. • Component: offers the selection of components (for example, usum, s12, and IRF) available for the
chosen plot. • Show on Section Cuts: Shows the ply angle on section cuts in the same color scale (angle plot
only). • Ply Offsets: Visualize the results of a ply-wise plot on the selected plies at their true or scaled offset
from the reference surface (angle plot only). • Spot: Displays the position through the ply thickness for the result evaluation. Either top, mid or
bottom. • Solution Set
: Specifies the time for which the results are generated. The Legend tab allows you to control titles, labels, and legend ranges: • The legend is formatted automatically by default but can be customized to suit. • Limits can be set be set to be min/max limits. • Limits can be set as thresholds on the penultimate labels on the contour plot scale. • Values above limits can be colored in non-rainbow scale colors (grey and pink).
2.1.18.3.2.. Visualization Mismatch 2.1.18.3.2
Failure plots show the critical values for all defined failure criteria (modes) and integration points. The strain and stress plot illustrates the values at the element center (interpolation). Therefore the absolute strain and stress peaks are not displayed in the plots and the elements have a constant value. This can cause graphical inconsistency between the strain/stress and failure plot.
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Usage Reference
2.1.18.3.3. Deformation Plot Displays nodal deformation results and can plotted for the following: Translation n in X direction. direction. • ux: Translatio • uy: Translation Translation in Y directio direction. n.
Translation n in Z direction. direction. • uz: Translatio • rotx: Rotation around the X axis. • roty: Rotation around the Y axis. • rotz: Rotation around the Z axis.
2.1.18.3.4. Strain Plot Shows strain values at the bottom, mid, or top position of the ply and at the element center, or at the bottom, or top of the laminate if ply-wise is disabled. In the ANSYS Mechanical application, this corresponds to the Elemental Mean display option. Strains can be displayed ply-wise or for an entire laminate. Strain results can be plotted for the following component directions: • 1: Material 1 direction. • 2: Material 2 direction. • 3: Out-of-plane normal direction. • 12: In-plane shear. • 13: Out-of-plane shear terms. • 23: Out-of-plane shear terms. • I: 1st principal direction. • II: 2nd principal direction. • III: 3rd principal direction.
2.1.18.3.5. Stress Plot Displays stress values at the bottom, mid, or top position of the ply and at the element center, or at the bottom, or top of the laminate if ply-wise is disabled. In the ANSYS Mechanical application, this corresponds to the Elemental Mean display option. here is an option to compute interlaminar normal stresses stresses (p. (p. 351) 351) for for shell elements. Stress results can be plotted for the following
stress component directions: • 1: Material 1 direction. • 2: Material 2 direction. • 3: Out-of-plane normal direction.
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Features • 12: In-plane shear. • 13: Out-of-plane shear terms. • 23: Out-of-plane shear terms. • I: 1st principal direction. • II: 2nd principal direction. • III: 3rd principal direction.
2.1.18.3.6. Failure Mode Plot Failure plots can be used to display the safety factor for first ply failure of a pre-defined failure criteria definition. Failure results can be displayed in the following ways: • Ply-wise Failure: Results show the critical failure at each element for the selected Analysis Ply,
calculated over all of its integration points and defined failure criteria. • Element-wise Failure: Results show the critical failure over all plies, integration points, and
defined failure criteria at each element. This guarantees that the critical results results are shown. The failure evaluation for each defined failure criterion uses stress or strain results at each integration point. In contrast, stress and strain plots display the elemental mean results. There are three kinds of safety factors that can be displayed in a failure contour plot. Text labels can be activated to show the critical failure mode and in what layer it occurs. In the case of an envelope solution, the critical load case can also be shown. The toolbar button switches the display of activated element text labels on and off. For information on failure definitions see Postproc processing essing (p. 233) 233).. Post Available safety factor components: • Inverse Reserve Factors (IRF) • Margins of Safety (MoS/MS) • Reserve Factors (RF)
The failure plot properties have the following additional options: • Failure Criteria Definition: Drop-down menu for selecting the desired failure criteria definition. • Show Critical Failure Mode: Show the critical failure mode as an element text label. • Show Critical Layer: Show the layer index of the critical failure mode as an element text label.
• Show Critical Load Case: Show the solution index of the critical failure mode as an element text
label (Envelope Solution only).
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Usage Reference • Threshold for Text Visualization: Set the threshold so that element labels are only shown for as
of a certain IRF, RF or MoS level.
Note: The critical layer index i ndex counts from the reference surface s urface upwards and starts at layer 1. The sandwich failure criteria top and bottom sheet wrinkling are evaluated for a sandwich structure as a whole and cannot to be linked to specific layer. layer. The layer index shows 0 in this case. The critical load case index starts at 0. In the Envelope Solution, the solution in position n is plotted with number n - 1. Figure 2.151: Scene with Failure Mode Plot Activated
2.1.18.3.7 2.1.18.3.7.. Temperatur emperature e Plot The temperature plot can display a temperature field results on solid elements if temperature data is available in the results file.
2.1.18.3.8. Progressive Damage Plot This plot object canno display progressive damage Thedamage overall damage statusThe candamage be displayed indicating whether damage, some damage, orresults. complete has occurred. variables give an indication of how much the stiffness has reduced for fiber and matrix in tension or compression. The damage variable scale goes from 0 (no damage, 0% stiffness reduction) to the maximum stiffness reduction specified. The highest reduction possible is 1 (complete damage, 100% stiffness reduction).
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Features Note that a failure analysis for this analysis type should be done with care and may not make sense for damaged elements. See Damage Results in Results in the Mechanical User's Guide for more information on each result component. The following components can be plotted: • Damage Status: – 0 = undamaged – 1 = damaged – 2 = completely damaged • Fiber Tensile Damage Variable (FT) • Fiber Compressive Damage Variable (FC) • Matrix Tensile Damage Variable (MT) • Matrix Compressive Damage Variable (MC) • Shear Damage Variable (S)
2.1.18.3.9. Material Plot The Material Plot enables you to visualize ply-wise variable material properties properties (p. (p. 300) 300)..
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Usage Reference Figure 2.152: Material Plot General Properties Tab
By default, all available field variables are used to evaluate the selected material property. However, you can also deactivate some of these variables to inspect the dependency of the selected material property more easily with respect to some specific factors. During the evaluation, inactive variables are kept fixed at their default value. Available field variables include the Shear Angle (defined by draping draping simulation simulation (p. 347) 347) in in ACPPre), Temperature (if temperature data is available in the results fil file), e), and your your own variables 151) in in ACP-Pre. defined using Field Definition Definitionss (p. 151)
For this plot type, the plot-specific options of the General tab include: • Material Property: This property displays a list of supported material properties: Engineering
Constants, Density, Strain, and Stress Limits.
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Features • Component: The options listed for this attribute include dependent variables associated with
the selected material property. Examples include Orthotropic Young's Modulus, Poisson's Ratio, and Shear Modulus. • Use All Available Field Variables: By default, the application uses all available field variables
to evaluate the selected material property. • Internal Variables: If you disable the Use All Available Field Variables option, you can select-
ively enable the Shear Angle and Temperature fields. • User-Defined Variables: If you disable the Use All Available Field Variables option, you can
selectively enable specific field variables defined through a Field Definition.
2.1.18.3.10. User-Defined Plot This plot object can be used to plot a scalar data set provided as a Python list or numpy.ndarray , as well as associated custom text labels provided as a list of strings. Once the plot has been loaded, you can query active element indices, labels, and respective element centroid coordinates through the plot user interface properties based on the data scope. User-defined plots can be created as a lay-up plot or a solution plot. The plot is defined using the Python interface. The code can be placed in the script field of the plot object. This ensures the plot is refreshed following model updates. Alternatively, the plot definition can be executed through the Python shell. For more information about the Python interface, see The ACP Python Pyth on Scripting User Interface (p. 395) 395)..
Caution: The model.update() command must not be executed in the user-defined script field as it leads to an infinite update loop. Because of this limitation, changes to objects preceding the user-defined script object cannot be handled within the script field, as a model.update() would be required.
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Usage Reference Figure 2.153: Script Field in the User-Defined Plot Properties
Python User Interface Properties user_element_indices
Retrieve a numpy.ndarray with the active element indices in the relevant order. user_element_labels Retrieve a numpy.ndarray with the active element labels in the relevant order. user_element_centroids Retrieve a numpy.ndarray with the active element centroid coordinates in the relevant order. user_data
Retrieve or provide the user data, which must obey the order of the user_element_indices or user_element_labels, respectively.
user_script_enabled
Boolean that controls if a custom script is run on update. user_script
The body of the script to be executed on update if user_script_enabled = True.
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Features user_text
Access to the user-defined text of the plot. Empty strings can be inserted when no labels are to be shown for certain elements.
Example Scripts All examples basedof ontwo thescripts. class40.wbpz example example provided with the installation. Each exampleare consists The firstWorkbench script is used to set provided up the user-defined plot whereas the second script needs to be inserted in the script window of the user-defined plot. The plot’s data scope cannot be set from within the script window of the plot as this requires a model update and this is not permitted. • This project contains a material called E_Glass_shear_dependent. • This material is contained within cell B5 (ACP).
The sample code below shows how to create an advanced material plot. The Material Plot can be used to plot variable material data. In this case, however, we would like plot variable material data with a custom label. The User-defined Plot allows us to do so. The example plots the effective Young's modulus as a function of draping simulation with shear angle labels. Example 2.1: Plot Material Property Distribution
The following commands must be deployed from within the UI of cell B5: # get active model model = db.active_model # get angle plot ap = model.layup_plots['Angle.1'] # set the angle plot to display the draped shear angle ap.component = 'shear' # set the plot data scope to modeling ply 'outer_skin_1' which uses a draping simulation scope = model.modeling_groups['hull'].plies['outer_skin_1'] model.modeling_groups['hull'].plies['outer_skin_1'] ap.data_scope = scope # update the model model.update() # create a user defined lay-up plot up = model.layup_plots.create_user_defined_plot(name = 'myplot') # apply the same scope as before up.data_scope = scope # enable the script field up.user_script_enabled = True up.show_user_text = True
The following code must be placed within the Script field of UserDefinedPlot object myplot: # get active model, angle plot and data scope model = db.active_model
ap = model.layup_plots['Angle.1'] scope = model.modeling_groups['hull'].plies['outer_skin_1'] model.modeling_groups['hull'].plies['outer_skin_1'] plot.data_scope = [scope] # get a list of the shear angles of the selected modeling ply shear_angles = ap.get_data(visible = ap.data_scope, selected = scope) # get the shear dependent material mat = model.material_data.materials['E-Glas_shear-dependant'] moduli = [] # loop thru list of shear angles and determine the corresponding
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Usage Reference # elastic modulus in 1 direction for i in shear_angles[0]: moduli.append(round(mat['engineering_constants'].query('E1', moduli.append(round(mat['eng ineering_constants'].query('E1', {'Shear Angle' : i}),3)) # set the plot to display the list of moduli plot.user_data = moduli # set the user text to display the corresponding shear value as string, rounded to 2 digits import functools plot.user_text = list(map(str, map(functools.partial(round, ndigits = 2), shear_angles[-1]))) # add formatting to the plot plot.color_table.use_defaults = False plot.color_table.description = 'E_1 [MPa] with shear angle labels'
This script should result in the following plot:
The sample code below shows how you can ca n plot the margin against the combined interlaminar
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shear stresses
:
Example 2.2: Plot Combined Shear Stress Values
The following commands must be deployed from within the UI of cell E5: # get active model model = db.active_model
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Features # set data scope to element set scope = model.element_sets['HULL_BELWL'] model.element_sets['HULL_BELWL'] # create a stress plot for out-of-plane shear stress s13 sp = model.solutions['Solution 1'].plots.create_stress_plot() 1'].plots.create_stress_plot() sp.data_scope = scope sp.component = 's13' # create a second stress plot for out-of-plane shear stress s23 sp1 = model.solutions['Solution 1'].plots.create_stress_plo 1'].plots.create_stress_plot() t() sp1.data_scope = scope sp1.component = 's23' # update the model, to make stress data available model.update() # create user defined solution plot up = model.solutions['Solution 1'].plots.create_user_defined_plot(name = 'myplot.1') # apply the same data scope as before up.data_scope = scope up.user_script_enabled = True
The following code must be placed within the script field of the UserDefinedPlot object myplot: # import numpy extentsion for mathematical operations import numpy # get active model, set data scope as before and select core layer model = db.active_model scope = model.element_sets['HULL_BELWL'] model.element_sets['HULL_BELWL'] ply = model.modeling_groups['hull'].plies['core_bwl'].production_plies model.modeling_groups['hull'].plies['core_bwl'].production_plies['ProductionPly.9'].analysis_pli ['ProductionPly.9'].analysis_plies['P es['P # retrieve references to stress plots created before sp = model.solutions['Solution 1'].plots['Stress.1'] sp1 = model.solutions['Solution 1'].plots['Stress.2'] # get list of s13 and s23 stresses s13 = sp.get_data(visible = sp.data_scope, selected = ply)[0] s23 = sp1.get_data(visible = sp1.data_scope, selected = ply)[0] # take the sqrt of the sum of squares combined = numpy.sqrt(numpy.power(s13,2) + numpy.power(s23,2)) # define a stress limit slimit = 1.1 # calculate the inverse reserve factors (irfs) irf = combined / slimit # set the plot to display the list of irfs plot.user_data = irf # add formatting to the plot plot.color_table.use_defaults = False plot.color_table.description = 'irf_plot'
This script should result in the following plot:
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Usage Reference
User-defined plots can also show results on solid elements. The sample code below shows how to execute mesh selections and mesh queries for solids. Example 2.3: Mesh Selections and Queries on a Solid Model
The following commands must be deployed from within the UI of cell B5: # get model # set scope
active model = db.active_model data scope to element set 'BULKHEAD_ALL' = model.element_sets['BULKHEAD_ALL'] model.element_sets['BULKHEAD_ALL']
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# create a user defined lay up plot and apply the data scope set before up = model.layup_plots.create_user_defined_plot(name = 'myplot.2') up.data_scope = scope # enable the script field up.user_script_enabled = True # activate the solid model display option up.show_on_solids = True
The following code must be placed within the script field of the UserDefinedPlot object myplot.2:
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Features
# get active model model = db.active_model # select all elements attached to 'SolidModel.1' model.select_elements('sel0', attached_to=model.solid_model attached_to=model.solid_models['SolidModel.1']) s['SolidModel.1']) # retrieve the element type numbers for the selected elements using a mesh query data = model.mesh_query(selection='sel0', model.mesh_query(selection='sel0', name='etypes', position='centroid') # set the plot to display the element type number on the solid elements plot.user_data = data.astype(float)
This script should result in the following plot. The prism and brick elements are highlighted separately:
2.1.19. Scenes Scenes areorwindows visualization settings of the composite model. NewThe scenes can be added existingthat onescontain can bethe modified by hiding or showing visualization features. visualization of the following features is saved in a scene: • Element Sets • Edge Sets • CAD Geometries • Rosettes
• Section Cuts • Solid Models
In a new scene, all Element Sets, Section Cuts and Solid Models are shown. In the Scene Properties dialog you can set the Name and Title which are displayed in the top right corner of the scene.
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Usage Reference Figure 2.154: Scene Properties
2.1.20.Views Views can be used to save a certain view. The selection of a view automatically updates the scene and transfers the properties of the View to the active scene. New Views can be created with the n (p. 22) 22))) or via the object tree. Different parameters button in the toolbar (see Scene Manipulatio Manipulation can also defined manually.
2.1.21. Ply Book The Ply Book feature allows you to create a report for production with relevant information such as material, orientation, angle and extension.
2.1.21.1. Ply Book Properties
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The Ply book is divided in three parts: Title Page, Chapter Title (for each chapter), and the Ply Definition. Any modifications can be saved and opened later to be used as a template. In the second part of the window, a preview of the resulting .HTML file is available.
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Features
2.1.21.2. Create Chapter A Chapter is defined by a Modeling Group and certain Views Views (p. 228 228)) which make up the figures in the chapter. You can also define the name of the chapter. ch apter.
2.1.21.3. Automatic Setup Automatic Setup quickly defines the whole ply book. It defines a Chapter for each Modeling Group in the selected view. Names and views can be changed later.
2.1.21.4. Generate the Ply Book The configured Ply Book can be exported as .HTML, .PDF, Open Document, or plain text. Figure 2.155: One Page of a Ply Book
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Usage Reference
2.1.22. Parameters The Parameter feature connects Inputs and Outputs to the Parameter Interface Inter face in the Workbench project. Figure 2.156: Connection of ACP and Workbench Parameter Interface
A Parameter is created by selecting Create Parameter in the context menu of the Parameters object in the tree view. The Parameter connection connection is then defined in the Parameter Properties dialog: Figure 2.157: Parameter Properties
• Category:
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– Input: Input parameter taken from the Workbench Parameter interface – Output: Output parameter given to the Workbench Parameter interface – Expression Output (p (p.. 23 231) 1):: Output parameter that can contain a regular ACP script
parameter acts. • Object: The object on which the parameter
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Features • Property: The property of the object to be parameterized.
possible ble option. Units are • Type: The parameter format. Determined automatically if there is only one possi not transferred from ACP to Workbench. Parameters appear as dimensionless numbers in the Workbench interface. – Bool: Boolean (true or false). – Float: Real number. – Int: Integer. – None: Default selection if multiple options are available. – String: Text string from a list of strings. The values in the string list can be called up via an index
number in the Workbench Workbench interface. interface. The first entry in the string list has the index value 1. The rest follows sequentially. parameter. This option can be modified depending on if a parameter • Value: The current value of the parameter. is an Input or an Output.
Caution: The ACP systems s ystems do not automatic convert Parameter units un its in the Parameter Manager. Man ager. Always verify that the units of any ACP-related Parameter are consistent with the unit system selected in the ACP system. For Parameters in ACP (Post), linked to an object in ACP (Pre), the Parameter will become invalid if you rename the ACP (Pre) object. To correct, correct, redefine redefine the source object for the Parameter.
2.1.22.1. Settings for an Expression Output The formulation of an expression output requires a basic understanding of The of The ACP Python Scripting Scripti ng User Interface Interface (p. 395) 395).. The Parameter Properties dialog displays a Source field that accepts Python code. Various information stored in the ACP database can be accessed. It is possible to enter a script and perform most of the operations available within ACP's Shell View. The script's result can be returned by assigning a ssigning a value to the global return_value variable. Example 2.4: Simple Expression Output
An example of a simple expression output is shown here. In it, the maximum inverse reserve factor
An example of a simple expression output is shown here. In it, the maximum inverse reserve factor is retrieved from the active contour plot.
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Usage Reference
Example 2.5: Complex Expression Output of Maximum Thickness in the Kiteboard Model # Get active model model = db.active_model # Create new selection of all elements attached to a specific ply modeling_ply = model.modeling_groups['Core'].plies['mp_4'] model.modeling_groups['Core'].plies['mp_4'] model.select_elements(selection='sel0',op='new',attached_to=[modeling_ply]) # Get total thickness of the first entity of selection sel0 thicknesses = list(model.mesh_query(name='thickness',position='centroid',sele list(model.mesh_query(name='thickness',position='centroid',selection='sel0', ction='sel0', # Get maximum thickness
entities=[model
max_thickness = max(thicknesses) # Pass the found maximum thickness as the script's result. return_value = max_thickness
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Postprocessing
2.1.23. Material Databank It is possible to build a Material Databank which can be used in different projects. projects. The databank can also be saved on a intranet drive for sharing to other ACP users. The structure of the Material Databank is exactly the same as in the model. For more information, see Materi Material al Data (p. (p. 64) 64).. The Databank Databank is stored as .acpMcd and it can be managed through the context menu: Figure 2.158: Material Databank
The units of the Databank and the model can be different. Use Copy and Paste to transfer a material from one to the other; values of the materials are converted automatically to the correct unit system. A default Material Databank is installed with ACP: ANSYS_INSTALL_DIR\v202\ACP\databases.
2.2. Postprocessing More information regarding the background of the ACP postprocessing can be found in Failure Analysis (p. (p. 357 357)) and Interlaminar Interlaminar Stresses Stresses (p. 351) 351).. 2.2.1. Failure Criteria 2.2.2. Failure Mode Measures 2.2.3. Principal Principal Stresses and Strains 2.2.4. Linearization Linearization of Inverse Reserve Factors 2.2.5. Postprocessing of a Composite Solid Model 2.2.6. Postprocessing of Drop-off and Cut-off Elements 2.2.7. Evaluating Custom Failure Criteria 2.2.8. Limitations & Recommendations
2.2.1. Failure Criteria
All available failure criteria are listed together with their failure mode abbreviations as used in failure mode plots. Terms: • e = strain, s = stress
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Usage Reference • 1 = material 1 direction, 2 = material 2 direction, 3 = out-of-plane normal direction, 12 = in-plane shear,
13 and 23 = out-of-plane shear terms • I = principal I direction, II = principal II direction, III = principal III direction • t = tension, c = compression
Criteria: • Maximum Strain: e1t, e1c, e2t, e2c, e12 • Maximum Stress: s1t, s1c, s2t, s2c,s3t, s3c, s12, s23, s13 • Tsai-Wu 2-D and 3-D: tw • Tsai-Hill 2-D and 3-D: th • Hashin: hf (fiber failure), hm (matrix failure), hd (delamination failure) • Puck (simplified, 2-D and 3-D Puck implementations are available): pf (fiber failure), pmA (matrix tension
failure), pmB (matrix compression failure), pmC (matrix shear failure), pd (delamination) • LaRC 2-D and 3-D: lft3 (fiber tension failure), lfc4 (fiber compression failure under transverse compression),
lfc6 (fiber compression failure under transverse tension), lmt1 (matrix tension failure), lmc2/5 (matrix compression failure) • Cuntze 2-D and 3-D: cft (fiber tension failure), cfc (fiber compression failure), cmA (matrix tension failure),
cmB (matrix compression failure), cmC (matrix wedge shape failure) • Sandwich failure criteria: – Wrinkling: wb (wrinkling bottom face), wt (wrinkling top face) – Core Failure: cf – Shear Crimping failure criteria: sc • Isotropic failure criteria - Von Mises: vMe (strain) and vMs (stress)
Weighting factor: The inverse reserve factor of each failure mode is multiplied by the accordant weighting factor. • 1: no safety • 2: safety of two
Failure lure Analysis Analysis (p. 357) 357).. An overview of all available failure criteria is given in the Section Fai
2.2.2. Failure Mode Measures Three failure mode measures are available: • IRF = Inverse Reserve Factor (IRF) defines the inverse margin to failure. Load divided with IRF is equal
to the failure load. IRF >1 discloses failure.
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Postprocessing • MoS = Margin of Safety (MoS) defines the margin to failure. MoS is defined as (1/IRF - 1). MoS < 0 discloses
failure. • RF = Reserve Factor (RF) defines the margin to failure. Load multiplied with RF is equal to the failure
load. RF < 1 discloses failure.
2.2.3. Principal Stresses and Strains For strains, only the first (eI) and second (eII) principals are evaluated. The principal strain (e) and stress (s) values are ordered in descendent order.
2.2.4. Linearization of Inverse Reserve Factors Failure criteria are functions that describe a failure envelope and the output of the function is the inverse reserve factor (IRF). IRF is a measure of where the load point is in relation to the failure envelope. IRFs calculated in ACP-Post can differ from those determined in Mechanical APDL. This is because IRFs in ACP-Post are linearized. For failure criteria without quadratic terms, such as maximum strain or maximum stress, the failure output from Mechanical APDL should match closely with IRFs from ACP-Post. For those involving quadratic terms, however, IRFs output from ACP are normalized and will thus not match those output from Mechanical APDL. Because of this normalization of IRFs, an increase of twice the force does not result in four times the IRF in ACP-Post. The determination of failure criteria being exceeded does not change as a result of the linearization (because ). However, However, the numerical values for failure criteria involving nonlinear differs between ACP-Post and Mechanical APDL. The implementation of some failure criteria (Puck, LaRC, etc.) differs between ACP-Post and Mechanical APDL.
2.2.5. Postprocessing of a Composite Solid Model ACP supports failure analysis for composites for shell and solid models. These analyses are based on the same theory, including for sandwich criteria where the entire laminate stack is evaluated for instances of wrinkling. In the case where a solid model model (p. (p. 163) 163) is is generated in ACP-Pre and a solution (p. 208) 208) is is available for the solid model, failure analysis for a solid model can be performed in two ways.
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Usage Reference Figure 2.159: Failure Plot Dialog
If the Show on Solids option is enabled, the worst failure value and mode per solid element is shown on the solid mesh. This plot can give you an overview overview about the general safety of the part, but may overlook some hot spots since the worst failure can occur inside the laminate and be obscured. In layered structures a critical failure may not occur in every layer, as opposed to isotropic parts where critical stresses are on the surface. If the Show on Solids option is disabled, the worst failure per solid stack is projected onto the shell mesh. This makes internal failures visible, giving you a more detailed view of how the composite composite structure reacts under stress. The following figure shows the difference between the two graphical evaluation modes. The failure plot on the solid mesh (left) appears less critical when compared to the shell mesh (right), however, the overall maximum failure value is equal for both plots. Figure 2.160: Failure Analysis of a Solid Model. Show on Solids (left) and Show on Shells (right)
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For an Imported Imported Solid Model (p. (p. 189) 189),, both the Show on Solids option and the Entire Model scoping option must be enabled in order to show the failure results on the solid mesh. This also means the failure plot cannot be projected onto a shell mesh, as is the case for a standard Solid Model.
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Postprocessing In addition to the failure plot (p. (p. 217) 217),, strain strain (p. 216 216)), stress (p. 216) 216),, and progr progressive essive damage damage (p. 218) plots can be created with the Show on Solids option.
2.2.6. Postprocessing of Drop-off and Cut-off Elements A structured layered element is turned into one or several homogeneous elements if it is cut or it represents a ply drop-off. As a result, these drop-off and cut-off elements do not hold any layered information. These elements are represented represented with one (isotropic or orthotropic) material. In ACP-Post, the stresses and strains of the homogeneous elements (prisms and tetrahedrons) are read from the .RST file. The failure evaluation is equivalent for homogeneous and layered elements. The failure results can be displayed on the solid models and the critical (maximum) IRF can be projected on to the shell mesh. The evaluation of stress and strain distributions is not the same for homogeneous and layered elements. The stresses and strains of the homogeneous elements can be displayed on the solid models but cannot be mapped back on to the shell mesh. In this case, zero stress and strain are displayed where cut-off and drop-off elements are present. Drop-off off and Cut-off Elements (p. (p. 287) 287).. For more information, see Drop-
2.2.7. Evaluating Custom Failure Criteria User-defined plots User-defined plots (p. 221) 221) and and the Python scripting scripting interface (p. (p. 395) 395) allow allow you to implement custom postprocessing evaluations. The following example shows how a custom core failure criterion is evaluated. This script should be executed within an ACP-Post analysis anal ysis system. The ACP-Post should shoul d be linked to a solution. The script should be copied into a text text editor and saved as a .py file, and then executed from ACP-Post using File > Run Script. The script evaluates the following failure function for homogeneous and honeycomb core material types:
# Background Information ######################## # This script serves as an example on how to evaluate custom failure criteria. # The failure criteria evaluation is based on stresses or strains at integration point level. # The script shows how stresses at integration point level are accessed. It is worth noting that stress # and strain plots shown in the scene or the sampling point are elemental averages. # The script requires two inputs: the name of an element set as a data scope for the evaluation as
# well as the name of the attached solution. # The script loops through all analysis plies of the model and checks whether there is core material. # For plies containing core material the s13 and s23 stresses are retrieved. The maximum stress per # element across its integration points is used to calculate the inverse reserve factor (IRF) ################################ element_set_name = 'All_Elements' solution_name = 'Solution.1' # Start of Script # NO INPUT NECESSARY! #####################
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Usage Reference
# Loading Python modules import numpy import os import logging # initialize logger log = logging.getLogger(__name__) # num_ip dictionary maps the element type to the number of integration points num_ip = {125: 1, 128: 3, 123: 1, 124: 4, 126: 4} # get active ACP model and update it model = db.active_model model.update() # Define Data Scopes #################### element_set = model.element_sets.get(element_set_name) if element_set is None: log.error("element set %s not found!" % element_set_name) elem_scope = [element_set] model.select_elements(selection='sel0', op='new', attached_to=element_set) labels = model.mesh_query(name='labels', position='centroid', selection='sel0') # create a dictionary that maps element labels to element indices label2index_map = {} for i, v in enumerate(labels): label2index_map [v] = i
# results array initialization with -1. This means areas that do not contain core can be shown in grey in the plo irf = numpy.ones(len(labels)) * -1 # Create shear stress plot ########################## solution = model.solutions[solution_name] if solution is None: log.error("solution %s not found!" % solution_name) # Within the script, the stress plots are only used to retrieve element labels of an analysis ply. # They can also be used to retrieve stress values at averaged at element level. s13_plot = solution.plots.create_stress_plot( name='s13_plywise', ply_wise=True, solution_set=-1, active=True, component='s13', show_ply_offsets=False, ply_offset_scale_factor=1.0, spot='bot', interlaminar_normal_stresses=False, show_on_solids=False, data_scope=[element_set]) s13_plot.update() s23_plot = solution.plots.create_stress_plot( name='s23_plywise', ply_wise=True, solution_set=-1,
active True, component='s23', show_ply_offsets=False, ply_offset_scale_factor=1.0,
spot='bot', interlaminar_normal_stresses=False, show_on_solids=False, data_scope=[element_set]) s23_plot.update() # Loop thru all analysis plies ##############################
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Postprocessing
# Loop thru Modeling Groups for mg_name in model.modeling_groups.keys(): mg = model.modeling_ groups[mg_name] # Loop thru Modeling Plies for mp_name in mg.plies: mp = mg.plies[mp_na me] # Loop thru Production Plies
for pp in mp.production_ plies.values(): # Loop thru Production Plies for ap in pp.analysis_plie s.values(): material = ap.ply_material. material is_core = False # Check if the analysis ply material is a core material if material.ply_typ e.find('core') > -1 or material.ply_ty pe.find('honeyco mb') > -1: is_core = True
log.info("evalu ate core failure for analysis ply %s of type %s" % (ap.id, material.ply_typ e))
# Get stresses and eval irf ###########################
# Common analysis ply properties ap_elem_labels = s13_plot.get_e lement_labels(vi sible=s13_plot.d ata_scope, selected=[ap]) ap_material = model.material_ data.materials[a p.material.name] ap_s13_stress_l imit = ap_material['st ress_limits'].ge t('Sxz') ap_s23_stress_l imit = ap_material['st ress_limits'].ge t('Syz')
model.select_el ements(selection ='sel0', op='new', labels=[int(v) for v in ap_elem_labels]) etypes = model.mesh_que ry(name='etypes' , selection='sel 0', position='centr oid')
# ip-wise stresses for bot, mid and top for spot in ['bot', 'mid', 'top']:
s13 = solution.query( definition='stresses', position='integration_point', component='s13', selection='sel0', entity=ap, spot=spot) s23 = solution.query( definition='stresses', position='integration_point', component='s23', selection='sel0', entity=ap, spot=spot)
ap_irf_absolute = numpy.absolute( s13 / ap_s13_stress_l imit) + numpy.absolute( s23 / ap_s23_stress_l imit)
# need to check whether both element labels arrays are the same if len(s13) != len(s23): log.error("s13 and s23 are of different shape!")
index = 0 for i, et in enumerate(etyp es): elem_irf_max = -1. for n in range(0, num_ip[et]):
elem_irf_max index += 1
max(elem_irf_ma x, ap_irf_absolute[ index])
# insert results into the global irf results array
global_index = label2index_map[ ap_elem_labels[i ]] irf[global_inde x] = max(irf[global _index], elem_irf_max)
# Delete shear stress plots del (solution.plots[s13_plot.name]) del (solution.plots[s23_plot.name]) # Create user defined plot for IRFs
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Usage Reference ################################### plot_name = "Core Shear Failure" # User defined plot basic settings udp = solution.plots.create_user_defined_plot(name=plot_name) udp.user_script_enabled = False udp.user_script = "" udp.show_ply_offsets = False= 1.0 udp.ply_offset_scale_factor udp.show_on_solids = False udp.data_scope = [element_set] # plot color settings udp.color_table.use_defaults = False udp.color_table.auto_lower_value = False udp.color_table.auto_upper_value = False udp.color_table.upper_value_as_threshold = True udp.color_table.grey_values_below = True udp.color_table.lower_value = 0.0 udp.color_table.upper_value = 1.0 # load irf data in plot udp.user_data = irf udp.update() # End of script log.info("End of script")
2.2.8. Limitations & Recommendations Interlaminar shear strains of linear triangular shell elements can not be evaluated. Interlaminar shear stresses of linear triangular shell elements can be evaluated by ANSYS but not by ACP. By default, the ANSYS .RST results file contains stress and strain data, however, they may be excluded. In the case of excluded stresses and strains, ACP can evaluate stresses and strains on the basis of the deformation and rotation fields in the results file. Nonlinear effects are not considered by ACP and can induce inaccurate stresses and strains. In general, it is recommended to include the stress and strain data in the .RST data. More information can be found in Solutions (p. 208) 208).. ACP provides a unique method to evaluate evaluate interlaminar normal stresses (INS) for shell elements. This calculation of the INS requires the evaluation of the shell curvature. It is therefore recommended to use quadratic shell elements when INS are of interest. The quadratic elements contain the curvature information per element and offer a better approximation approximation than linear elements. The curvature for a linear shell element is determined from its neighboring elements. This evaluation does not consider INS induced by edge effects or out-of-plane loads (e.g. inserts, pressures, etc.).
2.3. Exchanging Exchanging Composite Definitions Defini tions with Other O ther Programs This section describes how data can be exchanged between ACP and other programs. The following interfaces are available:
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2.3.1. HDF5 Composite CAE Format 2.3.2. Mechanical APDL File Format 2.3.3. Import of Legacy Mechanical APDL Composite Models 2.3.4.TTabular Data Format for Excel 2.3.4. 2.3.5. CSV Format 2.3.6. ESAComp
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Exchanging Composite Definitions with Other Programs 2.3.7. LS-Dyna 2.3.8. BECAS
2.3.1. HDF5 Composite CAE Format HDF5 Composite is a vendor independent specification an accurate of composite lay-upsCAE between different CAE and CAD packages.that packages. Theallows specification uses exchange HDF5 for data storage, an open and widely used file format that efficiently stores binary data (http://www.hdf( http://www.hdfgroup.com/).). group.com/ The import and export interfaces are accessible through the Model Co Context ntext Menu (p. (p. 54) 54).. Figure 2.161: Export and Import Options in Model Context Menu
Note: The HDF5 Composite CAE format does not take the Fab Fabric ric Fiber Angle (p. (p. 68) 68) property property into account. As a result, if the Fabric Fiber Angle property is active in ACP when the composite layup is exported, Mechanical properties might not be accurate.
2.3.1.1. Export Only the effective lay-up in ACP is extracted during the HDF5 Composite CAE export. This means, for example, ACP will export the ply's thickness distribution but not the taper definitions that affect the ply ’s thickness. Neither will it export the reference shell surface. It will, however, extract Information on the ply ’s material, coverage, dimensions, thickness distribution, reference direction field, as well as the overall ply sequencing. All this information gets stored in the .H5 file.
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Usage Reference You can then import the extracted data into a program such as FiberSIM for further design and production management. For Export Settings, refer to the dialog box below and the explanations which follow. Figure 2.162: HDF5 Composite CAE File Export Settings
• File Path: Specify the destination file name and file path. • Remove Midside Nodes of Quadratic Elements: By default, midside nodes of the quadratic elements
are not exported. • Scope: – All Elements: Uncheck this option to restrict the lay-up export to a region of interest. – User Defined Set of Elements: Here you can limit the exported plies to the specific Element Sets
and/or Oriented Element Sets that interest you. – All Plies: By default, all plies of the scope are exported. Uncheck this option to select a user-defined
set of plies to be exported. – User Defined Set of Plies: Specify the set of Modeling Plies and/or Modeling Groups to be exported.
2.3.1.2. Import 2.3.1.2.1. Import Projection Types The HDF5 Composite CAE Import supports two types of projections. The first one maps layup second option option directly converts the ply data data onto the shell mesh (reference surface) in ACP . The second Objects (p. 146) 146) in in ACP . Below is a more detailed exfrom the Composite CAE H5 into Imported Plies Plies Objects planation of each projection type.
Mapping onto The Reference Surface During the import process, the mapping algorithm in ACP begins by computing the ply extent with respect to the reference surface in ACP. It then maps the fiber directions, thicknesses, and other properties onto the surface. Ply material information gets transferred to the Material Data object in ACP, and Oriented Selection Sets are generated based on ply coverage. Finally, thickness
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Exchanging Composite Definitions with Other Programs distributions and reference direction fields are stored in Look-Up Tables which are then used to define the modeling plies in the lay-up reconstruction. A ply in the Composite CAE H5 has its own mesh that typically differs from the reference surface in ACP, requiring an adjustment to the mapping parameters. For example, different mesh sizes on curved surfaces can cause element normals to deviate. Nodal locations in the out-of-plane and in-plane directions can also vary, depending on mesh sizing You can manage these effects with appropriate import tolerances. Large tolerances can result in mapping issues, especially with convergent meshes, as with a T-joint. If the tolerances are too large, ply boundaries cannot be accurately replicated.
Exposed as 3D Plies (Imported Plies) Instead of mapping the composite data of the HDF5 Composite CAE onto the reference surface in ACP, the data is directly converted into Imported Ply objects if the projection is set to Expose as 3D Plies. Since each Imported Ply has its own mesh that is independent of the reference surface, the meshes of the HDF5 and Imported Plies are identical. This enables you to build complex 3D lay-up models in a CAD environment and load it into ACP for detailed analyses. The remaining data, such as Thicknesses Thick nesses and Reference Direction, are stored in the same manner as the Mapping onto the Reference Surface import option. Ply material information gets transferred to the Material Data object in ACP ACP.. Thickness Distributions and Reference Direction Fields are stored in look-up tables which are then used to define the Imported Plies.
2.3.1.2.2. Import Settings A number of settings and tolerances control the import of the composite model. Refer to the dialog box below and the explanations which follow.
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Usage Reference Figure 2.163: HDF5 Composite CAE File Import Settings
Path
Specify the path to the .h5 file you wish to import. Import Mode • Append: Imported data and objects will be appended to the existing model/layup. • Overwrite: Replaces existing objects that have the same id, unless objects are locked. Note: To
preserve the ply ordering specified in the HDF5 Composite CAE file, imported plies will be added to the top of the existing lay-up, or moved to the top if they already exist. Projection
(p. 242) For additional information on Projection types, see the detailed explanation explanation above. (p. • Map onto Reference Surface: This option maps the plies onto the shell surface in ACP and
exposes them as Modeling Plies. converts the plies into Imported • Expose as 3D Plies (Imported Modeling Plies): This option converts Modeling Plies, uncoupled from the reference surface.
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Exchanging Composite Definitions with Other Programs Ply Angles • Minimum Angle Tolerance: Minimum angle tolerance for which tabular correction angles are
computed for plies. • Recompute Reference Directions: When this option is selected, reference directions are recom-
puted from tabular angle data. Mapping Scope • All Elements: By default, the lay-up data specified in the .h5 file is mapped onto all the ele-
ments of a reference shell mesh in ACP. Uncheck this boolean to restrict the lay-up mapping to a user-defined region of interest. • User-Defined Set: The lay-up data is mapped onto the Element Sets specified here.
Ply Area Mapping
Figure re below (p. (p. 246) 246) for for an illustration of the Tolerance Settings. Refer to the Figu • Relative Thickness Tolerance: This sets the mapping tolerance in the element thickness direction
relative to a edge minimum element edge length.will In the box dialog box (p. 244) (p. 244) shown showninabove, assuming a minimum length of 1mm, elements be mapped if their deviation the element thickness direction is between -0.5 and 0.5 mm. • Relative In-Plane Tolerance: This sets the mapping tolerance in the element in-plane direction
(p. 244) 244) shown shown above, assuming relative to a minimum element edge length. In the dialog box box (p. a minimum edge length of 1mm, elements will be mapped if their in-plane coordinates are within the shell mesh with a maximum allowable tolerance of 0.01mm. • Angle Tolerance: Mapping tolerance for angles between element normals (in degrees). • Small Hole Threshold: Holes in plies/element sets with an area smaller than this threshold
times the area of the element set/ply are filled.
