NASA/SP--2000-6111
Fault
Tree Analysis
A Bibliography
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July 2000
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NASA/SP--2000-6111
Fault
Tree Analysis
A Bibliography
National
Aeronautics
and
Space Administration NASA
Scientific
Information
July 2000
and Technical
Program
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Table of Contents
Subject
Divisions
Document citations are grouped first by the following category-level Table of Contents.
divisions.
Select
a division
A° Aeronautics
H.
Physics
B, Astronautics
I.
SociaJ
and Information
J,
Space
Sciences
K.
General
C, Chemistry
and MateriaJs
D, Engineering
title to view
the
Sciences
E, Geosciences R
Life Sciences
G° Mathematical
and Computer
Science_,_
ndexes Two indexes are available. You may use the find command under the tools menu while viewing the PDF file for direct match searching on any text string. You may also select either of the two indexes provided
for searching
Subject
Author
AvailabiJity
Information Center Server),
(STI)
subject
terms
and personal
author
names.
index
Document Select
Thesaurus
Index
Term
PersonN
on NASA
Availability Info
Program
for AeroSpace and availability
for important Office
Information and pricing
products (CASI)
information and
services,
for access
information
about
NASA
including
to the NASA
for cited documents.
Scientific
registration CASI
TRS
and with
Technical the NASA
(Technical
Report
Subject
Select
01
Categories
a category
to view the collection
Aeronautics Includes
research
within
the Earth's
of aircraft.
information
02
fans
and
related
to manned
atmosphere.
to space
means
no abstracts
in that category.
topics
Also
and unmanned
includes
in aeronautics
vehicles
aircraft
and the problems
manufacturing,
maintenance,
see categories
02 through
and
09.
of
see 12 Astronautics.
elements
and Heat
passenger and
operations
vehicles, surfaces.
cargo
and
aircraft
and to airport
Utilization
and Surface
Transportation.
Aircraft
Communications
Aircraft Includes aircraft
all stages
For related Surface
with
see also
aircraft and
ground
hardware
stators, 34 Fluid
are covered
operations; specific
in 09 Research
Communications
Transportation
and Safety;
flight
to ground and Support
and Navigation. and
85 Technology
NoA.
and between
air traffic
control. 17
and Tracking,
aircraft;
air navigation
For related Space
information
systems see also 06
Communications;
and 32 Communications
Spacecraft
and Radar.
'_:esting and Performance
of design
Mechanics.
of aircraft
and aircraft
and evaluation,
structures
and aircraft
see also 18 Spacecraft For land transportation
3
Design, vehicles,
and systems.
and flight Testing
Also includes
simulation
technology.
and Performance
see 85 Technology
and 39
Utilization
and
Transportation.
Avionh;s
and Aircraft
Includes
all avionics
intended
for use in aircraft.
and Navigation; Astrionics;
information,
and
and Navigation and
performance,
information,
Structural
of rotors,
in 04 Aircraft
Instrumentation;
Command
Design,
testing,
based);
Aircraft
Communications,
Space
of communication
ground
and
related
Systems
construction
is covered
see also 16
and
aerodynamics
operations;
accidents.
information
(satellite
components
2
air transport
aircraft
For related
Avionics
For
airframe
and Safety
(Air). Air traffic control
all modes
bodies,
Also includes
of turbomachinery.
and
Includes
test
Transfer.
hazards; of
Facilities
flight
and control
Air Transportation safety
For
NoAo
wings,
other
Includes
O6
topics
aerodynamics
Mechanics
05
N.A.
Aerodynamics combinations,
04
cited.
1
For specific
related
Includes
O3
of records
A. Aeronautics
(GenerN)
general
of flight repair
of the Division
Instrumentation
systems,
08 Aircraft
cockpit
For related Stability
and 35 Instrumentation
and cabin
5 display
information, and
Control;
and Photography.
vi
devices;
and
see also 04 Aircraft 19 Spacecraft
flight
instruments
Communications
Instrumentation
and
07
Aircraft
Propulsion
Includes
prime propulsion
compressors;
and
Power
systems and systems components,
and onboard
auxiliary
also 20 Spacecraft Propulsion Production and Conversion.
08
Aircraft
Stability
Includes For
Avionics
09
and Aircraft
Includes water
Subiect Select
12
a category
qualities;
05 Aircraft
piloting;
Design,
Facilities
tubes;
and flight
equipment
and Safety.