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Usage Reference Figure 2.164: Schematic of Tolerance Settings for a Single Element
2.3.2. Mechanical APDL File Format A Mechanical APDL input file requires specific element settings if it is to be used with ACP in Stand Alone mode. This applies to preprocessing models that are used to define a composite lay-up as well as postprocessing models where reading stresses and strains in future analyses is required. For more Workflow kflow in Stand Alone Operation Operation (p. 50) 50).. information, see Wor Nodal solutions can be loaded from: • PRNSOL file formats. An example export could be: /format,10,G,25,15,1000,1000 prnsol,u
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prnsol,rot
• The .RST file interface allows ACP to load nodal and element results directly from the ANSYS result
file. Use these options for element result import: 247) ) – SHELL181: SHELL181: Keyopt(8) = 2 (See Figure 2.165: SHELL181 Keyopts (p. 247)
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Exchanging Composite Definitions with Other Programs SHELL281:: Keyopt(8) = 2 (SeeFigure (See Figure 2.166: SHELL281 Keyopts (p. 248) 248) ) – SHELL281 /SOLID186 SOLID186:: Keyopt(3) = 1 (See Figure 2.167: SOLID185 Keyopts (p. 248) 248) and and Figure 2.168: SOL– SOLID185 / ID186 Keyopts Keyopts (p. (p. 249) 249))) Keyopt(3) must be defined via the command line: KEYOPT,ET_NUM ,3,1 ,3,1 SOLSH190:: Keyopt(8) = 1 – SOLSH190 – ERESX,NO (copy integration point results to nodes)
SHELL281,, SOLID185 SOLID185,, Supported shell and solid (for post-processing only) element types: SHELL181, SHELL181, SHELL281 SOLID186 Supported element property definition commands: SECTYPE, SECOFFSET, SECCONTROL, RLBLOCK Figure 2.165: SHELL181 Keyopts
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Usage Reference Figure 2.166: SHELL281 Keyopts
Figure 2.167: SOLID185 Keyopts
247
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Exchanging Composite Definitions with Other Programs Figure 2.168: SOLID186 Keyopts
2.3.3. Import of Legacy Mechanical APDL Composite Models Composite shell models with section definitions created in Mechanical APDL can be imported to ACP. Upon import, the lay-ups are converted into ACP composite definitions (Rosettes, Oriented Selection Sets and Modeling Plies). The converted model can be subsequently used in Workbench projects. See Speciall Cases (p. (p. 251) 251) and and the Known Limitations Limitations (p. (p. 251) 251) sections sections for more information. the Specia Review the following import scenarios. The scenarios are different based upon whether or not you are working with the mesh of the legacy model in ACP.
Equal Meshes In this case the section definitions of the legacy model are mapped according to the element labels and it assumes that also the element normals are equal. To import a legacy model that can be used in Workbench projects :
1. Add an External Model system to the Workbench project page and load the legacy file. 2. Add a new ACP (Pre) system to the Workbench project page. 3. Link the External Model system with the Engineering Data cell of the ACP system. system. This loads the materials (cells A2-B2). 4. Link the External Model system with the Model cell of the ACP system in order to load the mesh
(cells A2-B3). 5. Re Refr fres esh h the the ACP ACP syst system em Setup cell. Launch ACP. 6. Make sure sure that the unit system system in ACP ACP and the legacy legacy model model are the same. same. 7. From From the the acti action on men menu u of the the Model folder in ACP, select the option Import Section Data from Legacy Model. Select the file you have opened in the External Model system (see Import Section Data from from Legacy Model Model (p. 60) 60)).). Verify that you have the correct material mapping mask.
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Usage Reference Figure 2.169: Configuration Overview
Note: • Engineering Data renames the materials. The pre- and suffix masks enables the automatic
mapping between legacy material IDs and WB material IDs. • Because the mapping is based on the element labels, we recommend that you import each
legacy model separately. You can assemble the legacy files in a downstream Mechanical Model as needed.
To import a legacy model in ACP standalone mode:
1. Start Start ACP ACP in ACP ACP stan standa dalon lone. e. 2. Load Load the the file file usin using g the the Import Model option from the Models action menu or File tab in the application toolbar and select the Convert Section Data check box.
Different Meshes If you are working with different meshes, you have to convert the legacy model by using the Composite CAE H5 file format. To convert a legacy model onto a different mesh :
1. In Workbench, Workbench, import and convert convert the legacy legacy model model as described described above above (system (system A and B) 2. Update AC ACP Setup cell (A4) and export the lay-up to a HDF5 Composite CAE file (p. 60) 60)..
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3. Create the ACP ACP system system (C) where where you want want to map map the legacy legacy lay-up lay-up to. to. 4. Link the External Model with the Engineering Data component to load the materials (A2-C2). Composite posite CAE H5 file file (p. 60) 60).. 5. Open Open th the e ACP Setup cell (C5) and import the Com
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Exchanging Composite Definitions with Other Programs Figure 2.170: Configuration Overview
2.3.3.1. Special Cases Lay-ups in ACP are either stacked on the top or the bottom of a shell surface. If the shell offset direction of a Mechanical APDL model is not set to top or bottom then the ply lying on the shell surface is split into two plies on either side of the shell surface during the conversion. Figure 2.171: A Four Ply Mechanical APDL Lay-up Where a Ply Crosses the Reference Surface is Converted to a Five Ply ACP Lay-up
2.3.3.2. Known Limitations The conversion of the composite lay-up of legacy Mechanical APDL models mo dels to ACP models only works for shell models. Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Usage Reference The proper translation of Mechanical APDL sections to ACP modeling plies can only be guaranteed if the Mechanical APDL section points to a connected region of elements where all element normals are oriented the same way. If this is not the case, a warning is issued on export and the resulting lay-up may not be entirely correct. The material transfer from External Model to Engineering Data is not supported on Linux. Alternatively you can load the model in ACP standalone and export the materials in the ANSYS Workbench XML formatt (p. forma (p. 64) 64) and and import from this file.
2.3.4.Tabular Data Format for Excel A definition block starts star ts with a cell value of BEGIN TABLE TABLE and ends with END TTABLE. ABLE. This cell is in the first column (A) of the worksheet. The block DEFINITION is used to identify the type of tabular data defined in the block. ModelingGroup, LookUpTable3D, and LookUpTable1D are currently the only supported definition types. Empty lines are not allowed inside of sub-blocks. Lines between sub-blocks are ignored. The formatting of existing cells is not changed when the lay-up is pushed from ACP. Missing field in the DATA block are ignored and not set when synchronized with ACP. Hidden cells are not ignored and are synchronized with ACP. Figure 2.172: ModelingGroup Tabular Format in Excel
In the case of Look-Up Tables, if you add the text string "(Read Only)" to the column name, the corresponding Excel column is ignored.
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Exchanging Composite Definitions with Other Programs Figure 2.173: Look-Up Table Tabular Format in Excel
References to other objects (ply material, oriented selection sets, etc.) are defined by the object's ID. In the case of ply material, the type of material and the material's ID are joined with a forward slash (for example, fabrics/E-Glass). For the angle and thickness fields, the column name and the ID of the lookup table must be provided (LookUpTable.1/Angle). Communication to Excel is accomplished through the COM COM interface. The identifier used to connect to Excel is Excel.Application. You can find more information on how to exchange model data with Excel in Edit Entities with Excel (p (p.. 23) 23)..
2.3.5. CSV Format Materials, Look-Up Tables, Selection Rules definitions, and Modeling Groups can be exported and imported using a .CSV format (comma separated value file). The .CSV file format for the import and export of Look-Up Tables and Modeling Groups follows the
same format as the T the Tabular abular Data Format for Excel E xcel (p. ( p. 252) 252)..
Caution: The CSV format uses a '','' as list separator. In some Regional Options in Windows, Wi ndows, the list separator is defined by another character (very often '';''). In this case, the .CSV files will not be properly read and written by Excel. Change the list separator in Windows Settings.
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Usage Reference
2.3.6. ESAComp Model format: ESAComp XML files.
The following operations are available: 2.3.6.1. Export 2.3.6.2. Import
2.3.6.1. Export Material data (Fabrics, Stackups and Sublaminates) and Sampling Points can be exported to ESAComp XML. A Fabric represents a Ply in ESAComp and Stackups, Sublaminates and Sampling Points are exported as Laminates. To To be sure that the imported values in ESAComp are a re in accordance to the ACP model, mod el, the FE import units in ESAComp should be checked first. • Open FE import and export units in ESAComp. • Adjust units in the Model Properties dialog (see ACP Model (p. 57) 57)).). Model (p.
2.3.6.2. Import Import As for the export, check that the units match in ESAComp and ANSYS Composite PrepPost. In ESAComp, there are 2 ways to export the data:
Script Format (recommended) In ESAComp, you can export Plies and Laminates through the FE Export / ANSYS ACP option option in the menu. It generates a Python script, in which all the information is stored in ACP format.
XML Format In ESAComp, export your data as .XML file using the File menu. Import this data in ANSYS Composite PrepPost with the context menu for the Material object in the tree (see Material Material Data (p. (p. 64) 64)).). Only material data can be imported.
Important:
The Import from ESAComp XML operation does not create the material in ANSYS Composite PrepPost. It only changes the properties. So the material must be created before with the same name as in ESAComp.
2.3.7. LS-Dyna There are three ways to exchange an ACP composite model with LS-Dyna:
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Exchanging Composite Definitions with Other Programs Workbench rkbench model, including com• LS-DYNA (Extension Library): This approach allows you to convert a Wo posite definitions, to an LS-Dyna model. This is the recommended approach. • LS-Dyna Interface (ACP Add-on): Allows you to define composite definitions for LS-Dyna meshes/models. • LS-Dyna Solid Model (ACP Add-on): Allows you to export to the solid model in the .K file format.
Caution: The add-on features described in this section are not recommended for general use. It is strongly suggested that you use the Workbench interface to transfer information between ACP and LS-Dyna.
2.3.8. BECAS ACP can export the 2-D mesh of a surface section cut to the cross-section cross-section analysis tool BECAS. BECAS . This enables you to derive a beam model from an ACP shell model. The 2-D mesh is built with linear elements and includes material information as well as lay-up orientations. As a result, geometric and material-dependent coupling can be taken into consideration. The 2-D mesh can also be exported to Mechanical APDL. In this case, no lay-up information is transferred. For more details on exporting surface section cuts, see Section Cuts Cuts (p. (p. 156) 156).. For more information on the BECAS tool, see the BECAS website. website.
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Chapter 3: Composite Modeling Techniques The various composite modeling techniques available in ACP are a re described in the sections below: 3.1.T-Joint 3.2. Local Reinforcements 3.3. Ply Tapering and Staggering 3.4.Variable 3.4. Variable Core Thickness Thickness 3.5. Draping 3.6. Ply Book 3.7. Guide to Solid Modeling 3.8. Guide to Composite Visualizations 3.9. Guide to Composite Failure Criteria 3.10. Element Choice in ACP 3.11.Variable 3.11. Variable Material Data in Composite Analyses
3.1.T-Joint T-joints are used to bond a primary structure to a secondary one. A good example is a frame with a stringer of a boat hull. Oriented Selection Sets (OSS) allow you to define complex laminates by an intuitive approach. For an example of a T-Joint analysis, see Workshop Workshop 2: T-Joint T-Joint.. The laminate of a T-joint can be split into several sublaminates: • Base plate (skin) • Stringer (frame) • Bonding • Cover
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Composite Modeling Techniques Figure Figur e 3.1: T-Joint T-Joint Lay-Up
The laminate is modeled by defining different Oriented Selection Sets for the different regions. The modeling plies are then associated with the OSS and their order defines the stacking sequence of the laminate. The first OSS is defined for the base. The offset direction of this OSS shows from top to bottom as shown 259).. in Figure 3.2: OSS for the Base Plate (p. 259)
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T-Joint Figure 3.2: OSS for the Base Plate
The OSS of the string has an orientation parallel to the global X-direction as shown in Figure 3.3: OSS for the Stringer Stringer (p. (p. 260) 260)..
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Composite Modeling Techniques Figure 3.3: OSS for the Stringer
The OSS feature allows you to define several offset directions for one element: OSS can overlap and can have different orientations. This functionality is used to define the offset direction for the bonding layers as shown in Figure 3.4: OSS for Bonding Plies (p. 261) 261).. The offset offset direction of the base plate is 259).. different if compared with Figure 3.2: OSS for the Base Plate (p. 259)
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T-Joint Figure 3.4: OSS for Bonding Plies
In addition, the OSS feature allows you to define the reference directions for complex shapes (twisted surfaces, right angles). The reference direction is computed from one or several reference coordinate systems (CSYS) as shown in Figure 3.5: Reference Direction (p. 262) 262).. In this case two CSYS are selected.
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Composite Modeling Techniques Figure 3.5: Reference Direction
After all the necessary OSS are defined, define the Modeling Plies in the same order as the structure is produced later. First, the base layup is defined using the OSS of the base plate.
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T-Joint Figure 3.6: Laminate of the Base Plate
The next plies are added to the stringer.
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Composite Modeling Techniques Figure 3.7: Laminate of the Base Plate and Stringer
It is important to define the base plate and stringer laminate before the bonding plies are defined because 265),, the the order is responsible for the final offset. As shown in Figure 3.8: First Bonding Laminate (p. 265) bonding layers are applied to the top of the base plate and onto the plies of the stringer.
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T-Joint Figure 3.8: First Bonding Laminate
On the other side, the second bonding laminate is offset to the top (base plate) and to the left (stringer).
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Composite Modeling Techniques Figure 3.9: Second Bonding Laminate
Cover plies complete the layup definition of the T-joint. Figure 3.10: Cover Plies (p. 267) 267) shows shows that ACP can also handle drop-offs.
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Local Reinforcements Figure 3.10: Cover Plies
3.2. Local Reinforcements Regions with cut-outs, holes or load introduction elements are normally highly stressed and require local reinforcements to prevent failure. ACP offers different ways to define local patches. Selection Rules can be used to apply reinforcements to selected areas of the structure's geometry. The shape of a reinforcing ply is defined by the intersection of an Oriented Selection Set and the selected Selection Rules. Tutorial 2 use 2 use Parallel Selection Rule and Tube Selection Rule to define The examples Class40 and Class40 and Tutorial Tutorial 2 describes patches. Tutorial patches. 2 describes how a Tube Selection Rule can be defined to add a ply following an edge. The procedure involves these steps:
1. Define an an Edge Set from the boundaries of an Element Set. 2. Create a Tube Selection Rule along the defined Edge Set with a certain inner and outer radius.
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Composite Modeling Techniques Figure Figur e 3.11: Tube Selection Rule
3. Create Create a new ply and confi configur gure e the the Selection Rules in the Rule tab of the Modeling Ply Properties dialog. Figure 3.12: Rules Tab of the Modeling Ply Property Dialog
The selection rule parameters can be modified for each Modeling Ply. This allows allows you to work with with
one Selection Rule to define the staggering of a laminate. You can activate a template and set the new parameters. The final result can be double-checked with Section Cuts or a thickness contour plot as shown in the figure below.
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Ply Tapering and Staggering Figure 3.13: Resulting Local Reinforcements
Selection Rules can also be combined with Oriented Selection Sets and other Selection Rule types like Parallel, Spherical, or Cylindrical are also implemented in ACP. Any combination of these selection
rules allows you to create plies with complex shapes.
3.3. Ply Tapering Tapering and Staggering Ply tapering and staggering can be quickly defined within ACP. Several examples are shown below.
3.3.1. Ply Tapering Core plies are generally much thicker than regular or woven woven plies. This means that core edges must be tapered for structural and manufacturing reasons. When a taper is applied to an edge of a ply in ACP and the corresponding thicknesses are evaluated and mapped automatically onto the finite elements.
3.3.1.1. Edge Tapering This section gives an overview of how the edge tapering feature works. The Taper Edges option (p. 131) 131).. Its definition requires a constant taper angle along an can be applied to modeling plies (p. edge set. Optionally, a taper offset can be specified. Based on this definition, a virtual taper plane is evaluated to taper the thickness of plies. The effective tapering or thickness distribution over the taper is further dependent on the resolution of the mesh. Figure 3.14: Simple Edge Tapering (p. 270) 270) shows shows a schematic of a simple edge tapering. An edge set runs along the side of a square of elements. Ply tapering is evaluated at each element along the edge set. The taper edge offset specifies the normal (thus out-of-plane) distance from each element adjacent to the element set. This offset forms a plane parallel to the underlying element.
The taper angle specifies the angle between this offset plane and the resulting taper plane. In the figure, the resulting taper plane is the same for the whole edge set. The resulting taper planes are oriented differently if the edge set follows a curved path. The offset direction is set to be positive in the orientation direction of the oriented selection set of the modeling ply. Depending on the mesh and application, it may have to be specified as a negative value.
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Composite Modeling Techniques Figure 3.14: Simple Edge Tapering
3.3.1.2. Class40 The Class40 Class40 example example uses a tapered core. Open the model and check the Modeling Ply core_bwl in the Modeling Group Hull. In the Thickness tab of the properties dialog a taper angle of 15 degrees is defined for the edge edgeset.2. A Section Cut or thickness contour plot illustrates 270).. the final result as shown in Figure 3.15: Tapered Edge (p. 270) Figure Figur e 3.15: Tapered Edge
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Ply Tapering and Staggering
3.3.1.3.T Tutorial 2 3.3.1.3. In Tutorial In Tutorial 2, 2 , a ply tapering is defined along 2 edges. The procedure inv involves olves these steps: 1. Defin fine an Edge Set. In this case, the Edge Set is defined through a Named Selection in Mechanical. 2. Open the Thickness tab in the Modeling Ply Properties dialog. Figure Figur e 3.16: Tapering in Ply Definition
3. Select Select the edge edge and defi define ne the the taper taper angle angle..
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Composite Modeling Techniques Figure 3.17: Thickness Distribution After Core Tapering
3.3.1.4. Tapering of Multiple Plies 3.3.1.4.T The Taper Edges option for Modeling Plies is suitable for defining individual taper angles for specific modeling ply. Its intended purpose is for use with a single tapered ply, such as a core, however it can be used for tapering multiple plies. If the Modeling Ply tapering option is used for multiple layers the taper angle is applied to each Modeling Ply and the vertical ply thickness distribution is superimposed. In such a case, the total taper angle of the layup is generally higher than the individual taper angles. The total taper angle scales non-linearly with the number of p plies lies and their thicknesses. Furthermore, the taper size is a dependent on the size of the mesh. For this reason, care should be taken when using the Taper Edges option for multiple plies. When modeling a composite with a defined total taper angle a Selection Rule definition may be more suitable. The trailing edge of an airfoil blade is an example for such an application. The example below shows the effects of superposing multiple modeling plies that have the same taper angle. The middle column shows a layup schematic while the right column displays the corresponding representation of which a section in ACP. ACP. The of two different ply thicknesses results in two taper angles of onecut is steeper thansuperposition the nominal angle. Figure 3.18: Superposition of Modeling Plies with Identical Taper Angles. Schematic (Middle) and Section View Illustration (Right)
3.3.2. Ply Staggering Cutoff Selection Rule A Cutoff Selection Rule is used to cut plies and is suitable to define a ply staggering. This feature is not limited to an edge because the staggering is derived from a CAD Geometry. The interse intersection ction
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Ply Tapering and Staggering between the ply and geometry defines where the plies are cut. The ply offsets are taken into consideration. This allows you to define a laminate where the ttotal otal thickness follows a 3D shape. Figure 3.19: Thickness Distribution of a Laminate with a Cutoff Selection Rule
Template Selection Rule The template selection rule feature of the Modeling Ply allows you to use one Selection Rule to define plies of different extensions. You can redefine the parameters of a selection rule in the Modeling Ply Properties dialog. A wind turbine blade, for example, has hundreds of similar plies that only differ in their the axial extension. Such plies can be defined with one Oriented Selection Set and one Parallel Selection Rule and the use of template parameters. The template parameters are easily ad justed using the Import from / Export to CSV file feature in the context menu of the Modeling Group. Figure 3.20: Template Selection Rule Definition
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Composite Modeling Techniques
3.4.Variable Core Thickness In many cases, the thickness of a sandwich panel is constant or single plies have a constant thickness. For structural efficiency, cores with variable thickness are used more often since CNC milling allows the production of core plies with complex shapes. In ACP there are three different ways to define a laminate with variable thickness: 3.4.1. Solid CAD Geometry 3.4.2. Look-Up Table 3.4.3. Geometry Geometry Cut-off Selection Rule 3.4.4. General Application
3.4.1. Solid CAD Geometry An external core geometry can be used to define the variable variable core thickness. The 3-D shape of the core is modeled in a CAD tool as a 3-D solid or a closed shell. This CAD Geometry can be imported directly into ACP or via Workbench. Figure 3.21: Imported Core Geometry
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In the Thickness tab of the Modeling Ply Properties dialog, the thickness definition can be changed from Nominal to From Geometry. In this case, ACP samples through the geometry in the normal direction and evaluates the thickness of the core core for each element. The original thickness defined in the Fabric definition becomes obsolete. This method is used in the Class40 example.. Class40 example..
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Variable Core Thickness Figure 3.22: Modeling Ply Thickness Definition
Figure 3.23: Section with Variable Core Thickness
3.4.2. Look-Up Table The variable core thickness t hickness can also be defined with a Look-Up Table. A Look-Up Table is used to define a data field or tabular values. Thicknesses, angles and directions can be defined in a Look-Up Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
Composite Modeling Techniques Table and the 3D mapping function of ACP inter- or extrapolates the values for each element. You
define the thickness of the ply material for certain support points. The figure below shows a list of different angles and thicknesses for selected data points. Figure Figur e 3.24: Table Definition
Following on, the corresponding tabular field can be selected in the Thickness tab of the Modeling Ply Properties dialog. Figure 3.25: Thickness Definition Through Tabular Tabular Values
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The final result can be investigated with Section Cuts or a thickness contour plot as per usual.
3.4.3. Geometry Cut-off Selection Rule Another way of achieving a variable core thickness is to use a Cut-off Selection Rule. Even if the cutting operation only applies to a core layer, it is dependent on the entire layup. If the thickness of the bottom laminate is changed, the thickness of the core is cutoff at a different height. In this way,
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Variable Core Thickness a laminate thickness limit can be set. This can be a very useful in places where the laminate thickness is limited, near a trailing edge of a blade for example. Figure 3.26: Section Cut and Thickness Contour Plot
The core thickness t hickness can be set to be cut in different ways depending on the Ply Tapering option of the Selection Rule. It can either follow the exact intersection with the CAD Geometry or can be cutoff to two discrete size - its nominal thickness or no thickness at all. The Cut-off Selection Rule has to be used with precaution as any modification of the underlying plies might modify the core. An example of a Cut-off Selection Rule can be found in Tutorial in Tutorial 2 2.. Figure 3.27: Imported Cut-off Geometry
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Composite Modeling Techniques Figure 3.28: Resulting Thickness Distribution (Ply Tapering Activated)
3.4.4. General Application The described features can also be used in combination with regular or woven materials and are not restricted to core materials. The selection of the method is often derived from the manufacturing process. Tabular values can be used for a winding process and CAD geometries for a CNC milling (p. 276) 276) is is often used in regions of sharp tapered edges (trailing edge process. A Cut-off Cut-off Selection Rule (p. of a wind turbine blade).
3.5. Draping
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The ply application (draping) on doubly curved surfaces changes the theoretical fiber orientations. In many cases the effect is small and can be neglected. On the other side it is important to know how big this effect can be and if it has to be considered. ACP allows you to evaluate the draped fiber directions. These angles can be visualized and are considered in all analyses, resulting in more accurate evaluations. The draping is evaluated on the Production Ply level. In addition the draping algorithm of ACP evaluates the flatwrap of the Production Plies which can be exported for manufacturing purposes.
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Draping Figure 3.29: Flatwrap (Boundary)
3.5.1. Internal Draping Algorithm of ACP The draping algorithm is described in Draping Draping Simulation Simulation (p. 347) 347)..
Draping Method Definition The draping effect depends highly on the manufacturing process. Process-relevant values can be defined in the ACP draping algorithm.
Seed Point The Seed Point is the starting point where the ply is laid into the mold. At this location the fiber direction is unchanged and the draped fiber direction is equal to the theoretical one. The Seed Point can have a big influence on the final result of the draped fiber angles. Assuming a half sphere and a
Seed Point located on the pole, the maximum draped fiber angle is much smaller than the same evaluation with a Seed Point on the equator. equator. The Seed Point corresponds to the first element of the
348)).). draping mesh (left representation in Figure 5.1: Draping Scheme (p. 348)
Draping Direction After the first point is applied on the mold, the Draping Direction defines along which route the ply is laid into the mold. mold. The draping algorithm first walks along the Draping Direction, then orthogonal and finally proceeds with the 45-degree zones. Figure 5.1: Draping Scheme (p. 348) 348) shows shows the scheme in which the ply is applied.
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Composite Modeling Techniques
Draping Mesh The draping algorithm minimizes the shear energy dissipation where an internal Draping Mesh is used for the evaluation. This mesh is independent from the structural mesh and has its own size. Analog to the structural mesh, the optimal Draping Mesh size is established by balancing the precision of the draping evaluation and the computational cost. In the case of an incomplete draping, select another Seed Point, define a different Draping Direction and/or change the Draping Mesh size. The draping draping mesh is built as shown in Figure 5.1: Draping Scheme (p. 348) 348).. Figure 3.30: Draping Mesh with Shear Energy
Draping Definition on OSS Level The draping can be activated in the Draping tab of the Oriented Selection Set Properties dialog.
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Draping Figure 3.31: Draping Definition in OSS
If draping is activated on the OSS level, the Reference Direction of the OSS is adjusted and all associated modeling plies use this draped reference direction. If the Modeling Ply also has an active draping definition, then an independent draping simulation is started for the modeling ply.
Draping Definition on Modeling Ply Level Just like OSS, draping can be activated on the Modeling Ply level. To activate the draping you toggle the Draping check box and define a Seed Point. By default, the Mesh Size and Draping Direction are evaluated automatically. By default, during the draping simulation the draping mesh is laid on the reference surface of the model independently of the layup thickness. If the model property Use Draping Offset Correction is enabled, the draping mesh follows the bottom offset (relative to the reference surface orientation) of the selected ply, thus taking into account the layup thickness. An additional feature, Thickness Correction, is implemented in the Internal Draping algorithm. Due to the shear deformation, the fiber direction and thickness of the ply change. This change can also be considered by activating the Thickness Correction option.
3.5.2. User-Defined Draping ACP can also handle user-defined draping results. The draped fiber directions can be imported as a Look-Up Table and used instead of Internal Draping.
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Composite Modeling Techniques Figure 3.32: Tabular Values Values Definition of Draping
The first angle Correction Angle 1 defines the correction of the material reference direction and is also considered considered in the analysis. analysis. The second value Correction Angle 2 can be used to define the correction angle of the material 2 direction for woven materials. In ACP, the second correction is not considered in any evaluation and is just for information or third party products.
3.5.3.Visualization The result of the draping evaluation can be visualized on the Production Ply and the Analysis Ply level. The flatwrap and the draping mesh can be visualized through the use of a Draping Mesh Plott (p. 196 Plo 196)). The contour plot plot of the draping shows the average shear (distortion) angle of each element (in degree). Zero means no shear deformation. Depending on the scene configuration the flatwrap (p. 228) 228).. In addition the Production Ply functionality allows you to is also available in the Ply Book (p. export the flatwrap as a .dxf file. The last result of the draping are the draped fiber directions which are considered in the analysis.
These directions can be visualized with the Show Draped Fiber Directions button. This visualization visualization combined with Show Fiber Directions highlights the influence of the draping.
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Ply Book Figure 3.33: Fiber and Draped Fiber Directions
3.6. Ply Book A Ply Book is is the easiest way to forward the production data to other members of your project (designers, manufacturers and others). It is a good medium to exchange information generated automatically. A Ply Book is is separated in different chapters. In the automatic setup, a chapter is generated for each allows to predefine predefine a View showing the details Modeling Group. Each chapter has its own View. This allows of this specific section of the model. Therefore the first step is to generate a new View through the button in the toolbar or by right clicking the tree view. Figure Figur e 3.34: View Definition Definition
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Composite Modeling Techniques Create the chapters by right clicking the Ply Book and and selecting Automatic Setup from the context menu, or define your own chapters.
After the chapter definition, right click the Ply Book and and select Generate the Ply Book from from the context menu. Ply books can be exported in the .html, .pdf, .odt or .txt formats. The export operation operation can take several minutes, depending on the format. The image size used in the Ply Book can can be defined in the Scene Pre Prefere ferences nces (p. 17) 17)..
Class40 example, example, a Ply Book with with different chapters and different views is already defined. In the Class40 Figure 3.35: Example of a Production Ply Representation
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Guide to Solid Modeling
3.7. Guide to Solid Modeling This section describes when and how to work with the Solid Model Model (p. (p. 163) 163) feature feature in ACP (Pre). In this context we are talking about the solid model extrusion and not the layup mapping feature within the Imported Solid Model. In the case of thick composites, the layered shell theory can cause significant errors in the obtained results. In some cases it is necessary to work with 3-D models (solid models). ACP has the advanced features to generate layered solid models based on the shell layup definitions. Based on the shell mesh and the ACP composite definitions, ACP generates layered solid elements representing one-to-one the composite part. Drop-offs, staggering and tapering are also considered. In addition the solid model extrusion allows to define extrusion directions, boundary curves, and cut-outs. In general we recommend to work with the "standard" Solid Model because the extrusion approach allows you to generate a one-to-one solid model. If this is not feasible then the layup mapping approach (p. 189) 189) is is a great alternative. Modeling full cross-section composites within the Imported Imported Solid Model (p. such as composite springs or turbine blades, for instance. Example analyses for both approaches are Composite site Solid Model (p. (p. 312) 312) and and Analysis Analysis of a Mapped Composite Composite Solid Model (p. 328) 328).. available: Compo The following sections give a brief guide to Solid Modeling: 3.7.1.When to Use a Solid Model 3.7.2. How to Use the Solid Model Feature 3.7.3. Principles Principles of Solid Model Generation 3.7.4. Drop-off and Cut-off Elements 3.7.5.Workflow 3.7.6. Practical Tips 3.7.7. Known Limitations
3.7.1.When to Use a Solid Model From an analysis point of view, the choice between a shell or solid element analysis models largely depends on the structure and the type of structural investigation. Solid models are inherently larger and computationally more expensive than shell models. It is therefore wise to start an analysis with a shell model before moving on to a solid model. It provides a basis for comparison but it is also a good check on whether the model is solvable. Typically, a solid model describes the behavior of a structure more precisely when its out-of-plane Typically, response becomes significant. ACP has the unique feature of representing the 3-D stress state for a
shell model. Shell model stress behavior can therefore be taken as a first indication of the 3-D stress state. If the out-of-plane stresses are significant then it may be worthwhile analyzing the structure as a solid element model. The following list shows cases examples. where are a solid element model can be used. The solid modeling feature is not limited to these • Analysis of thick structures • Investigation into 3-D stresses (high element resolution necessary)
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Composite Modeling Techniques • Investigation into debonding • Investigation into edge effects • Buckling analysis of sandwich structures
There are no hard rules on this matter. It remains entirely the choice of the designer when to use a solid model in addition to or instead of a shell model.
3.7.2. How to Use the Solid Model Feature The intention of the solid model feature is to generate analysis models for structures that are built in one piece. The feature itself makes no distinction between generating solid element models that are analyzed in isolation or ones that are analyzed in combination with other components. There is however a distinct difference in how the analysis of a solid element model of multiple components can be approached. The components of an assembly can either be extruded individually or extruded as one assembly. Both approaches are possible within ACP yet they both have advantages and limitations. The recommended approach is to generate individual components and connect them using contacts in a Workbench Workbench Analysis System. This follows the intention that Solid Models are only created for components that are to be built in one piece. Additional connecting structures can be also fully modeled or dimensioned with the help of substitute model. The other approach is the extrusion of an entire assembly in one solid model generation. This method is not only limited by the topological complexity of a geometry but also by a reduced stiffness at transitions as a result of drop-off elements. On the other hand, this approach offers the ability to model all connecting structures in full.
3.7.3. Principles of Solid Model Generation The solid modelmodel. feature requires a reference shell s hell geometry and a composite definition to construct a solid element Solid model settings control how the solid model is divided into elements in the thickness direction and how drop- and cut-off elements are handled. The level of detail required in the solid model depends on how accurate certain features are to be modeled. This depends on the judgment of the designer. The feature has additional ways to enhance the resulting solid model to be as detailed as necessary: necessary : ply staggering and tapering are transferred from the composite definitions. Extrusion guides add
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more complex possibilities in shaping the model. The snap-to functionality makes an alignment with an external CAD geometry possible. Arbitrary cut-outs or cut-offs can be created with Cut-off Geometries. The cut-off operation is analogous to machining a composite composite part after curing. Geometry operations (extrusion guides, snap-to and cut-off geometries) help to shape a solid model into the desired shape. These operations are applied applied sequentially to the solid model. You should explore all possibilities of shaping the solid model first with the help of extrusion guides and snap-to geometries before moving on to cut-off features. While cut-off geometries allow great freedom in shaping a solid model, they also introduce degenerated elements which are limited in representing a layered composite. For more information, see Drop-off Drop-off and Cut-off Elements (p. (p. 287) 287)..
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Guide to Solid Modeling Details of the solid model feature are explained in the Usage Referenc Reference e (p. 53) 53)..
3.7.4. Drop-off and Cut-off Elements Drop-off and cut-off elements cannot store any layered information and therefore must be associated with a homogenous material. Drop-off elements are created when ply boundaries exist inside the part. When the plies come to an end, the solid model extrusion creates a drop-off element in the shape of a triangular prism. The drop-off elements can be modeled with either the ply (or core) material, a different material such as resin, or as a void. Cut-off elements are created when a hexahedral element is diminished by a cut-off operation and decomposed into prism or tetrahedral elements. These elements can also be modeled with different homogenous materials. The cut-off features offer great freedom in shaping a solid model. The trade-off when using the cutoff feature is that elements diminished by the cutting operation are decomposed into homogenous tetrahedral and prism elements. These elements cannot store any layered information and the postprocessing results for cut-off regions must be interpreted with care. Both drop- and cut-off elements can cause steps in the structural stiffness, which may lead to stress peaks and higher IRFs. This affects the homogenous elements as well as the layered elements in their proximity. For information on the postprocessing of stresses and strains of homogeneous elements, see Postprocessing of Drop-off Drop-off and Cut-off Cut-off Elements (p. 237) 237)..
3.7.5.Workflow A solid model is easily created alongside an existing shell model in Workbench. Once a solid model has been generated in ACP-Pre it can be linked to new Analysis System. A single ACP-Pre system can be used to create a shell and a solid model analysis. This workflow is shown below:
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Composite Modeling Techniques Figure 3.36: Analyzing a Solid Model Alongside a Shell Model
The analysis of an assembly requires multiple solid model components to be connected in a Workbench system. The components can be connected with contacts in Mechan Mechanical, ical, for example. As a consequence, the connections connections can be modeled and analyzed analyzed in detail. The Composite Failure Tool in Tool in Mechanical permits the analysis of all composite parts at once or for a selected scope of interest. The post-processing of ACP Post supports more features with respect to composites but it is limited to a single component (ACP Pre system).
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Guide to Solid Modeling Figure 3.37: Solid Model Assembly Workflow
3.7.6. Practical Tips The solid modeling process is generally more complicated than shell modeling is. The shape and mesh of a structure have a strong influence on the robustness of the solid modeling process. Generally speaking, the less complex complex the model the more robust the p process. rocess. The challenges of composite modeling can vary greatly. Following composite design principles for structural concepts will aid the solid modeling process. Abrupt changes in shape and sharp edges are not advisable in composite design and also cause problems in composite modeling.
3.7.7. Known Limitations Awareness of the limitation of solid modeling can help you build a better solid model. It is worth spending time thinking about aspects of your model such as mesh sizing, extrusion methods, and geometry operations. For example, it can often be more robust to extrude from the inside out. This section gives an overview of the limitations of these advanced modeling features:
Mesh Extrusion
The solid model relies on the extrusion of a shell geometry mesh. As the extrusion directions and operations increase the solid model generation reaches a limit of how heavily a shell mesh can be distorted. If the topology of the structure is complex then the extrusion operations can result in ill-formed elements which are subsequently deleted in the element check. Drop-Off Elements
There are transition regions where an edge of a solid model extrusion is reduced to a series of dropoff elements. This reduction in thickness will result in a local reduction in stiffness that should not be overlooked.
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Composite Modeling Techniques Cut-off Elements
Cut-off elements are decomposed decomposed into homogenous tetrahedral and prism elements. These elements can cause abrupt changes in the structural stiffness which may lead to higher stresses and IRFs. The results in the proximity of cut-off elements should be evaluated with care. Connect Butt-Jointed Plies
The ability to connect adjacent plies is currently restricted to plies that appear sequentially in the same modeling group. Consequently, there a certain arrangement where a ply drop-off cannot be evaded. Solid Model Extrusion Offset
The solid model extrusion starts from a reference shell s hell and the layup definition. An extrusion with an offset to the reference geometry is not possible. Sampling Points, Section Cuts, and Sensors
Sampling points, Section Cuts, and Sensors give information about the lay-up as it was defined in the Modeling Ply Group. The changes as a result of geometric operations in the solid model are not reflected in these features. While cut-off plies still appear in the sampling point, these plies show zero stress and strain during postprocessing. Recomputation of ISS of interlaminar shear stresses only corrects the stresses of layered elements. The recomputation el ements. Homo-
genous elements (drop-off and cut-off elements) retain the interlaminar shear stresses of the .RST file. Cutting Operations Effect on Interface Layers
Interface elements intersecting with the cut-off geometry are deleted and not updated according to the new shapes of the adjacent bottom and top elements. Node Merge Operations on Composite Solid Model Assemblies
The use of node merge operations in Mechanical on composite solid models can lead to incorrect deformation results in ACP-Post deformation plots. When node merge operations are used, the Read (p. 210) 210) should should be active. Appropriate warnings Strains and Stresses option in the Solution Properties Properties (p. are issued.
3.8. Guide to Composite Visualizations There are several features available in ACP that t hat help in visualizing a composite model. Some features aid in the verification of the layup definition. Others provide an insight into the stresses, strains, and failures and can thus help in the optimization of a structure. This section aims to be a brief guide to the some of the available functionality.
3.8.1. Model Verification Two features are very useful for checking the layup definition before solving the model. One is the Orientation Visualization, the other is the Section Cut feature. The Orientation Visualization can display the direction and/or orientation of the elements, Oriented Manipulation ulation (p. (p. 22) 22) for for more information. Selection Sets, and plies. Refer to Scene Manip
After the whole definition of the lay-up, a visual verification of the lay-up sequence can be very useful. Section Cuts offer a useful visual check once the layup has been determined. By defining one or
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Guide to Composite Visualizations several Section Cuts, the ply position (number in the sequence) and orientation can easily be verified. Refer to Section C Cuts uts (p. (p. 156) 156) for for more information. Figure Figur e 3.38: T-Joint T-Joint Section Cut
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Composite Modeling Techniques Figure 3.39: Class40 Section Cut
3.8.2. Postprocessing Visualizations There are several features that can be used for viewing the results of a simulation. They all can give a different insight into the behavior of the composite structure. The different postprocessing visualizations mentioned below are also described in the last part of Tutorial of Tutorial 1. 1.
Deformation The deformation of a structure can be visualized with deformation plot for a specific solution (see Solution Plots (p. (p. 214) 214)).). The plot can be scaled by setting the deformation scale factor in the Solution Properties dialog.
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Guide to Composite Visualizations Figure 3.40: Activate Deformed Geometry in the Solution Properties Visualizations
Figure 3.41: Activate the Deformation Plot for Total Deformation
Failure Criteria The failure plot displays the critical safety factors (reserve factors, inverse reserve factors & margin of safety) to first ply failure for a given failure criteria definition. The safety factors are evaluated for every element and every layer and the critical value through the thickness of the layup is then projected on to the reference shell mesh. A failure plot for an envelope Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Composite Modeling Techniques solution works in the same way and is a display of the most critical failure of all included solution sets. Alternatively, the safety factors can be displayed ply-wise for each analysis ply. A failure criteria definition must be defined before creating a failure plot (see Definit Definitions ions (p. (p. 207) 207)).). A failure plot can be inserted under a normal solution or an envelope solution and the predefined failure criteria definition can be selected. Additionally, critical failure modes, critical plies and critical load case (in case of solution envelope) can be displayed as element labels. Figure 3.42: Activate the Failure Criteria Plot with Failure Mode and Critical Ply Information
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Guide to Composite Visualizations Figure 3.43: IRF Value and Text Plot for Each Element (Tutorial 1)
Figure 3.44: Zoom on Critical Area (Class 40)
Ply-Wise Results The structural behavior throughout the layup at each layer is i s of great interest in composite design. Ply-wise information helps to identify and optimize layers that are critical and ones that are not. All the solution plots except the deformation plot have the option of displaying results ply-by-ply (p. 214) 214)).). The plot will only display results if a ply is selected. Plies can be selected (see Solution Plots (p. in the Modeling Groups, Sampling Point, or Solid Model Analysis Plies. Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
Composite Modeling Techniques Figure 3.45: Activate the Ply-Wise Results in the Plot Properties
Figure 3.46: Select an Analysis Ply in the Modeling Groups or Sampling Points
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Guide to Composite Visualizations Figure 3.47: Ply-Wise Stress (Tutorial 1)
The Sampling P Points oints (p. (p. 154) 154) are are an alternative way of analyzing a layup on a ply level. A point of interest on the composite part is selected and its local layup is sampled. The feature can display failure criteria, stresses and strains through the thickness of the laminate. In this way, the Sampling Point gives a detailed insight into the laminate behavior ply-by-ply.
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Composite Modeling Techniques Figure 3.48: Stress Analysis for Selected Sampling Point
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3.9. Guide to Composite Failure Criteria ACP-Post provides a number of failure criteria for the strength assessment of composites. Both established and basic as well as recent and advanced failure criteria are included in the program. program. This section provides some guidance on the selection of failure criteria. • It is advised that you use failure criteria that distinguish between different failure modes (for example,
fiber failure or matrix failure).
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Element Choice in ACP • The use of all-inclusive quadratic failure criteria is not advised (for example, Tsai-Wu, Tsai-Hill, or Hoffman).
In most situations, these criteria are less accurate than others and provided minimal information on any failure. • It is more conservative to combine different failure criteria (Puck, Max Stress, and LaRC) than using any
single criterion. • In general, failure criteria that consider all in-plane stresses (s1, s2, s12) and the out-of-plane interlaminar
shear stresses (s13, s23) should be used, as these results are available in a shell model. • 3-D stresses (s3) can often be ignored in thin laminates with moderate curvature. Otherwise, Puck 3-D
can be used to investigate delamination. • 3-D solid models can be used to get more accurate results, especially if out-of-plane stresses are being
investigated. • Wrinkling and Core Failure should be evaluated for sandwich structures. • The use of Puck 2-D 2- D is recommended over the use of Puck Simplified.
Analysis (p. 357) 357) and and Postproce Postprocessing ssing (p. 233) 233).. A comprehensive comparFor more information, see Failure Failure Analysis ison of composite failure criteria was carried out in the worldwide failure exercise [ 38 (p. (p. 529 529)) ].
3.10. Element Choice in ACP This section describes the composite modeling techniques for the t he use of shell, solid, and solid-shell elements. 3.10.1. Introduction 3.10.2. Shell Elements 3.10.3. Solid Elements 3.10.4. Solid-shell Elements
3.10.1. Introduction The underlying principle of ACP is that a composite lay-up is defined on a shell geometry. The model of the lay-up that is passed from the ACP preprocessor to the solver can be a shell element mesh but also a solid or a solid shell element mesh. The solid model mesh is an extrusion of the shell element input mesh. If this input shell mesh uses linear elements (SHELL181 ( SHELL181)) the solid model mesh generated in ACP can have either layered solid elements (SOLID185 (SOLID185)) or layered solid shell elements (SOLSH190 ( SOLSH190).).
If it is quadratic (SHELL281 ( SHELL281)) the solid model mesh can only have quadratic layered solid elements (SOLID186). SOLID186). The geometry and loading of the engineering problem ultimately dictate what element type is best suited for the analysis. The following sections outline a few general considerations about the element types in ACP. For more detailed information, see Element Library Library in in the Mechanical APDL Theory Reference.
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3.10.2. Shell Elements Shell elements are suited for modeling thin-walled to moderately thick-walled structures. Shell elements are compliant in bending and give good deformation results while being computationally inexpensive.
3.10.3. Solid Elements Solid elements are aimed at modeling thick walled structures. As laminate thicknesses increase, outof-plane stresses become more significant; Solid elements are better at approximating these effects. Furthermore, layered solid elements allow the incorporation of composite parts in larger solid model assemblies. A shortcoming of these element types is that they are typically too stiff in bending when elements are thin. Displacements can be wrong by an order of magnitude as the elements undergo a phenomenon called locking. Element technologies such as Enhanced Strain Formulation try to remedy this numerical locking but are not sufficient to do so in linear 3-D solid elements. Quadratic solid elements (SOLID186) SOLID186) offer a better solution, however, this comes at an increased computational cost.
3.10.4. Solid-shell Elements Solid-shell elements cover the spectrum between shell and solid elements and are best suited for modeling thin to moderately thick structures. Thin solid-shell elements do not undergo locking and are able to give good results for out-of-plane stresses and strains.
3.11.Variable Material Data in Composite Analyses Composite modeling in Workbench provides the possibility to account for variability in the mechanical properties of composite materials due to any scalar user-defined user- defined quantity. Temperature, Shear Angle 278)),), and Degradation Factor are predefined variables in Workbench (defined through ACP-Pre draping (p. 278) Engineering Data to be used for refining a composite material's behavior. beh avior. You are free to define your own field variables. The following mechanical properties can be defined as variable: • Isotropic elasticity • Orthotropic elasticity • Orthotropic stress limits
• Orthotropic strains limits
Data.. Dependencies are specified in tabular form in Engineering Data An interpolation scheme is used to evaluate the locally effective properties given the local field variable states in the model. For information on how the interpolation scheme is controlled, see Variable Data Interpolation Interp olation Settings Settings (p. 303) 303).. Once the dependencies are defined in Engineering Data, they are accounted for in subsequent composite analyses and postprocessing. The Shear Value is defined by draping simulati simulation on in ACP-Pre, the TemperTemperature is computed or defined in Structural, Transient Thermal, or External Data systems. The state of all
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Variable Material Data in Composite Analyses other fields should be defined in ACP-Pre. The state of all other fields can be defined by means of Field Definitions in ACP-Pre or External Data systems. Variable material data is compatible with both shell and solid elements. An example analysis using variable material data is given in Analysis Using Variable Material Data (p. 320) 320)..
3.11.1. Element- or Layer-wise Field Definition You can specify the distribution of any variable used in the definition of a Variable Material in ACP. This is done by means mea ns of Look-up Tables. A scalar Look-up Table column can be associated with with a field variable. The state of the field variable is interpolated from the scalar s calar Look-up Table Table column over the finite element model. To this end, you you can specify whether this interpolation is applicable for the entire model or only specific parts of it. The field definition can be scoped to a co combination mbination of: • Element Sets • Oriented Selection Sets • Modeling Plies.
Element Sets or Oriented Selection Sets as scope of the field definition always affect all layers of their underlying finite elements. In contrast, scoping Modeling Plies refines the selection to specific layers of their underlying finite elements. The Field Definition then applies to the layers of the covered finite elements associated with the Analysis Plies of each Modeling Ply. Elements and layers not covered with a field variable definition assume the default value for this variable. Altogether, a Field Definition can be scoped to the full FE-model or refined to affect only subparts and, furthermore, only layers. See the Fiel Field d Definition Definition (p. 151) 151) for for additional information about the object as well as object set-up.
3.11.2. Draping Shear Ply draping on arbitrarily shaped surfaces leads to local shearing of the plies. This manufacturing-induced artifact can lead to significant deviation between the assumed and effective mechanical properties. This is because the shearing can be in the order of several degrees before ply wrinkling becomes an issue. Thus, the configuration of the composite can vary considerably from point to point, as can the mechanical properties.
In order to reflect the mechanical properties ’ dependence upon draping shear, ACP-Pre provides a draping simulation tool. Upon specifying shear-dependent material properties in Engineering Data (p. 278) 278) in in ACP-Pre for individual plies or Oriented Selection Sets, downstream and enabling draping draping (p. analysis systems take this effect into account. The draping shear angle is defined as: |draped_transverse_angle - draped_fiber_angle| - 90 Where "draped_fiber_angle" and "draped_transverse_angle" denote the angles of the draped fiber and transverse directions with wit h respect to the reference direction, respectively respectively.. Thus, a shear angle of 0 degrees indicates that the ply at the corresponding location is unsheared. Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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3.11.3. Degradation Factors Composite parts can exhibit a number of artifacts leading to local degradation of mechanical properties. Such flaws can be the result of a manufacturing process or can develop during operation. Examples of these types of flaws include voids, imperfect resin impregnation of fibers, deviation of the fiber alignment from the design angle, and resin traps. If such artifacts are known, you can account for them using degradation factors. The typical assumption is that a degradation factor of 1.0 indicates a sound material, while a degradation factor of 0.0 implies a disintegrated material. Degradation-dependent material properties can be specified in Engineering Data.. Data
3.11.3.1. Definition of the Degradation Factor Field The degradation factor fields are defined by means of a Field Definition Def inition object. If Degradation Factor Data for for the current composite analysis, has been used to define one of the materials in Engineering Data you can select it from the drop-down menu under Field Variable Name, as shown in the Figure below. The scope of applicability of this Field Field Definition is set under Scope Entities to a combination of Element Sets, Oriented Sets and Modeling Plies. are interpolated from the selected Look-upSelection Table Column upon update of theThe ACPdegradation system: for factors shell elements the field state values are evaluated at the element centroid taking into account the actual ply offsets if Include Shell Offset is activated; for solid elements the actual ply position is always considered and this behavior cannot be changed. All downstream analysis systems will make use of the information provided for the Degradation Factor in the Field Definition object. Figure 3.49: Field Definition Properties to Set Up a Degradation Factor Field
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Variable Material Data in Composite Analyses
3.11.4. Definition of General User-Defined Fields in ACP-Pre The Engineering Data enables you to define Isotropic and Orthotropic Elasticity as well as Stress and Strain limits as a function of up to nine user-defined scalar field variables. Engineering Data pre-defines Temperature, Temp erature, Degradation Factor and Shear Angle fields. If necessary, you can add a custom field variables. From within ACP, the custom field variables have to be defined as described by Field Definition Definiti on Object Properties Properties (p. 151) 151) for for Element- or Layer-wise definitions. From the Workbench-level, External Data components can be used to define custom field variables. Please note, however, that External Data components do not permit layer-wise field definitions.
3.11.5.V 3.11.5. Variable Data Interpolation Settings The interpolation algorithm and its settings can be controlled from Workbench Engineering Data. For details of the interpolation schemes available and settings of the interpolation engine, see General Interpolation Interp olation Library Library (p. 387) 387)..
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Chapter 4: Example Analyses The following examples demonstrate some of the most commonly used features of ACP: Analysis of a Composite Shell Model 4.1. Analysis 4.2. Analysis Analysis of a Composite Solid Model 4.3. Analysis Using Variable Material Data 4.4. Analysis Analysis of a Mapped Composite Solid Model 4.5. Shear Dependent Materials in Composite Analysis 4.6. 3D Ply Workflow – Imported Plies
4.1. Analysis Analysis of a Composite Shell Model The tutorials 1 & 2 (Introduction) Introduction) give a good insight into the ACP ACP functionality. While the tutorials always start with an existing model this section outlines the generic build-up of a composite shell model. Selected steps are explained in more detail below and highlighted with a link. • Preprocessing
(Pre) re) component to the project (p. (p. 306) – Add ACP (P Engineering Data Data (p. 307) – Define Engineering – Import or construct construct Geometry (Units) (Units) (p. 309) – Open the Model and →
Selections/Element Define Named Selections/Elem ent Sets (p. 309)
→
Generate Mesh
(Pre) (p. 309) 309) and – Open ACP (Pre) →
Define Fabric
→
Define Rosettes and Oriented Selection Sets
→
Create Modeling Plies
• Workbench Analysis System
(p. 310) – Add Analysis System to the project (p. – Open the Analysis System and →
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Example Analyses
→
Define Boundary Conditions
– Solve model (update the project) • Postprocessing – Add ACP (Post) (p. 311) (Post) component to the project (p. – Open ACP (Post) and run the post-processing
4.1.1. Preprocessing The steps involved in pre-processing are described in the sections below: 4.1.1.1.Workbench Workbench Integration Integration 4.1.1.1. 4.1.1.2. Adding ACP Components to the Project 4.1.1.3. Engineering Data 4.1.1.4. Properties 4.1.1.5. Geometry and Units 4.1.1.6. Named Selections and Elements/Edge Sets 4.1.1.7. Starting and Running ACP
4.1.1.1.Wo 4.1.1.1. Workbench rkbench Integr Integration ation The Workbench Add-in of ACP installs two additional Component Systems to the Workbench Toolbox: Toolbox: ACP (Pre) and a nd ACP (Post). These systems allow transferring the composite definitions of ACP between ACP and Mechanical on the Workbench schematic level. ACP is now fully integrated in the data structure of ANSYS Workbench and the update and refresh logic. It is important that the user updates (refresh) the upstream data to pass the modifications to the ACP components. The update symbols can be used to check the up-to-date status of each component.
4.1.1.2. Adding ACP Components to the Project The components ACP (Pre) ( Pre) and an d ACP (Post) are available in the Toolbox menu. Figure 4.1: ACP Components
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Analysis of a Composite Shell Model These components are handled in the Project Schematic like the other standard components (dragand-drop or right mouse-click menu).
4.1.1.3. Engineering Data With the installation of ACP a new material catalog named Composite Materials is available in the databank. This catalog contains contains typical materials used in composite structures like unidirectional and woven carbon and glass, glas s, or core core materials. Within the Workbench workflow of ACP, ACP, the materials have to be defined in Engineering Data and not in ACP (Pre). Figure 4.2: Engineering Data Sources
Figure 4.3: Outline of Composite Materials
4.1.1.4. Properties To To fulfill the ACP requirements, requi rements, the materials in ANSYS Workbench have some additional properties which are highlighted below.
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Example Analyses Figure 4.4: Material Properties for ACP
The new properties are: • Ply Type: Physical behavior of the material like core, unidirectional or woven ply. • Strengths:
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– Orthotropic Stress Limits – Orthotropic Strain Limits – Isotropic Strain Limits • Composite Failure Parameters: – Tsai-Wu Constants – Puck Constants
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Analysis of a Composite Shell Model – LaRc03/04 Constants – Additional Puck Constants – Woven Specification for Puck.
(p. 64) 64).. More information about the ACP material definitions are described in Section Material Data (p.
4.1.1.5. Geometry and Units A shell geometry is required for building any composite model in ACP. ACP. The geometry can either be constructed in the ANSYS Design Modeler or imported as a CAD file. The ACP unit system is independent from the unit system in the Mechanical application (User Interface or Solver). The transfer from the Mechanical application to ACP and vice versa automatically converts the data. The current unit system is displayed in the status bar of ACP at the bottom of the screen.
4.1.1.6. Named Selections and Elements/Edge Sets Named Selections based on bodies, surfaces and edges defined in the Design Modeler or the Mechanical application are transferred to ACP as Element Set and Edge Set, respectively. respectively. They are necessary for building a composite model.
4.1.1.7. Starting and Running ACP First, an ACP (Pre) component has to be defined in the Workbench project. Double-click on Setup to open ACP (Pre). You ccan an also use the context menu and select s elect Edit, or run a Python script in which the ACP commands are included, from the context menu. After defining the composite data in ACP (Pre), the user can return to the Workbench Project to proceed. The ACP data is saved with Save in the Workbench Project or any other Save Project command in the different components.
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Example Analyses Figure 4.5: Context Menu of ACP (Pre) Setup
4.1.2. 4.1.2.W Workbench Analysis System The Workbench analysis system is described in the sections below: 4.1.2.1. Adding an Analysis System to the Project
4.1.2.1. Adding an Analysis System to the Project The ACP components are handled in the Workbench project schematic like any other standard components. The components can be connected by drag-and-drop operations or using the context menu. The Mesh, Engineering Data, Named Named Selections and Coordinate Systems are transferred to the Analysis System. Figure 4.6: Connecting a Static Structural Analysis to ACP (Pre) using a Drag and Drop Operation
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Analysis of a Composite Shell Model
4.1.3. Postprocessing Postprocessing the analysis is described in the following sections: 4.1.3.1. Adding an ACP (Post) Component to the Project
4.1.3.1. Adding an ACP (Post) Component to the Project The ACP (Post) component can be linked to one or several solutions and allows postprocessing of composite shell and solid structures. As ACP (Post) is linked with the Engineering Data, Geometry, and the Model of the ACP (Pre) component, the composite definitions (Section Data) are transferred to ACP (Post) automatically. As before, the ACP (Post) component can be added to the project by a drag and drop operation. Pick the ACP (Post) component from the toolbar and drop it on the Model cell of the ACP (Pre) analysis system. Figure 4.7: Adding ACP (Post) by Drag and Drop Operation
In the second step, one or several solutions can be linked to the ACP (Post) component by dragging and dropping the Solution cell into the Result cell of ACP (Post).
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Example Analyses Figure 4.8: Linking a Solution with ACP (Post)
The complete composite shell model is now ready to be analyzed in ACP (Post). ( Post). Figure 4.9: Complete Composite Shell Analysis Model
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4.2. Analysis of a Composite Solid Model In the case of thick composites, the layered shell theory can cause significant errors in the obtained results. In some cases, it is necessary to work with 3D models - also referred to as Solid Models. ACP has the unique feature to generate layered solid models based on the shell layup definitions. ACP generates layered solid elements based on the shell mesh and the ACP Composite Definitions thus representing one-to-one the composite part. Drop-offs, staggering and tapering are also considered. In addition, the Solid Model extrusion allows to define extrusion directions and boundary curves.
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Analysis of a Composite Solid Model In this section, the workflow of modeling a composite solid is outlined as it differs to some extent from shell modeling. Selected steps that differ from shell modeling are explained in more detail below and highlighted with a link. • Preprocessing – Add ACP (Pre) component to the project – Define Engineering Data – Import or construct Geometry – Open the Model and →
Define Named Selections/Element Sets
→
Generate Mesh
– Open ACP (Pre) and →
Define Fabric
→
Define Rosettes and Oriented Selection Sets
→
Create Modeling Plies
→
Create (p. 314) Create Solid Model (p.
• Workbench Analysis System
System m (WB ( WB Mechanical/Mechanic Mechanical/Mechanical al APDL) (p. 314) – Choose an Analysis Syste (p. 315) – Add Analysis System to the project (p. – Add other systems systems (p. (p. 318) – Open the Analysis System and →
Define Analysis Settings
→
Define Boundary Conditions
– Solve model • Postprocessing – Post-process complete assembly (p. 318) – Add ACP (Post) (p. 318) (Post) component to the project (p. – Open ACP (Post) and run the post-processing for composite parts
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Example Analyses
4.2.1. Preprocessing Creating a Solid Model The generation of a layered solid s olid element model has to be configured in ACP with the Solid Model Models odels (p. (p. 163) 163).. feature. See the usage references for details on Solid M In the ACP solid model export settings, the user has to set an individual NUMOFF to avoid node and element numbering conflicts between multiple models (see section Properties Properties (p. (p. 164) 164) for for more details). Further, it is recommended to use homogenized drop-off elements with a global drop-off material 164)).). (for more information see General (p. 164) Element sets and edge sets can be transferred from ACP (Pre) to the Static Structural component where they appear as named selections. Named Selections from the Mechanical Model are also (p. 164) 164) for for more transferred. This aids the definition of boundary conditions (See section Properties Properties (p. information).
4.2.2.W Workbench Analysis System 4.2.2. Within ANSYS workbench, there are two ways to analyze composite solid models. On the one hand the analysis can be done in Workbench Mechanical, on the other hand it can be carried out in Mechanical APDL (ANSYS Classic). The functionality is identical, the user interface is very different however. Alternatively, the composite solid models can be exported from ACP for processing outside of ANSYS.
Analysis with Mechanical The composite layered solid element model appears in Mechanical as a meshed body. Any other bodies in the ACP (Pre) component component are not carried forward. The user can define loads, boundary conditions and connections to other parts in the usual Mechanical fashion. An example of such a solid model workflow is shown below: Figure 4.10: Workbench Workflow for Composite Solid Modeling with Mechanical
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Analysis of a Composite Solid Model
Analysis with Mechanical APDL A further option is to link solid models to a Mechanical APDL where the boundary conditions and loads are defined. Typically Typically,, an APDL script is used to set boundary conditions and analysis settings for a workflow with Mechanical APDL. An example of a solid model workflow with Mechanical APDL is shown below: Figure 4.11: Workbench Workflow for Composite Solid Modeling with Mechanical APDL
Adding an ACP (Pre) Component to the Project The solid modeling workflow in ANSYS allows the assembly of many pre-processing components into one Analysis System. In some cases, it may be desirable to analyze thick-walled composites in isolation but, often enough, it is of interest to see the interaction between multiple bodies. The connection procedure is explained with the help of two examples for both analysis methods (WB Mechanical and Mechanical APDL).
Link with Workbench Mechanical The procedure for building an analysis model is illustrated with a Static Structural Analysis System as an example. A composite tube connected to two metal inserts is subjected to torsion. A project schematic is shown below:
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Example Analyses Figure 4.12: Analysis of a Composite Tube with Metal Inserts Modeled with Mechanical
In the case of this example, the geometry consists of one shell and two metal inserts. The link between ACP (Pre) (B5) and the Static Structural (C2) only transfers the generated layered solid element model. The link between the Mechanical (F4) and the Static Structural (C2)parts transfers all active As such, the shell geometry has toModel be suppressed. Consequently, all three appear as solidbodies. bodies in the Static Structural (C2) component. The connections, boundary conditions and all other preprocessing definitions can be defined in the Setup (C3) in the usual fashion. The global solution can be determined and analyzed in Workbench Mechanical while the composite component can be analyzed in detail in ACP (Post) (D5). Figure 4.13: Suppressed Shell in Mechanical Model
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Analysis of a Composite Solid Model Figure 4.14: Assembly of Composite and Metal Solids
Link with Mechanical APDL Two composite components serve as an example for the Mechanical APDL workflow workfl ow procedure - a plate and a t-joint. A project schematic is shown below: Figure 4.15: Analysis of Composite Plate and T-joint Modeled with Mechanical APDL
The sequence of connecting the system is to always connect an ACP (Pre) component first. In this case, it is not important because both inputs are ACP (Pre) solid models. In the Mechanical APDL component the boundary conditions, loads and all other pre-processing definitions can be defined throughinAPDL macros. These macros can be linked with the Mechanical APDL cell which will be integrated the automatic update functionality of Workbench. A macro file can be added to the component through the right click menu (see figure below). Add Input File... appends the APDL running sequence with an additional macro. Check the order of the files of the Mechanical APDL component. The macros should be listed after the Solid Model Pr Process ocess Setup file(s).
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Example Analyses Figure 4.16: Add Reference File
Figure 4.17: List of Used Files and Their Order in Mechanical APDL
Multiple Parts (Adding Other Systems) It is possible to add multiple components to one Analysis System. Two composite composite parts or a composite part connected to two isotropic parts, for example.
4.2.3. Postprocessing Global Postprocessing In general, the global solution of all parts can be viewed in Workbench Mechanical or in Mechanical APDL. Analyzing the results of a multi-part assembly is not possible in ACP (Post) for Solid Models.
Adding an ACP (Post) Component to the Project The post-processing functionality for Solid Models of ACP allows the mapping of ply wise results on to the reference surface of the solid model. This ensures that also failures occurring inside the laminate
can be observed and investigated. The connection between an Analysis System and ACP (Post) ( Post) always requires the same two steps regardless of whether the Analysis System is Workbench Mechanical or Mechanical APDL. First of all, the ACP (Post) system has to be associated with an ACP (Pre) system. Subsequently, a solution from an Analysis System can be linked with the ACP (Post) (Post) Results. There are other ways of of connecting ACP (Post) with an Analysis System yet they all fall short when it comes to linking the Analysis Solution cell with the ACP (Post) Results cell. This is a known limitation of the W Workbench orkbench integration.
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Analysis of a Composite Solid Model Figure 4.18: Step 1: Drag and Drop an ACP (Post) System on to an ACP (Pre) System
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Example Analyses Figure 4.19: Step 2: Drag and Drop the Static Structural Solution Cell into the ACP (Post) Results Cell
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When multiple ACP (Pre) solid model systems are linked to an Analysis System then every ACP (Pre) system has to have a corresponding ACP (Post) system. See Figure 4.15: Analysis of Composite Plate and T-joint T-joint Modeled with Mechanical APDL APDL (p. 317) 317) for for an example workflow.
4.3. Analysis Using Variable Variable Material Data This simple example of a race car nose and wing demonstrates a possible workflow for composite analyses using variable material data, ACP draping draping simulation, and temperature dependence. Variable
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Analysis Using Variable Material Data material data is used to simulate incomplete curing of the composite material in the model. Note that the wing geometry, composite lay-up, and material data are fictitious and are not to be used in any real world analysis or application. The following figure shows the Workbench setup. Cell D (External Data) contains the results of a Fluent analysis which provides the surface pressure distribution the race andE wing. TheData) composite lay-up, draping, and incomplete curing field are defined inonACP-Pre incar Cellnose A. Cell (External defines the temperature field. The structural effect of the airflow around the race car nose and wing are analyzed in Cell B (Static Structural). Cell C (ACP-Post) contains the failure analysis of the composite race car nose and wing. file.. The model used in this example analysis is available by downloading this file A general overview of the use of variable material data can be found in Variable Material Data in Composite Analyses Analyses (p. (p. 300) 300).. Figure 4.20: Race Car Workbench Setup
4.3.1.Workbench Engineering Data: Setup Variable Data Variable data for composite composite materials are configured in Engineering Data. The following properties can be functions of up to 9 field variables: • Density • Elasticity parameters
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Example Analyses • Stress limits • Strain limits
Temperature, Temp erature, Shear Angles and Degradation Factor are predefined field variables. User-defined field variables created. In this example, the effect of incomplete across the is modeled.can As aalso firstbe step, the field variable is definedcuring and specified asparts dimensionless. Incomplete Curing A value of 1.0 indicates perfect curing while a value of 0.0 indicates that no curing took place. Figure 4.21: Predefined and User-Defined Field Variables in Engineering Data
In the next step, the field variables are assigned to the material properties. Make the elasticity parameters of the Epoxy_Carbon_Woven_230GPa_Prepreg material a function of Temperature , Shear Angle, and Incomplete Curing. To accomplish this, select the material and then select the Orthotropic Elasticity property. Double-clicking a field variable assigns it to the Orthotropic Elasticity property. Fill the table for the Orthotropic Elasticity property by manually entering values or by importing a CSV file.. file Figure 4.22: Assigning a Field Variable to Material Property
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Analysis Using Variable Material Data Figure 4.23: Populating the Tabular Material using the CSV Interface
During finite element computations and postprocessing, the effective material properties are interpolated from these tables based on the local field variables state. The interpolation scheme can be controlled when selecting Interpolation Interpolation Options Options (p. 388) 388).. When selecting the Material Field Variables Variables property, the unit, default data, lower, lower, and upper limit can be set. The software suggests program controlled values for some of the options. options. The default data defines the assumed state of the field variable, if it is not specified in the model. In this way, you can have full material specifications in Engineering Data, but only use a subset of the specified dependencies during the simulation. For more details, see ACP-Pre: Define Fields for Shear Angle, Degradation Factor, Factor, and User-Defined Field Variables Variables (p. 324) 324)..
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Example Analyses Figure 4.24: Setting Interpolation Options
4.3.2. ACP-Pre: Define Fields for Shear Angle, Ang le, Degradation Factor, and UserDefined Field Variables ACP-Pre provides the ability to set up fields for Shear Angle (draping), Degradation Factor, and all user-defined field variables for a complete composite model. The Shear Angle can be defined as a result of ACP draping simulation or imported via look-up tables (p. (p. 94) 94).. Degradation Factor and userdefined field variables can be defined per shell or solid element as an interpolation result from a scalar look-up table column. For example, you can define the state of a field variable at various spatial (p. 94) 94).. By creating a Field De Definition finition (p. (p. 151) positions in a .CSV file and import it as a 3-D look-up table (p. object in ACP-Pre, you can assign the imported scalar look-up table column to the field variables
previously specified in Engineering Data and scope them to part of your model, even to single Mod 301) section. eling Plies. See the Element- or Layer-wise Layer-wise Field Definition (p. 301) The application automatically considers the result of the draping simulation when evaluating the effective material properties in downstream analyses and postprocessing.
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Analysis Using Variable Material Data Figure 4.25: Draping Results
Use look-up tables to define scalar fields on composite models. The interpolation result from the lookup tables can be visualized using Scalar Look-up Table plots and the Field Definition objects in turn can be visualized using Field Definition plots. The following figure shows Curing Degr Degree ee over the race car nose and front wing (upside down).
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Example Analyses Figure 4.26: Curing Degree Plot
To activate a 3D look-up table as the Curing Degree field, you need to assign it in the ACP-Pre by setting up a respective Field Definition. Note that you must maintain unit consistency between the Look-up Table column values and the active unit system in Mechanical (units of the look-up table column are not converted to the active unit system). See the Field Field Definitions (p. (p. 151) 151) section section for additional details. The following figure shows this process: Figure 4.27: Activating a Look-up Table to Define Curing per Modeling Ply (layer-wise)
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Analysis Using Variable Material Data
4.3.3. Mechanical,Thermal Loading, and External Data Thermal loading through the Temperature field fiel d variable can be accomplish by: • Transient Thermal analysis • External Data analysis component in Workbench • Setting the environmental or part temperature directly in Mechanical
The resolution of the temperature field is per element node. Figure 4.28: Using External Data to Define Temperature Field
4.3.4. ACP-Post: Analysis Effect of Variable Data Stress and strain limits can be defined in Engineering Data as a function of field variables. These dependencies are fully reflected in ACP-Post when evaluating respective failure criteria. The following figure shows inverse reserve factor plots of combined Maximum Stess, Hashin, Face Sheet Wrinkling, and Core Failure failure criteria. The structure is viewed from the bottom. On the left is the result with constant material properties, and on the right the effect of Temperature, Shear Angle, and Incomplete Curing is shown. The color bar ranges are the same. The maximum IRF is about
18% higher on the right.
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Example Analyses Figure 4.29: Inverse Reserve Factor
4.4. Analysis of a Mapped Composite Solid Model In the case of thick composites, the layered shell theory can cause significant errors in the obtained results. In some cases, it is necessary to work with 3D models, also referred to as Solid Models. ACP has the feature to map the ACP Composite Definitions onto external solid meshes. In this section, the workflow of modeling mapped composite solid meshes is outlined. To a large extent solid lid model (p. (p. 312) 312),, except there are two main differences: the workflow is the same as that of a standard so • The solid mesh is imported via Mechanical Model and not generated in ACP (Pre) itself. See Solid
Modeling Modelin g (p. (p. 43) 43).. tool.. • The composite post-processing is only available in Mechanical Model via the composite failure tool An exemplary complete workflow contains these steps: 1. Pre-Processing: Define the Composite Definitions in ACP (Pre) as described in the Analysis of a Composite Compo site Solid Model (p. (p. 312) 312) section. 2. Mapping of the Composite Definitions: Import the external volume mesh and configure the Imported Solid Model object in ACP (Pre).
3. Analysis: Transfer the solid composite data to a downstream downstream analysis (p. (p. 314) 314) (structural, (structural, modal, etc.). 4. Post-Processing: run the composite failure analysis for the composite structures in Mechanical. This example examines how a full cross-section composite spring can be modeled with the approach of mapping Composite from ACP an that existing mesh. Youthis cancapability get the Workbench archive for this exampleDefinitions by downloading file. Aonto this (Pre) file. video demonstrates can be found here. here.
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Analysis of a Mapped Composite Solid Model Figure 4.30: Full Cross-Section Composite Spring
Note: This example assumes that you have properly completed your composite definitions. The example begins by creating the external solid mesh and transferring it to ACP Pre.
4.4.1. Import External Solid Mesh In the case of this example, the geometry was imported via DM (System E) and passed to Mechanical. The geometry contains both the molding surface that is used to specify the Composite Definitions in the ACP (Pre) (System C) and the volume of the composite spring that is used to generated the solid mesh in Mechanical (System F).
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Example Analyses Figure 4.31: Complete Workbench Project Schematic
The geometry is passed to Mechanical Model F5. Since only the volume is used in System F, the shell geometry is suppressed in Mechanical.
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Analysis of a Mapped Composite Solid Model A cross section view of the composite spring shows the layup of the composite spring. It contains 3 sections: ±45 layers, core and a roving in the center of the section. Figure 4.32: Layup of the Composite Spring
The layup mapping algorithm in ACP (Pre) is currently designed for structured meshes where degenerated elements can be filled with an orthotropic material. Therefore, the solid mesh that gets layup data from ACP (Pre) (Pre) should mainly consist of structured elements (hex). The approach here is to generate a structured mesh for the two outer sections (±45 layers and core). In this example, the inflation and sweep mesh options are used to get the appropriate appropriate mesh. The inflation feature allows us the define the total thickness of the inflation layers and therefore indirectly defines the radius of the roving section. With this approach the roving roving section is not a strict structured mesh. This does not matter because we will use the filler option of the Imported Solid Model feature to define the material and orientations of this section. Figure 4.33: Mesh Features and Solid Mesh with the Inflation Layers and Roving Cross Section
In the next step the solid mesh is passed to the ACP (Pre) system by transferring F4 to C5.
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4.4.2. Layup Mapping An Imported Solid Model object is automatically generated in ACP (Pre) as soon as a Mechanical Model is linked to an ACP Setup component. The file format, unit system and file path are automatically set and cannot be changed. First the scope of the layup mapping has to be defined where the scope distinguish between elements and plies. In that case here we select all elements (element set All_Elements). As mentioned above, we map only the ±45 and core core plies onto the external solid mesh. Thus we deselect `All Plies` and select the Modeling Group `Laminate` that contains the ±45 and core plies.
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Analysis of a Mapped Composite Solid Model
The remaining elements are filled with carbon roving and the orientations of these elements are defined by two edge-wise rosettes as shown below. below. The result of the mapping is shown in the figur figures es below. The first figure shows the solid elements of the ±45 and core core plies and the second figure the filler elements and their fiber directions.
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Example Analyses
Figure 4.34: Selection of the ±45° and Core Plies
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Analysis of a Mapped Composite Solid Model Figure 4.35: Filler Elements and Fiber Directions
4.4.3. Analysis of A Mapped Composite Model The Imported Solid Mesh is passed to a structural system to analyze the nonlinear compression of the composite spring. Solid meshes with mapped Composite Definitions can only be post-processed in Mechanical. For that, a Composite Failure Tool is Tool is set up to address the different material types (woven and UD fabrics and core materials). This can be achieved by selecting the Max Stress, Puck and Core Shear failure criteria.
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Example Analyses Figure 4.36: Composite Failure Analysis in Mechanical that Shows the Maximum Failure per Element
4.5. Shear Dependent Materials in Composite Analysis This example demonstrates a possible workflow for composite analyses using homogenized material data (with shear dependency) dependenc y) for a woven composite provided by Material Designer Designer.. To this end, a simple model consisting of an inflated half-sphere is considered. The effect of ACP draping simulation combined with shear-dependent material properties will be shown. The following figure shows the Workbench setup. The material data of a Carbon/Epoxy woven fabric are computed by Material Designer (Cells A and B) as illustrated in the Material Designer Woven Composite Tutorial. The composite lay-up and draping options are defined in ACP-Pre (Cell C). Finally, Finally, the structural effect of an internal pressure load is analyzed in Cell D (Static Structural). Figure Figur e 4.37: Workbench Workbench Project Project Setup
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If desired, you can download the download the model used in this example analysis and perform the steps yourself.
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Shear Dependent Materials in Composite Analysis
Homogenized Material Data Following the Material Designer Woven Composite Tutorial, Tutorial, we generate homogenized material data for a Carbon/Epoxy woven fabric. In particular, we use an RVE whose material directions are aligned with the yarns bisectors, so that the resulting homogenized material remains orthotropic in presence of shear (see Fabric Fabric Fiber Fiber Angle (p. 68) 68) in in the Material Designer User's Guide). Guide). Figure 4.38: Woven Woven RVE defined defined in Material Designer
We set up two analyses in Material Designer (Cell B in the Workbench project): a constant material analysis and a variable one with a shear angle between -30° and 30° as parameter. parameter. The resulting materials are then transferred to the Engineering Data component of the ACP system. Figure 4.39: Materials in the Engineering Data Component of the ACP system
Note that the constant material has a constant Fabric Fiber Angle equal to 45°, while the variable material has a shear dependent Fabric Fiber Angle.
Figure 4.40: Shear Dependent Fabric Fiber Angle
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Example Analyses
Fibers and Material 1 Directions in ACP In ACP, we define a ply with a variable woven fabric and a ply angle of 0°. Figure 4.41: Ply Definition
The effect of the Fabric Fiber Angle property can be highlighted by comparing the ply fiber directions with the material 1 direction. Figure 4.42: Fiber (Light Green), Transverse Transverse (Dark Green) and Material 1 (Red) Directions
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The material 1 direction identifies the direction in which the material properties are specified. However, However, the fiber direction is still the nominal modeling direction in ACP, that is, the Ply Angle still defines the orientation of the fibers with respect to the reference direction.
Draping The Shear Angle can be defined as a result of ACP draping simulation (see Draping Draping (p. (p. 278) 278)).).
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Shear Dependent Materials in Composite Analysis You can enable the Internal Draping algorithm in the Draping tab of the Modeling Modeling Ply Properties Properties (p. 127) dialog. Figure 4.43: Draping Definition
Figure 4.44: ACP Draping Mesh
You can plot the local ply shear value due to draping using an Angle Plot Plot (p. (p. 196) 196) with with Draped Shear Angle as component.
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Example Analyses Figure 4.45: Shear Angle Plot
In addition, you can further investigate the shearing effect due to draping by plotting the draped fiber and transverse directions, as well as the material 1 direction. Figure 4.46: Draped Fiber Direction (Light Blue), Draped Transverse Direction (Blue) and Material 1 Direction (Red)
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Plot of Shear Dependent Material Properties The application automatically considers the result of the draping simulation when evaluating the effective material properties in downstream analyses and postprocessing. In ACP, you can plot the effective material properties (for example, the Young's modulus) as a function of the Shear Angle using Material Plott (p. 219 Plo 219)).
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Shear Dependent Materials in Composite Analysis Figure 4.47: Shear-Dependent Young's Modulus
Analysis The composite model is passed to a structural system to analyze the effect of a uniform pressure load. It is worth comparing the result with the one obtained considering a constant material and no draping: in the latter case the maximum deformation is underestimated by more than 30%.
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Example Analyses Figure 4.48: Deformation Plot (variable material on left, constant material on right)
4.6. 3D Ply Workflow – Imported Plies Many different manufacturing processes are available to build composite structures. Traditional processes are mainly used to fabricate thin or moderately thick laminated structures which can be modeled based on a reference surface, also called a mold surface. In ACP Pre, this is covered by the Oriented Selection Set (p. (p. 118 118)) and Modeling Ply (p. 127) 127)features. features. New and alternative processes, such as 3D printing and winding, can produce thick and complex structures. In such cases the approach of building the entire laminate on only one reference surface (p. 146) 146) feature feature often proves unfeasible or results in an inaccurate model. The Imported Imported Modeling Ply (p. allows you to model laminated structures independent of a reference surface, where the geometrical information (ply extent and so on) is imported from an external source. The lay-up mapping capability, capability,
which is part of the Imported Imported Solid Model (p. (p. 189) 189),, is then used to map the Imported Modeling Plies (3D plies) onto a solid mesh. You can employ this workflow in combination with thermal and structural analyses such as linear, transient, or explicit for example.