AstronaL_tics
flight controls;
Testing
and autopilots.
and Performance
and
aircraft
6
repair
simulators;
and systems.
and overhaul and
aircraft
For airport
facilities
facilities; engine
ground
wind tunnels,
test
stands.
operations
see 14 Ground
of the Division
research
platforms
Support
Systems
and
of records
cited.
B, Astronautics
N.A.
means
no abstracts
in that category.
topics
or objects
For
related
to space
launched
into,
Also includes
specific
topics
exploration,
flight
and manned
or assembled
manufacturing
in astronautics
see 91 Lunar
and unmanned
in, outer
space;
and maintenance
see
categories
and Planetary
Science
13
Includes
of such vehicles through
20.
Includes
and free-flight
Support launch
e.g., mobile
trajectories;
Systems
complexes,
transporters;
and supporting
Facilities
For
and Exploration.
N,A.
powered
Ground
space
and related
Astrodynamics
and
research
[:acilities
and production
and test chambers
equipment.
and orbital
For related
and launching
dynamics.
(Space} facilities;
and simulators. information
7
ground Also
support
includes
see also 09 Research
equipment,
extraterrestrial and Support
(Air).
Launch launch
Also
see 03 Air
6
and equipment.
extraterrestrial
Includes
06
(Genera0
general
or platforms.
bases
see
(Air)
For astronautical
to view the collection
components
15
also
hangars,
Categories
vehicles,
14
and 44 Energy
(Space).
Includes
13
shock
ground
Transportation
information
and Fuels,
Instrumentation.
and
airport
Facilities
see
runways,
tunnels,
includes
For related
28 Propellants
NoAo
handling
and Support
airports,
engines and
plants for aircraft.
and Power,
aircraft
information,
Research
power
e.g., gas turbine
and Control
flight dynamics,
related
5
Vehicles all classes
operations.
Performance;
and
Launch
of launch
vehicles,
Operations
NoAo
launch/space
For related
information
and 20 Spacecraft
Propulsion vii
see also
vehicle
systems,
18 Spacecraft
and Power.
and boosters;
Design,
Testing,
and and
16
Space Transportation Includes
passenger
techniques. Vehicles space
17
and cargo
For related
space
Vehicles,
NoAo
transportation,
information,
and Launch
suits,
and Safety e.g., shuttle
see also 03 Air Transportation
and 18 Spacecraft
see 54 ManSystem
operations;
Technology
Space Communicatkms,
Design,
and space rescue
and Safety
Testing
and 15 Launch
and Performance.
For
and Life Support.
Spacecraft
Communicatkms,
Command
and ]°racking Includes
space
guidance;
and
N_A_ systems
telemetry;
spacecraft
radio
Communications
18
satellites;
as thermal For
life
Design,
information, Mechanics,
19
controlling, vehicles
manufacture, For related
For spaceborne
and Photography;
For spaceborne
astronomical
instruments
Spacecraft main
auxiliary
power
propulsion sources.
systems
Subject Categories Materials
23
a category
Includes chemical For
research
compounds
specific
astrochemistry
topics
Performance,
For related 39
Structural
or processing information,
NoAo
for the purpose data
related
see also
not integral
and
Photography;
other For
of measuring, to the
detecting,
operation
06 Aircraft
to the vehicle
of space
Instrumentation
and
itself see 35 Instrumentation
astronomical spaceborne
instruments telescopes
see 89 and
other
components,
information, Vehicles
of records
e.g.,
topics
in chemistry
cited.
rocket
engines;
see also 07Aircraft and
Launch
and
Propulsion
Operations;
and 44 Energy
C. Chemistry
N.A.
means
spacecraft and Power;
no abstracts
and
in that category.
(Genera0 related
and materials
see category
and
8
of the Division
and Materials
general
and
characteristics.
Support.
and Astrionics
15 Launch
to view the collection
Chemistry
Testing
and stability
and Life
such
and Power
For related
28 Propellants and Fuels; Production and Conversion.
Select
control
and components
see 89 Astronomy.
Propulsion
Includes
systems
and Safety.
telescopes
and
7
Technology
Design,
instruments
Instrumentation
04 Aircraft
and Radar.
spacecraft
or use of devices
recording,
or platforms.