4.6.1. Inputs The 3D Ply Workflow requires two additional inputs, compared to the standard workflow. One is is a finite element mesh of the solid that represents the 3D composite part, and the other is the 3D representation of the lay-up. The figure below shows how their data can be transferred to ACP Pre. In this example, the solid geometry is meshed in ANSYS SpaceClaim by using block meshing (see A3). The solid mesh is then transferred to ACP Pre-Setup by linking the ANSYS Mechanical model (the A4B5 link). Another option option is to mesh the solid geometry in Mechanical. You can import meshes from
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3D Ply Workflow – Imported Plies third party applications (such as HyperMesh) via an external model. Note: Named Selections (NS) of the finite element mesh of the solid get transferred to the downstream systems. These Named Selections can be used to define boundary conditions, contacts, and so on, to make the model associative. Figure 4.49: 3D Ply Workflow (Courtesy of 9T Labs)
There are two ways to create the 3D ply representations in ACP Pre. Option A: By geometry. Or option Composite posite CAE (p. (p. 241) 241) in in ACP Pre. B: By loading an HDF5 Com C AD faces and are transferred to ACP Pre by linking Option A: The ply surfaces are represented by CAD one or more geometrical components with ACP Pre (see D2-B5). All the additional information, such as fiber directions and material, can be defined in ACP Pre using the standard ACP features- such as Fabrics, Rosettes, and so on. Option B: This option allows you to import ply definitions from a third-party application. The HDF5
Composite CAE file includes all the information of a layered composite, so the imported ply objects, their fiber directions, and their thicknesses are created automatically on import. Currently, many CAE applications support the HDF5 Composite CAE. Contact your ANSYS Support Team for further information about this format. The figure below shows you you how an HDF5 Composite CAE is loaded using the context menu of the ACP model.
Figure 4.50: HDF5 Composite CAE Imported as 3D Plies (Imported Modeling Plies)
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Example Analyses
4.6.2. Example of Use - HDF5 Composite CAE The following example has been provided by 9T Labs (https://www.9tlabs.com/) who (https://www.9tlabs.com/) who automates and digitizes composite manufacturing. It shows how a 3D printed composite structure, designed with Fibrify,, can be imported into ANSYS Workbench/ACP for simulation. This workflow allows you to import Fibrify a 3D composite lay-up definition and convert it into a solid FE model with minimal effort. You can download the Workbench project archive here. here. You will find the required HDF5 Composite CAE file in the following location: user_files\200401_Rocker_PA_print_2NEW.hdf5cc The model is already fully configured, and the description below highlights the most important steps. Figure 4.51: 3D Printing with Endless Fiber Reinforcement and F Final inal Part (Courtesy of 9T Labs)
The following figure shows the Workbench project schematic. The 3D geometry of the printed composite part (shown above) is loaded into system A (Solid Mesh) and meshed in SpaceClaim. Three Named Selections are defined in Model A4 which are used to define the forces and supports later in the analysis system system C3. This is important if you want to have an associ associative ative model. The material material properties (such as stiffness and strengths) are defined in the Engineering Data component (B2) of the ACP Pre system. The solidSolid meshModel is transferred to ACP Pre by linking Model A4 with ACP Setup B5 which results in an Imported in ACP Pre. Figure 4.52: Simulation of a 3D Printed Composite (Courtesy of 9T Labs)
At this point, only a few mouse-clicks are needed in ACP Pre to load the 3D plies and to configure the mapping. You can perform the import using the context menu of the ACP Model as shown above Modelin g Plies) (p. 343) 343)).). The imported (Figure 4.50: HDF5 Composite CAE Imported as 3D Plies (Imported Modeling plies are accessible in the object tree and are displayed when selected. To see the Fiber Directions and other properties, enable the options in the display ’s toolbar. Of course, the input data can be modified as well if needed.
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3D Ply Workflow – Imported Plies
The solid mesh on which the plies are mapped is already available (mesh transfer from A4-B5). The mapping algorithm must be switched over to Imported Plies (3D plies) by enabling the Use Imported Plies option in the Imported Solid Model Property Dialog. By default, all plies are mapped and the result can be verified by selecting the plies of the solid model. The figure below shows a few few plies which are visualized and select the plies.) on the solid mesh. (Enable the Show on Solid option
in the display toolbar
You now transfer theassolid mesh downstream for workflow many different of analyses, such as of a a staticcan structural analysis shown in System C in the abovetypes ( Figure 4.52: Simulation 3D Printed Composite (Courtesy of 9T Labs) (p. 344) 344)).). After solving the analysis, you can employ the Composite Failure Tool to Tool to predict the safety margin of the composite part. As an example, the figure below shows the maximum Inverse Reserve Factor per element. Of course, you can easily generate ply-wise plots for a more detailed assessment.
Figure 4.53: Distribution of the Inverse Reserve Factors in the Mapped Composite Solid Model
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Chapter 5:Theory Documentation The theory chapter consists of the following sections: 5.1. Draping Simulation 5.2. Interlaminar Stresses 5.3. Failure Analysis 5.4. Classical Laminate Theory 5.5. General Interpolation Library 5.6. Nomenclature
5.1. Draping Simulation Draping simulation is explained in the following sections: 5.1.1. Introduction 5.1.2. Draping Procedure 5.1.3.Thickness Correction 5.1.4. Limitations Limitations of Draping Simulations
5.1.1. Introduction Layered composite structures are typically formed by placing reinforced plies against a mold surface in desired orientations. In the case of flat and singly curved surfaces, the orientation of the ply stays practically unchanged over the whole application area. When it comes to doubly curved surfaces, a ply can follow the surface only by deforming. In particular, dry and pre-impregnated woven fabrics can adapt to the shape of a doubly curved surface without use of excessive force. Deformation occurs with in-plane shear and up to a certain deformation level the shear stiffness of a fabric is insignificantly p. 527 527)) ]). small ([ 2 ((p.
When a ply deforms by shearing to follow the surface, the fiber orientation changes. Different approaches have been developed for the simulation of the draping process [ 3 (p. (p. 527 527)) ]. The need need for for draping simulation is twofold. First, the manufacturability of the composite product can be assessed. Areas where the reinforcement cannot follow the surface are indicated and hence measures can be taken in design to avoid this. Second, the draping simulation gives the actual fiber orientations at any location in the model. This information is needed for accurate finite element analysis of the structure.
5.1.2. Draping Procedure The draping simulation in ACP uses an energy algorithm. In this approach, a reinforced ply is idealized with a pin joint net model ([ 1 ((p. p. 527 527)) ] and [ 6 (p. (p. 527 527)) ]). The net consists consists of unit cells which which can undergo different types of deformation depending on the selected draping material model. Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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5.1.2.1. Propagation Strategy During the simulation, the unit cells are laid one by one on the surface of the model to ensure full contact with the surface. The simulation starts from a given seed point and progresses in the given draping direction. In this phase, each draping cell initially has two known node points. Draping cells are laid until the model edge is reached. Then, the procedure is repeated in the opposite direction (if applicable) and in the orthogonal directions as shown below in Figure 5.1: Draping Scheme (p.. 34 (p 348) 8).. After the main draping paths have been determined, the cells with three known nodes are populated. The algorithm resolves if the whole model is draped or if there are areas where the draping simulation needs to be restarted.. Figure 5.1: Draping Scheme
Note: Above figure represents draping of a cell that has two (left) or three (middle) known node points and propagation scheme using orthogonal directions (right). The draping procedure involves the search for two types of draping cells: those with two known nodes or three known nodes as shown above. When two node points are known and the locations of the other two must be determined, the search algorithm is based on the minimization of the 527)) ]: shear strain energy [ 4 (p. (p. 527 (5.1)
where G is the elastic shear modulus of the uncured reinforcement. The shear deformation is related 527)) ]: to the angle α between the originally orthogonal fibers [ 3 (p. (p. 527 (5.2) The total shear strain energy of the draping cell is defined as the sum of energy computed at the four corners. The two constants can be excluded and the minimization problem becomes: becomes: (5.3)
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Draping Simulation Figure 5.2: Angle Notation for the Draping Energy Algorithm
From this, the locations of the two node points can be determined with an iterative minimization algorithm. In the case of three known points, the search algorithm seeks the fourth node point in different ways depending on the material model in use.
5.1.2.2. Woven 5.1.2.2.Wo ven Material Model In the woven material model, unit cells are made of inextensible bi-directional fibers pinned together at crossover node points. The deformation of the fabric takes place by pure rotation of the fibers around the pins as illustrated in Figure 5.3: Deformation Deformation of the Draping Unit Un it Cell (p. 349) 349).. Figure 5.3: Deformation of the Draping Unit Cell
When using this model, in case of three known node points the search algorithm seeks the fourth one from the surface so that the distances (along the surface) to the adjacent node points are equal
to a unit cell side length. The model is specifically developed for woven fabrics, but it has been proven to work for cross ply prepreg stacks and also for single unidirectional plies when the deformation is moderate [ 8 (p. (p. 527 527)) ].
5.1.2.3. Unidirectional Material Model In the unidirectional model, the inextensibility assumption in the transverse direction is removed. Still, due to the high modulus of individual fibers, cell edges along the fiber direction are assumed to be inextensible. As a result, given three node points the fourth one is not uniquely determined by geometrical considerations. In fact, the length of the missing edge in the transverse direction is a degree of Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Theory Documentation freedom. This unknown length freedom. length (l ) (and therefore the position of the fourth node) is computed by minimizing an energy function featuring two contributions weighted by the UD coefficient ω ∈ [0,1]: (5.4) The first term promotes low shear energy, while the second term favours edge lengths (in the transverse direction) close to the reference unit cell length (l ref ). By varying and possibly fitting to experimental or manufacturing data the UD coefficient, the user can control the amount of deformation allowed in the transverse direction. It is worth noting that the unidirectional model reduces to the woven material model when the UD coefficient is set to zero.
5.1.2.4. Output of the Draping Simulation The simulation determines fiber principal directions. These directions are mapped to the finite element model to correct laminate lay-ups accordingly. The shearing angle β is defined as
(5.5)
It expresses the deviation from the ideal non-sheared case. The visualization of β values over the model surface is useful for depicting problem areas. For most fabric reinforcements, the maximum 527)) ]. When a fabric is sheared to a specific deformation deformation angle α is 30-40 degrees [ 7 (p. (p. 527 level, the shear force starts to increase radically with little increase in the shear deformation. This limit is called the locking angle, and beyond beyond it buckling is observed. The locking angle of a reinforcement can be determined experimentally [ 5 (p. (p. 527 527)) ].
5.1.3.Thickness Correction The thickness correction option of the internal draping feature changes the thickness of a draped ply when it is sheared. The draping mesh is laid down on top of the finite element mesh and its size is independent of the finite element mesh. Thickness correction algorithm is based on conservation of volume per draping element. For that purpose, the ratio of the area of the distorted draping element to its plane reference is computed and the thickness of the analysis plies being considered is corrected accordingly.
5.1.4. Limitations of Draping Simulations The draping simulation approach has the following limitations: • The surfaces to be draped must be smooth. No sharp edges are allowed. • The draping procedure does not change mechanical properties of the ply by default. However, mechan-
ical properties can be altered if a shear-dependent material is defined. For more information, see Variable Material Data in Composite Composite Analyses (p. 300) 300).. • Ply thickness does not automatically change as a result of a draping procedure. A thickness correction
can, however, be activated in the modeling ply properties. • It is assumed that fabric transverse direction is initially perpendicular to the principal direction 1.
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Interlaminar Stresses • The fiber slippage is a phenomenon that takes place after the locking limit and is noticeable only at
relatively high deformation levels. The fiber slippage is not considered in this draping approach. • It is known that some geometries can lead to flawed or deficient results, for example draping across a
complete cylinder. This issue can be rectified by subdivision of the draping geometry geometry..
5.2. Interlaminar Stresses This section contains detailed background information on the evaluation of interlaminar stresses. A ing (p. 233) 233).. short general overview of the stress, strain, and failure analysis can be found in Postprocess Postprocessing 5.2.1. Introduction 5.2.2. Interlaminar Normal Stresses 5.2.3.Transv 5.2.3. Transverse erse Shear Stresses
5.2.1. Introduction In the analysis of layered composite structures, shell elements are widely used to keep the computational effort reasonable. In-plane stresses and even transverse shear stresses can be predicted with accuracy using shells based on the first-order shear deformation theory (FSDT). However, in the analysis of thick-walled curved structures, interlaminar normal stresses (INS) can play a significant role. The normal stresses may affect the failure mode or even cause delamination failure. INS computation is not commonly available in shell element formulations, which leads to use of computationally expensive solid modeling instead. The approach by Roos et al. ([ 14 (p. (p. 527 527)) ]) for INS computation of doubly curved laminate structures represents an alternative for solid modeling. The basis for the INS calculation is the displacement solution obtained from a shell based model. In conjunction with the INS approach, transverse shear 527)) ]) and Rolfes ([ 12 ((p. p. 527 527)) stresses are computed with the approach presented by Rohwer ([ 11 (p. (p. 527 ]). When considered at layer interfaces, transverse shear stresses are referred to as interlaminar shear stresses (ISS).
5.2.2. Interlaminar Normal Stresses A cylindrical coordinate system is used for describing an arbitrary doubly curved shell [ 9 (p (p.. 52 527) 7) ]. Geometr y (p. 352) 352),, is described by Curved shell geometry, illustrated in Figure 5.4: Doubly Doubly Curved FE Geometry the coordinates
and it is subdivided into angular segments with the apex angles
and
the coordinates and it is subdivided into angular segments with the apex angles and the constant curvature radii of the centerline and .
and
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Theory Documentation Figure 5.4: Doubly Curved FE Geometry
The radial equilibrium equation becomes (5.6) where:
Each segment is embedded between four cross-sections which are assumed to remain straight and perpendicular to the midplane. Studies on singly curved plates ([ 10 ((p. p. 527 527)) ] and [ 13 (p. (p. 527 527)) ]) show that the shear terms have only small effect and are thus neglected here. Equation Equation 5.6 (p. (p. 352) 352) reduces reduces to (5.7) where only direct stresses appear and the material law reduces to (5.8)
where are components of the 3-D stiffness matrix expressed in reference coordinates which are Reference ence Coordinates Coordinates (p. 353) 353).. The parallel to the principal direction. The evaluation is described in Refer term indicates free layer strains due to spatially constant changes of temperature and moisture content . (5.9) Direct strains in Equation Equation 5.8 (p. (p. 352) 352) can can be expressed through the displacements u, v, v, and w w.. The kinematic relations in the modified coordinate system are: (5.10)
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Interlaminar Stresses The in-plane deformations u and v are expressed by the laminate deformations and . The throughthe-thickness coordinate is replaced with the radial coordinate and the curvature radii of the midplane: (5.11)
The direct strains become (5.12)
The combination of the material law of Equatio Equation n 5.8 (p. (p. 352) 352) with with the kinematic relations of Equation 5.10 (p. 352) 352) leads leads to the direct stresses expressed by the deformations:
(5.13)
Equation (p. 353) 353) is is combined with the radial equilibrium Equation Equation 5.7 (p. (p. 352) 352) and and the differential Equation 5.13 (p. equation of the through-the-thickness displacement is: (5.14) where:
5.2.2.1. Reference Coordinates The reference coordinates, which are needed to evaluate the material stiffness
and strains
are
evaluated depending on the laminate properties or the curvature. If the laminate is non-isotropic, the reference coordinates are parallel to the principal laminate directions, where the first principal laminate stiffness has its maximum. In the case of a quasi-isotropic laminate, the reference coordinates are parallel to the principal curvature directions.
5.2.2.2. Numeric Solution The solution of Equation Equation 5.14 (p. (p. 353) 353) is found with the finite difference method. method. The differential equation represents a linear second order boundary value problem. (5.15) where the derivatives are replaced with
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where are the displacements at the supporting points through the thickness and is the distance between two consecutive supporting points. Their placement scheme for a single-layer laminate is 354).. The boundary boundary conditions conditions lead to a nonshown on the left of Figure 5.5: Integration Scheme (p. 354) singular linear system of equations (LSoE) and are represented by the INS which have to vanish at the top and bottom surfaces of the laminate. Figure 5.5: Integration Scheme
The above figure shows single layer (left) and multilayer laminate (right) where the indices 1, 2, and 3 count the layers and refers to . The through-the-thickness through-the-thicknes s INS distribution is obtained by combining Equatio Equation n 5.8 (p. (p. 352) 352) and Equation 5.10 (p. Equation (p. 352) 352).. (5.16) This equation can be transformed to: (5.17) and is integrated in the LSoE where side of the LSoE, respectively.
and
modify the first and the last row of the left and right
Every additional layer leads to two more interface continuity conditions that have to be fulfilled:
(5.18) The first derivative of the through-the-thickness displacements is found using Equation Equation 5.16 (p. (p. 354) 354).. Additional supporting points, which are placed outside the layer, are necessary to evaluate the INS at the layer intersections. An integration scheme for a three layer laminate is plotted on the right 354) where where the supporting points n = [7,8,15,16] guarantee the of Figure 5.5: Integration Scheme (p. 354) through-the-thickness continuity of the INS.
5.2.3. 5.2.3.T Transve ransverse rse Shear Stresses The method employed for computing transverse (interlaminar) shear stresses of FSDT-based shell 527)) ]) and Rolfes ([ 12 (p. (p. 527 527)) ]). The transverse transverse elements is based on the work by Rohwer ([ 11 (p. (p. 527 shear stresses are calculated from the three dimensional equilibrium equations of elasticity:
354
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Interlaminar Stresses
(5.19)
In to calculate the shear stresses from the equilibrium equations, the in-plane stresses need to beorder derived first and then integrated with respect to the thickness coordinate: (5.20) In-plane stresses are piecewise continuous functions, so the integration must be done in parts. Applying (p. 355) 355) takes takes the form the stress-strain relation for in-plane stresses, Equation Equation 5.20 (p. (5.21) where:
Strain derivatives in Equation Equation 5.21 (p. (p. 355) 355) can can also be transformed to give an expression in terms of force derivatives by applying the constitutive equations. In order to calculate the stresses straight from the shear forces, some additional assumptions have to be made. The influence of the in-plane force derivatives der ivatives is neglected, that is (5.22)
Strain derivatives then reduce to the form
(5.23)
where
and
are the laminate compliance matrices.
The actual displacement fields are further simplified by assuming a ssuming two separate cylindrical bending modes. The moment derivatives then reduce to the simple resultant shear forces:
(5.24)
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Theory Documentation Applying Equation Equation 5.22 (p. (p. 355) 355),, Equatio Equation n 5.23 (p. (p. 355) 355),, and Equation Equation 5.24 (p. (p. 355) 355) to Equation Equation 5.21 (p. (p. 355) yields: (5.25)
This simplifies to: (5.26)
where are the components of the 3 x 3 matrix . The components of the piecewise continuous, second order functions of determined by:
matrix are (5.27)
where:
The functions
and
are defined by the th e continuity of stresses at the layer interfaces:
(5.28)
(p. 356) 356) give give the laminate stiffness It can be seen that the functions and of Equation Equation 5.27 (p. matrices and at the lower surface of the laminate and zero at the top surface of the laminate: (5.29)
Therefore, the transverse shear stresses of Equation Equation 5.26 (p. (p. 356) 356) become become zero for the top and bottom surfaces and fulfill the boundary conditions of transverse shear stresses going to zero at the laminate surfaces. In the local coordinate system the transverse shear stresses are: (5.30) where the 2 x 2 transformation matrix
is (5.31)
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Failure Analysis
5.3. Failure Analysis This section contains detailed background information on the evaluation of interlaminar stresses. A generalized overview of failure analysis is shown in Postproc Postprocessing essing (p. 233) 233).. 5.3.1. Reserve Factor 5.3.2.Weighting 5.3.2. Weighting Factors Factors 5.3.3. Failure Criterion Function 5.3.4. Failure Criteria for Reinforced Materials 5.3.5. Sandwich Failure 5.3.6. Isotropic Material Failure 5.3.7. Adhesive Failure (Beta Version) 5.3.8. Failure Criteria Cri teria vs. Ply Type Table Table
5.3.1. Reserve Factor The reserve factor indicates margin to failure. The applied load multiplied by the reserve factor gives the failure load: (5.32) Reserve factor values greater than one indicate positive margin to failure and values less than one indicate negative margin. The values of reserve factors are always greater than zer zero. o. The critical values of reserve factors lie between zero and one, whereas the non-critical values range from one to infinity. Whether the results are shown in numeric form or as contour plots, the noncritical values tend to be emphasized in comparison to critical values. Therefore, the inverse reserve factor is often preferred in practical use: (5.33) The non-critical values of
range from zero to one and the critical values from that on.
The margin of safety is an alternative for the reserve factor in indicating margin to failure. The margin of safety is obtained from the corresponding reserve factor with the relation (5.34)
A positive margin of safety indicates the relative amount that the applied load can be increased before reaching failure load. Correspondingly, a negative margin of safety indicates how much the applied load should be decreased. Margins of safety are typically expressed as percentages.
5.3.2.W Weighting Factors 5.3.2. Several implemented in possible ACP are to able to predict the failure for example whether fiber or failure matrix criteria failure occurs first. It is assign weighting factorsmode, to individual failure mode criteria and thus create a certain bias towards or against a specific failure mode. As a result, failure criteria can be tuned to specific requirements. A design may require a higher safety against delamination than against fiber failure and the weighting factor of delamination is increased.
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Theory Documentation Using the maximum stress criterion given in Equation Equation 5.37 (p. (p. 359) 359) as as an example, the following shows the implementation of weighting factors in ACP: (5.35)
5.3.3. Failure Criterion Function The strength of materials and material systems under multiaxial loads can be predicted based on different failure criteria. Failure criteria relate the material strength allowables, defined for uniaxial tension-compression and shear, to the general stress-strain state due to multiaxial loads. Typically failure criteria are presented presented as mathematical expressions called failure criterion functions , which are functions of the stresses (or strains) and the material strength. The values of failure criterion functions change with load similarly as the inverse reserve factor (values below one are non-critical and one indicates failure). However, the values are generally not equal except at the failure point. The reserve factor describes the distance from the point of the applied load to the failure point. Typically a numeric line search method is used ffor or determining the value of basedallowables. on the selected failure criterion, stresses and strains due to the applied load, and material strength
5.3.4. Failure Criteria for Reinforced Materials This section contains the following information: 5.3.4.1. Maximum Strain Criterion 5.3.4.2. Maximum Stress Criterion 5.3.4.3. Quadratic Failure Criteria 5.3.4.4. Hashin Failure Criterion 5.3.4.5. Puck Failure Criteria 5.3.4.6. LaRC Failure Criterion 5.3.4.7. Cuntze's Failure Criteria
5.3.4.1. Maximum Strain Criterion In the maximum strain criterion, the ratios of the actual strains to the failure strains are compared
in the ply principal principal coordinate system. The failure criterion function is written as (5.36) where:
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Failure Analysis
5.3.4.2. Maximum Stress Criterion In the maximum stress criterion, the ratios of the actual stresses to the failure stresses are compared in the ply principal coordinate system. Thus, the failure criterion function is (5.37) where:
5.3.4.3. Quadratic Failure Criteria In quadratic criteria all the stress or strain components are combined into one expression. Many commonly used criteria for fiber-reinforced composites belong to a subset of fully interactive criteria called quadratic criteria. The general form of quadratic criteria can be expressed as a second-order polynomial. (5.38) In pla plane ne str stress ess-st -stat ate e(
), the po poly lynom nomial ial reduc reduces es to to the the simp simpler ler form form (5.39)
359),, Tsai-Hill ((p. p. 360) 360),, and Hoffman (p. 361) 361))) differ The quadratic failure criteria in ACP ( Tsai-Wu Tsai-Wu (p. 359) in how the coefficients and are defined. Generally, the coefficients and are determined so that the value of the failure criterion function corresponds to the material strength when a unidirectional stress state is present. However, not all coefficients can be determined in this way.
5.3.4.3.1.Tsai-W 5.3.4.3.1.Tsai-Wu u Failure Criterion For the plane stress-state the Tsai-Wu criterion coefficients
have the values
(5.40)
Thus, the criterion can be written as: (5.41)
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Theory Documentation The coefficient cannot be obtained directly from the failure stresses of uniaxial load cases. For accurate results it should be determined through biaxial load tests. In practice, it is often given in the form of a non-dimensional interaction coefficient: (5.42)
T To o insure that the criterion represents a closed conical failure surface, the value of within the range
. However, However, the value range for physically meaningful material beha-
vior is more limited. The often used value The final Tsai-Wu constant
must be
corresponds to a "generalized Von Mises criterion".
Equation n 5.43 (p. (p. 360) 360).. Similarly becomes -1 as used in Equatio
can be dealt with using the corresponding values expression:
and
,
, which leads to the Tsai-Wu 3-D
(5.43)
In ACP the Tsai-Wu constants are: , default -1 , default -1 , default -1
5.3.4.3.2.Tsai-Hill Failure Criterion In the Tsai-Hill criterion, either tensile or compressive strengths are used for determining the coefficients depending on the loading condition. The coefficients are:
(5.44)
where the values of
and
are:
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Failure Analysis
(5.45)
The Tsai-Hill failure criterion differentiates between UD and woven plies. The Tsai-Hill failure criterion function for UD plies can be written in the form (5.46) For woven plies, the function becomes (5.47)
where
.
528)) ]: For the full 3-D case another formulation can be used, as in [ 25 (p. (p. 528 (5.48) where
(5.49)
5.3.4.3.3. Hoffman Failure Criterion The Hoffman criterion defines the biaxial coefficients ial strength expressions for the 3-D stress state:
,
, and
with the following mater-
(5.50)
The Hoffman failure criterion for a 3-D stress state can be written as: (5.51) The biaxial coefficient
for the plane stress state reduces to: (5.52)
The entire Hoffman criterion in the plane stress case reduces to:
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Theory Documentation
(5.53)
5.3.4.4. Hashin Failure Criterion The Hashin criterion [ 43 (p. (p. 529 529)) ] is used to predict failure in UD (transversal-isotropic orthotropic 23) materials. There are two formulations, formulations, one for for plane stress and another for the full 3-D stress state. In the Hashin criterion, criticality of tensile loads in the fiber direction expression:
is predicted with the
(5.54)
Under compressive loads in the fiber direction
, failure is predicted with an independent
stress condition (for both 2-D and 3-D): (5.55) In the case of tensile transverse stress, the expression for predicting matrix failure is: (5.56)
This expression is used when the transverse stress is compressive: (5.57)
In addition and optionally, ACP predicts delamination (tension and compression) with this expression: (5.58)
The most critical of the failure modes is selected: (5.59)
5.3.4.5. Puck Failure Criteria There are several different Puck Failure criteria, the following sections describe them.
5.3.4.5.1. Simple and Modified Puck Criterion The two oldest Puck failure criterion formulations are simple Puck and modified Puck. Both criteria consider failure due to longitudinal loads and matrix failure mode due to transverse and shear 528)) ] and [ 28 (p. (p. 528 528)) ]). loads separately ([ 27 (p. (p. 528
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Failure Analysis For both the simple and modified Puck criteria, failure in fiber direction is calculated the same way as in the maximum stress criterion: (5.60) (p. 363) Matrix failure is calculated differently for each formulation as illustrated in Equation Equation 5.61 (p. for simple Puck. Equatio Equation n 5.62 (p. (p. 363) 363) demonstrates demonstrates how tensile or compressive failure stresses are used depending on the stress state. (5.61) where:
(5.62)
The modified Puck criterion differs from the simple criterion only in the formulation for matrix failure: (5.63) As in Hashin Failure Failure Criterion Criterion (p. 362) 362),, the failure occurs when either
or
reaches one, so the
failure criterion function is: (5.64) Despite being called simple in the failure criteria configuration in the Failure Criteria Definition dialog the Puck modified version is actually implemented. The name is referring to the simplicity of that criterion in comparison to Puck's Puck's Action Plane Strength Criterion Criterion (p. 363) 363)..
5.3.4.5.2. Puck's Action Plane Strength Criterion The following sections describe the different failure modes for Puck ’s action plane strength criterion.
5.3.4.5.2.1. Fiber Failure (FF)
As in the simple Puck criterion, one option for evaluating fiber failure is to use the maximum stress criterion for that case ([ 29 (p. (p. 528) 528) ], ], [ 30 (p (p.. 528 528)) ], and [ 31 ((p. p. 528 528)) ]): (5.65) and similarly a maximum strain criterion: (5.66) A more complicated version for FF criterion was presented by Puck for the World Wide Failure Exercise, but the maximum stress criterion is considered sufficient for the case of FF.
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Theory Documentation
5.3.4.5.2.2. Interfiber Failure (IFF) Interfiber failure is formulated differently depending on the model type.
Plane stress-state Interfiber failure, or interfiber fracture ([ 29 (p. (p. 528 528)) ] and [ 30 ((p. p. 528 528)) ]) can be explained in the cutting plane for which the principal stress of a UD UD layer is zero in the case of of plane stress. Figure 5.6: Fracture Curve in
σ2, τ21 Space
for
σ1 =
0
The curve consists of two ellipses (modes and ) and one parabola (mode ). Generally Puck's action plane strength criterion is formed utilizing the following 7 parameters, , where
stands for fracture resistances and
for slope para-
meters of the fracture curves. The symbols
and
denote the reference to direction parallel
to the fibers and transverse (perpendicular) to the fibers. The values for and define the intersections of the curve with -axis, as well as for the intersection with -axis. The slope parameters
and
are the inclinations in the latter intersections.
The failure conditions for IFF are:
(5.67)
The superscript
denotes that the fracture resistance belongs to the action plane.
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Failure Analysis
(5.68)
The assumption
is valid here and leads to: (5.69)
Equation 5.70 (p. Equation (p. 365) 365) is is also valid. (5.70) As the failure criterion functions and the functions for their corresponding stress exposure factors are the same, they can be written as follows (given Equation Equation 5.69 (p. (p. 365) 365) and and Equation 5.70 (p. 365) 365)):):
(5.71)
3-D Stress State While the la While latt tter er fo formu rmula latio tions ns have have be been en a red reduc uced ed ca case se worki working ng in ( 3-D stress state can be described with Equation Equation 5.72 (p. (p. 365) 365)::
)-str )-stres esss sspa pace ce,, th the e
(5.72)
where:
From the above equations, the failure criterion function is formulated in the fracture (action) plane plan e using using the corres correspon ponding ding str stresse essess and strains strains.. The formula formulation tionss for the str stresse essess , , and in an arbitrary plane with the inclination angle are:
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Theory Documentation
(5.73)
To find the stress exposure factor
the angle
is iterated to find the global maximum, as
the failure will occur for that angle. An analytical solution for the fracture angle is only available for plane stress-state by assuming: (5.74) which leads to formulations for the exposure factor: (5.75)
p. 528 528)) ] that the latter criterion can be used as a criterion to determine Puck illustrated in [ 29 ((p. delamination, if an additional weakening factor for the interface resulting in:
is applied, finally
(5.76)
The active failure mode depends on the fraction angle and the sign of occur if is positive and is 90 degree. The failure modes and ative .
. Delamination can happen with neg-
Puck Constants Different default values for the coefficients are set for carbon and glass fiber plies to: Carbon:
Glass: 528)) ]. Those values are compliant with recommendations given in [ 32 (p. (p. 528
Influence of fiber parallel stresses on inter-fiber failure To take into account that some fibers might break already under uniaxial loads much lower than loads which cause ultimate failure (which can be seen as a kind of degradation), weakening factors can be introduced for the strength parameters. Puck formulated a power law relation in [ 29 (p. (p. 528 528)) ]: (5.77)
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Failure Analysis where
and
and
can be can be experimentally determined.
Different approaches exist to handle this problem numerically. numerically. The function given in Equation 5.77 (p. 366) 366) can can be replaced by an elliptic function: (5.78)
where:
and
are degradation parameters.
In ACP, the stress exposure factor is calculated by intersecting the weakening factor ellipse with a straight line defined by the stress vector using the parameters:
Otherwise Otherwis e the fiber failure criterion determines the stress exposure factor Default values for the degradation parameters are
5.3.4.6. LaRC Failure Criterion
and
.
.
LaRC03 (2-D) and LaRC04 (3-D) are two sets of failure criteria for laminated fiber-reinforced composites. They are based on physical physical models for each failure mode and distinguish between fiber and matrix failure for different transverse fiber and matrix tension and compression modes. The LaRC criteria take into account that the apparent (in-situ) strength of an embedded ply, constrained by plies of different fiber orientations, is different compared to the same ply embedded in a UD laminate. Specifically, moderate transverse compression increases the apparent shear strength of a ply. Similarly in-plane shear significantly significantl y reduces the compressive strength of a ply. The evaluation of the in-situ strength also makes a distinction between thin and thick plies. The definition for a thick ply is a ply in which the slit crack is much smaller than the ply thickness. For epoxy E-glass and 528)) epoxy carbon laminates, the suggested threshold between thin and thick plies is 0.7 mm ([ 21 (p. (p. 528 ] and [ 26 (p. (p. 528 528)) ]). The implemented LaRC04 (3-D) failure criterion ACP assumes a ssumes linear shear behavior and small angle deflection. The abbreviation LaRC stands for Langley Research Center. Center.
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Theory Documentation
5.3.4.6.1. LaRC03/LaRC04 Constants The required unidirectional properties for the criteria are: ,
,
where I and II.
,
,
,
,
,
,
,
, and
.
is the longitudinal shear strength and
and
are the fracture toughness for mode
The following LaRC Constants are required for postprocessing in ACP: • Fracture Toughness Ratio: • Fractu racture re Tough oughnes nesss Mode Mode I:
ractur ure e Tou Tough ghne ness ss Mod Mode e II: II: • Fract
(Dimensionless) (F (For orce ce / LLen engt gth) h) (F (For orce ce / Len Lengt gth) h)
•
Fractu racture re Ang Angle le unde underr Comp Compre ressi ssion on:: • Thin Ply Thickness Limit (Length)
(Degr (Degree ees) s)
The fracture angle can be determined in tests or taken to be which has proven to have 528)) ]. The Thin Thin Ply Thickness Thickness good results for carbon/epoxy and glass/epoxy laminates [ 30 (p. (p. 528 Limit is the only default value set for the LaRC parameters. The following reference values are drawn from [ 37 (p (p.. 529 529)) ]: Parameter
Typical Values (Carbon/epoxy)
Elas El asttic Modulus,
(GPa)
Elastic Modulus,
,
(GPa)
Fracture Angle
(deg)
128 7.63 53
Fract ractur ure e Tou ough ghne ness ss Mode Mode 1,
(N (N/m /mm) m) 0.28
Fracture Toughness Mode 2, (N/mm)
0.79
367
Fracture Toughness Ratio, g
0.35
Thin Ply Thickness Limit (mm)
0.7
5.3.4.6.2. General Expressions Several failure functions involve the friction coefficients, in-situ strengths, and fiber misalignment. These values are described in the following sections.
Friction Coefficients Laminates tend not too fail in the plane of maximum shear stress. This is attributed to internal friction and considered in the LaRC failure criteria with two friction coefficients:
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Failure Analysis
Transverse Friction Coefficient: Longitudinal Friction Coefficient:
In-Situ Ply Strength The in-situ transverse direct strength and longitudinal shear strength for a thin ply are: (5.79)
where: = thickness of an embedded ply
For a thick ply, the in-situ strengths are not a function of the ply thickness: (5.80)
5.3.4.6.3. Fiber Misalignment Frame Fiber compression, where the plies fail due to fiber kinking, is handled separately for transverse tension and transverse compression. In the model, imperfections in the fiber alignment are represented by regions of waviness, where transformed stresses can be calculated using a misalignment frame transforming the "original stresses". There are two different misalignment frames for LaRC03 (2-D) and LaRC04 (3-D). LaRC03
For LaRC03, the stresses in the misaligned frame are computed as follows: (5.81)
370)) using The misalignment angle for pure compression can be derived to 114 (p. (p. 370 and in the equations above as well as the stresses and the quadratic interaction criterion presented in Equation Equation 5.93 (p. (p. 372) 372) for for matrix compression.
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Theory Documentation
(5.82)
The total misalignment angle
is calculated from: (5.83)
LaRC04
The 2-D misalignment model assumes that the kinking kinkin g occurs in the plane of the lamina. LaRC04 incorporates a more complex 3-D model for the kink band formation. The kink plane is at an angle to the plane of the lamina. It is assumed to lie at an angle so that and is thus given by: (5.84) and the stresses rotated in this plane are:
Following the definition of a kink plane, the stresses are rotated into a misaligned frame. This frame defined by evaluating the initial and the misalignment angles for pure compression as well as the shear strain under the assumption of linear shear behavior and small angle approximation: (5.85) where:
= the misalignment angle for pure compression.
Following this, the stresses can be rotated into the misaligned coordinate system:
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Failure Analysis
5.3.4.6.4. LaRC03 (2-D) The following sections describe the failure modes for LaRC03 (2-D).
Fiber Failure For fiber tension a simple maximum strain approach is applied: (5.86) Fiber compression failure for matrix compression is calculated as follows: (5.87) For fiber compression failure with matrix tension, the following quadratic equation has to be solved: (5.88)
Matrix Failure The formulation for matrix tensile failure is similar to that of fiber compressive failure under transverse compression. The difference is that the stress terms are not in the misaligned frame. (5.89)
Matrix compression failure is divided into two separate cases depending on the longitudal loading. The failure function for the first case is: (5.90)
where the effective shear stresses for matrix compression are based on the Mohr-Coulomb criterion which relates the effective shear stresses with the stresses of the fracture plane in Mohr's circle. (5.91)
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Theory Documentation
The transverse shear strength angle can be written as:
in terms of the transverse compressive strength and the fracture (5.92)
The failure function for the second case
is: (5.93)
where the effective shear stresses are rotated into the misaligned frame:
5.3.4.6.5. LaRC04 (3-D) The following sections describe the failure modes for LaRC04 (3-D).
Fiber Failure The LaRC04 fiber tensile failure criteria is simply a maximum allowable stress criterion with no interaction of other components: (5.94) Fiber compressive failure is divided into two components depending of the direction of the transverse stress. For transverse compression it is: (5.95) The failure function for fiber compression and matrix tension is based on the ANSYS Combined Stresses and Strains formulation for the LaRC criteria.
(5.96)
Matrix Failure The failure function for matrix tension is based on the ANSYS Combined Stresses and Strains formulation for the LaRC criteria. (5.97) Matrix compressive failure is given by: (5.98)
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Failure Analysis where:
Matrix compressive failure with transverse tension is given by: (5.99)
5.3.4.7. Cuntze's Failure Criteria Cuntze's approach is based on his general invarient-formulated failure mode concept (applicable for isotropic and orthotropic materials), applied here to transversely isotropic UD materials. This concept strictly separates the 5 strength failure modes inherent to UD materials. Material symmetry requires strength measurements in 5 directions, and physical fracture morphology dictates that each failure mode is dominated by strength in a single direction only. Cuntze's strength of failure conditions (SFC) can be termed modal conditions according to the fact that a failure function F describes just one failure mode and involves just the mode-associated strength: (5.100) with the vector of 6 stresses
.
A set of modal SFCs requires an interaction of the 5 failure modes. The observed failure modes are two fiber failure modes (FF1 tension, and FF2 compression) and three interfiber failure modes (IFF1 transverse tension, IFF2 transverse compression, and IFF3 shear) which represent cohesive and adhesive matrix failures between fiber and matrix. Cuntze provides equivalent stresses for all 5 fracture failure modes of the brittle-behaving UD material similarly to the Hencky-Mises-Huber yielding failure mode of ductile-behaving materials.
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Theory Documentation Figure 5.7: UD Failure Modes
An equivalent stress includes all stresses that are acting together in a given failure mode. The vector containing all equivalent stresses is: (5.101) where an equivalent stress is related to the mode strength and the material stressing effort
by: (5.102)
(5.103)
where the overbar marks statistical average values and the mode strengths can be substituted by the respective material stress limits. In addition to the 5 strengths, Cuntze uses two material-inherent fracture parameters, (required by Mohr-Coulomb), because SFCs for brittle-behaving materials cannot be based on strength values alone. Macromechanical SFCs must consider that materials fail on the micromechanical level, with respect to the fiber failure modes. 528)) ]: Five invariants are used for the generation of the five SFCs (2-D or 3-D) [ 17 (p. (p. 528
374
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Failure Analysis
(5.104)
5.3.4.7.1. 3-D Failures Replacing the invariants in Cuntze's invariant formulated SFCs [ 19 (p. (p. 528 528)) ] [ 20 (p. (p. 528) 528) ] ] with the associated stress states (factoring in IFF3 not the full stress state components but just the mode failure driving stress) and resolving for the simplified material stressing efforts yields the following:
(5.105)
where the superscripts
and
stand for tension and compression, respectively.
The friction parameter
can be computed from the available friction coefficients of the UD ma-
terial, derived in [ 20 (p (p.. 528 528)) ] (5.106)
with typical ranges being:
If measurement data of the fracture angle is given, the friction coefficient
is determined as: (5.107)
or the directly related parameter
as: (5.108)
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Theory Documentation
where
.
If the IFF2 and IFF3 curves are based on enough test data, the 2 friction parameters can be determined using the following formulas [ 20 (p. (p. 528 528)) ]: (5.109)
An interaction of the failure modes occurs due to the fact that the full (global) failure surface consists of five parts. Cuntze models these interactions by a simple, probability-based series spring 528)) ]. This model describes the lamina failure system as a series failure system model [ 17 (p. (p. 528 which fails whenever any of its elements fail. Each mode is one element of this failure system and is treated as independent of the others. By this method, the interaction between FF and IFF modes as well as between the various IFF modes acts as a rounding-off procedure, enabling the determination of the final or inverse reserve factor (IRF). (5.110) In other words, the interaction equation includes all mode stressing efforst and each of them represents a portion of load-carrying capacity of the material. In 2-D practice at maximum 3 of the 5 modes will interact. The modes' interaction exponent is obtained by curve-fitting cur ve-fitting of test data in the interaction zones. Experimental data showed that (for CFRP) . The exponent is high in case of low scatter and low in the case of high scatter, hence chosing chos ing a low value value for for the interactio interaction n exponent exponent is conservativ conservative. e. As an engineering engineering assumption, assumption, is always always given by the same value, regardless of the distinct mode interaction domain. For pre-design, Cuntze recommends
and
5.3.4.7.2. 2-D Failures Cuntze's approach delivers the following simplified material stressing efforts
for the five failure
modes:
(5.111)
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Failure Analysis
5.3.5. Sandwich Failure The following sections describe the different failure criteria for sandwich failure. 5.3.5.1. Core Failure 5.3.5.2. Face Sheet Wrinkling 5.3.5.3. Shear Crimping Failure
5.3.5.1. Core Failure The Core Failure criterion predicts failure of core materials in sandwich structures due to interlaminarr shear ina shear ( , ) and norma normall stre stresse ssess . It is assume assumed d th that at core core fai failur lure e is hig highly hly do domin minat ated ed by the out-of-plane stresses and therefore the in-plane terms are neglected. The normal stress is only considered in the 3-D formulation of the criterion. By default, the 2-D formulation is active. The failure criterion distinguishes between isotropic (isotropic-homogeneous) and orthotropic (orthotropic homogeneous and honeycomb) core materials. For isotropic cores, a simplified formulation 359) is 359) used (p. 529 529)) ]. For orthotropic materials, the maximum stress approach of implemented the Tsai-Wu (p.[ 41 the Tsai-Wu is (p. is529 (p. 529) ) ]. [ 42 (p. Isotropic Core (5.112)
Orthotropic Core (5.113)
In previous releases of ACP, ACP, the core failure criterion was implemented differently. The previous implementation can still be evaulated using custom failure criteria. An example implementing the 237).. previous core failure criterion is provided in Evaluating Custom Failure Criteria (p. 237)
5.3.5.2. Face Sheet Wrinkling
Wrinkling of sandwich face sheets is a local instability phenomenon, in which the face sheets can be modeled as plates on an elastic foundation formed by the core. Simple formulas for estimating wrinkling stresses of sandwich face sheets under uniaxial load have been presented in the literature 528)) ] and [ 33 (p. (p. 528 528)) ]). Linear elastic material behavior is assumed. Possible interaction of ([ 23 (p. (p. 528 the top and bottom face sheets is not considered. In the follow following ing,, , , and ref refer er to a coordi coordinate nate system system in which which the -axis -axis is in the directi direction on of compression and the -axis is perpendicular to the face sheets. The subscripts F and C indicate the face sheet and the core, respectively. For sandwich laminates with homogeneous cores, the wrinkling stress of a face sheet is: (5.114)
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377
Theory Documentation where the theoretical value of the wrinkling coefficient is 0.825. The effects of initial waviness and imperfections of the face sheet are normally accounted for by replacing the theoretical value of the wrinkling coefficient with a lower value. it is recommended that you use the value p. 528 528)) ] and [ 33 (p. (p. 528 528)) ]). as a safe design value for homogeneous cores ([ 23 ((p. The wrinkling stresses for sandwich laminates with honeycomb cores are estimated with the expression: (5.115) The theoretical value of (p. 528 33 (p. 528)) ]).
is 0.816, whereas a safe design value is
528)) ] and [ ([ 23 (p. (p. 528
528)) ]. When in-plane The prediction of wrinkling under multiaxial stress state is discussed in [ 33 (p. (p. 528 shear stresses exist, it is recommended that the principal stresses are determined first. If the other of the two principal stresses is tensile, it is ignored and the analysis is based on the equations given above. When biaxial compression is applied, wrinkling can be predicted with an interaction formula. The condition for wrinkling w rinkling is: (5.116) 528)) ]. For orthotropic sandwich face where is the direction of maximum compression [ 33 (p. (p. 528 sheets, is more more logically logically interpre interpreted ted as the most most critical critical of the two directions. directions. The wrinkling wrinkling stresses and are computed from the formulas for uniaxial compression by considering the compressive stresses in the - and -direction independently. The average face sheet stresses , , are obtained from the layer stresses of the face sheets. The following procedure for the computation of reserve factors is then used independently for the top and bottom face sheets. If the shear stress of the face sheet is zero, the normal stresses and are used directly in the prediction of wrinkling. Otherwise, the principal stresses are determined first: (5.117) The orientation of the normalized principal stresses with respect to the xy-coordinate system is
(5.118)
where:
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Failure Analysis
5.3.5.3. Shear Crimping Failure Shear crimping failure [ 39 (p. (p. 529 529)) ] appears to be a local mode of failure, but is actually a form of general overall buckling in which the wavelength of the buckles is very small because of low core shear modulus. The crimping of the sandwich occurs suddenly and usually causes the core to fail in shear at the crimp. It may also cause shear failure in the bond between the facing and core.
Equation n 5.119 (p. (p. 379) 379) describes describes the shear crimping allowable force which is a function of the core Equatio and the face sheet properties in the direction of loading. (5.119) where = allowable compressive force [Force/length] = weighting factor = shear modulus in the loading direction = thickness
= bending stiffness in the loading direction = core = face sheet The shear crimping factors and are derived from test data. If the face sheets are much thinner compared compa red to to the core thickness and no characteristic characteristic value is available available,, can be set to to 0 (default). (default). The default value of is 1. For uniaxial compression the effort is: (5.120) where
[Force/length] is the in-plane laminate load.
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Theory Documentation In the case of shear loading, the effort in Equation Equation 5.120 (p. (p. 379) 379) is is evaluated with respect to the principal direction of loading. The material parameters parameters of Equation Equation 5.119 (p. (p. 379) 379) can can be easily rotated into the principal direction of loading to get the allowable forces and with respect to the first and second principal directions of loading. In the case of biaxial compression, the failure condition of shear crimping is the sum of the efforts in the first and second loading direction: (5.121) where
and
are the first and second principal laminate loads, respectively.
5.3.6. Isotropic Material Failure The failure criteria for isotropic materials is based on the von Mises stress (or equivalent stress in Mechanical): (5.122) or on the von Mises strain (or equivalent strain in Mechanical): (5.123) where and are the where the first first and and second second princ principa ipall strains strains.. For For iso isotro tropic pic mate material rial,, the stre stress ss failur failure e function is defined as: (5.124) and the strain failure function is defined as: (5.125)
(Be ta Version) 5.3.7. Adhesive Failure (Beta Version) This section describes the available failure criteria for adhesive materials. All criteria calculate an ef-
fective stress that corresponds to the applied load. If this value is greater than the allowable limit , then failure occurs. occurs. is defined by the Tensile Yield Streng Strength th in Engineering Engineering Data.
5.3.7.1. Peel Stress Criterion This criterion predicts failure in an adhesive material that is dominated by the peel stress If
is > 0, then
=
, else
.
= 0.
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Failure Analysis
5.3.7.2. Shear Stress Criterion The shear stress criterion predicts failure caused by the th e interlaminar shear stresses and allowable limit is typically determined by a tensile lap shear test (lap shear strength).
. The
Notes Note that: • The listed failure criteria can be activated via the application menu ( Tools - Preferences - ACP -
Add-Ons - Adhesive Failure Criteria). • If both the peel and shear stress criteria are active, then the weighting factor can be used in one
of the criteria in order to adjust
because the peel and shear strengths typically differ. differ.
Limitations Review the following limitations: • Failure mode labels are not currently exposed and display "na" (not available). • Adhesive failure criteria are not currently exposed in Mechanical.
Reference Yarrington, P., Zhang, J., Collier, C., Bednarcyk, B.A., Failure Analysis of Adhesively Bonded Composite Joints, American Institute of Aeronautics and Astronautics.
Criter ia vs. Ply Type Table 5.3.8. Failure Criteria Table The table below illustrates which failure criteria evaluates the safety of the different ply types. Ply Type Failure
Regular
Woven Homogeneous Honeycomb Isotropic Adhesive Sandwich
Criteria
(UD)
Max Strain
√ √ √ √ √
Max Stress Tsai-Wu Tsai-Hill Hofmann Hashin Puck Cuntze LaRC
√ √ √ √
Core
Core
√ √ √ √ √ √ [1]
√ [2]
Wrinkling
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Theory Documentation Ply Type Failure Criteria
Regular (UD)
Core Failure
Woven Homogeneous Honeycomb Isotropic Adhesive Sandwich Core Core
√
√ √
Von Mises Shear Crimping
√
√
Shear Stress Peel Stress
√ [3] √ [3]
1. In combinat combination ion with with Puck Puck for for Woven Woven specificat specifications. ions. 2. Sandwic Sandwich h is a laminate laminate with with at least least one core core layer layer.. 3. Only available available if the the add-on "Adhesive "Adhesive Failure Failure Criteria" Criteria" is enabled enabled in ACP ACP..
5.4. Classical Laminate Theory The Classic Laminate Theory Theor y analysis described in the following sections can be evaluated using the Sampling Point, Stack-up and Sublaminate Properties. In a Sampling Point, the laminate properties and stiffness/compliance matrices are evaluated based on the lay-up on the shell mesh. The changes to the lay-up incurred by solid model operations (extrusion guides, snap-to and cut-off operations) are not considered. The laminate forces can only be evaluated if the shell mesh has a solution with nodal deformations. 5.4.1. Overview 5.4.2. Analysis
5.4.1. Overview Classical Laminate Theory provides useful information about the mechanical behavior of a composite structure. The in-plane and flexural laminate stiffness represent characteristic values which can be compared with other laminates. These information can be quite useful since no external loads and boundary conditions are necessary to evaluate these values.
381
Classical Laminate Theory is described in many text books ([ 34 (p. (p. 528 528)) ] and [ 35 (p. (p. 528 528)) ]). The basic basic assumptions are: • Layers are perfectly bonded together.
a re constant through the thickness. • The material properties of each layer are • Linear-elastic strain-stress behavior. • Lines originally straight and normal to the mid-plane remain straight and normal in extension and
bending. • Plane stress state. • In-plane strains and curvature are small compared to all other dimensions.
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Classical Laminate Theory This requirements are fulfilled in a relatively thin or moderate thick laminate where the thickness is small compared to the in-plane extensions (length and width).
5.4.2. Analysis The following sections describe analysis using Classical Laminate Theory. Theor y. 5.4.2.1. Laminate Laminate Stiffness and Compliance Matrices 5.4.2.2. Normalized Normalized Laminate Stiffness and Compliance Matrices 5.4.2.3. Laminate Laminate Engineering Constants 5.4.2.4. Out-of-Plane Out-of-Plane Shear Moduli and Correction Factors 5.4.2.5. Polar Properties 5.4.2.6. Analysis Options
5.4.2.1. Laminate Stiffness and Compliance Matrices The laminate stiffness matrix is an 8 x 8 matrix that contains the ABD matrix (6 x 6) as well as the shear matrix C (2 x 2). (5.126)
The ABD matrix of the laminate is the stiffness matrix of the laminate. A is the in-plane stiffness matrix, B describes the coupling between in-plane forces and bending moments and D is the flexural stiffness stiffness matrix. The B matrix becomes 0 in the case of a symmetrically balanced laminate. In addition to the ABD terms the shear matrix C is evaluated as well. The shear matrix has form form
and
represent the
and
stiffness, respectively.
The compliance matrix is an 8 x 8 matrix that contains the inverse of the ABD matrix and the inverse
of the C matrix. The inverse inverse of the ABD is also called the abd matrix (ABD -1).
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Theory Documentation Figure 5.8: Relation Between ABD Matrix and the Coupling Between Laminate Forces and Deformations
5.4.2.2. Normalized Laminate Stiffness and Compliance Matrices The stiffness and compliance matrices can also be written in a normalized form where laminate thickness. thickness. The normalized stiffness matrices matrices ABD * are: • In-plane stiffness matrix:
is the
Coupling matrix: • Flexural stiffness matrix:
• Out-of-plane shear matrix: *
And the normalized compliance matrices abd are: • In-plane compliance matrix: • Coupling matrix:
384
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Classical Laminate Theory
• Flexural compliance matrix:
.
• Out-of-plane shear matrix:
5.4.2.3. Laminate Engineering Constants The laminate engineering constants are derived from the normalized compliance matrices which can be compared with the ply compliance matrix. Therefore the in-plane engineering constants are derived from the normalized in-plane compliance matrix: • Laminate stiffness:
• Laminate stiffness:
• Laminate shear stiffness:
and the out-of-plane shear terms are derived from the normalized shear compliance matrix: Shearr cor corre rect ctio ion n ffac acto tors rs:: • Shea
an and d k 55
• Out-of-plane shear stiffness:
• Out-of-plane shear stiffness:
And the flexural constants are derived from the normalized flexural compliance matrix: • Flexural laminate stiffness:
• Flexural laminate stiffness:
• Flexural laminate shear stiffness:
In the case of of coupling coupling between between in-plane in-plane and bending bending forces forces ( matrix has non-zero non-zero elements elements),), the engineering constants represents the case where the laminate is free to curve when loaded with in-plane forces.
5.4.2.4. Out-of-Plane Shear Moduli and Correction Factors The out-of-plane shear stiffness matrix C is is computed by:
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Theory Documentation where t i is the i -th -th ply thickness and G the i -th -th ply out-of-plane shear matrix (2x2) in the laminate coordinate system. The laminate out-of-plane shear stiffnesses
G31 and G23 are
overestimated by the first order shear
deformation This[ 44 can((p. overcome by using correction factors. ACP ACP uses the theory developed bytheory. Isaksson p.be529 529) ) ] to compute theshear out-of-plane shear correction factors k 44 and k 55. The final out-of-plane shear moduli are computed as:
where t is is the total laminate thickness. So the shear correction factors are already included in laminate properties computed by ACP. Figure 5.9: Laminate Properties with Out-of-Plane Shear Stiffness and Shear Correction Factors
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5.4.2.5. Polar Properties The polar plot shows the in-plane laminate engineering constants of the laminate ( , and ) rotated by 0 to 360 degrees. This plot highlights the anisotropy of the laminate and the influence of the orientation.
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General Interpolation Library
5.4.2.6. Analysis Options The options Offset is Middle and Consider Coupling Effect allow you to modify the evaluation of the laminate properties. • Offset is Middle: This option moves the reference plane of the laminate to the middle (default: True).
This option is useful since the layers in a FE analysis mostly have one offset direction and hence the reference plane is at the top or bottom of the laminate. This option reduces the coupling effect between in-plane and bending forces. It considers the results of the stiffness and compliance matrices, polar properties, and laminate engineering constants. • Consider Coupling Effect: The polar properties and laminate engineering constants constants are derived from
the laminate compliance matrix (inverse ABD matrix) where, by default, the coupling effect is considered
(default: True). This option allows you to neglect this effect which causes the polar properties properties and laminate engineering constants to represent the values of a symmetrically balanced laminate. Note that the coupling effect can significantly reduce the polar properties and laminate engineering constants.
5.5. General Interpolation Library The General Interpolation Library (GIL) is the interpolation engine used in ACP and a nd Mechanical APDL during Variable Variable Material Data analyses available with composite workflows. The following sections describe the available options and algorithms: 5.5.1. Algorithms 5.5.2. Options 5.5.3. Extrapolations Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Theory Documentation
5.5.1. Algorithms The General Interpolation Library (GIL) currently provides 3 interpolation algorithms: • Nearest-neighb Nearest-neighbor or (p. 388) multivariate variate (p. (p. 388) • Linear multi • Radial b basis asis (p. (p. 390)
The GIL is a suitable library for scattered data interpolation. For example, consider a set of materials testing results that represent the Young's modulus of a material at different temperatures and humidities. The test series will contain only a few combinations of temperature temperature and humidity at which an actual measurement was made. When transferring this testing data to Workbench Engineering Data and performing an analysis making use of this material, it is expected that Workbench makes reasonable guesses at the Young's modulus at intermediate combinations of temperature and humidity as the simulation is performed. Generally, the GIL interpolates a dependent variable, whichvariables: is only known at a few scattered points in the n-dimensional space of the independent (defining)
is the interpolation function. The set of points in the independent data space together with their given dependent variable values are called supporting points. The point in the independent space for which the dependent value is requested is called the query point. The GIL has no restriction on the dimensions of the independent data space. However, However, composite analyses with variable material data data are currently restricted to 9 dimensions. This means that properties such as Young's modulus can be controlled by up to 9 variables.
Note: The GIL is only suitable for interpolation of scalar quantities.
5.5.1.1. Nearest-Neighbor Interpolation
Given a query point, the nearest neighbor algorithm searches the supporting point with the smallest Euclidean distance to the query point and returns the corresponding dependent value:
where X is the set of all supporting points and q is the query point.
5.5.1.2. Linear Multivariate Interpolation The current implementation of the linear multivariate algorithm works as follows: 1. Triang Triangulat ulate e the independ independent ent variab variable le space. space.
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General Interpolation Library 2. Search the simplex simplex containing containing the query point point (or the closest closest simplex simplex to the query query point). point). 3. Span a hyperpla hyperplane ne through through n+1 vertices vertices (supporting (supporting points) of the this this simplex. simplex. 4. Evaluate Evaluate the dependent dependent value value along the hyperp hyperplane lane at the position position of the query query point. point. If the independent variable space is 2D, then this procedure is like finding the triangle containing the query point, then defining a plane in the third dimension through the dependent values of its three vertices, which are supporting points, and eventually reading out the dependent variable on the plane at the position of the query point. Another interpretation of this procedure are barycentric coordinates of the query point with respect to the vertices of the simplex spanned by the n+1 supporting points. This approach is well-known in finite element theory. Writing the query point
as a linear combination of the n+1 vertices vertices of the respective simplex:
and assuming a linear interpolation function
:
we find:
where is the dependent value of the supporting point of of the query point.
. The
are a function of the coordinates
More details can be found in [40] ((p. p. 529 529)). The following figure is an illustration of the linear multivariate algorithm for two independent fields, and . The dots represent the independent data which are provided. The dashed line represents the bounding bounding box. The simplex simplex containing containing the the query query point point x is visualized visualized with so solid lid lines. lines. the respective vertices of this simplex.
represent represent
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Theory Documentation Figure 5.10: Linear Multivariate Algorithm
5.5.1.3. Radial-Basis Algorithm Radial-basis interpolation is a global algorithm that is C1 continuous, especially useful for higherdimensional scatter data.
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Interpolation of the parameters is done by solving the following radial-basis function Z = f(X1, X2, X3… XO) at all input data points:
where N is the number of data points and O is the number of free variables (or the order of the interpolation). Input data is (xj,1, xj,2, …, zj) where j varies from 1 to N. The unknown values are ai (where i varies from 1 to N) and c. Z is the unknown and Xj refers to the query point. The equation is evaluated for all data points provided in the input to calculate the ai and c values. This algorithm is computationally intensive. Large data sets can affect performance adversely.
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Nomenclature
5.5.2. Options The GIL provides a set of options to control the interpolation process: Default MustData be specified for each independent variable. This value is assumed for incomplete queries, this is
if only a subset of the independent variables is specified for a query. Cache
If enabled, GIL caches interpolation results, which improves performance if multiple queries are made for the same query point. Will increase memory memory usage. Normalize
In order to set the different independent variable axes into perspective to each other, each axis is normalized when this option is turned on. The resulting normalized axes are given as:
where whe re
is the indepen independen dentt variabl variable, e, is the normali normalized zed inde indepen pendent dent variab variable, le, is the axis' axis' Lower Limit, and is the Upper Limit.
Normalization is relevant to all GIL algorithms. Lower and Upper Limit
These two values control the normalization of the independent variable axes. A reasonable choice for the upper and lower limit could span the typical range for the independent variable, for example.
5.5.3. Extrapolations The GIL constructs a bounding box around a round the independent data of the supporting points. Query points outside of this bounding box are projected to the bounding box before interpolation.
5.6. Nomenclature
Greek Symbols α β γ η ∆ ε ϑ κ ν σ
Coefficient of thermal expansion / Fracture angle in LaRC Coefficient of moisture expansion / Shearing angle in draping Shear strain, shear angle Coefficient of influence Load change Normal strain Third coordinate of the modified cylindrical coordinate system Curvature Poisson's ratio Normal stress
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Theory Documentation
τ φ ϕ
Shear stress
ξ, η , ζ
Principal stress/strain coordinate system
Misalignment angle Second coordinate of the cylindrical coordinate system
Latin Symbols Curve fitting parameter for Cuntze's failure criterion Components of the 3-D stiffness matrix Young's modulus Coefficients in quadratic failure criteria, stress space Interaction coefficient in the Tsai-Wu criterion Failure criterion function Shear modulus Toughness Toug hness ratio Moisture / humidity Thickness IRF
Inverse Reserve Factor
MoS
Margin of safety Interaction exponent for Cuntze's failure criterion Slope parameter for Puck's action plane criterion Shear failure stress in the 23-plane/Wrinkling coefficient Shear failure stress in the 13-plane/Midplane curvature radius Fracture resistance in Puck's action plane criterion Radial ordinate R+z
rd
Radius difference
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RF
Reserve Factor Shear failure stress/strain in the 12-plane Temperature Temp erature In-plane displacement in x, y-direction Failure stress/strain for isotropic material Through-the-thickness displacement Failure stress/strain in the 1-direction Global x-coordinate Failure stress/strain in the 2-direction Global y- and longitudinal coordinate of the cylindrical coordinate system
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Nomenclature Thickness coordinate 1, 2, 3
Ply principal coordinate system
Subscripts Core Compressive Delamination Exposure Effective Face sheet Bottom face sheet Top face sheet Fiber failure mode In-situ Matrix failure mode Supporting point number Tensile Perpendicular to fiber Parallel to fiber Wrinkling ,
Derivative
Superscripts Midplane strain Action plane
Under compression load Sum of temperature and moisture effects Longitudinal In misalignment frame coordinate system Under tension load / Transverse
Acronyms FF
Fiber Failure
IFF
Inter-fiber Failure
INS
Interlaminar Normal Stress
ISS
Interlaminar Shear Stress
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Theory Documentation LSoE
Linear System of Equations
UD
Unidirectional
393
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Chapter 6:The ACP Python Scripting User Interface The ACP Python Module provides the scripting user interface of ACP. ACP. 6.1. Introduction to ACP Scripting 6.2.The 6.2. The Python Object Tree 6.3. DB Database 6.4. Material Classes 6.5. Model Classes 6.6. Solid-model Classes 6.7. Solution Classes 6.8. Scene Classes 6.9. Postprocessing Definition Classes 6.10. Plot Classes
6.1. Introduction Introduction to ACP Scripting Basic Scripting The scripting language of ACP is i s Python which is an object oriented programming language. The user should have some basics experience in object oriented programming for the optimal use, but a basic script canView easily(p. written by modifying an existing one or copy and paste the History View (p. (p. 35) 35) or the Shell (pbe . 33) 33). . An example of one command is given below. In this command, the density of the material Corecell_A450 is defined (or modified if already defined) as 90.
db.models['class40.1'].material_data.materials['Corecell_A450']['density'].set(rho=90.0)
The easiest way to use scripting is to generate a script with the Graphical User Interface. Every action (p. 35) 35).. Use copy and paste to create your own performed via the GUI is written to the History View (p. scripts with a text editor. Save the scripts as *.py file and use the Run Script... functionality in the File ANSYS Composite PrepPost Menu Options (p. 11) Figure 1.3: ANSYS 11) to to run your script. In the case of error(s) check the Shell View (p. (p. 33) 33) for for more details.
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The ACP Python Scripting Scripting User Interface The aforementioned approach may be limited when it comes to retrieving solution results or specific (p. 396) 396) lists lists several examples of to how to access model information. information. The section Advanced Advanced Scripting (p. such information via a script.
Important: You cannot define any variable, class, or function with the name "db" because it is reserved for ACP core operations.
Advanced Scripting These examples are provided as a guide to more involved commands in the shell view. They all refer to the example model Workshop 6: Kiteboard. Kiteboard.
Maximum Layup Thickness # get active model model = db.active_model # get total thickness of all elements thicknesses = list(model.mesh_query(name='thickness',position='centroid',selection='all')) # get element labels labels = model.mesh_query(name='labels',position='centroid',selection='all') # get maximum thickness max_thickness = max(thicknesses) index_of_max = thicknesses.index(max_thickness) # get element label with max thickness element_label_with_max_thickness = labels[index_of_max]
Maximum Ply Thickness # get active model model = db.active_model # create new selection of all elements attached to a specific ply modeling_ply = model.modeling_groups['Core'].plies['mp_4'] model.select_elements(selection='sel0',op='new',attached_to=[modeling_ply]) # get total thickness of the first entity of selection sel0 thicknesses = list(model.mesh_q uery(name='thick ness',position=' centroid',select ion='sel0', # get element labels labels = model.mesh_query(name='labels',position='centroid',selection='sel0') # get maximum thickness
entities=[mode ling_pl
max_thickness = max(thicknesses) index_of_max = thicknesses.index(max_thickness) # get element label with max thickness element_label_with_max_thickness = labels[index_of_max]
Maximum Inverse Reserve Factor and Failure Mode # get active model model = db.active_model model.update() # get first solution solution = model.solutions.values()[0] # get the failure criterion definition fc_definition = model.definitions["FailureCriteria.MaxStrain_Core"] # get element labels labels = model.mesh_query(name='labels',position='centroid',selection='all') # get inverse reserve factors of all elements irfs = list(solution.query(definition=fc_definition,position='centroid',selection='all',component='irf')) # get failure modes of all elements
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DB Database failure_modes = solution.query(definition=fc_definition,position='centroid',selection='all',component='fm') # get the maximum IRF value max_irf = max(irfs) # get the index of maximum IRF index_of_max = irfs.index(max_irf) # get failure mode corresponding to maximum IRF critical_failure_mode = failure_modes[index_of_max] # get element label where the maximum IRF occurs element_label_of_max = labels[index_of_max]
Scripting Examples Review the following topics for additional scripting examples: 100) in in the Look-Up Tables section. • Look-Up Table with a Python Script (p. 100) (p. 223) 223) in in the User-Defined Plot section. • Example Example Scripts (p. forr an Expression Output Output (p. 231) 231) in in the Parameters section. • Settings fo • Evaluating Custom Failure Criteria (p. 237) 237) in in the Postprocessing section.
6.2.The Python Object Tree The ACP Python interface is organized as a static python object tree. This tree contains all loaded models, solutions, definitions, views and scenes. Access to the actually loaded object tree is always provided through the root object compolyx.DB in the embedded Python shell. An image of the python object tree appears only in the online help. If you are reading the PDF version of the help and want to see the figure, please access this section in the online help.
6.3. DB Database class compolyx.DB
Class to represent ComPoLyX database Access: >>> import compolyx >>> db = compolyx.DB()
active_model
Active model clear()
Clear database clear_generated_data (model=None)
Function clears the eventually stored update results and deletes the generated data such as Production and Analysis Plies, Solid Models etc.
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The ACP Python Scripting Scripting User Interface Parameters
-model: the ACP model to be cleared close(model=None)
Close model Parameters • model: model to close (optional) if no model is given all models were closed import_model(name, path, format, ignored_entities=None, convert_section_data=None, unit_sys-
tem_type=None, reference_surface_input_unit_system_type=None)
Create a model from file Parameters • name: Custom name of the model • path: Path to the data file • format: File format string. Choose one of ‘abaqus:inp’,’ansys:cdb’, ‘ansys:dat ’, ‘nastran:bdf ’, ‘ansys:h5’ • ignored_entities: Entities to ignore. Can be a subset of the following list: [ ‘mesh’, ‘element_sets’, ‘materials’, ‘coordinate_systems’, ‘shell_sections ’]
convert the shell section data into A ACP CP composite • convert_section_data: Whether to import and convert definitions. Default is false. • unit_system_type : Set the unit system of the model to this type. Ignored if a unit system was already
defined in the data file. • reference_surface_input_unit_system_type : Set the unit system of the reference surface if the unit
system cannot be read from the input material_data
Material Data Base
models
Models open(path, replace_workbench_inputs=None, pre_db=None, unit_system_type=None,
load_cached_data=False, apply_shared_commands=False)
Open ACP file and append the model to models container :Parameters: - path: Path to ACP file - replace_mesh_kwargs Optional keyword arguments to replace the mesh to load in db.import_model( …) upfront - replace_workbench_inputs Optional dictionary with Workbench inputs to replace before executing the .acp file open_h5(path, cache_data=False, apply_shared_commands=False)
Load a model from an ACPH5 database. Parameters
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Material Classes refresh_acph5(path, external_sources, input_parameters=None, initialize=False, unit_sys-
tem_type=None, upgrade_from=None)
Refresh an acph5 db (Workbench mode only) Parameters • path: file path to acph5 file • external_sources: nested dict provided by ACP WB Add-in containing all the
external sources info (the file path, whether the source was modified, its ID etc.). The keys of the dict are: [‘model’, ‘materials’, ‘cad_geometries’, ‘imported_solid_models ’, ‘pre_db’, ‘solutions’]. Values for ‘model’ and ‘materials’ are dicts with the following fields [ ‘path’, ‘external_id ’, ‘modified’]. Values for ‘cad_geometries’, ‘imported_solid_models ’ and ‘pre_db’ are list of dicts with fields [‘name’, ‘path’, ‘external_id ’, ‘modified’]. Values Values for for ‘solutions’ are dicts with fields [‘name’, ‘path’, ‘external_id ’, ‘modified’, ‘renumbering_mapping_paths’] where renumbering_mapping_paths is a list of file paths. • input_parameters: a dict of (name, value) pairs of WB input parameters. • initialize: specifies whether the acph5 database needs to be initialized (i.e. the file does not
yet exist). • unit_system_type: Defines the unit system of the main / downstream ACP file. (TODO: Do we need
this?) • upgrade_from: Defines the path of a legacy (.acp) ACP DB that has to be upgrade to the new format
(load composite definitions and save as ACPH5). reload (model) (model)
Reloads the reference surface (mesh) of the model. See reload_mesh in the model for more details Parameters
-model: the model to be reloaded save(path=None, model=None, cache_data=None)
Save active model
Parameters • path: file path • model: active model • cache_data: whether to store the update results or not. set_unit_system (unit_system_type) (unit_system_type)
Set the unit system of all models opened in the database
6.4. Material Classes This section contains the following topics: 6.4.1. MaterialData Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
The ACP Python Scripting Scripting User Interface 6.4.2. Material 6.4.3. Fabric 6.4.4. Stackup 6.4.5. SubLaminate
6.4.1. MaterialData class compolyx.MaterialData(graph, parent=None)
MaterialData manages all composite material data. copy(source, on_duplicate_name='keep_both')
copy a list of material data source, keeps track of all dependencies Parameters • source : a list of source of copy • on_duplicate_name
action to take if source.name is already contained in self.fabrics keep_both : create a new instance with the same name (different id) overwrite : replace first instance with equal name in self with source keep_existing : ignore copy action, returns first existing instance in self with equal name copy_fabric(source, on_duplicate_name='keep_both', memo=None)
Copy a fabric Parameters • source: Source object to copy • on_duplicate_name
action to take if source.name is already contained in self.fabrics keep_both : create a new instance with the same name (different id) overwrite : replace
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first instance with equal name in self with source keep_existing : ignore copy action, returns first existing instance in self with equal name • memo : a dict to collect copied items (for internal dependency tracking when copying stackups or
sub-laminates) Returns
New Instance of Fabric copy_material(source, on_duplicate_name='keep_both', memo=None)
Copy a material Parameters • source: Source object to copy
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Material Classes • on_duplicate_name
action to take if source.name is already contained in self.materials keep_both : create a new instance with the same name (different id) overwrite : replace first instance with equal name in self with source keep_existing : ignore copy action, returns first existing instance in self with equal name • memo : a dict to collect copied items (for internal dependency tracking when copying stackups or
sub-laminates) Returns
New instance of material copy_stackup(source, on_duplicate_name='keep_both', memo=None)
Copy a stackup Parameters • source: Source object to copy • on_duplicate_name
action to take if source.name is already contained in self.stackups keep_both : create a new instance with the same name (different id) overwrite : replace first instance with equal name in self with source keep_existing : ignore copy action, returns first existing instance in self with equal name • memo : a dict to collect copied items
Returns
New Instance of Fabric copy_sub_laminate(source, on_duplicate_name='keep_both', memo=None)
Copy a sub lamiante Parameters
• source: Source object to copy • on_duplicate_name
action to take if source.name is already contained in self.sub_laminates keep_both : create a new instance with the same name (different id) overwrite : replace first instance with equal name in self with source keep_existing : ignore copy action, returns first existing instance in self with equal name • memo : a dict to collect copied items
Returns
New Instance of sub laminate
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The ACP Python Scripting Scripting User Interface create_fabric(name, id=None, material=None, thickness=0.0, area_price=0.0, ignore_for_post-
processing=False, drop_off_material_handling='Global', cut_off_material_handling='Computed', drop_off_material=None, cut_off_material=None, draping_material_model='woven', draping_ud_coefficient=0.0)
Create a new fabric Parameters • name: Name for the Fabric • material: Material of the Fabric
Fabric • thickness: Thickness of the Fabric • area_price: Area Price of the Fabric • ignore_for_postprocessing: Flag if this material is post-processed • drop_off_material_handling: Type defining how drop-off material is used in drop-off areas of the
fabric • cut_off_material_handling: Type defining how cut-off material is used in cut-off areas of the fabric • drop_off_material: Material to use for ‘Custom’ drop-off material handling • cut_off_material: Material to use for ‘Custom’ cut-off material handling • draping_material_model: Material model for draping, either ‘woven’ or ‘unidirectional ’ • draping_ud_coefficient: Coefficient for the unidirectional draping material model
Returns
The created Fabric Examples >>> material_data = db.models['beam'].material_dat db.models['beam'].material_data a >>> fabric_1 = material_data.create_fabric(name='Fabric.1', material=material_data.materials['Mate material=material_data.materials['Material.1'], rial.1'],
create_material(name, id=None, ply_type='undefined', E1=0.0, E2=0.0, E3=0.0, G12=0.0, G31=0.0,
G23=0.0, nu12=0.0, nu13=0.0, nu23=0.0, rho=0.0, locked=False, ext_id=None)
Create a constant Material Parameters • name: Name of the new Material • ply_type: Type of the ply for the material. Allowed string values: regular, regular, woven, woven, orthotropic_homo-
geneous_core, isotropic_homogeneous_core, honeycomb_core, isotropic, adhesive, undefined. undefin ed. • E1 - rho: Material parameters
Returns
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Material Classes New Instance of Material create_stackup(name, id=None, fabrics=None, area_price=0.0, symmetry='No Symmetry', lay-
up_sequence='Top-Down', drop_off_material_handling='Global', cut_off_material_handling='Computed', drop_off_material=None, cut_off_material=None, draping_material_model='woven', draping_ud_coefficient=0.0)
Create a new Stackup Parameters • name: Name for the Stackup • fabrics: Fabrics of the Stackup • area_price: Area Price of the Stackup • symmetry: Symmetry the Stackup can be ‘No Symmetry ’, ‘Even Symmetry ’ or ‘Odd Symmetry ’
Top-Down’ or ‘Bottom-Up’ • layup_sequence: Layup sequence of the Stackup can be ‘ Top-Down • drop_off_material_handling: Type defining how drop-off material is used in drop-off areas of the
stackup • cut_off_material_handling: Type defining how cut-off material is used in cut-off areas of the stackup • drop_off_material: Material to use for ‘Custom’ drop-off material handling • cut_off_material: Material to use for ‘Custom’ cut-off material handling • draping_material_model: Material model for draping, either ‘woven’ or ‘unidirectional ’ • draping_ud_coefficient: Coefficient for the unidirectional draping material model
Returns
The created Stackup Examples
>>> material_data = db.models['beam'].material_dat db.models['beam'].material_data a >>> stackup_1 = material_data.create_stackup(name='Stackup.1', fabrics=(material_data.fabrics['Fab fabrics=(material_data.fabrics['Fabric.1'],), ric.1'],),
create_sub_laminate (name, id=None, fabrics=None, symmetry='No Symmetry', layup_se-
quence='Top-Down')
Create a new SubLaminate Parameters • name: Name for the Sub Laminate • fabrics: Fabrics of the Sub Laminate • symmetry: Symmetry the Sub Laminate can be ‘No Symmetry ’, ‘Even Symmetry ’ or ‘Odd Symmetry ’
Top-Down’ or ‘Bottom-Up’ • layup_sequence: Layup sequence of the Sub Laminate can be ‘ Top-Down
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The ACP Python Scripting Scripting User Interface Returns
The created SubLaminate Examples
>>> material_data = db.models['beam'].material_dat db.models['beam'].material_data a >>> sublaminate_1 = material_data.create_sub_laminate(name='SubLaminate.1', fabrics=(material_data.fabrics[' fabrics=(material_data.fabrics['
enabled
Whether MaterialData is currently enabled or not. export_matml(path, unit_system=None)
Export materials to ANSYS Engineering Data MatML format. Parameters • path: Path to file to write. • unit_system
Convert Conv ert all quantities quantities into this unit system. The units will be stored in the file written. The default is the unit system of the model.
fabrics
Dictionary with all fabrics defined. find_materials(**properties)
Find materials with the given properties or property ranges Parameters • properties: Arbitrary material properties which must be matched.
Note that a single property value can be given as string, number or min-max range Returns
A list with materials which match the given properties. If nothing matches an empty list is returned.
Examples >>> >>> >>> >>>
material_data = db.models['model.1'].material_ db.models['model.1'].material_data data materials = material_data.find_materials(E1=100000.0, material_data.find_materials(E1=100000.0, nu12=0.3) materials = material_data.find_materials( material_data.find_materials( name='1') materials = material_data.find_materials(E1=[200000.0, material_data.find_materials(E1=[200000.0, 220000.0], nu12=0.3, G12=[4500.0,5500.0])
import_matml(path, material_apdl_path='')
Import material data from MatML file as provided by Workbench Engineering Data. Parameters • path: File to read from. • material_apdl_path
Specify the APDL file containing the
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Material Classes ANSYS Engineering Data material definitions. material_apdl_path
Optional path to file with APDL material definitions to be used in the CDB export. materials
Dictionary with all materials defined. matml_path
Path to MatML file as provided by Workbench EngineeringData name
Currently a name is needed for every object in the db tree. serialize()
Serialize to Python string stackups
Dictionary with all stack ups defined. sub_laminates
Dictionary with all sub laminates defined. unit_system
Unit system of material data, propagated from model
6.4.2. Material This section contains the following topics: 6.4.2.1. PropertySet class compolyx.Material(graph, obj, parent=None)
ComPoLyX material class. This class allows to retrieve all material properties defined within the loaded Finite Element model.