Astronomy,
Aircraft
see also
and
Performance
stations;
Transportation
computing,
Avionics;
20
05
astronavigation
information,
and spacecraft
Ir-_strumentation
the design,
related
see 54 ManSystem
and 16 Space
Spacecraft Includes
also
space
controls;
systems,
see
and
platforms;
and environmental support
For
networks;
and 32 Communications
Testing
space
communications
blackout.
and Navigation
Spacecraft Includes
space
to the composition,
as they relate and
12
materials
90 Astrophysics.
viii
properties,
to aircraft, see
launch
categories
structure,
vehicles, 24
and use of
and spacecraft.
through
29.
For
24
Composite
MateriNs
Includes physical, materials.
25
Inorganic, Includes
and mechanical
analysis,
and
and MetalJic
Includes
physical,
of laminates
and other
composite
Chemistry
and use inorganic
and photochemistry.
and Thermodynamics,
MetNs
properties
Physical
synthesis,
electrochemistry;
Dynamics
26
chemical,
Organic,
the
theory;
12
13
and
organic
For related
For astrochemistry
compounds;
information
see category
combustion
see also 34 Fluid
90 Astrophysics.
Materials
chemical,
N_A.
and mechanical
properties
of metals
and metallic
materials;
and
metallurgy.
27
NonmetalJic Includes
28
physical, textiles,
Composite
Materials.
PropelJants
adhesives,
and
propellants,
igniters
07 Aircraft Production
Propulsion and Power, and Conversion.
For nuclear
application. reduced-gravity Science
Also
their
composite
storage
Physics.
20 Spacecraft
general
of materials,
includes
materials
and handling
For related
Propulsion
and Space
compounds,
the development
environments.
see
see also
and 44 Energy
and processes of space
for research
research
technology,
topics
industrial
or
and compounds
commercialization
in see
Policy.
of records
cited.
N.A.
D. Engineering means
no abstracts
in that category.
(GenerN)
in engineering
24
procedures;
information
and Power,
of materials
For legal aspects
of the Division
to view the collection
Engineering
topics
and oxidizers;
fuels see 73 Nuclear
development
Categories
a category
vacuum
For
lubricants,
NoAo
space-based
84 Law, Political
Includes
materials.
ceramic
elastomers,
Processing
simulated
Subject
of plastics,
NoAo
fuels.
Space
properties
and Fuels
rocket
commercial
31
and mechanical
and aircraft
Includes
Select
N_Ao
chemical,
polymers,
Includes
29
Materials
13 to engineering engineering,
see categories
and applied cryogenics,
32 through ix
39.
physics,
and particular
and fire prevention.
areas
For specific
of
32
Commt:_nications Includes
radar;
radio,
communications Navigation;
for search
Transportation
34
information
lasing
information
Space
microelectronics Operations
and
integrated
and Hardware;
and devices
devices
mass
and
circuitry.
and
For
76 Solid-State
see 32 Communications
and Radar.
NoAo of heat transfer;
transfer
and
boundary
ablation
layer
cooling.
For
flow; related
measuring
NoA.
instruments
and holography.
For aerial
information
and
gauges;
photography
see also 06 Avionics
detectors;
cameras
and
see 43 Earth
Resources
and
and Aircraft
Instrumentation;
Instrumentation.
theory,
N_Ao
laser pumping
and maser
For cases category
maser where
where
amplifiers,
laser materials,
the application
the application
of the laser is treated.
and the or maser
For related
Physics.
Engineering
mechanical the application
category
where
Intelligence,
the
devices
approaches
17 and equipment;
of a device application
or vehicle
to,
and and
machine
or the host vehicle
and Robotics;
AssL._rance
maintainability,
techniques,
outputs.
see also the specific
Artificial
Includes
and
16
Photography
see also 76 Solid-State
Mechanical
QuNity
and
of electrical/electronic
and all forms
fluidics;
For related
of laser
is emphasized
38
Command
Safety,
and Masers
assessment
where
and
and kinematics
sensors;
supplies;
Sensing.
Includes
and
15
and maintainability
equipment
and
and 19 Spacecraft
Includes
Communications,
Transportation
and
Engineering
equipment,
hydraulics;
remote
Lasers
Spacecraft
03 Air
communications;
Communications
and Thermodynamics
instrumentation
Remote
land and global
see also 04 Aircraft
see also 02 Aerodynamics.
photographic
37
test
fluid dynamics
Includes
see
see also 60 Computer
Mechanics
hydrodynamics;
36
rescue
For communications
Includes
35
Communications,
performance,
related
information
Fluid
communications;
information
and EJectrical
components; Physics.