Access >>> >>> >>> >>> >>> >>>
import compolyx db = compolyx.DB() model = db.models['class40.1'] materials = model.material_data.materials mat_UD300 = materials['UD300_GLAS'] print mat_UD300.property_names
[‘density ’, ‘engineering_constants ’, ‘larc_constants’, ‘puck_constants’, ‘strain_limits ’, ‘stress_limits’, ‘thermal_expansion_coefficients ’, ‘tsai_wu_constants ’, ‘woven_characterization’, ‘woven_puck_constants_1’, ‘woven_puck_constants_2’, ‘woven_stress_limits_1’, ‘woven_stress_limits_2’] >>> property_set_eng_const = mat_UD300['engineering_constants']
active_properties
List of the active properties for the underlying material.
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The ACP Python Scripting Scripting User Interface create_property_set (property_name, **kwargs)
Function to create a specific property set. Parameters • property_name: A string defining the PropertySet to be created.
Key word arguments can be passed to define the constant properties of the newly created PropertySet. If the property already exists, it will be overwritten with the new data. Example >>> m = db.active_model >>> mat = m.material_data.materials['Corecell_A450'] >>> mat.create_property_set('density', rho=2150.0)
delete_property_set (property_name)
Function to delete a specific property set. Parameter • property_name: String defining the PropertySet to be deleted. ext_id
Id of corresponding Material in external source. is_constant
True if engineering constants are constant. is_isotropic
True if ply_type is isotropic or isotropic_homogeneous_core. link_path
Root path of the current node in the tree for links to this object locked
Material is generated from an external source and cannot be changed.
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ply_type
Ply type. Allowed string values: regular, woven, orthotropic_homogeneous_core, isotropic_homogeneous_core, honeycomb_core, isotropic, adhesive, undefined property_names
List with all available property keys. serialize()
Serialize to Python string
6.4.2.1. PropertySet class compolyx.PropertySet(gil_wrapper, parent_=None, name_='')
Python PropertySet class.
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Material Classes This class wraps GIL-functionality and adds Python-UI utilities to all material PropertySets (Engineering Constants, Stress Limits, …). Examples >>> >>> >>> >>>
model = db.active_model Eglas = model.material_data.materials['E-Glas'] Eglas_strain_limits = Eglas['strain_limits'] print Eglas_strain_limits.property_names
[‘eXt’, ‘eXc’, ‘eYt’, ‘eYc’, ‘eZt’, ‘eZc’, ‘eSxy ’, ‘eSxz ’, ‘eSyz’, ‘effective_strain’] >>> Eglas.update() >>> Eglas_Xt = Eglas_strain_limits.query('eXt', {'UserVar1' : 0.3, 'Temperature' : 65.7})
get(variables=None)
Get raw PropertySet data. For puck_constants and woven_characterization the Puck Material Classification can be retrieved. Parameters • variables: Optional string of variable to be retrieved (property or envrionment variable). If this
string is set to mat_type the Puck Material Classification is returned if available. Returns • If no variable was specified, all PropertySet raw data will be returned in dictionary-form. If a variable
was specified, then only this data will be returned. Examples >>> m = db._active_model() >>> mat = m.material_data.materials['Corecell_A450'] m.material_data.materials['Corecell_A450'] >>> gil_data = mat['engineering_constants'].get() mat['engineering_constants'].get()
>>> m = db._active_model() >>> mat = m.material_data.materials['Corecell_A450'] m.material_data.materials['Corecell_A450'] >>> mat_type = mat['puck_constants'].get('mat_type') mat['puck_constants'].get('mat_type')
>>> m = db._active_model()
>>> mat = m.material_data.materials['Corecell_A450'] m.material_data.materials['Corecell_A450'] >>> E1_data = mat['engineering_constants'].get('E1') mat['engineering_constants'].get('E1')
independent_names
List of the independent variable names. is_constant
True if the Engineering Constants of this material are constant. property_names
Propety name list.
query(variables=None, environment_point=None)
Query PropertySet data. The available property names on this PropertySet can be retrieved through property_names.
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The ACP Python Scripting Scripting User Interface An empty query returns all properties at the default environment point in dictionary-form. If the PropertySet is not up-to-date, zeros are returned and a warning is thrown. Parameters • variables: String or list of strings that defines which properties to query for. If a list of properties
is provided, the returned list of results retains the order of properties. • environment_point: Dictionary defining at which environment state the queried properties are requested. The dictionary takes the form {Var1 { Var1 : value_1, …}. For unspecified environment variables,
their default value is assumed. Unkown environment variables will be ignored. Examples >>> m = db._active_model() >>> mat = m.material_data.materials['Corecell_A450'] m.material_data.materials['Corecell_A450'] >>> data = mat['engineering_constants'].query() mat['engineering_constants'].query()
>>> m = db._active_model() >>> mat = m.material_data.materials['Corecell_A450'] m.material_data.materials['Corecell_A450'] >>> data = mat['engineering_constants'].query(['E1', 'E3'], {'Temperature' : 25.73, 'Shear Angle' : 1.8})
set(props=None, **kwargs)
Set constant and variable material data. Constant properties can be given as keyword arguments. Parameters • props: A dictionary or tuple of two dictionaries defining the data
Examples >>> >>> >>> >>>
m = db._active_model() mat = m.material_data.materials['Corecell_A450'] m.material_data.materials['Corecell_A450'] data_dict = {'Xc' : 5.1, 'Sxy':0.3} mat['stress_limits'].set(dat mat['stress_limits'].set(data_dict) a_dict)
>>> mat['stress_limits'].set(Xc= mat['stress_limits'].set(Xc=5.1,Sxy=0.3) 5.1,Sxy=0.3)
>>> >>> >>> >>>
m = db._active_model() mat = m.material_data.materials['Corecell_A450'] m.material_data.materials['Corecell_A450'] data_dict = ({'rho' : [1000.0, 1020.5, 1025.0]}, {'Temperature' : ([22., 50., 150.], 25.)}) mat['density'].set(data_dict mat['density'].set(data_dict) )
6.4.3. Fabric class compolyx.Fabric(graph, obj, parent=None)
Class to represent fabric area_price
Area price of fabric area_weight
Area weight of fabric Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Material Classes clt_query(query='laminate_properties')
Returns the properties of the classical laminate theory: Parameters • query: result type
Options
laminate_prop _properties: erties: Young’s, flexural and shear moduli of the laminate • laminate • polar_properties: E1, E2 and G12 depending on the laminate orientation
Example >>> fab.clt_query(query='polar_pro fab.clt_query(query='polar_properties') perties')
create_plot(query={'polar_properties': ['E1', 'G12']})
Generates 2D-plots with the results of interest Parameters • query: query arguments
Options • layup:[‘pp’] Production plies • polar_properties:[ ‘E1’,’E2’,’G12’] polar plot of laminate stiffess • text_plot:[‘materials’, ‘angles’, ‘thicknesses ’]
Examples
>>> query={'polar_properties':['E1', 'G12'], layup:['pp'], text_plot:['materials', 'angles', 'thicknesses']}
cut_off_material
Cut-off material used in cut-off areas of this fabric.
cut_off_material_handling
Type defining how cut-off material is used in cut-off areas of this fabric. Types: [‘Computed’, ‘Global’, ‘Custom’] draping_material_model
Draping material model. draping_ud_coefficient
UD draping coefficient drop_off_material
Drop-off material used in drop-off areas of this fabric. drop_off_material_handling
Type defining how drop-off material is used in drop-off areas of this fabric. Types: [‘Global’, ‘Custom’]
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The ACP Python Scripting Scripting User Interface graph_plot
Graph Plot object used to configure 2D plots. ignore_for_postprocessing
Flag if this material is NOT post-processed. is_constant()
Returns True if all engineering constants and strength limits of the assigned material are constant. material
Material of the fabric serialize()
Serialize to Python string thickness
Thickness of fabric update_plot Updates the()2D plot
Note: The coupling effect is always neglected (which is anyway 0 for a single fabric)
6.4.4. Stackup class compolyx.Stackup(graph, obj, parent=None)
Class to represent stack-up add_fabric(fabric, angle=0.0)
Add fabric at end of fabrics of the Stackup area_price
Price per area of the Stackup
area_weight
Area weight of the Stackup
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clear_fabrics()
Clear all fabrics clt_query(query='laminate_properties')
Returns the properties of the classical laminate theory Parameters • query: query parameters
Options • layup: Return the layup
laminate_prop _properties: erties: Young’s, flexural and shear moduli of the laminate • laminate
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Material Classes • polar_properties: E1, E2 and G12 depending on the laminate orientation • stiffness_matrix: Returns the laminate stiffness matrix (ABD) • compliance_matrix: Returns the lamiante compliance matrix (inverse of ABD)
Example >>> stackup.clt_query(query='lamin stackup.clt_query(query='laminate_properties') ate_properties')
create_plot(query={'layup': ['pp', 'ap'], 'polar_properties': ['E1', 'G12']}, core_scale_factor=None)
Generates 2D-plots with the results of interest Parameters • query: Query parameters • core_scale_factor: Scale core thickness by this value.
Options • layup:[‘pp’, ‘ap’] Production Ply and Analysis Plies • polar_properties:[ ‘E1’,’E2’,’G12’] polar plot of laminate stiffesses • text_plot:[‘materials’,’angles’,’thicknesses ’] property to show as label in the layup plot
Examples >>> query={'polar_properties':['E1', 'G12'], layup:['pp'], text_plot:['materials']}
cut_off_material
Cut-off material used in cut-off areas of this Stackup. cut_off_material_handling
Type defining how cut-off material is used in cut-off areas of this stackup. Types: [‘Computed’, ‘Global’, ‘Custom’]
draping_material_model
Draping material model. draping_ud_coefficient
UD Draping Coefficient drop_off_material
Drop-off material used in drop-off areas of this Stackup. drop_off_material_handling
Type defining how drop-off material is used in drop-off areas of this stackup. Types: [‘Global’, ‘Custom’]
fabrics
Fabrics property of the Stackup get_ordered_fabrics ()
Returns all fabrics and orientations including symmetry and layup sequence option. Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
The ACP Python Scripting Scripting User Interface graph_plot
Graph Plot object used to configure 2D plots. insert_fabric(pos, fabric, angle)
Insert fabric at given position is_constant()
Returns True if all engineering constants and strength limits of the assigned fabrics are constant. layup_sequence
Layup Sequence of the Stackup can be ‘ Top-Down Top-Down’ or ‘Bottom-Up’ remove_fabric(pos)
Remove fabric from position Parameters • pos: Position of the Fabric to remove serialize()
Serialize to Python string symmetry
Symmetry of the Stackup can be ‘No Symmetry’, ‘Even Symmetry’ or ‘Odd Symmetry’ thickness
Thickness of the Stackup update_plot()
updates the data of the 2D plot
6.4.5. SubLaminate class compolyx.SubLaminate(graph, obj, parent=None)
Class to represent sub-laminate
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add_fabric(fabric, angle=0.0)
Add fabric at end of fabrics list area_price
Price per area of the Sub Laminate area_weight
Area weight of the Sub Laminate clear_fabrics()
Clear all fabrics
clt_query(query='laminate_properties')
Returns the properties of the classical laminate theory Parameters
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Material Classes • query: result type
Options • layup: Return the layup of the laminate
laminate_prop _properties: erties: Young’s, flexural and shear moduli of the laminate • laminate • polar_properties: E1, E2 and G12 depending on the laminate orientation • stiffness_matrix: Returns the laminate stiffness matrix (ABD) • compliance_matrix: Returns the lamiante compliance matrix (inverse of ABD)
Example >>> sub.clt_query(query='layup')
create_plot(query={'layup': ['mp', 'pp', 'ap'], 'polar_properties': ['E1', 'G12']}, core_scale_factor=None)
Generates 2D-plots with the results of interest Parameters • query: query parameters • core_scale_factor: Scale core thickness by this value.
Options • layup:[‘mp’, ‘pp’, ‘ap’] Modeling Ply, Production Plies and Analysis Plies • polar_properties:[ ‘E1’,’E2’,’G12’] polar plot of laminate stiffesses • text_plot:[‘materials’,’thicknesses’,’angles’] text plot shown in the layup plot
Example >>> query={'polar_properties':['E1', 'G12'], layup:['pp'], text_plot:['materials']}
fabrics
Fabrics property of the Sub Laminate get_ordered_fabrics ()
Returns a list with all sub materials (fabrics and stackups) and orientations including symmetry and layup sequence option. get_ordered_sub_materials ()
Returns a list with all fabrics and orientations including symmetry and layup sequence option. graph_plot
Graph Plot object used to configure 2D plots. insert_fabric(pos, fabric, angle)
Insert fabric at given position
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The ACP Python Scripting Scripting User Interface is_constant()
Returns True if all engineering constants and strength limits of the assigned fabrics are constant. layup_sequence
Layup Sequence of the Sub Laminate can be ‘ Top-Down Top-Down’ or ‘Bottom-Up’ remove_fabric(pos)
Remove fabric from position serialize()
Serialize to Python string symmetry
Symmetry of the Sub Laminate can be ‘No Symmetry’, ‘Even Symmetry’ or ‘Odd Symmetry’ thickness
Thickness of the Sub Laminate update_plot()
Updates the data of the 2D plot
6.5. Model Classes This section contains the following topics: 6.5.1. Model 6.5.2. Rosette 6.5.3. LookUpTableBase 6.5.4. LookUpTable1D 6.5.5. LookUpTable3D 6.5.6. LookUpTableColumn 6.5.7. ElementSelectionRule Classes 6.5.8. EntitySet Classes
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6.5.9. Geometry Classes 6.5.10. OrientedSelectionSet 6.5.11. ModelingGroup 6.5.12. ModelingPly 6.5.13. ProductionPly 6.5.14. AnalysisPly 6.5.15. InterfaceLayer 6.5.16. ButtJointSequence 6.5.17. FieldDefinition 6.5.18. SamplingPoint 6.5.19. SectionCut 6.5.20. Sensor
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Model Classes 6.5.21. PlyBook
6.5.1. Model class compolyx.Model(name=None, path=None, format=None, ignored_entities=None,
graph=None, parent=None, convert_section_data=False, unit_system_type=None, reference_surface_input_unit_system_type=None, cache_data=False) Class to represent a finite element model Access: >>> import compolyx >>> db = compolyx.DB() >>> model = db.import_model(name='class40.1', path='class40.cdb', format='ansys:cdb')
Get existing model: >>> class40_model = db.models['class40.1']
active_scene
Active Scene add_solution(name, id='', path=None, path2=None, format='ansys:rst', subcase=False, 0, set=- 1,
load_factor=False, 0.0, read_stresses_strains=True, use_felyx_to_compute_pp_results=True, use_solid_results=True, recompute_iss_of_solids=False, renumbering_mapping_paths=[], ext_id='', active=True)
Load a nodal solution from file(s) and add it to the model Parameters • name: Custom name of the solution • path: Path to the data file • path2: Optional path to second result file. Useful for ANSYS PRNSOL solution, where nodal deform-
ations and nodal rotations can be exported to different files only.
• format: File format string. Choose one of ‘abaqus:fieldreport ’, ‘ansys:prnsol ’,’ansys:rst ’ or ‘nastran:f06 ’ • subcase: Optional subcase to read. Only valid for ‘nastran:f06’ format. (False,0) if not given in the
F06 file. • load_factor: Optional load factor within substep of non-linear solution where the nodal solution should be taken from. Only valid for ‘nastran:f06’ format. (False,0) if not given in the F06 file. • set: Result set for ANSYS RST files, None is last result set • read_stresses_strains: Reads strain and stress results from the RST file (necessary to post-process
non-linear solutions) • ‘use_felyx_to_compute_pp_results’: Use ACP to compute strain and stress data • use_solid_results: Mapps solid element solution onto ‘Layered Solid Reference Surface’
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The ACP Python Scripting Scripting User Interface • recompute_iss_of_solids: For solids the interlaminar shear stresses are recalculated considering the
laminate stacking • renumbering_mapping_paths: List of paths of the assembly renumbering files used to map the
results of composite assemblies • active: Active/inactive flag Returns
The new Solution instance just added to the model analysis_model_path
Analysis model file path angle_tolerance
Section computation angle tolerance (in degree) average_element_size ()
Average element size of the model cache_update_results
Define whether to store the update results or not. copy_combined_failure_criteria (source)
Copy a Combined Failure Criteria Definition Parameters • source: Source object to copy
Returns
New instance of Combined Failure Criteria Definition copy_edge_set(source)
Copy a edge set :Parameters: - source: Source object to copy
Returns
New instance of edge set copy_element_set(source)
Copy a element set Parameters • source: Source object to copy
Returns
New instance of element set copy_field_definition (source)
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Model Classes Parameters • source: Source object to copy
Returns
New instance of FieldDefinition copy_lookup_table(source)
Copy a Look-up Table Parameters • source: Source object to copy
Returns
New instance of a Look-Up Table copy_oriented_selection_set (source)
Copy an oriented element set Parameters
• source: Source object to copy
Returns
New instance of oriented element set copy_rosette(source)
Copy a Rosette Parameters • source: Source object to copy
Returns
New instance of Rosette copy_sampling_point (source)
Copy a sampling point Parameters • source: Source object to copy
Returns
New instance of a sampling point copy_section_cut(source)
Copy a section cut
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The ACP Python Scripting Scripting User Interface Parameters • source: Source object to copy
Returns
New instance of a section cut copy_selection_rule (source)
Copy a rule Parameters • source: Source object to copy
Returns
New instance of rule copy_sensor(source)
Copy a sensor Parameters
• source: Source object to copy
Returns
New instance of a sensor copy_solid_model(source)
Copy a solid model Parameters • source: Source object to copy
Returns
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New instance of a solid model create_boolean_selection_rule (name, id=None, include_rule_type=True, selection_rules=[])
Create new Boolean Selection Rule Parameters • name: Name of the Rule • id: ID of the Rule • include_rule_type: Whether the rule is of type include or exlude • selection_rules: list of tuples of attached rules and operation type
Returns
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Model Classes The created Boolean Selection Rule create_combined_failure_criteria (name, set=[], id=None)
Create Combined Failure Criteria Parameters • name: Name for the Combined Failure Criteria • set: set of Failure Criteria to be assigned • id: id to be assigned (optional)
Returns • created Combined Failure Criteria create_cutoff_selection_rule (name, id=None, cutoff_rule_type='geometry', offset=0.0,
angle=0.0, origin=0.0, 0.0, 0.0, direction=1.0, 0.0, 0.0, distance_type='along_direction', ply_cutoff_type='production_ply_cutoff', ply_tapering=False, cutoff_geometry=None, edge_set=None, offset_method='laminate_stack', offset_type='out_of_plane')
Create new Cut-off Rule Parameters • name: Name of the rule • cutoff_rule_type: geometry, taper, or variable_taper • offset: Offset of the rule (float for cutoff_rule_type=`geometry` or taper, LookUpTableColumn for
cutoff_rule_type=`variable_taper`) • angle : Angle of the rule (ignored for cutoff_rule_type=`geometry`, float for taper, LookUpTableColumn
for variable_taper) • origin : Origin of the offset and angle interpolation for variable_taper
• direction : Direction of the offset and angle interpolation for variable_taper • distance_type : along_direction or along_edge (only relevant for variable_taper) • ply_cutoff_type: Determines on which ply level the cutoff is done. • ply_tapering: Use ply tapering • cutoff_geometry: CADGeometry for the rule (only relevant for cutoff_rule_type=`geometry`) • edge_set: Edge Set for cutoff_rule_type=`taper` or variable_taper • offset_method : Method to compute offset of plies laminate_stack or attached_plies • offset_type : Measure offset from edge set normal to element reference surface (out_of_plane) or
in element reference surface (in_plane) Returns
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The ACP Python Scripting Scripting User Interface The created rule create_cylindrical_selection_rule (name, id=None, origin=None, direction=None, radi-
us=None, relative_rule_type=False, include_rule_type=True, rosette=None, use_global_coordinate_system=None) Create new Cylindrical Selection Rule Parameters • name: Name of the rule • origin: Origin of the Cylindircal Rule • direction: Direction of the Cylindircal Rule • radius: Radius of the Cylindircal Rule • relative_rule_type: If True parameters are evaluated relative to size of the object • include_rule_type: Include or Exclude area in rule • use_global_coordinate_system: Use global coordinate system to define rule parameters • rosette: Rosette used if use_global_coordinate_system is False
Returns
The created Cylindircal Rule create_edge_set(name, id=None, origin=0.0, 0.0, 0.0, limit_angle=- 1.0, edge_set_type='By Ref-
erence', element_set=None, node_labels=[], show=False)
Create new Edge Set Parameters • name: Name of the Edge Set
edge_set_type: By Nodes Nodes,, By Reference, Reference , Imported (only for imported Edge Sets) • origin: Origin • limit_angle: • element_set: element set • node_labels: list of nodes defining the edge set (only if edge_set_type= ’By Nodes’)
Returns
The created Edge Set create_element_set (name, id=None, element_labels=None, element_sets=None, x=None, y=None,
z=None, op='new', middle_offset=False, show=False)
Create new element set
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Model Classes Parameters • name: Name of the Element Set •
element_labels: Indices of elements to be assigned to Element Set • element_sets: Select elements of these sets • x: X-range to select. • y: Y-range to select. select. • z: Z-range to select. • op: Select operation. Can be all, new (default), add, remove, intersect, inverse or none • middle_offset: Boolean to enforce that the laminate mid-plane is moved onto the reference surface.
Returns
The created Element Set If element set already exists, it is updated depending on the operation given in op. create_envelope_solution (name, id=None, solution_sets=[])
Create Envelope Solution Parameters • name: Name for the Envelope Solution • solution_sets: list of Solution Sets that are combined
Returns
The new envelope solution s olution object create_field_definition (name, id=None, field_variable_name=None, scope_entities=None,
scalar_field=None, full_mapping=False, active=True, locked=False)
Create a new Field Definition Parameters
element set • name: The name of the oriented element oriented ted elemen elementt set. • id: The id of the orien • field_variable: String identifier of the field • scope_entities: A list of scope entities defining the region of definition • scalar_field: Tabular scalar column defining the field • full_mapping: Bool. Whether offsets are to be included during the interpolation process
Returns Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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The ACP Python Scripting Scripting User Interface The created Field Definition Def inition create_geometrical_selection_rule (name, geometrical_rule_type='geometry', id=None,
use_defaults=True, in_plane_capture_tolerance=0.0, neg_capture_tolerance=0.0, pos_capture_tolerance=0.0, include_rule_type=True, geometry=None, use_projection_normal=False, projection_normal=0.0, 0.0, 0.0, element_sets=None)
Create new Geometrical Selection Rule Parameters • name: Name of the Rule • geometrical_rule_type: Define whether the rule extent is defined by a geometry of element sets. The value can be ‘geometry ’ or ‘element_sets’. Default is ‘geometry. • use_defaults: Whether to use the offset value of the CAD geometry. • in_plane_capture_tolerance: In-plane extend (extend) if CAD geometry is a surface. • neg_capture_tolerance: Offset in the negative direction if CAD geometry is a surface. • pos_capture_tolerance: Offset in the positive direction if CAD geometry is a surface. • include_rule_type: Whether the selection is inside or outside the CAD geometry • geometry: CAD geometry used to determine the selection (only relevant for geometric-
al_rule_type=`geometry`) • use_projection_normal: Boolean wheter to use the projection normal or not. • projection_normal: Normal direction used to map elements on outlines / curves • element_sets: Preselection of elements in the form of an element set where the rule is applied on
(only relevant for geometrical_rule_type=`element_sets`) Returns
The created rule create_imported_solid_model (name, id='', active=True, element_sets=None, extern-
al_file_path=None, unit_system='undefined', format='ansys:cdb', ext_id='', mapping_type='structured_mesh', rosette_selection_method_type='minimum_distance', use_default_element_index=True, element_index=0, use_default_node_index=True, node_index=0, use_default_section_index=True, section_index=0, use_default_material_index=True, material_index=0, use_default_coordinate_system_index=True,, coordinate_system_index=0, use_solsh_elements=False, drop_hanging_nodes tem_index=True drop_hanging_nodes=True =True,, use_solid_model_prefix=True, write_degenerated_elements=True, delete_lost_elements=True, delete_lost _elements=True, scale_ply_thicknesses=True, all_plies=True, sequences=[], rosettes=[], minimum_void_material_thickness=- 1.0, void_material=None, filler_material=None, global_cut_off_material=None, transfer_all_sets=True, transferred_element_sets=[], transferred_edge_sets=[], locked=False, from_pre=False)
Create a new Solid Model Parameters
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Model Classes Model • name: The name of the Solid Model the e Solid Model Model • id: The id of th • active : Active status of the solid model • element_sets: a list of Element Sets • external_file_path: File path to the external source • unit_system: Unit system of the imported mesh • format: File format of the external source • mapping_type: Mapping method • use_default_element_index : consecutive element numbering if set to true • element_index : start index for first element (only relevant if use_default_element_index) • use_default_node_index : consecutive node numbering if set to true • node_index : start index for first node (only relevant if use_default_node_index) • use_default_section_index : consecutive section numbering if set to true • section_index : start index for first element (only relevant if use_default_section_index) • use_default_material_index : consecutive material numbering if set to true • material_index : start index for first element (only relevant if use_default_material_index) • use_default_coordinate_system_index : consecutive coordinate system numbering if set to true • coordinate_system_index : start index for first coordinate system (only relevant if use_default_co-
ordinate_system_index) • use_solsh_elements : the solid model is created out of solsh elements
• drop_hanging_nodes: whether to skip mid-side nodes that are not shared by adjacent elements.
Only relevant when the object has applies cut-off geometries and a quadratic mesh. • use_solid_model_prefix : the name of the solid model is used as a prefix for all components written
to the *cdb file • write_degenerated_elements : If false, degenerated (homogeneous) elements are not exported • delete_lost_elements : Delete elements which are outside the laminate • filler_material : Global filler material which is assigned to the elements without any layers • rosette_selection_method_type : Defines the mapping method for the selected rosettes • scale_ply_thicknesses : Scale plies within layered solid element if they do not fill the entire element,
else add void layers
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The ACP Python Scripting Scripting User Interface • all_plies : Whether all plies of the selected scope should be mapped or only specified sequences • sequences : List of Modeling Groups and/or Modeling Plies which are mapped onto the element
scope • rosettes : List of rosettes used to orient the lost elements • minimum_void_material_thickness : Specifies the minimum thickness of void layers. Default is equal
to the minimum analysis ply thickness of the model. • void_material : Global void material which is assigned to layered elements that are not fully filled
with ply material • global_cut_off_material : Defines the global cut-off material • transfer_all_sets: defines whether all edge and element sets should be transferred to the solid
model. • transferred_element_sets: element sets to transfer to the solid model if transfer_all_sets is set to
false. • transferred_edge_sets: edge sets to transfer to the solid model if transfer_all_sets is set to false.
Returns
The created Solid Model create_lookup_table1d (name, (name, id='', tabular_data=None, origin=None, direction=None, dimen-
sions=[])
Create a new 1D Look-Up Table object Parameters • name : Name • id : ID
Returns
The created Look-Up Table object create_lookup_table3d (name, (name, id='', tabular_data=None, use_default_search_radius=True,
search_radius=0.0, num_min_neighbors=1, dimensions=[])
Create a new 3D Look-Up Table object Parameters • name : Name • id : ID
Returns
The created Look-Up Table object
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Model Classes create_oriented_selection_set (name, id=None, orientation_point=0.0, 0.0, 0.0, orienta-
tion_direction=0.0, 0.0, 0.0, element_sets=None, geometries=None, rosettes=None, rosette_selection_method='minimum_angle', selection_rules=None, draping=False, draping_seed_point=0.0, 0.0, 0.0, auto_draping_direction=True, draping_direction=0.0, 0.0, 1.0, draping_mesh_size=False, draping_material_model='woven', draping_ud_coefficient=0.0, reference_direction_field=None)
Create a new Oriented Selection Set Parameters
• name: The name of the oriented element element set
oriented ted elemen elementt set. • id: The id of the orien • orientation_point: Orientation Point for the Oriented Selection Set • orientation_direction: Orientation Direction for the Oriented Selection Set • element_sets: Element Sets
geometries: ries: Virtual geometries geometries • geomet • rosettes: Rosettes for the Oriented Selection Set • rosette_selection_method: Method to calculate element orientation (‘minimum_angle’, ‘maximum_angle’, ‘minimum_distance’, ‘minimum_angle_superposed ’, ‘minimum_distance_superposed ’, ‘maximum_angle_superposed ’, ‘ansys_classic ’, or ‘tabular_values’)
reference directions • reference_direction_field: Table column used to compute reference • draping: Draping enabled • draping_seed_point: Seed Point used to start draping • draping_direction: Direction for draping • auto_draping_direction: Generate direction for draping
• draping_mesh_size: Mesh size for draping • draping_material_model: Material model for draping, either ‘woven’ or ‘unidirectional ’ • draping_ud_coefficient: Coefficient for the unidirectional draping material model
Returns
The created Oriented Selection Set create_parallel_selection_rule (name, id=None, origin=None, direction=None, pos_distance=None, neg_distance=None, relative_rule_type=False, use_global_coordinate_system=None, rosette=None, include_rule_type=True)
Create new Parallel Selection Rule Parameters • name: Name of the Rule
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The ACP Python Scripting Scripting User Interface • origin: Origin of the Parallel Selection Rule • direction: Direction of the Parallel Selection Rule • pos_distance: Positive Disance of the Parallel Selection Rule • neg_distance: Negative Distance of the Parallel Selection Rule • relative_rule_type: If True parameters are evaluated relative to size of the object • use_global_coordinate_system: Use global coordinate system to define rule parameters • rosette: Rosette used if use_global_coordinate_system is False • include_rule_type: Include or Exclude area in rule
Returns
The created Parallel Selection Rule create_published_parameter (name, source_object=None, source_property='', user_script='',
category='input', acp_type=None, description='', lower_limit=None, upper_limit=None, cyclic=False, float_list=[], string_list=[])
Create published parameter create_rosette(name, id=None, origin=0.0, 0.0, 0.0, dir1=1.0, 0.0, 0.0, dir2=0.0, 1.0, 0.0,
rosette_type='PARALLEL', edge_set=None, show=False)
Create a new rosette Parameters
Rosette • name: The name of the Rosette • id: ID (optional) • origin: The origin of the Rosette Rosette
• dir1: Direction 1 of the Rosette • dir2: Direction 2 of the Rosette • rosette_type: Type of the Rosette ( ‘PARALLEL’, ‘RADIAL’, ‘CYLINDRICAL’, ‘SPHERICAL’, ‘EDGE_WISE’
) • edge_set: Edge Set to be used in Rosette • show : Whether the newly created rosette is shown in the scene / the 3D window or not
Returns
The created Rosette Example >>> rosette_1 = model.create_rosette('Rosette.1', model.create_rosette('Rosette.1', origin=(0.,0.,0.),
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Model Classes
dir1=(1.,0.,0.), dir2=(0.,1.,0.), rosette_type='PARALLEL')
create_sampling_point (name, id=None, point=0.0, 0.0, 0.0, direction=0.0,consider_coupling_ef0.0, 0.0, locked=False, use_default_reference_direction=True, rosette=None, offset_is_middle=True, fect=True, solution_set=None)
Create new Sampling Point Parameters • name: Name of the Sampling Point • point: Sampling point • direction: Sampling direction • use_default_reference_direction: whether to use the default reference direction for the evaluation • rosette: Rosette used for the evaluation of the reference direction • offset_is_middle: Specifies the offset of the reference plane used for the CLT analyses • consider_coupling_effect: Specifies whether the laminate properties are evaluated considering the
coupling effect (B matrix) or not • solution_set: Specifies the solution and the set of the element-wise post-processing. Note, this must
be given as a tuple. Returns
The created Sampling Point create_scene(name, id=None, title='', active_set=None, projection='perspective', scale_factor=1.0, show_draped_fiber_directions=False, show_draped_transverse_directions=False, show_edges=False, show_fiber_directions=False, show_global_coordinate_system=True, show_legend=True show_legend=True,, show_normals=False, show_orientations=False, show_ref_directions=False, show_selec-
ted_mesh=False, show_section_cut_plots=False, show_solid_elements=False, show_surface=True, show_transverse_directions=False, continuous_pick_enabled=False, show_material_1_directions=False)
Create a new scene Paramter • name: Name of the scene
deformed mesh • show_deformed_mesh: Whether to show the deformed • show_undeformed_mesh: Whether to show the undeformed mesh • scale_factor: Scale factor of the deformed mesh
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The ACP Python Scripting Scripting User Interface create_section_cut (name, id=None, origin=0.0, 0.0, 0.0, normal=0.0, 0.0, 1.0, in_plane_refer-
ence_direction1=1.0, 0.0, 0.0, scale_factor=1.0, core_scale_factor=1.0, intersection_type='normal_to_surface', section_cut_type='modeling_ply_wise', extrusion_type='wire_frame', use_default_tolerance=True, tolerance=0.0, use_default_lut_settings=True, search_radius=0.0, number_of_interpolation_points=1, locked=False)
Creates a new section cut Parameters
• name: The name of the section section cut
off the section cut cut • id: The ID o • origin: Origin of the section cut plane • normal: Normal of the section cut plane • in_plane_reference_direction1: Local x-direction of the sectin cut • scale_factor: Scale factor for the thicknesses • core_scale_factor: Scale factor for core materials • intersection_type: Intersection type for the wireframe section cut • section_cut_type: Ply resolution • extrusion_type: Type of representation and extrusion • use_default_tolerance: Whether to use the default tolerance or not. Default is 0.1% of the averaged
element size. • tolerance: Tolerance Tolerance used to generate the surface section cut • use_default_lut_settings: Use default interpolation properties for the sweep based extrusion • search_radius: Search radius of the interpolation algorithm
• number_of_interpolation_points: Number of points of the interpolation algorithm create_sensor(name, id=None, sensor_type='SENSOR_BY_AREA', entities=None, locked=False)
Create new Sensor Parameters • name: Name of the Rule • sensor_type: Type of Sensor values are: SENSOR_BY_AREA, SENSOR_BY_MA SENSOR_BY_MATERIAL, TERIAL, SENSOR_BY_PLIES • entities: Entities of the Sensor
Returns
The created Sensor
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Model Classes create_solid_model (name, id='', active=True, element_sets=None, ex_type=None,
drop_off_type=None, offset_type=None, max_thickness=None, ply_group_pointers=None, element_set=None, use_default_element_index=Tru use_default_eleme nt_index=True, e, element_index=0, use_default_node_index=True, node_index=0, use_default_section_index=True, section_index=0, use_default_material_index=True, material_index=0, use_default_coordinate_system_index=True, coordinate_system_index=0, connect_butt_joined_plies=True, write_degenerated_elements=True, use_solsh_elements=False, use_solid_model_prefix=True, global_drop_off_material=None, global_cut_off_material=None, transfer_all_sets=True, transferred_element_sets=[], transferred_edge_sets=[], delete_bad_elements=True, disable_dropoffs_on_top=False, disable_dropoffs_on_bottom=False, disable_dropoff_sets_on_top='all', disable_dropoff_sets_on_bottom='all', warping_limit=0.4, drop_hanging_nodes=True, locked=False)
Create a new Solid Model Parameters
Model • name: The name of the Solid Model • id: The id of th the e Solid Model Model • active : Active status fo the Solid Model • element_sets: a list of Element Sets • ex_type: monolithic (1 element through the thickness),
analysis_ply_wise (1 element per layer), modeling_ply_wise (1 element for each modeling ply), production_ply_wise (1 element for each production ply) specify_thickness (1 element per layer, layers thicker than max_thickness are split to several solids of at most max_thickness) user_defined (groups plies by global ply numbers to groups material_wise (groups subsequent plies with equal material) • drop_off_type: inside ply (one element inside the ply boundary), outside ply (one element outside
the ply boundary) • offset_type
shell normal (offset to the shell normal), surface normal (update normal direction by normal of layered solids),
distortion controlled (surface normal with local corrections) • max_thickness : maximum thickness for one solid, splits the layer into more solids, if a single layer
is thicker than this value (only for ex_type=`specify thickness`) • ply_group_pointers : step used to make user-defined ply groups • element_set : (deprecated, use element_sets instead) a single element set • use_default_element_index : consecutive element numbering if set to true • element_index : start index for first element (only relevant if use_default_element_index) • use_default_node_index : consecutive node numbering if set to true • node_index : start index for first node (only relevant if use_default_node_index)
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The ACP Python Scripting Scripting User Interface • use_default_section_index : consecutive section numbering if set to true • section_index : start index for first element (only relevant if use_default_section_index) • use_default_material_index : consecutive material numbering if set to true • material_index : start index for first element (only relevant if use_default_material_index) • use_default_coordinate_system_index : consecutive coordinate system numbering if set to true • coordinate_system_index : start index for first coordinate system (only relevant if use_default_co-
ordinate_system_index) • connect_butt_joined_plies : connect adjacent plies without intermediate drop-offs • write_degenerated_elements : degenerated drop-off and cut-off elements are written to the *cdb
file • use_solsh_elements : the solid model is created out of solsh elements • use_solid_model_prefix : the name of the solid model is used as a prefix for all components written
to the *cdb file • global_drop_off_material: defines the global drop-off material • global_cut_off_material: defines the global cut-off material • transfer_all_sets: defines whether all edge and element sets should be transferred to the solid
model. • transferred_element_sets: element sets to transfer to the solid model if transfer_all_sets is set to
false. • transferred_edge_sets: edge sets to transfer to the solid model if transfer_all_sets is set to false. • delete_bad_elements: Boolean whether to delete the erroneous elements or not
• disable_dropoffs_on_top: Boolean whether to disalbe the drop-off elements on the top surface of
the laminate. • disable_dropoffs_on_bottom: Boolean whether to disalbe the drop-off elements on the bottom
surface of the laminate. • disable_dropoff_sets_on_top: List of element or oriented selection sets defining the region where the drop-offs are disabled on the top skin of the laminate. Default is ‘all’ • disable_dropoff_sets_on_bottom: List of element or oriented selection sets defining the region
where the drop-offs are disabled on the bottom skin of the laminate. Default is ‘all’ • warping_limit: Warping limit factor used to detect erroneous elements • drop_hanging_nodes: Hanging nodes are dropped (not exported) if set to true. Hanging nodes are
mid-side nodes that are not shared by adjacent elements. Returns
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Model Classes The created Solid Model create_spherical_selection_rule (name, id=None, origin=None, radius=None, relat-
ive_rule_type=False, include_rule_type=True, use_global_coordinate_system=None, rosette=None)
Create new Spherical Selection Rule Parameters • name: Name of the rule • origin: Origin of the Spherical Selection Rule • radius: Radius of the Spherical Selection Rule • relative_rule_type: Flag for relative rule • include_rule_type: Include or Exclude area in rule • use_global_coordinate_system: Use global coordinate system to define rule parameters • rosette: Rosette used if use_global_coordinate_system is False
Returns
The created Spherical Selection Rule create_tube_selection_rule (name, id=None, outer_radius=1.0, inner_radius=0.0, in-
clude_rule_type=True, edge_set=None)
Create new Tube Selection Rule Parameters • name: Name of the rule • radius: Radius of the rule • include_rule_type: Include or Exclude area in rule
• edge_set: Edge Set for the rule
Returns
The created rule create_variable_offset_selection_rule (name, id=None, radius_origin=None, radius_dir-
ection=None, edge_set=None, offsets=None, angles=None, element_set=None, relative_rule_type=False, include_rule_type=True, use_offset_correction=False, distance_along_edge=False, inherit_from_lookup_table=True)
Create new Slab Offset Rule Parameters • name: Name of the Rule
unique e ID of the rule • id: The uniqu
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The ACP Python Scripting Scripting User Interface • radius_origin: Reference point of the 1D lookup table used for the offsets • radius_direction: Normal of the cutting plane. • edge_set: Guide/axis of variable tube • offsets: 1D lookup table including the radii of the variable tube • angles: Optional taber edge angles • element_set: Preselection of elements in the form of an element set where the rule is applied on • include_rule_type: Boolean whether to select the element inside or outside the variable tube. • use_offset_correction: Boolean whether to evaluate the evaluat the radius/offset along the surface
or not. • distance_along_edge: Boolean whether to evaluate the distance along the edge or direction of the
rule. Default is false. • inherit_from_lookup_table: Boolean whether to inherit origin and direction from the attached
lookup table. Default is false. Returns
The created rule definitions
Definitions deformation_scale_factor
Factor with which the deformed shape plot is scaled. draping_offset_correction
Define whether to consider lay-up thickness in draping analysis. edge_sets
Dictionary with all Edge Sets defined. element_normal(globalID)
Returns the element normal (direction) Parameters • globalID: Element label element_sets
Dictionary with all Element Sets defined. export(path)
Exports all ACP composite defintions. Parameters • path: .acp file path
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Model Classes export_composite_cae_h5 (path, remove_midside_nodes=True, element_sets=None, model-
ing_plies=None)
Export layup to Composite CAE HDF5 file. parameters • path : Save path of the h5 file. • remove_midside_nodes : Whether midside nodes should be exported or not. • element_sets
A list of Element Sets and/or Oriented Selection Sets. Only plies defined over the selected elements will be exported. If empty list or None, all elements will be considered. • modeling_plies
A list of Modeling Plies and/or Modeling Groups. If empty list or None, all modeling plies will be exported export_h5_composite_definitions (path)
Save composite definitions to HDF5 file. Function is mainly used to exchange composite definitions with ANSYS Workbench parameters • path Save path of the h5 file export_ply_geometries (filename, plies=[], boundary=True, surface=True, offset_type='middle_off-
set', direction_arrows=False, first_direction=True, second_direction=False, arrow_length=1.0, arrow_type='no_arrow')
Exports the surface, boundary and/or fiber directions of modeling, production and analysis ply to igs or step file. Parameters
• filename: File path (allowed extensions are iges, igs, step, stp and stl). • plies: List of plies (allowed are modeling, production and analysis plies). • boundary: Boolean whether to export the boundary. Default is True. • surface: Boolean whether to export the ply surface. Default is True. • offset_type: Offset type (can be ‘no_offset ’, ‘middle_offset ’, ‘top_offset’ or ‘bottom_offset’). Default is ‘middle_offset ’ • direction_arrows: Boolean whether to export the direction arrows. Default is False. • first_direction: Boolean whether to export the first (main) material direction. Default is True. • second_direction: Boolean whether to export the second material direction. Default is False. • arrow_length: Length of the arrows. Default is 1.
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The ACP Python Scripting Scripting User Interface • arrow_type: Defines the arrow type (can be ‘standard_arrow ’, ‘no_arrow ’, ‘half_arrow ’). Default is ‘no_arrow ’.
Note: Directions and boundaries are not supported by the STL format. export_solid_models (directory=None, prefix='ACPSolidModel_', delete_existing=True,
formats=['cdb', 'h5'])
Save solid models to files. Function is used within Workbench updates Parameters • directory: Directory to save the models. • prefix: Prefix of the model. Default ACPSolidModel_ • delete_existing: Flag if existing models should be deleted. Default True • formats: Available file formats are ‘cdb’ or h5. Default [‘cdb’, ‘h5’]. field_definitions
Dictionary with all defined field definitions. find_materials(**properties)
Find materials with the given properties or property ranges Parameters • properties: Arbitrary material properties which must be matched. Note that a single property value
can be given as string, number or min-max range Returns
A list with materials which match the given properties. If nothing matches an empty list is returned. Examples: format
File format string. Choose one of ‘ansys:h5’, ‘ansys:cdb’, ‘ansys:dat ’, ‘matwind:mdr ’ or ‘layup’ geometry
Geometry node get_element_by_point (point)
Returns the element label of the closest element with respect to the given point. Parameters
-point: Tuple of the global coordinates get_layup(path, format=None, objects=None, mode='update_entities')
Load layup from excel or csv file Parameters
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Model Classes • mode: can be: update_properties_only: Definitions are updated with properties given
update_entities: Definitions are update, additional plies are generated and deleted recreate: Existing layup is deleted generated from scratch get_layup_from_csv_file (path, objects=None, mode='update_entities', modeling_group=None)
Function that reads the layup data from a csv file and adds the data to the graph Parameters • objects: List of objects to be synced • path: the path to the file
• mode: can be: update_properties_only: Definitions are updated with properties given
update_entities: Definitions are update, additional plies are generated and deleted recreate: Existing layup is deleted generated from scratch • modeling_group: key of the mpg_collection dict = the id of the mpg. Only plies of this model-
ing_group will be imported from the file if none is specified all mpgs are read get_layup_from_excel_file (path, objects=None, mode='update_entities')
Load layup from Excel File Parameters • path: Path to file to load • objects: Objects to be loaded and overwritten • mode: can be: update_properties_only: Definitions are updated with properties given
update_entities: Definitions are update, additional plies are generated and deleted recreate: Existing layup is deleted generated from scratch import_composite_cae_h5 (path, mode='append', projection='shell', tol_thickness=0.5,
tol_in_plane=0.01, tol_angle=35.0, small_hole_threshold=0.05, tol_min_angle=0.001, recompute_ref_directions=False, element_sets=None, offset='bottom_offset')
Import a composite layup definition from a HDF5 file. Parameters • path : Load path of the h5 file • mode
Specify how objects are imported – append : Imported data/objects are appended to existing model/layup. – overwrite : Replace objects with equal ids in the model with imported instances if possible
(not locked). • projection: Defines whether the imported data is treated as shell or solid data
eference surface and converted – shell: Default. The imported components are mapped onto the rreference into Modeling Plies.
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The ACP Python Scripting Scripting User Interface – solid: The components are imported one-to-one exposed as Imported Plies. Can be used in
combination with ImportedSolidModel (lay-up mapping) • tol_thickness : Mapping tolerance in element thickness direction relative to min element edge length. • tol_in_plane : Mapping tolerance in element in-plane direction relative to min element edge length. • tol_angle : Mapping tolerance for the angles between element normals. • small_hole_threshold : Holes in plies/element sets with an area smaller than this threshold times
the area of the element set/ply are filled. • tol_min_angle : Minimum angle tolerance for which tabular correction angles for plies are computed. • recompute_ref_directions’ : Whether reference directions should be recomputed from tabular angle
data or not. • element_sets : A list of Element Sets. • offset: Offset for imported plies. Defines if imported mesh is interpreted as bottom, middle
or top ply surface.
Valid modes are ‘bottom_offset’, ‘middle_offset ’, ‘top_offset’ import_composite_definitions_from_acp_file (path=None, import_mode='keep_both')
This functions loads the ACP composite definitions from an external ACP system. Within WB, this function loads all objects but the mesh, materials and plots In stand-alone mode, all objects but the mesh and plots are imported. Parameters • path: *.acp file path • import_mode: Defines how to solve conflicts of objects of equal name.
Global Resolution Actions
keep_both: Keep target and source. Default. • keep_existing: Imported entities are ignored • overwrite: Overwrite target with source import_section_data_from_legacy_model (path, format='ansys:cdb', materials_mask_pre-
fix='mat', materials_mask_suffix=' (setup, file1)')
Import and convert the lay-up of a legacy (MAPDL) shell model into ACP composite definitions. The mapping is based on the element labels and therefore it is a requirement that the element labels in the legacy and ACP model match. The import is only performed if the file and ACP Model units are consistent. Parameters • path: file path. Supported file extensions are CDB, DAT and INP. • format: file format. Supported are ‘ansys:cdb’ and ‘ansys:dat ’
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Model Classes • materials_mask_prefix: Defines the prefix that is added to the Matierla ID while importing materials
via ExternalModel. • materials_mask_suffix: Defines the suffix that is added to the Matierla ID while importing materials
via ExternalModel. Materials mapping
Only relevant when the import happens within WB. The materials mask pre- and suffix parameters allow to automatically map WB material and legacy material ids. For instance the pre- and suffix MATT and ` (Setup, File1)` allows to map MAT1 MA MAT1 (Setup, FFile1) ile1) with legacy legac y material 1. The mapping is case independent. Pass empty mapping masks when no mapping is needed Example >>> db.active_model.import_section db.active_model.import_section_data_from_legacy_model(path=r'D _data_from_legacy_model(path=r'D: :
mp\class40_analysis_model.cdb', forma
layup_plots
Plots lookup_tables
Dictionary with all Look-Up Tables material_data
Dictionary with all Material Data defined. mesh
Mesh of this model mesh_query(name, position, selection='all', entity=None, entities=None, simulate=False, compon-
ent=None)
Query arbitrary data from the mesh of the model Parameters • name
Data type to query: – labels, indices – etypes – coordinates – angles (needs component) –
thickness (needs component) – normals – orientations, ref_directions, fiber_directions, transverse_directions – draped_fiber_directions, draped_transverse_directions – ply_offsets (offset vector) Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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The ACP Python Scripting Scripting User Interface – area, volume, mass, price – cog (centre of gravity) – offset (offset in the thickness direction) • component
Defines the component. Needed for name=’angles’ or ‘thickness ’ – angles: design_angle, shear, draped_fiber_angle, draped_transverse_angle. design_angle is
the default. – thickness: thickness, relative_thickness_correction. thickness is the default. • position
Position where data is queried: – nodal – centroid – element_nodal • selection
The selection set determines the selected nodes and elements. Can be given as string ‘sel0’ - ‘sel5’ or ‘all’ or can be given as ObjectSelection object such as - model.selection - scene.active_set • entity
Specialized queries require the specification of an additional associated entity, e.g. an oriented element set is needed to compute orientations. Entity can be given as NamedGraphObjects or vertex descriptor. • entities : If a list of entities is given, the query will also compute and return a list of results, with one
array for each entity. • simulate
Whether the query is only simulated to test if it will return data. If this flag is set the mesh_query( …) function will only return 0 or 1. minimum_analysis_ply_thickness
Section computation minimum analysis ply thickness (in length unit of model) modeling_groups
Dictionary with all Modeling Groups defined. oriented_selection_sets
Dictionary with all oriented element sets defined. parameters
List of parameters visible to the workbench
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Model Classes path
Path to the reference surface input file. Read only. plot_dependencies(path=None, parent=None, levels=3)
Generates a graph with all dependencies. The output is a dot, png and pdf file Parameters • path: file path without file extension • parent: Parent object • levels: Depth levels to look for children
Output
A dot file which can be opend with Graphviz Usage >>> model.plot_dependencies(r'C:\tmp\hull_dependencies', model.element_sets['HULL'], 3)
plybook
PlyBook pre_path
Save path of pre database linked to currently loaded post database reference_surface_bounding_box
Tuple with corners of bounding box of reference surface s urface mesh. reference_surface_input_unit_system_locked
If the unit system of the reference surface is not defined in the mesh input, the unit system can be changed. reference_surface_input_unit_system_type
Unit System of the Reference Surface (set by user) refresh_material_data (matml_file_path, apdl_file_path)
Refresh material external data sources in the model acph5 db. Needs the save_path to be set. relative_thickness_tolerance
Section computation relative thickness tolerance reload_mesh(path=None, format=None)
Reloads the mesh (nodes, elements and named selections) Ignored imported entities are the materials and rosettes. Parameters: • path: New mesh path. Default is the current model path. • format: New format. Default is the current format
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The ACP Python Scripting Scripting User Interface rosettes
Dictionary with all Rosettes defined. sampling_points
Sampling Point Container save(path=None, cache_data=None)
Save ACP model to .acph5 file :Parameters: - path : P Path ath to file - cache_data : Whether to cache current state of model or not. save_analysis_model (path)
Save actual analysis model to disc parameters • path Save path of the cdb file save_apdl_commands (path)
Save APDL commands for composite definitions of actual model parameters • path Save path of the cdb file save_h5(path, cache_data=False)
Save ACP model in ACPH5 format save_layup(path, format=None, objects=None)
Function that saves the layup data to a csv file Parameters • path: the path to the file • format: format can be csv and excel (on windows only)
• objects: optional parameter if left the entire layup is written to the file, else only the layup defined
within modeling_groups save_layup_to_csv_file (path, objects=None)
Function that saves the layup data to a csv file Parameters • path: the path to the file • modeling_groups: optional parameter if left the entire layup is written to the file, else only the layup
defined within modeling_groups save_layup_to_excel_file (path, objects=None)
Function that saves the layup data to an excel file. Windows only! Parameters • path: the path to the file Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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Model Classes • objects: optional parameter if left the entire layup is written to the file, else only the layup defined
within modeling_groups scenes
Scenes section_cuts
Section Cuts select_elements(selection='sel0', op='new', labels=None, indices=None, attached_to=None,
x=None, y=None, z=None, element_type='all')
Selects element within active model. (Marks the given selection as SELECTED) Parameters • selection
The selection to update Can be given as string ‘sel0’ - ‘sel5’ or ‘all’ or can be given as ObjectSelection object such as - model.selection - scene.active_set • op: Select operation. Can be all, new (default), add, remove, intersect, inverse or none • labels: List with element labels to select. • indices: List with element indices to select. • attached_to: Elements attached to entities / vertices in this list will be selected. • x: X-range to select.
select. • y: Y-range to select. • z: Z-range to select. • element_type: Element type: solid, shell
select_nodes(selection='sel0', op='new', labels=None, attached_to=None, x=None, y=None,
z=None)
Function selects nodes in graph and marks the given selection as SELECTED. Parameters • selection
The selection to update Can be given as string ‘sel0’ - ‘sel5’ or ‘all’ or can be given as ObjectSelection object such as - model.selection - scene.active_set • op: Select operation. Can be all, new (default), add, remove, intersect, inverse, none • labels: List with node labels to select. • attached_to: Nodes attached to the given list of entities or vertices will be selected. If attached_to=”elements” all nodes attached to selected elements are selected
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The ACP Python Scripting Scripting User Interface • x: X-range to select.
select. • y: Y-range to select. • z: Z-range to select. select_solid_elements_from_shells (selection='sel0')
Selects the solid element within given selection and deselects the shell elements. Parameters • selection : The selection to update. Can be given as string ‘sel0’ - ‘sel5’
Return
Number of selected solid elements selection
Selected objects of this model selection_rules
Dictionary with all Selection Rules defined. sensors
Dictionary with all Sensors. show_deformed
Whether to show result plots in the deformed and scaled configuration. show_solver_elements
Whether mesh selections and plot should consider solver elements in solid models or not. solid_models
SolidModel solutions
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Solutions solve(wait=False)
Convenience function to directly solve the current model Parameters • wait: Wait until solver process finishes computation solver
Solver instance unit_system
Create a unit system and assign it to the model. Unit system types are: si,mks,cgs,umks,mpa,bft,bin,undefined update(objects='all', relations_only=False)
Main update function
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Model Classes Parameters • objects: List of objects to update. • relations_only: Set this option to true to only update and propagate the status of all objects. use_default_section_tolerances
Boolean whether to uses angle and thickness tolerances of the application preferences for section computation. Otherwise model specific values are used. use_nodal_thicknesses
Define whether to use nodal thicknesses or element thicknesses. views
Views
6.5.2. Rosette class compolyx.Rosette(graph, obj, parent=None)
Rosette class. Access: >>> model = db.models['class40.1'] >>> rosette_1 = model.rosettes['Rosette.1'] >>> rosette_2 = model.create_rosette(name='Rosette.2', origin=(1.5, 5.75, 7.), dir1=(-0.4, -0.4, 0.8), dir2=(-6.0
changed
Status boolean. Set to true if the underlying data has been changed. Write only property dir1
Direction 1 of the Rosette dir2
Direction 2 of the Rosette
Direction 2 of the Rosette edge_set
Edge Set for Rosette get_global_coordinates (coordinates)
Evaluates the global coordinates of a point given in local rosette coordinates: CYLINDRICAL, RADIAL and SPHERICAL coord sys type: Give phi and theta in RAD Parameters • (x, y, z): x = x for PARALLEL, r for CYLINDRICAL, RADIAL and SPHERICAL)
y = y for PARALLEL, phi for CYLINDRICAL, RADIAL and SPHERICAL z = z for PARALLEL, CYLINDRICAL, RADIAL and theta for SPHERICAL)
Usage >>> rosette.get_global_coordinates rosette.get_global_coordinates((1.,2.,3.)) ((1.,2.,3.))
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The ACP Python Scripting Scripting User Interface get_global_vector_components (vector)
gets global vector components from local rosette vector components CYLINDRICAL, RADIAL and SPHERICAL coord sys type: Give phi and theta in RAD Parameters Usage >>> rosette.get_global_vector_comp rosette.get_global_vector_components((1.,2.,3.)) onents((1.,2.,3.))
get_local_coordinates (coordinates)
Evaluates the local rosette coordinates of a point given in global coordinates: Parameters Usage >>> rosette.get_local_coordinates( rosette.get_local_coordinates((1.,2.,3.)) (1.,2.,3.))
get_local_vector_components (vector)
gets local rosette vector components from global vector components Parameters Usage >>> rosette.get_local_vector_compo rosette.get_local_vector_components((1.,2.,3.)) nents((1.,2.,3.))
local_direction(point, angle)
Get local orientation for a given relative angle and position in space locked
Rosette is generated from an imported rosette and cannot be changed. origin
Origin of the Rosette
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rosette_type
Rosette Types can be: parallel,radial,cylindrical,spherical,edge_wise serialize()
Serialize to Python string set_Xy()
sets dir2 orthogonal to dir1 as y- and x-axis set_Xz()
sets dir2 orthogonal to dir1 as z- and x-axis
set_Yz()
sets dir2 orthogonal to dir1 as z- and y-axis set_xY()
sets dir1 orthogonal to dir2 as x- and y-axis
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Model Classes set_xZ()
sets dir1 orthogonal to dir2 as x- and z-axis set_yZ()
sets dir1 orthogonal to dir2 as y- and z-axis
6.5.3. LookUpTableBase class compolyx.LookUpTableBase(obj, parent=None)
Bases: compolyx.graph_interface.NamedGraphFuncObject Look-Up Table Class associates scalar or vector values to points Example: >>> >>> >>> >>> >>>
table = db.models['class40.1'].create_lookup_table1d(name='LookUpTable1D.1') table.columns['Location'].values = [0,1,2,3] db.models['class40.1'].lookup_tables['LookUpTable1D.2'].create_column( name='Radius', type='scalar' ) r = db.models['class40.1'].lookup_tables['LookUpTable1D.2'].columns['Radius'] r.values = [0,0.3,0.6,1]
active
LookUpTable active clear()
clear table data (rows and columns) clear_rows()
clear table rows (keep columns) column_types
a list of column types ( ‘scalar ’, or ‘direction’)
columns
Dictionary with all columns create_column(name, type=None, values=None, dimension='dimensionless')
Create a new column. Parameters • name : name of column • type : a string (‘scalar ’, ‘direction’) specifying the column type (the values will be initialized to NaN) • values : a numpy array with values (the type is determined from its shape) empty
True if table is empty load_from_csv_file (path)
load the table from csv file in path Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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The ACP Python Scripting Scripting User Interface Load LookUpTable from CSV file Parameters • path: path to output file num_cols
Number of rows num_rows
Number of columns save_to_csv_file(path)
Save LookUpTable to CSV file Parameters • path: path to output file tabular_data
a tuple containing a list of column labels and a 2d array with floats for all cells. This is a flattened view of all columns.
LookUpT UpTable1D able1D 6.5.4. Look class compolyx.LookUpTable1D(obj, parent=None)
Bases: compolyx.lookup_table.LookUpT compolyx.lookup_ta ble.LookUpTableBase ableBase A LookUpTable to associate arbitrary data to a one-dimensional field of Locations column_factory
alias of LookUpTable1DColumn direction
The Direction of the Look Up Table origin
The Origin of the Look Up Table tabular_data
a tuple containing a list of column labels and a 2d array with floats for all cells. This is a flattened view of all columns.
6.5.5. LookUpT able3D Look UpTable3D class compolyx.LookUpTable3D(obj, parent=None)
Bases: compolyx.lookup_table.LookUpT compolyx.lookup_ta ble.LookUpTableBase ableBase A LookUpTable to associate arbitrary data to a three-dimensional field of locations
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Model Classes column_factory
alias of LookUpTable3DColumn num_min_neighbors
Number of neighbors used for interpolation search_radius
Search Radius used for interpolation tabular_data
a tuple containing a list of column labels and a 2d array with floats for all cells. This is a flattened view of all columns. use_default_search_radius
True if the search radius is estimated automatically
Look UpTableColumn 6.5.6. LookUpT ableColumn class compolyx.LookUpTableColumn(name, parent)
an object to hold a column in a table enabled
Whether this object is currently enabled or not. Mainly defined through the current application mode pre or post. status
column status (‘UPTODATE’,’NOTUPTODATE’, or ‘LOCKED’) type
column type (scalar or direction) values
numpy array containing the column values
6.5.7. ElementSelectionRule Classes This section contains the following topics: 6.5.7.1. ParallelSelectionRule 6.5.7.2. CylindricalSelectionRule 6.5.7.3. SphericalSelectionRule 6.5.7.4.TubeSelectionRule 6.5.7.5. CutoffSelectionRule 6.5.7.6. GeometricalSelectionRule 6.5.7.7.VariableOffsetSelectionRule class compolyx.ElementSelectionRule(graph, obj, parent=None)
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The ACP Python Scripting Scripting User Interface Base class for Rules This acts as an interface to the cpp object of the rules. The base class implements _py_update which is called after the cpp update. It sets the changed flag. Since NameGraph derives from Observable, observers can listen on ‘changed’. In order to support csv_serialization, the classes have to implement a ‘_dict ’ method and a list named ‘_csv_parameters’ The _dict method specifies which properties are written and _csv_parameters specifies which parameters are read and how they are parsed. parsed. The keys in _dict and the elements in _parameters_csv have to be consistent. If the conversion from the string to an object is more than simple type conversion, it can be implemented in _update_rule_from_csv. changed
Triggers Observable Obser vable to dispatch changed message extent
extent of the rule include_rule_type
include type relative_rule_type
relative type
6.5.7.1. ParallelSelectionRule class compolyx.ParallelSelectionRule(graph, obj, parent=None)
Bases: compolyx.selection_rule.ElementSelectionRule Parallel Selection Rule direction
Direction of the Parallel Selection Rule. direction_in_global_coordinates
Direction of the rule in global coordinates
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neg_distance
Negative distance origin
Origin of the Parallel Selection Rule. origin_in_global_coordinates
Origin of the rule in global coordinates pos_distance
Positive distance rosette
Rosette of the used for origin and direction serialize()
Serialize to Python string
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Model Classes use_global_coordinate_system
Use global coordinate system for origin and direction
6.5.7.2. CylindricalSelectionRule class compolyx.CylindricalSelectionRule(graph, obj, parent=None)
Bases: compolyx.selection_rule.ElementSelectionRule Cylindrical Selection Rule direction
Direction of the Cylinder. direction_in_global_coordinates
Direction of the rule in global coordinates origin
Origin of the Cylinder. origin_in_global_coordinates
Origin of the rule in global coordinates radius
Radius of the Cylinder rosette
Rosette of the used for origin and direction serialize()
Serialize to Python string use_global_coordinate_system
Use global coordinate system for origin and direction
6.5.7.3. SphericalSelectionRule class compolyx.SphericalSelectionRule(graph, obj, parent=None)
Bases: compolyx.selection_rule.ElementSelectionRule Spherical Selection Rule direction_in_global_coordinates
Direction of the rule in global coordinates origin
Origin of the Sphere. origin_in_global_coordinates
Origin of the rule in global coordinates
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The ACP Python Scripting Scripting User Interface radius
Sphere Radius rosette
Rosette of the used for origin and direction serialize()
Serialize to Python string use_global_coordinate_system
Use global coordinate system for origin and direction
6.5.7.4.TubeSelectionRule class compolyx.TubeSelectionRule(graph, obj, parent=None)
Bases: compolyx.selection_rule.ElementSelectionRule Tube Selection Selecti on Rule edge_set
Edge Set for the Tube Selection Rule inner_radius
Inner tube-radius outer_radius
Outer tube-radius serialize()
Serialize to Python string
6.5.7.5. CutoffSelectionRule
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class compolyx.CutoffSelectionRule(graph, obj, parent=None)
Bases: compolyx.selection_rule.ElementSelectionRule angle
Cut-Off angle cutoff_geometry
Cut-off Geometry for the Cut-off Rule cutoff_rule_type
Cutoff rule type, valid values geometry,taper,variable_taper direction
Direction of the offset and angle interpolation for ‘variable_taper ’ distance_type
Distance type for offset and angle interpolation for ‘variable_taper ’
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Model Classes edge_set
Edge Set for cutoff_rule_type=`taper` or variable_taper offset
Cut-Off offset offset_method
Method to compute the offset of a ply. offset_type
Take offset from edge set perpendicular to element reference sur face (out_of_plane) or in element reference surface (in_plane) origin
Origin of the offset and angle interpolation for ‘variable_taper ’ cutoff rules ply_cutoff_type
Cutoff Types can be: production_ply_cutoff,analysis_ply_cutoff ply_tapering
Use Ply Tapering Orientation
6.5.7.6. GeometricalSelectionRule class compolyx.GeometricalSelectionRule(graph, obj, parent=None)
Bases: compolyx.selection_rule.ElementSelectionRule Geometrical Selection Rule add_element_set(element_set)
Add Element Set to GeometricalSelection Rule clear_element_sets()
Clear Element Sets of Oriented Selection Set
element_sets
Element Sets for the Geometrical Selection Rule. geometrical_rule_type
Geometrical rule type, valid values geometry,element_sets geometry
Virtual Geometry for the Geometrical Selection Rule. in_plane_capture_tolerance
In-plane capture tolerance neg_capture_tolerance
Capture tolerance in the negative direction of the CAD surface. pos_capture_tolerance
Capture tolerance in the positive direction of the CAD surface.
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The ACP Python Scripting Scripting User Interface projection_normal
Projection direction used to map curves onto the shell mesh. serialize()
Serialize to Python string use_defaults
Whether to use the offset value of the CAD Geometry or not. use_projection_normal
Whether to use a projection normal for outlines or not.
6.5.7.7.VariableOffsetSelectionRule class compolyx.VariableOffsetSelectionRule(graph, obj, parent=None)
Bases: compolyx.selection_rule.ElementSelectionRule angles
Link to lookup table column with taper angles distance_along_edge
Whether to evaluate the distance along the edge or direction of the rule edge_set
Link to edge set element_set
The element set on which the rule is applied. inherit_from_lookup_table
Whether to inherit the Look-Up Table object properties. offsets
Link to lookup table column with offsets
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Link to lookup table column with offsets radius_direction
Direction for offset value interpolations radius_origin
Origin for offset value interpolations serialize()
Serialize to Python string use_offset_correction
Use offset correction on mesh
6.5.8. EntitySet Classes This section contains the following topics: 6.5.8.1. ElementSet
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Model Classes 6.5.8.2. EdgeSet class compolyx.EntitySet(graph, obj, parent=None)
Base class for entity sets add (entity) (entity)
Add entity to the set remove(entity)
Remove entity from the set size
Number of entities
6.5.8.1. ElementSet class compolyx.ElementSet(graph, obj=None, parent=None)
Bases: compolyx.entity_set.EntitySet Element set class Exemplary usage >>> >>> >>> >>> >>> >>>
m=db.models.values()[-1] eset=m.element_sets['DECK'] eset.modify(op='none') eset.modify(op='new', element_labels=[1,2,3,4]) eset.modify(op='add', element_sets=[ m.element_sets['Deck_layup-1'] ]) eset.modify(op='intersect', x=[-6.5,-5.5])
boundaries
Get the boundaries of the Element Set locked
Element Set is imported and cannot be changed. middle_offset
Middle offset flag modify(op='new', element_labels=None, element_sets=None, x=None, y=None, z=None)
General method to modify the elements in an element set Parameters • op: Selection method: new, add, remove, intersect or inverse • element_labels: List of element ids • element_sets: List of element sets • x: Min and max of x location • y: Min and max of y location
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The ACP Python Scripting Scripting User Interface • z: Min and max of z location normals
Get the Normals of the Element Set orientable
True if the Element Set has an orientable topology partition()
Partitions this ElementSet into new ElementSets with an orientable topology if this ElementSet is already orientable, a copy will be created planar
True if the Element Set has a planar topology serialize()
Serialize to Python string write_boundaries(filename, format=None)
Write boundaries in iges/step format :Parameters: - filename: output file - format: ‘iges’, ‘step’, None (automatic format recognition)
6.5.8.2. EdgeSet class compolyx.EdgeSet(graph, obj=None, parent=None)
Edge Set class changed
Status boolean. Set to true if the underlying data has been changed. Write only property display_data
The edge set mesh plot
edge_set_type
Edge Set Types can be: “By Reference”, “By Nodes” get_nodes()
Return python list with nodes as objects is_closed
Edge Set is closed. limit_angle
Edge Set limit angle for creation of edge set by reference locked
Edge Set is imported and cannot be changed. mesh
The edge set mesh
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Model Classes node_labels
Node labels defining the NodeSet (only if type=’By Nodes’) nodes
Node indexes/labels of the Edge Set origin
Edge Set origin for createion of edge set by reference serialize()
Serialize to Python string
6.5.9. Geometry Classes This section contains the following topics: 6.5.9.1. CADGeometry 6.5.9.2. CADCompound 6.5.9.3. CADSolid 6.5.9.4. CADShell 6.5.9.5. CADFace 6.5.9.6.VirtualGeometry 6.5.9.7. CADReference
6.5.9.1. CADGeometry class compolyx.CADGeometry(graph, obj, visible_sub_shapes=None, parent=None) cad_compounds
Dictionary with all compounds in the CAD Geometry. cad_faces
Dictionary with all face shapes. cad_solids
Dictionary with all solid shapes. cad_surfaces
Dictionary with all shell shapes. changed
Status boolean. Set to true if the underlying data has been changed. Write only property display_data
CAD geometry mesh surface plot
ext_id
External ID of the CAD Geometry object. locked
CAD geometry is generated from an imported geometry and cannot be changed.
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The ACP Python Scripting Scripting User Interface normals_display_data
CAD geometry normals visualization offset
Offset value used to analyze the surface’s coverage regarding the mesh. path
The file path where the CAD geometry is loaded from. precision
Precision of geometrical operations (intersection points, thickness sampling, …). refresh_external_source (enforce=False)
Reload the geometry from the external source. Parameters root_shapes
Dictonary with all free shapes of the CAD Geometry scale_factor
Geometry is scaled with this factor. shape_type
Topological type of the shape. show_normals
Visibility of Face Normals. sub_shape_selection_display_data
CAD face selection plot sub_shapes
Sub faces of the CAD Geometry.
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use_default_offset
Whether to use the default value or not. use_default_precision
Whether to use default precision value or not. visible_sub_shapes
Ids of CAD sub shapes to be displayed, stored per-scene id visualization_mesh
Visualization mesh of this geometry
6.5.9.2. CADCompound class compolyx.CADCompound(graph, obj, parent=None)
ComPoLyX Class to represent CADCompound
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Model Classes sub_shapes
Sub faces of the CAD Compound.
6.5.9.3. CADSolid class compolyx.CADSolid(graph, obj, parent=None)
ComPoLyX Class to represent CADSolid sub_shapes
Sub faces of the CAD Solid.
6.5.9.4. CADShell class compolyx.CADShell(graph, obj, parent=None)
ComPoLyX Class to represent CADShell sub_shapes
Sub faces of the CAD Shell.
6.5.9.5. CADFace class compolyx.CADFace(graph, obj, parent=None)
ComPoLyX Class to represent CADFace
6.5.9.6.VirtualGeometry class compolyx.VirtualGeometry(graph, obj, parent=None)
ComPoLyX Class to represent VirtualGeometry
add (shape) (shape)
Creates a new CADReference object for the given shape. Returns the new CADReference object or the existing one if available Parameters • shape: A tuple. The first item is the shape object and the second the link path (root path) of the
shape. If the first item is None, the link path is used to link the shape with the virtual geometry. Usage >>> cad = db.active_model.geometry.cad_geometries['CadGeome db.active_model.geometry.cad_geometries['CadGeometry.1'] try.1'] >>> db.active_model.geometry.virtual_geometries['RefGeom'].add( db.active_model.geometry.virtual_geometries['RefGeom'].add( (cad.root_shapes['top_surface'], "") ) or >>> db.active_model.geometry.virtual_geometries['RefGeom'].add( db.active_model.geometry.virtual_geometries['RefGeom'].add( (None, "CadGeometry.1/top_surface") )
cad_geometry
Returns the linked CADGeometry. Read only.
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The ACP Python Scripting Scripting User Interface cad_references
Dictionary of all cad references. clear_cad_references()
Clear all linked references (VirtualGeometry becomes empty) create_cad_reference(name='VirtualGeometry.1', id=None, path=None, size=None, cog=None,
dimension=None, bounding_box_min=None, bounding_box_max=None)
Creates a new Cad Reference and links it with the Virtual Geometry Parameters • name: Name of the object • id: ID of the object • path: Geometry path of the linked cad component • size: Size of the linked cad component. Size can be the volume, area or length depending on the
type of the linked cad component.
• cog: Center of gravity of the linked cad component.
th e cad component. CADCompound, CADSolid, CADShell or CADFace. • dimension: The shape type of the • bounding_box_min: Minimum point of the bounding box • bounding_box_max: Maximum point of the bounding box
Return • the new cad reference object dimension
Highest dimension of all cad references. 3=solid, 2=surface, 1=curve
remove(shape)
Removes the CADReference object for the given shape Usage >>> cad = db.active_model.geometry.cad_geometries['CadGeome db.active_model.geometry.cad_geometries['CadGeometry.1'] try.1'] >>> db.active_model.geometry.virtual_geometries['RefGeom'].remove( db.active_model.geometry.virtual_geometries['RefGeom'].remove( (cad.root_shapes['top_surface'], "") ) or >>> db.active_model.geometry.virtual_geometries['RefGeom'].remove( db.active_model.geometry.virtual_geometries['RefGeom'].remove( (None, "CadGeometry.1/top_surface") )
serialize()
Serialize to Python string set(shapes)
Clears the existing CAD References and creates a new one for each given shape Parameters
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Model Classes • shapes: A list of tuples. The first item is the shape object and the second the link path (root path)
of the shape. Usage
>>> shell = db.active_model.geometry.cad_geometries['CADGeometry.1'].root_s db.active_model.geometry.cad_geometries['CADGeometry.1'].root_shapes['cut_surface'] hapes['cut_surface'] >>> db.active_model.geometry.virtual_geometries['RefGeom.1'].set(shapes=[ db.active_model.geometry.virtual_geometries['RefGeom.1'].set(shapes=[ (shell, "") ] ) or >>> db.active_model.geometry.vir db.active_model.geometry.virtual_geometries['RefGeom.1'].set tual_geometries['RefGeom.1'].set(paths=[ (paths=[ (None, "CADGeometry.1/cut_surface
sub_shapes
Sub components of the VirtualGeometry.
6.5.9.7. CADReference class compolyx.CADReference(graph, obj, parent=None)
ComPoLyX Class to represent CAD Reference bounding_box_max
Maximum of the bounding box. bounding_box_min
Minimum of the bounding box. cog
Center of gravity of the linked shape dimension
Dimension of the linked shape (1 for lines, 2 for surfaces and 3 for solids). path
Link path of the CADReference size
Size of the linked cad shape status
Status of the CADReference
6.5.10. OrientedSelectionSet class compolyx.OrientedSelectionSet(graph, obj, parent=None)
Class to represent Oriented Selection Set add_element_set(element_set)
Add Element Set to Oriented Selection Set add_rosette(rosette)
Add Rosette to Oriented Selection Set add_selection_rule (rule)
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The ACP Python Scripting Scripting User Interface auto_draping_direction
Automatic selection of draping direction. boundaries
Get the boundaries of the Oriented Selection Set clear_element_sets ()
Clear Element Sets of Oriented Selection Set clear_rosettes()
Clear Rosettes of Oriented Selection Set clear_selection_rules ()
Clear Selection Rules of Oriented Selection Set draping
Flag for using draping or not draping_direction
The direction in which the draping starts. draping_material_model
Draping material model. draping_mesh_size
The mesh size for draping. draping_obj
Draping representation draping_seed_point
The seed point where the draping starts. draping_ud_coefficient
UD draping coefficient
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element_sets
Element Sets of the oriented element set. elements
Elements of the Oriented Selection Set. normal_from_id (id) (id)
Returns the element normal normals
Get the Normals of the Oriented Selection Set orientation_direction
The Orientation Direction of the Oriented Element set. orientation_point
The Orientation Point of the Oriented Selection Set.
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Model Classes orientations
Get the oriented normals of the Oriented Selection Set ref_directions
Get the Refernce Directions of the Oriented Selection Set reference_direction_field
a look-up table column or None for external reference directions remove_element_set (element_set)
Remove Element Set from Oriented Selection Set remove_rosette(rosette)
Remove Rosette from Oriented Selection Set remove_selection_rule (rule)
Remove Rule from Oriented Selection Set rosette_selection_method
Selection Method for Rosettes of the Oriented Selection Set. rosettes
Rosettes of the Oriented Selection Set. save_flat_wrap(filename)
Write the flatwrap to DXF, IGES or STEP file Parameters • filename: Path to the file to be writen selection_rules
Selection Rules of the Oriented Selection Set. serialize()
Serialize to Python string write_boundaries(filename, format=None)
Write boundaries in iges/step format :Parameters: - filename: output file - format: ‘iges’, ‘step’, None (automatic format recognition)
6.5.11. ModelingGroup class compolyx.ModelingGroup(graph, obj, parent=None)
Class to manage modeling groups. Access: >>> >>> >>> >>>
import compolyx db = compolyx.DB() model = db.models['class40.1'] mpg = model.modeling_groups['PlyGroup.1']
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The ACP Python Scripting Scripting User Interface Creation: >>> import compolyx >>> db = compolyx.DB() >>> model = db.models['class40.1'] >>> mpg_1 = model.create_modeling_group('PlyGroup.1')
copy_butt_joint_sequence (source, global_ply_nr=None, sort=True)
Makes a copy of a butt joint sequence Parameters • source: Source object to copy • global_ply_nr: Global ply number to use. If 0 the ply is added at the top. • sort: Whether to sort all plies of modeling group group after copy. copy.
If multiple plies are copied at once it can be useful to sort only once at the end of the copy operation. Returns
New instance of modeling ply copy_interface_layer (source, global_ply_nr=None, sort=True)
Copy a Interface Layer Parameters • source: Source object to copy • global_ply_nr: Global ply number to use. If 0 the ply is added at the top. • sort: Whether to sort all plies of Interface Layer Layer group after ccopy. opy.
If multiple plies are copied at once it can be useful to sort only once at the end of the copy operation.