For related and
development,
related
15
and Safety.
Electronics Includes
Radar
wire, and optical
theory.
and 17 Space
Tracking;
33
and
is treated.
and 54 ManSystem
elements
and processes.
is emphasized For
robotics
Technology
see 63 Cybernetics, and Life Support.
Reliability methods
and standardization.
for
For cases
see also the specific
18 reliability
analysis
and
control,
inspection,
39
Structural Includes
Mechanics
structural
weight
analysis;
in structure. Spacecraft
Subiect Select
42
a category
For
applications
Design,
Testing
Geosciences general
categories
42 through
remote products;
cited.
topics
related
geology.
and
and
of earth
N.A.
means
no abstracts
in that category.
sciences,
and the
specific
topics
specific
areas
in geosciences
analysis
Se_:_si_:N
features,
or remote
photogrammetry;
energy waterwave
and
phenomena sensing
information and Power,
Erwironment
and resources
photographs.
For
by aircraft,
see
balloon,
development
of remote
instrumentation
see 35
see
41 e.g.,
systems;
related
to nuclear
also
07 Aircraft
and 28 Propellants
fuel
energy
energy
cells;
and
storage;
production
Propulsion
solar,
and
geothermal,
traditional
see 73 Nuclear
and
Power;
20
Physics.
and Fuels.
Pollution
atmospheric,
water,
power
Spacecraft
NoAo soil, noise,
and thermal
pollution.
Geophysics
NoAo
earth
structure
and dynamics,
ionospheric
and magnetospheric
Meteorology
and Climatology;
Meteorology Includes
of
N°Ao
data and imagery;
aerial
systems,
conversion
For technologies
Includes
18
48.
conversion
Includes
and Performance
stresses
and Photography.
specific
Propulsion
of structures;
and thermal
Eo Geosciences
For other
Includes
related
Testing
to the Earth
and Conversion
generators.
48
Design,
Er_ergy Production
For
responses
NoA°
and Remote
and spacecraft;
windpower,
47
of records
and general
sensing
Instrumentation
46
see 05 Aircraft
dynamic
and mechanical
of the Division
Resources
sensing
and testing; properties;
and Performance.
research
minerology,
Earth
analysis
(Genera[)
petrology,
rocket,
45
design,
and other structural
to view the collection
Includes
44
element fatigue
Categories
Includes
43
40
weather
and
physics;
aeronomy;
and geomagnetism.
and 93 Space
forecasting
and
lower
For related
atmosphere information
studies; see 47
Radiation.
C[imatok:_gy
observation
NoA. and modification.
Oceanography Includes the physical, and marine resources.
upper
NoAo chemical and biological aspects of oceans and seas; ocean dynamics, For related information see also 43 Earth Resources and Remote
Sensing. xi
Subject Select
51
Categories
a category
to view the collection
Life Sciences Includes
55
means
no abstracts
in that category.
related
to plant
and animal
development,
environmental
structure,
conditions.
biology
(non-human);
and maintenance,
For specific
topics
ecology;
of animals
and
in life sciences
see
55.
biological
N°A° and
(weightlessness,
space
the prevention
of adverse
effects
of aerospace
animals
and plants
Behavioral
physiological
radiation,
effects
acceleration,
effects
on those
environments
of
atmospheric
and altitude
environments.
stress)
and
on the human
For psychological
see 53 Behavioral
Science.
space being;
psychological
For the effects
of space
N,A.
factors;
individual
'_echnoJogy factors
clothing.
Aerospace
Medicine..
and group
behavior;
crew training
and evaluation;
and Life Support
engineering;
For
related
bionics,
42
man-machine,
information
see
also
life support,
16 Space
space
suits and
Transportation
and
ExoNology astrobiology;
planetary
environments
biology;
on humans
and extraterrestrial
see 52 Aerospace and behavioral
life. For the biological
medicine;
effects
on animals
of aerospace
environments
G. Mathematical
Select
means
to view the collection
JVlathematic_l specific
general topics
of records
m'_d Computer topics
in these
and overviews
cited.
N.A.
Sciences related
areas see categories
xii
67.
see see
in that category.
(GenerN)
to mathematics
60 through
no abstracts
effects
and plants
Subject Categories of the Division and Computer Sciences
Includes
52
N,A,
51 Life Sciences. For psychological 53 Behavioral Science.
a category
on
research.
human
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Includes
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66
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69
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a public
sale
will be announced
papers
in a report
at the
NASA
but not distributed
xxii
are also welcome.
announcement Center
for
or sold.
if you wish; AeroSpace
otherwise
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Typical
0 O O O 19 O
t9 19
Report Citation
and Abstract
1997_)0_)11_26 NASA Langley Research Center, Hampton, VA USA Water "l_mne| Flow Vis_alizathm Study Thr_gh Pos_stz]! (ff 12 Nove_ P_anform Shapes Gatlin, Gregory M., NASA Langley Research Center, USA Neuhart, Dan H., Lockheed Engineering and Sciences Co., USA; Mar. 1996; 130p; In English Contract(s)/Grant(s): RTOP 505-68-70-04 Report No(s): NASA-TM-4663; NAS 1.15:4663; L-17418; No Copyright; Avail: CASI; A07, Hardcopy; A02, Microfiche To determine the flow field characteristics of 12 planform geometries, a flow visualization investigation was conducted in the Langley 16- by 24-Inch Water Tunnel. Concepts studied included flat plate representations of diamond wings, twin bodies, double wings, cutout wing configurations, and serrated forebodies. The off-surface flow patterns were identified by injecting colored dyes from the model surface into the free-stream flow. These dyes generally were injected so that the localized vortical flow patterns were visualized. Photographs were obtained for angles of attack ranging from 10' to 50', and all investigations were conducted at a test section speed of 0.25 ft per sec. Results from the investigation indicate that the formation of strong vortices on highly swept forebodies can improve poststall lift characteristics; however, the asymmetric bursting of these vortices could produce substantial control problems. A wing cutout was found to significantly alter the position of the forebody vortex on the wing by shifting the vortex inboard. Serrated forebodies were found to effectively generate multiple vortices over the configuration. Vortices from 65' swept forebody serrations tended to roll together, while vortices from 40' swept serrations were more effective in generating additional lift caused by their more independent nature. Author Water Tunnel Configurations
Tests;
Flow
Visualization;
Flow
Distribution;
Key 1. 2.
Document Title
ID Number;
Corporate
3. 4.
Author(s) and Affiliation(s) Publication Date
5. 6. 7. 8.
Contract/Grant Number(s) Report Number(s); Availability Abstract Abstract Author
9.
Subject Terms
Source
and Price Codes
xxiv
Free
Flow;
Planforms;
Wing
Profiles;
Aerodynamic
FAULT
TREE
A Special Bibfiography
ANALYSIS from the NASA Scientific
and Technical
Information
(STI) Program JULY 2000
01 AERONAUTICS(GENERAL)
Includes general research topics related to manned and unmanned aircraft and the problems of flight within the Earth's atmosphere. Also includes manufacturing, maintenance, and repair of aircraft. For specific topics in aeronautics see categories 02 through 09. For information related to space vehicles see 12 Astronautics.
19850008446
McDonnell
Aircraft
Co., Saint Louis, MO, USA
--_vion:_c_;fau_t tree an_ys_ and artifieal i_lte_/igence fer _t_we a_reraft ma_tena_ee Harris, M. E., McDonnell Aircraft Co., USA; Snodgrass, T. D., McDonnell Aircraft Co., USA; AGARD Design for Tactical Avionics Maintainability; Oct 1, 1984, pp. 12 p; In English; See also N85-16731 08-01; Avail: CASI; A03, Hardcopy; A03, Microfiche The avionics
fault tree analyzer
(AFTA) was developed
as an interim
support
tool for the Navy prior to attainment
of total
organic support capability, and as an alternate method of support to reduce life cycle/cost for F/A-18 foreign military sales. With the transformation of the AFTA concept from ground support equipment to avionics, a quantitative improvement in life cycle costs will be obtained through the application of artificial intelligence (AT) techniques. The AI is expected to see applications to practical problems in many disciplines; and one of which is the implementation of military fault diagnostic systems. A smart BIT was developed which will reduce false alarms, identify intermittent failures, and improve fault isolation to the lowest possible element by AI technique. Increasing density of computer memory, modularly designed avionic functions and the use of very large scale, and high speed integrated devices will allow future aircraft to fly with the AFTA function. Ramifications such as eliminating the need for intermediate avionic repair facilities, increased aircraft operational readiness, decrease in aircraft recurring costs, and a reduction in spares investment are discussed. The AFTA concept, life cycle cost advantages, and the implementation of artificial intelligence in future avionic designs relative to improved reliability and maintainability are summarized. E.A.K. Aircraft