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Returns
New instance of Interface Layer copy_modeling_ply(source, global_ply_nr=None, sort=True)
Copy a modeling ply Parameters • source: Source object to copy • global_ply_nr: Global ply number to use. If 0 the ply is added at the top.
group after copy. copy. • sort: Whether to sort all plies of modeling group
If multiple plies are copied at once it can be useful to sort only once at the end of the copy operation. Returns
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Model Classes New instance of modeling ply create_butt_joint_sequence (name=None, id=None, global_ply_nr=None, master_plies=None,
slave_plies=None, active=Tru act ive=True) e)
Creates an new butt joint sequences and adds it to this modeling group Parameters
-name: Name of the butt joint -id: ID of the name -global_ply_nr: Global ply number which orders the ply sequences -master_plies: List of tuples (modeling ply, level) -slave_plies: Single or list of modeling plies -active: Boolean whether the butt joint sequence is active or not Return
New butt joint sequence create_interface_layer (name=None, id=None, global_ply_nr=None, oriented_selec-
tion_sets=None, open_area_sets=None, active=True)
Create Interface Layer Parameters • name: Name of the new Interface Layer • id: Optional id of the new Interface Layer • global_ply_nr: Ply number for stacking sequence • oriented_selection_sets: Oriented Selection Set for the expansion
of the Interface Layer • open_area_sets: Defines the initial crack of a VCCT layer (optional) • active: Interface Layer active. Default True
Returns
The created Interface Layer Example >>> oes_1 = model.oriented_selection_sets['OrientedSelectionSet.1'] model.oriented_selection_sets['OrientedSelectionSet.1'] >>> mpg = model.modeling_groups['PlyGroup.1'] model.modeling_groups['PlyGroup.1'] >>> mp_1 = mpg.create_interface_layer( name='InterfaceLayer.1', name='InterfaceLayer.1', global_ply_nr=0, oriented_selection_sets=(oes_1,), active=True)
create_modeling_ply (name=None, id=None, ply_material=None, ply_angle=0.0, number_of_lay-
ers=1, global_ply_nr=None, oriented_selection_sets=None, selection_rules=None, draping='no_draping', draping_seed_point=None, auto_draping_direction=True, draping_thickness_correction=True, draping_direction=None, draping_mesh_size=None, thickness_definition='nominal', core_geometry=None, active=True, taper_edges=None, thickness_field=None, thickness_field_type='absolute', angle_1_field=None, angle_2_field=None)
Create modeling ply
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The ACP Python Scripting Scripting User Interface Parameters • name: Name of the new Modeling Ply • id: Optional id of the new Modeling Ply • ply_material: Ply Material (Fabric, Stackup, SubLaminate) • ply_angle: Angle of the Ply Material • number_of_layers: Multiplier of this layer • global_ply_nr: Ply number for stacking sequence • oriented_selection_sets: Oriented Selection Set for the expansion
of the Modeling Ply • selection_rules: Element Selection Rules for the Modeling Ply • draping: The type of draping to be used “no_draping”, “evaluate_draping”, or “tabular_values” • draping_seed_point: Start/Seed Point for Draping
Automatically set draping direction (Default: True) • auto_draping_direction: Automatically • draping_direction: Direction to go in Draping (Default: None) • draping_mesh_size: Mesh size used for Draping (Default: Calculated average element size from mesh
) • thickness_definition: Enum that describes the method used for thickness definition (Default: Nominal) • core_ core_geome geometry: try: The assigned core geometry • active: Modeling Ply active
• taper_edges: Taper Edges for the Modeling Ply • thickness_field: Look-Up table column with scalar values for thickness sampling (optional)
thickness_field_ty field_type: pe: The type of thickness field ‘absolute’ or ‘relative’ • thickness_ • angle_1_field: Look-Up table column with scalar values for angle 1 • angle_2_field: Look-Up table column with scalar values for angle 2
Returns
The created Modeling Ply Example >>> >>> >>> >>>
oes_1 = model.oriented_selection_sets['OrientedSelectionSet.1'] model.oriented_selection_sets['OrientedSelectionSet.1'] fabric_1 = model.material_data.fabrics['Fabric.1'] model.material_data.fabrics['Fabric.1'] mpg = model.modeling_groups['PlyGroup.1'] model.modeling_groups['PlyGroup.1'] mp_1 = mpg.create_modeling_ply( name='ModelingPly.1', name='ModelingPly.1', ply_angle=0.0,
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Model Classes
global_ply_nr=0, number_of_layers=1, ply_material=fabric_1, oriented_selection_sets=(oes_1,), selection_rules=(rule1,),
draping="no_draping", draping_seed_point = (1,0,0), auto_draping_direction = True)
export_ply_geometries (filename, ply_level='production_ply', boundary=True, surface=True surface=True,,
offset_type='middle_offset', direction_arrows=False, first_direction=True, second_direction=False, arrow_length=1.0, arrow_type='no_arrow')
Exports the surface, boundary and/or fiber directions of modeling, production and analysis ply to igs or step file. Parameters • filename: File path (allowed extensions are iges, igs, step and stp). • ply_level: Defines which plies are exported: modeling_ply_wise, production_ply_wise or analys-
is_ply_wise. Default is production_ply_wise.
• boundary: Boolean whether to export the boundary. Default is True. • surface: Boolean whether to export the ply surface. Default is True. • offset_type: Offset type (can be no_offset, middle_offset, top_offset or bottom_offset). Default is
middle_offset. • direction_arrows: Boolean whether to export the direction arrows. Default is False. • first_direction: Boolean whether to export the first (main) material direction. Default is True •
second_direction: Boolean whether to export the second material direction. Default is False. • arrow_length: Length of the arrows. Default is 1.
• arrow_type: Defines the arrow type (can be standard_arrow, no_arrow, half_arrow). Default is
no_arrow. plies
Modeling Plies of the Modeling Group reorder_plies(source, target, type='after')
Reorder the ply group. Take source plies and insert before/after target ply. Parameters • source: list of plies to insert at new position • target: position to insert plies can be modeling ply or global_ply_nr • type: insert type can be after`(default) and `before serialize(butt_joints=False)
Serialize to Python string
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The ACP Python Scripting Scripting User Interface Parameters
6.5.12. ModelingPly class compolyx.ModelingPly(graph, obj, parent=None, element_vd=None)
Class to represent Modeling Ply add_oriented_selection_set (oriented_selection_set)
Add Oriented Selection Set Parameters • oriented_selection_set: The Oriented Selection Set to be assigned to ModelingPly add_selection_rule (rule, template_rule=False, rule_values=(), operation_type='intersect')
Add Rule to Modeling Ply Parameters • rule: The Rule to be added to the Modeling Ply • template_rule: Bool • rule_values: Parameters of the template rule • operation_type: Boolean operation type (intersect, add, remove) add_taper_edge(taper_edge, angle, offset=0.0)
Add Taper Edge to Modeling Ply Parameters
Taper Edge to be added to the Modeling Ply • taper_edge: The Taper
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• angle: Angle for tapering • offset: Offset for tapering angle_1_field
Angle 1 Correction field angle_2_field
Angle 2 Correction field area
Area of the Modeling Ply auto_draping_direction
Automatic selection of draping direction. clear_oriented_selection_sets ()
Clear all Oriented Selection Sets of the Modeling Ply
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Model Classes clear_selection_rules ()
Clear all selection_rules assigned to the Modeling Ply clear_taper_edges()
Clear all taper_edges assigned to the Modeling Ply core_geometry
Assigned Core Geometry direction_arrows(arrow_length=None, arrow_type='standard_arrow', offset_type='no_offset')
Direction arrows of the ply Parameters • arrow_length: length of the arrow • arrow_type: ‘standard_arrow ’ (default), ‘no_arrow ’, ‘half_arrow ’ • offset_type: ‘no_offset’ (default), ‘bottom_offset’, ‘middle_offset ’, ‘top_offset’ draped_fiber_directions
Get the Draped Fiber Directions of the Modeling Ply draping
Type of draping to be used draping_direction
The direction in which the draping starts. draping_direction_from_calculation (analysis_ply=None)
Draping direction used for draping calculation draping_mesh_size
The mesh size for draping.
draping_obj
Draping properties of the Modeling Ply draping_seed_point
The seed point where the draping starts. draping_seed_point_from_calculation (analysis_ply=None)
Draping seed point used for draping calculation draping_thickness_correction
Thickness correction for draping. element_normal_is_equal (element_id=None, normal=None)
Returns 1 if the element normal is equal the orientation of the modeling ply, else -1 Parameters • element_id: Element label
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The ACP Python Scripting Scripting User Interface • normal: Reference normal direction fiber_directions
Get the Fiber Directions of the Modeling Ply number_of_layers
Number of layers of the Modeling Ply on_sampling_point
Flag if the modeling ply is on sampling point orientation_at_element (element_id=None)
Returns the orientation of this modeling ply for a certain element. If the element does not belong to the modeling ply the return value is [0,0,0] Parameters • element_id: Element label orientations
Get the oriented normals of the Modeling Ply oriented_selection_sets
Oriented Selection Sets of the Modeling Ply ply_angle
Ply Angle of the Modeling Ply ply_offsets
Get the offsetted Modeling Ply price
Price of the Modeling Ply
production_plies
Production Plies of the Modeling Ply ref_directions
Get the Reference Directions of the Modeling Ply remove_oriented_selection_set (oriented_selection_set)
Remove Oriented Selection Set from Modeling Ply Parameters • oriented_selection_set: The Oriented Selection Set to be removed from ModelingPly remove_selection_rule (rule)
Remove Rule from Modeling Ply Parameters
removed from Modeling Ply • rule: The Rule to be removed
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Model Classes remove_taper_edge(taper_edge)
Remove taper_edge from Modeling Ply Parameters • taper_edge: The taper_edge to be removed removed from Modeling Ply selection_rules
Element Selection Rule of the Modeling Ply. serialize()
Serialize to Python string taper_edges
Taper Edges of the Modeling Ply. thickness_definition
Type of thickness-definition thickness-defi nition to be used thickness_field
LookUpTable Column with tabular thicknesses or None thickness_field_type
The type of the Thickness Thick ness field ‘absolute’ or ‘relative’ weight
Weight of the Modeling Ply write_boundaries(filename, format=None, offset_type='no_offset', with_direction_arrows=False,
arrow_length=None, arrow_type='standard_arrow')
Write boundaries in iges/step format Parameters
filename: output file • format: ‘iges’, ‘step’, None (automatic format recognition) • offset_type: ‘no_offset’ (default), ‘bottom_offset’, ‘middle_offset ’, ‘top_offset’ • with_direction_arrows: the element directions should be written to • arrow_length: length of the direction arrows (default is average element edge size) • arrow_type: type to be used as arrows ( ‘standard_arrow ’(default), ‘no_arrow’, ‘half_arrow ’)
6.5.13. ProductionPly class compolyx.production_ply.ProductionPly(graph, obj, parent=None, ele-
ment_vd=None) Class to represent Production Ply
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The ACP Python Scripting Scripting User Interface analysis_plies
Analysis Plies of the Production Ply angle
Ply Angle of the Production Ply area
Area of the production ply const_thickness
True if this Production Ply has a constant thickness direction_arrows(arrow_length=None, arrow_type='standard_arrow', offset_type='no_offset')
Direction arrows of the ply Parameters • arrow_length: length of the arrow • arrow_type: ‘standard_arrow ’ (default), ‘no_arrow ’, ‘half_arrow ’ • offset_type: ‘no_offset’ (default), ‘bottom_offset’, ‘middle_offset ’, ‘top_offset’ draping_obj
Draping representation ply_material
Ply Material of the Production Ply price
Price of the production ply save_draping_input_data (filename)
Writes out Modeling Ply to Draping Interface File
Parameters • filename: Path to the file to be written save_flat_wrap(filename)
Write the flatwrap to DXF, IGES or STEP file Parameters • filename: Path to the file to be writen thickness
Thickness of the Production Ply
update()
Update the Production Ply weight
Weight of the production ply
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Model Classes write_boundaries(filename, format=None, offset_type='no_offset', with_direction_arrows=False,
arrow_length=None, arrow_type='standard_arrow')
Write boundaries in iges/step format Parameters • filename: output file • format: ‘iges’, ‘step’, None (automatic format recognition) • offset_type: ‘no_offset’ (default), ‘bottom_offset’, ‘middle_offset ’, ‘top_offset’ • with_direction_arrows: the element directions should be written to • arrow_length: length of the direction arrows (default is average element edge size) • arrow_type: type to be used as arrows ( ‘standard_arrow ’(default), ‘no_arrow’, ‘half_arrow ’)
6.5.14. AnalysisPly class compolyx.AnalysisPly(graph, obj, parent=None)
ComPoLyX Class to represent Analysis Ply active
Sequence Entity is active active_in_post_mode
True if failure criteria will be processed for this ply. angle
Ply Angle of the Analysis Ply direction_arrows(arrow_length=None, arrow_type='standard_arrow', offset_type='no_offset')
Direction arrows of the ply Parameters • arrow_length: length of the arrow • arrow_type: ‘standard_arrow ’ (default), ‘no_arrow ’, ‘half_arrow ’ • offset_type: ‘no_offset’ (default), ‘bottom_offset’, ‘middle_offset ’, ‘top_offset’ draping_obj
Get the Fiber Directions of the Analysis Ply material
Ply Material of the Analysis Ply ply_material
Ply Material of the Analysis Ply
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The ACP Python Scripting Scripting User Interface thickness
Thickness of the Analysis Ply update()
Update the Analysis Ply write_boundaries(filename, format=None, offset_type='no_offset', with_direction_arrows=False,
arrow_length=None, arrow_type='standard_arrow')
Write boundaries in iges/step format Parameters • filename: output file • format: ‘iges’, ‘step’, None (automatic format recognition) • offset_type: ‘no_offset’ (default), ‘bottom_offset’, ‘middle_offset ’, ‘top_offset’ • with_direction_arrows: the element directions should be written to • arrow_length: length of the direction arrows (default is average element edge size) • arrow_type: type to be used as arrows ( ‘standard_arrow ’(default), ‘no_arrow’, ‘half_arrow ’)
6.5.15. InterfaceLayer class compolyx.InterfaceLayer(graph, obj, parent=None)
Class to represent Interface Layer add_open_area_set(value)
Add Open Area Set to Interface Layer add_oriented_selection_set (oriented_selection_set)
Add Oriented Selection Set Parameters • oriented_selection_set: The Oriented Selection Set to be assigned to Interface Lay Layer er clear_open_area_sets ()
Clears the open area selection clear_oriented_selection_sets ()
Clear all Oriented Selection Sets of the Interface Layer enabled
Whether this object is currently enabled or not. open_area_sets
Open area set(s) of the Interface Layer oriented_selection_sets
Oriented Selection Sets of the Interface Layer
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Model Classes ply_offsets
Get the offsetted Interface Layer remove_open_area_set (value)
Remove Open Area Set from Interface Layer remove_oriented_selection_set (oriented_selection_set)
Remove Oriented Selection Set from Interface Layer Parameters • oriented_selection_set: The Oriented Selection Set to be removed from Interface Layer serialize()
Serialize to Python string
6.5.16. ButtJointSequence class compolyx.ButtJointSequence(graph, obj, parent=None)
Class to represent the Butt Joint Sequence master_plies
Master plies of the butt joint squence serialize()
Serialize to Python string slave_plies
Master plies of the butt joint squence
6.5.17. FieldDefinition
class compolyx.FieldDefinition(graph, obj, parent=None)
Class to represent Field Definition active
Field Definition is active enabled
Whether this object is currently enabled or not. Mainly defined through the current application mode pre or post. field_variable_name
The name of the field variable defined. full_mapping
Whether the field is interpolated to the shell reference surface or to the actual ply-position by taking into account the shell offset; in solid models the interpolation takes always place at the actual ply position.
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The ACP Python Scripting Scripting User Interface locked
Returns the locked status of the Field Definition scalar_field
Look-up table used with this field definition. scope_entities
The entities defining the scope of the field definition. Allowed are Element Sets, Modeling Plies and Oriented Selection Sets. serialize()
Serialize to Python string
6.5.18. SamplingPoint class compolyx.SamplingPoint(graph, obj, parent=None)
The Sampling Point allows al lows to pick through the laminate at a certain point to run detailed analyses. Usage >>> model.create_sampling_point(name='Sampling Point')
aligned () ()
Returns true if the sampling direction is aligned with the normal direction of the closest element clt_query(query='layup', offset_is_middle=True offset_is_m iddle=True,, consider_coupling_effect=True) consider_coupling_effec t=True)
Returns the properties of the classical laminate theory: Parameters • query: query parameter (see below) • offset is middle: Bool to set laminate reference to middle for the laminate stiffness evaluation.
• consider_coupling_effect: Bool whether to consider the coupling effect or not
Options • layup: Returns the layup of the laminate (Modeling, Production and Analysis Plies). Default.
laminate_prop _properties: erties: Young’s, flexural and shear moduli of the laminate • laminate • polar_properties: E1, E2 and G12 depending on the laminate orientation • text_labels: Returns a list with the material names, angles and thicknesses • stiffness_matrix: Returns the laminate stiffness matrix (ABD) • compliance_matrix: Returns the lamiante compliance matrix (inverse of ABD) • laminate_forces: Returns a dict with the laminate forces Nx, Ny, Nxy, Mx, My, Mxy, Qx and Qy. Offset
is middle is always true for this evaluation.
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Model Classes Usage: >>> se.clt_query(query='polar_pr se.clt_query(query='polar_properties') operties')
consider_coupling_effect
Specifies the coupling effect is considered or not. create_plot(query={'layup': ['mp'], 'polar_properties': ['E1', 'G12']}, offset_is_middle=True, con-
sider_coupling_effect=True)
Generates 2D-plots with the results of interest Parameters • query: query parameter • offset_is_middle: Bool to set lamiante reference plane to middle • consider_coupling_effect: Bool whether to consider the coupling effect or not
Options • layup:[‘mp’, ‘pp’, ‘ap’] Modeling Plies, Production Plies and Analysis Plies • polar_properties:[ ‘E1’,’E2’,’G12’] polar plot of laminate stiffesses • strains:[ ‘e1’, ‘e2’, ‘e3’, ‘e12’, ‘e13’, ‘e23’, ‘eI’, ‘eII’, ‘eIII’] - Strain definition name and component • stresses:[ ‘s1’, ‘s2’, ‘s3’, ‘s12’, ‘s13’, ‘s23’, ‘sI’, ‘sII’, ‘sIII’] - Stress definition name and component • failures:[‘FailureCriteria.1_irf ’, ‘FailureCriteria.1_rf ’, ‘FailureCriteria.1_mos’, ‘FailureCriteria.1_fm’] - Name
of FC and value • text_labels:[ ‘material’, ‘angle’, ‘thickness’]
Usage
>>> se.create_plot(query={layup:[' se.create_plot(query={layup:['mp'], mp'], failure:['FailureCriteria.1_irf']} failure:['FailureCriteria.1_irf']} >>> se.graph_plot.x_values >>> se.graph_plot.layer_thicknesse se.graph_plot.layer_thicknesses s
direction
Sampling Point Direction element_id
Element ID (label) of the Sampling Point enabled
Whether this object is currently enabled or not. SamplingPoints are always enabled. graph_plot
Graph Plot object used to configure 2D plots. locked
Sampling Point is generated from an imported source and cannot be changed.
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The ACP Python Scripting Scripting User Interface offset_is_middle
Specifies the offset of the reference plane for the CLT analysis. plies
Plies of the Sampling Point point
Sampling Point Point reference_direction
Reference direction rosette
Rosette of the Sampling Point solution_set
Solution and Set selection update_plot(offset_is_middle, consider_coupling_effect)
Updates the 2D plot Parameters • offset_is_middle: Boolean to set laminate reference plane to the laminate mid-plane (ignore coupling
effects due to the offset) • consider_coupling_effect: Bool whether to consider the coupling effect or not (ignore coupling effects
in general) use_default_reference_direction
Flag to use default reference direction
6.5.19. SectionCut
class compolyx.SectionCut(graph, obj, parent=None, color_table=None)
Section Cut Class showing the lay-up in the cutting plane. changed
Status boolean. Set to true if the underlying data has been changed. Write only property core_scale_factor
Get/set the core scale factor display_data
Section cut plots elastic_measures
Cross-sectional Measures of Elasticity element_labels
Label of elements within ex1 array.
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Model Classes element_nodes
Coincidence list element_types
Element types within ex1 array. enabled
Whether this object is currently enabled or not. SectionCuts are always enabled. export_surface_section_cut (path, format='becas:in', export_strength_limits=True)
Exports the suface section cut to BECAS or ANSYS MAPDL Paramters • path: File path or directory depending on the export format. • format: Export format. Implemented are ‘becas:in’ and ‘ansys:cdb’. ‘becas:in’ is the default. • export_strength_limits: Boolean whether to export the strength limits for BECAS. True by by default.
Usage >>> section_cut.export_surface_section_cut(r'D:\tmp\section_cut.cdb', section_cut.export_surface_section_cut(r'D:\tmp\section_cut.cdb', 'ansys:cdb', 1.e-3) >>> section_cut.export_surface_sec section_cut.export_surface_section_cut(path=r'D:\tmp', tion_cut(path=r'D:\tmp', format='becas:in', export_strength_limits=False)
Output • mapdl: CDB file including the nodes and elements • becas: BECAS IN input files: N2D, E2D, EMAT and MATPROPS. Optional FAILMAT. extrusion_type
Section Cut Types can be: wire_frame,surface_normal,surface_sweep_based geometric measures
Cross-sectional Measures of Geometry in_plane_reference_direction1
Reference direction for cross-sectional measures in_plane_reference_direction2
Reference direction for cross-sectional measures intersection_type
Intersection Types can be: normal_to_surface,in_plane locked Section cut was imported and cannot be changed. mass_measures
Cross-sectional Measures of Mass node_labels
Label of nodes within nx1 array.
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The ACP Python Scripting Scripting User Interface nodes
Returns nodes of this mesh as nx3 array. normal
Get/set the plane normal number_of_interpolation_points
User-defined number of interpolation points. origin
Get/set the plane origin scale_factor
Scale factor used for visualization of section cuts search_radius
User-defined search radius. section_cut_type
Section Cut Types can be: modeling_ply_wise,production_ply_wise,analysis_ply_wise surface_display_data
Section cut surface plot surface_mesh
Section cut line surface mesh tolerance
T Tolerance olerance used to generate the surface section cut. use_default_lut_settings
Boolean whether to use the dault settings of the LookUp Table. use_default_tolerance
477
Whether to use the default feature tolerance. 0.1% of the averaged element size. vtk_element_data
Returns mesh coincidence data in the format needed by VTK. wireframe_display_data
Section cut wireframe plot wireframe_mesh
Section cut line wireframe mesh
6.5.20. Sensor class compolyx.Sensor(graph, obj, parent=None)
Sensor object for meassuring areas, prices, weights, and centers of gravity add_entity(entity)
Add entity to Sensor
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Model Classes area
Area covered by all Entities of the Sensor center_of_gravity
Center of Gravity over all Entities of the Sensor clear_entities()
Clear all entities of this Sensor enabled
Whether this object is currently enabled or not. Sensors are always enabled. entities
Entities of the Sensor locked
Sensor cut was imported and cannot be changed. modeling_ply_area
Cumulated area of all modeling-plies involved price
Price over all Entities of the Sensor production_ply_area
Cumulated area of all production-plies involved remove_entity(entity)
Remove entity from sensor sensor_type
Sensor type. Allowed string values: sensor_by_area, sensor_by_plies, sensor_by_material and sensor_by_solid_model.
weight
Weight over all Entities of the Sensor
6.5.21. PlyBook This section contains the following topics: 6.5.21.1. PlyBook 6.5.21.2. Chapter
6.5.21.1. PlyBook class compolyx.PlyBook(name='PlyBook', parent=None, reST_ply='', reST_chapter='',
reST_title_page='', scene=None) Class to represent a ply book chapters
Dictionary with all chapters defined.
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The ACP Python Scripting Scripting User Interface create_chapter(name, view=None, ply_entities=[])
Add a chapter to the Ply book Parameters • name: Name of the chapter to be added
snapshots of the chapter • view: The view for snapshots • ply_entities: List of modeling plies and modeling groups for the chapter generate(filename, format=None)
Generate the complete plybook Parameters • filename: output filename • format: pdf, html, odt, txt reST_chapter
reST chapter template reST_ply
reST ply template reST_title_page
reST title page template
6.5.21.2. Chapter class compolyx.Chapter(name, parent, view=None, ply_entities=[], id=0)
Class to represent plybook chapter
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generate(reST_chapter, reST_ply, scene, tmp_dir)
Generate the reST file for one single ply ply_entities
Plies/PlyGroups for the chapter
6.6. Solid-model Classes This section contains the following topics: 6.6.1. SolidModel 6.6.2. ExtrusionGuide 6.6.3. SnapToGeometry 6.6.4. CutOffGeometry 6.6.5. ImportedSolidModel
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Solid-model Classes
6.6.1. SolidModel class compolyx.SolidModel(graph, obj, parent=None)
Solid Model class active
Solid-Model active add_disable_dropoff_set_on_bottom (set) (set)
Add set where the drop-offs on bottom surface are disabled add_disable_dropoff_set_on_top (set)
Add set where the drop-offs on top surface are disabled clear_disable_dropoff_sets_on_bottom (())
Clear sets where the drop-offs on bottom are disabled clear_disable_dropoff_sets_on_top ()
Clear sets where the drop-offs on top are disabled clear_generated_data ()
Function clears generated solid model but keeps all definitions. connect_butt_joined_plies
Do not make drop-offs between butt-joined plies if set to True copy_extrusion_guide (source)
Copy a Extrusion Guide Parameters • source: Source object to copy
Returns
New instance of a Extrusion Guide copy_snap_to_geometry_obj (source)
Copy a Snap To Geometry Parameters • source: Source object to copy
Returns
New instance of a Snap To Geometry create_extrusion_guide (name, edge_set=None, id='', cad_geometry=None, direction=0.0, 0.0,
0.0, radius=None, depth=1.0, use_curvature_correction=False, active=True)
Create a new extrusion guide Parameters
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The ACP Python Scripting Scripting User Interface • name : the name of the extrusion guide • edge_set : an edge set where this guide applies • id : the id of the extrusion guide • cad_geometry : a cad geometry object • direction: Extrusion direction • radius
distance up to which node translations due to the guide will be propagated through the mesh 0.0 : only the nodes extruded from edge_set will be shifted onto the guide • depth
intensity for the propagation of mesh corrections 1.0 : linear decay from guide to radius >1.0 : higher reach >> sm.reorder_extrusion_guides(source = sm.extrusion_guides['wall'], target=sm.extrusion_guides[' target=sm.extrusion_guides['leading_ed leading_ed
snap_to_geometry_objs
Snap to Geometry objects warping_limit
Defines the maximum allowable warping limit.
6.6.2. ExtrusionGuide class compolyx.ExtrusionGuide(obj, parent=None)
Extrusion guide class active
Extrusion Guide active Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
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The ACP Python Scripting Scripting User Interface cad_geometry
Associated CADGeometry. depth
intensity for the propagation of mesh corrections, depth=1 leads to a linear decay from the guide to the radius, depth>> >>> >>> >>>
import compolyx db = compolyx.DB() model = db.models['class40.1'] sol = db.models['class40.1'].add_solution(name='class40.1', path='class40.rst', format='ansys:rst')
ID
Id to be displayed in Envelope solution active
Activate or deactivate solution
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Solution Classes clear()
Clear all result data clear_element_results ()
Resets the post-processing results for each layered element clear_failure_criteria_results ()
Resets the failure criteria results for each layered element enabled
Whether this object is currently enabled or not. Mainly defined through the current application mode pre or post. export_results_to_csv (definition=None, entities=[], file_path=None, solution_set=- 1,
solids=False, spot='all')
Exports the shell results of the selected entities to a csv file. Parameters • definitions: Selected definition - CombinedFailure Criteria object or as string ‘deformations’, ‘strains’ or ‘stresses’ • entities: Defines the selection for the export. Can be a list of ElementSets, AnalysisPlies or SolidModels • file_path: File name • solution_set: Solution Set for which data is requested • solids: Boolean whether to take the results of the solid elements or not. Default is False (results of
shells). • spots: Layer positions for which the results are exported. Allowed are ‘bot’, ‘mid’, ‘top’, ‘bot/top’, and ‘all’.
Export results of solid models: Select the element set which is selected in the extrusion settings. Usage
>>> model = db.active_model >>> model.solutions['Solution.1']. model.solutions['Solution.1'].export_results_to_csv( export_results_to_csv( definition='stresses', entities=[model.element_sets
ext_id
Id of corresponding Solution in external solution (ComponentID). format
File format string. Choose one of ‘abaqus:inp’,’ansys:cdb’ or ‘nastran:f06 ’ has_element_temperatures
Boolean flag if element nodal temperatures are read from the rst file. has_progressive_damage
Boolean flag if progressive_damage data are read from the rst file.
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The ACP Python Scripting Scripting User Interface load () ()
Load result data from file load_factor
Optional load factor within substep of non-linear solution where the nodal solution should be taken from. Only valid for ‘nastran:f06 ’ format. Becomes (False,0) if not defined. path
Path to the data file path2
Path to the data file plots
Container with PostProcessing Plots query(definition, options={'eval_ins': False}, position='centroid', selection='all', entity=None, entit-
ies=None, spot=None, component=None, rosette=None, simulate=False, solution_set=- 1) Query results from the solution Parameters • definition
The postproc definition defines what results are evaluated. Can be given as CombinedFailureCriteria object or as string such as ‘strains’, ‘stresses’, ‘laminate_forces’, ‘deformations’, ‘temperatures’ or ‘progressive_damage’. • options
Dict with the additional options used to fully configure the definition. – stresses: options={“eval_ins”:True} to enable the interlaminar normal stress evaluation for
shells
• position
Position where data is queried: – nodal, centroid, element_nodal, integration_point or element_results • selection
The selection set determines the selected nodes and elements. Can be given as string ‘sel0’ - ‘sel5’ or ‘all’ or can be given as ObjectSelection object such as model.selection or scene.active_set • entity
Entity for which results are evaluated. Currently supported: Analysis ply or analysis ply vertex • entities : If a list of entities is given, the query will also compute and return a list of results, with one
array for each entity. • spot: Used to identify bot, mid or top when querying layered shells
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Solution Classes Components to query. Valid components for • component: Components – DEFORMATION - x, y, z, usum, rotx, roty, rotz -> (nx1) - all -> (nx6), translations, rotations ->
(nx3) – STRAIN - e1, e2, e3, e12, e23, e13, eI, eII, eII, von_mises -> (nx1) - all -> (nx6), principals ->
(nx3) – STRESS - s1, s2, s3, s12, s23, s13, sI, sII, sII -> (nx1) - all -> (nx6), principals -> (nx3) – FAILURE CRITERIA - irf (Inverse reserve factor), rf (Reserve factor), mos (Margin of safety) ->
(nx1) - fm (Failure mode) ->(n x string(size(n x 1) (Only available for element queries where no entity is given.) – LAMINATE FORCES - all -> (nx8) – PROGRESSIVE DAMAGE - status (damage status), ft, fc (fiber tensile/compressive) ->(nx1) - mt,
mc (matrix tensile/compressive), s (shear) ->(nx1) - sed (energy dissipated per unit volume), sedv (energy per unit volume due to viscous damping) ->(nx1) • rosette : If a rosette is given, the results are evaluated with respect to this coordinate system (not
recommended for non-linear results) • simulate
Whether the query is only simulated to test if it will return data. If this flag is set the query(…) function will only return 0 or 1. • solution_set : Identifier of the queried solution. -1 identifies the last available Set.
Usage
>>> solution.query(definition='lam solution.query(definition='laminate_forces',position='centroid inate_forces',position='centroid',selection='sel0',component='al ',selection='sel0',component='all',rosette l',rosette >>> solution.query(definition=model.defintions['FailureCriteria'], solution.query(definition=model.defintions['FailureCriteria'], position='centroid', selection='sel0', co >>> solution.query(definition='stresses', position='element results', selection='sel0', component='s3',solut
read_stresses_strains
True if the stresses and strains are to be read from rst file. Only valid for ‘ansys:rst ’ format. recompute_iss_of_solids
Use laminate-based computation method to recalculate the interlaminar shear stress distribution. renumbering_mapping_paths
Path of the assembly renumbering files. serialize()
Serialize to Python string set
Result set to be read. Only valid for ‘ansys:rst ’ format. solution_dict
The time or frequency dictionary used in the solution plots GUI.
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The ACP Python Scripting Scripting User Interface subcase
Optional subcase to read. Only valid for ‘nastran:f06’ format. Becomes (False,0) if not defined. time_or_frequency
The time or frequency associated with the active set. use_felyx_to_compute_pp_results
True if the stresses and strains are to be computed by felyx. If I f the stresses and strains are read from rst file, nothing is computed. use_solid_results
Allows to visualize the post-processing results of layered solid models on the ‘Layered Solid Reference Surface’.
6.7.2. EnvelopeSolution class compolyx.EnvelopeSolution(graph, obj, parent=None) add_solution_set(solution, sset=- 1)
Add solution set to solution sets of Envelope Solution Parameters • solution: Solution object • sset: Solution set (default: -1) clear_solution_sets ()
Clear Solution Sets of Envelope Solution enabled
Whether this object is currently enabled or not. Mainly defined through the current application mode pre or post.
remove_solution_set (solution, sset=- 1)
Remove solution set from solution sets of Envelope Solution Parameters • solution: Solution object • sset: Solution set (default: -1)
6.8. Scene Classes This section contains the following topics: 6.8.1. Scene 6.8.2.View
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Scene Classes
6.8.1. Scene class compolyx.Scene(graph, model=None, name='', id=None, title='', view=None, parent=None,
active_set=None) Class to represent Scene active_set
Set of active entities background
Background color background2
Background color 2 camera
Camera settings changed
Status boolean. Set to true if the underlying data has been changed. Write only property color_tables
Collection of color tables descriptions_changed
Set to True if descriptions should be updated. fit_to_window
Reset the zoom of the window foreground
Foreground color
logo_type
Logo type: default or black mode
Current ACP mode (pre or post). projection
Projection method: ‘parallel’ or ‘perspective’ save_snapshot(path, width=None, height=None, draw_background=False) draw_background=False)
Create a snapshot of the scene Parameters • path: File path
pixels of the snapshot • width: Width in pixels • height: Height in pixels of the snapshot
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The ACP Python Scripting Scripting User Interface • draw_background: Boolean whether to draw the background or not. If false, the background is
white. scale_factor
Scale factor of the deformed mesh. serialize()
Serialize to Python string show_global_coordinate_system
T Toggle oggle visibility of global coordinate system marker show_labeled_bounding_box
T Toggle oggle visibility of labeled bounding box show_selected_mesh
Specify whether to show/highlight currently selected Elements show_silhouette
Specify whether to show the outline of currently selected elements show_solid_elements
Specify whether to highlight Shell or Solid Elements in Selections status
Status of the object title
Scene title update_direction_display_data (entities)
“
Function syncronizes the following direction plots with the added/removed entities given: - orientations” - “ref_directions ” - “fiber_directions ” - “draped_fiber_directions ”
uptodate
Apply a view to the scene. Write only view
Apply a view to the scene.
6.8.2.View class compolyx.View(name, position=0.0, 0.0, 0.0, orientation=0.0, 0.0, 0.0, rotation_point=0.0,
0.0, 0.0, parallel_scale=1.0, projection='perspective', locked=False, parent=None) ComPoLyX class to capture view properties. Access: >>> import compolyx >>> db = compolyx.DB() >>> view1 = db.create_view(name='View.1', position=[1.5, 5.75, 7.], orientation=[-0.4, -0.4, 0.8], rotation_point
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Postprocessing Postproc essing Definition Classes locked
A View which is imported from an other source can not be modified. orientation
Get/set the view orientation parallel_scale
Get/set the view parallel perspective scale factor. position
Get/set the view position projection
Get/set the projection method parallel or perspective rotation_point
Get/set the view rotation point. serialize()
Serialize to Python string
6.9. Postprocessing Postprocessing Definition Definitio n Classes This section contains the following topics: 6.9.1. CombinedFailureCriteria
6.9.1. CombinedFailureCriteria This section contains the following topics: 6.9.1.1. MaxStressCriterion
6.9.1.2. MaxStrainCriterion 6.9.1.3.TsaiWu 6.9.1.4.TsaiHill 6.9.1.5. Hashin 6.9.1.6. Hoffman 6.9.1.7. Puck 6.9.1.8.Wrinkling 6.9.1.9. CoreShear 6.9.1.10. Larc 6.9.1.11. Cuntze 6.9.1.12.VonMises 6.9.1.13. ShearCrimping class compolyx.CombinedFailureCriteria(graph, obj, failure_criteria=[], parent=None)
CombinedFailureCriteria class
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The ACP Python Scripting Scripting User Interface enabled
Whether this object is currently enabled or not. Mainly defined through the current application mode pre or post. serialize()
Serialize to Python string
6.9.1.1. MaxStressCriterion class compolyx.MaxStressCriterion(s1=1, s2=1, s3=0, s12=1, s13=0, s23=0, wf_s1=1.0,
wf_s2=1.0, wf_s3=1.0, wf_s12=1.0, wf_s13=1.0, wf_s23=1.0) Max stress failure criterion configuration Properties are s1, s2, s3, s12, s13, s23, wf_s1, wf_s2, wf_s3, wf_s12, wf_s13, wf_s23 e.g. MaxStressCriterion(s1=1, s2=1, s3=0, s12=1, s13=0, s23=0, wf_s1=1, wf_s2=1, wf_s3=1, wf_s12=1, wf_s13=1, wf_s23=1) s1
specifies whether to compute max stress in 1 direction s12
specifies whether to compute max shear stress in 1 direction s13
specifies whether to compute max normal stress in 1 direction s2
specifies whether to compute max stress in 2 direction s23
specifies whether to compute max normal stress in 2 direction s3
specifies whether to compute max stress in 3 direction serialize()
Serialize to Python string wf_s1
weighting factor of s1 wf_s12
weighting factor of s12 wf_s13
weighting factor of s13 wf_s2
weighting factor of s2 wf_s23
weighting factor of s23
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Postprocessing Postproc essing Definition Classes wf_s3
weighting factor of s3
6.9.1.2. MaxStrainCriterion class compolyx.MaxStrainCriterion(e1=1, e2=1, e3=0, e12=1, e13=0, e23=0, wf_e1=1.0,
wf_e2=1.0, wf_e3=1.0, wf_e12=1.0, wf_e13=1.0, wf_e23=1.0, eXt=0.0, eXc=0.0, eYt=0.0, eYc=0.0, eZt=0.0, eZc=0.0, eSxy=0.0, eSxz=0.0, eSyz=0.0, force_global_strain_limits=False) Max strain failure criterion configuration e1
specifies whether to compute max strain in 1 direction e12
specifies whether to compute max shear 12 strain e13
specifies whether to compute max shear 13 strain
e2
specifies whether to compute max strain in 2 direction e23
specifies whether to compute max shear 23 strain e3
specifies whether to compute max strain in 3 direction eSxy
global limit shear strain in material 12 direction
eSxz
global limit shear strain in material 13 direction eSyz
global limit shear strain in material 23 direction eXc
global limit compression strain in material 1 direction eXt
global limit tension strain in material 1 direction eYc
global limit compression strain in material 2 direction eYt
global limit tension strain in material 2 direction eZc
global limit compression strain in material 3 direction
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The ACP Python Scripting Scripting User Interface eZt
global limit tension strain in material 3 direction force_global_strain_limits
force to use global strain limits serialize()
Serialize to Python string wf_e1
weighting factor of e1 wf_e12
weighting factor of e12 wf_e13
weighting factor of e13 wf_e2
weighting factor of e2 wf_e23
weighting factor of e23 wf_e3
weighting factor of e3
6.9.1.3.TsaiWu class compolyx.TsaiWu(dim=2, wf=1.0)
Tsai Wu failure criterion configuration
495
dim
dimension of the Tsai-Wu failure criterion (2 or 3) serialize()
Serialize to Python string wf
weighting factor
6.9.1.4.TsaiHill class compolyx.TsaiHill(dim=2, wf=1.0)
Tsai Hill failure criterion configuration dim
dimension of the Tsai-Hill failure criterion (2 or 3) serialize()
Serialize to Python string
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Postprocessing Postproc essing Definition Classes wf
weighting factor
6.9.1.5. Hashin class compolyx.Hashin(dim=2, hf=1, hm=1, hd=1, wf_hf=1.0, wf_hm=1.0, wf_hd=1.0)
Hashin failure criterion configuration dim
dimension of the Hashin failure criterion (2 or 3) hd
specifies whether to compute delamination hf
specifies whether to compute fiber failure hm
specifies whether to compute matrix failure serialize()
Serialize to Python string wf_hd
weighting factor wf_hf
weighting factor wf_hm
weighting factor
6.9.1.6. Hoffman class compolyx.Hoffman(dim=2, wf=1.0)
Hoffman failure criterion configuration dim
dimension of the Hoffman failure criterion (2 or 3) serialize()
Serialize to Python string wf
weighting factor
6.9.1.7. Puck class compolyx.Puck(dim=2, force_global_constants=False, p21_pos=0.325, p21_neg=0.275,
p22_neg=0.225, p22_pos=0.225, s=0.5, M=0.5, interface_weakening_factor=0.8, pf=1, pmA=1, pmB=1, pmC=1, pd=1, wf_pf=1.0, wf_pmA=1.0, wf_pmB=1.0, wf_pmC=1.0, wf_pd=1.0, cfps=True) Release 2020 R2 - © ANSYS, Inc. All rights reser ved. - Contains proprietary and confidential information of ANSYS, Inc. and its subsidiaries and affiliates.
The ACP Python Scripting Scripting User Interface Puck failure criterion configuration M
Degradation factor (Default=0.5) cfps
specifies whether to consider the influence of fiber parallel stresses on inter-fiber failure dim
dimension of the puck failure criterion (1, 2 or 3) force_global_constants
Use global Puck constants instead of material specific values. interface_weakening_factor
Interface weakening factor (Default=0.8) p21_neg
Inclination of the failure curve for negative normal matrix stresses (Default=0.275) p21_pos
Inclination of the failure curve for positive normal matrix stresses (Default=0.325) p22_neg
Inclination of the failure curve for negative normal matrix stresses (Default=0.225) p22_pos
Inclination of the failure curve for positive normal matrix stresses (Default=0.225) pd
specifies whether to compute delamination pf
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