Maintenance;
Artificial
Intelligence;
Avionics;
Fault Trees
:199_ 00326 _7 Aging Army aircraft Neri, Lewis, U.S. Army, Aviation
Systems
Command,
Corpus, USA; Jan 1, 1990; 10p; In English;
46th; AHS, Annual
Forum,
May 21-23, 1990, Washington, DC, USA; See also A91-17201; Copyright; Avail: Issuing Activity Reliability-centered maintenance is a broadbased management and system engineering program that emphasizes a preventive approach to maintenance. Corrosion detection and prevention are principal concerns in this program which utilizes an analytical approach based on fault tree analysis to facilitate development of improved airframe condition evaluation/aircraft analytical corrosion evaluation and preshop analysis. The U.S. Army Depot Engineering and Reliability Centered Maintenance Support Office is also investigating ion implantation and plasma chemical vapor deposition techniques to determine their feasiblity for prevention of corrosion. AIAA Aging
(Materials);
Corrosion
Prevention;
Military
Aircraft;
Military
Technology;
Structural
Failure
03 AIR TRANSPORTATION
AND SAFETY
Includes passenger and cargo air transport operations; aircraft ground operations; flight safety and hazards; and aircraft accidents. Systems and hardware specific to ground operations of aircraft and to airport construction are covered in 09 Research and Support Facilities (Air). Air traffic control is covered in 04 Aircraft Communications and Navigation. For related information see also 16 Space Transportation and Safety, and 85 Technology Utilization and Surface Transportation.
119950004035 Rolls-Royce Ltd., Industrial and Marine Gas Turbines., Coventry, West Midlands, UK The _lppfic_ltim_ o_° aerospace sa_*._' and refi_lb_fity amllysis teehnh_ues to high speed marine tnmsport Moore, T. C., Rolls-Royce Ltd., UK; Wilkinson, B., Rolls-Royce Ltd., UK; May 7, 1992; 14p; In English; Safety for High Speed Passenger Craft: The Way Ahead, 7-8 May 1992, London, UK Report No.(s): PNR-91071; Copyright; Avail: Issuing Activity (European Space Agency (ESA)), Unavall. Microfiche; Limited Reproducibility: More than 20% of this document may be affected by microfiche quality The application of aerospace safety and reliability techniques to high speed marine craft is discussed, taking into account the following: why failures occur; how safety is demonstrated; what is gained from safety and reliability analyses; the techniques used; and the cost of such analyses. It is concluded that the application of aerospace safety and reliability techniques in their entirety to high speed marine craft would impose an unnecessary burden both in terms of the time scales, complexity of the task, and the associated costs involved. The judicious use of Fault Tree Analysis (FTA), coupled with a Failure Mode Effect Significance Analysis (FMESA) study at a functional rather than at a component level, can provide a cost effective means of demonstrating objectively the safety and reliability levels of a high speed marine craft. This is of vital importance to an industry where the individual craft design production levels are unlikely to be high when compared with the aircraft industry. The use of PC (Personal Computer) based FMEA and FTA software could further reduce the cost, particularly the 'first time' cost. ESA Air Transportation;
Failure
Analysis;
Fault Trees; Marine Transportation
19980160660 lmp/eme_tafion of a_ h_tegrated sa_°ety-program - The MI)-90 znt_skid system Redgate, Marianne L., Douglas Aircraft Co., USA; McKelvey, Michael H., Douglas Aircraft Co., USA; Jolly, Carolyn L., Douglas Aircraft Co., USA; 1994, pp. 52-58; In English; Copyright; Avail: Aeroplus Dispatch At Douglas Aircraft Company (DAC), an integrated safety program is comprised of four major analyses, each of which is intended to provide design requirements and results that satisfy DAC, FAA, and Joint Aviation Administration requirements to maximize safety for the airplane, the flying public, and the public-at-large. These four analyses are: functional hazard analysis, system failure mode and effects analysis, fault tree analysis, and zonal analysis. Every new or major-modified system designed for DAC's latest airplane, the MD-90, incorporates an integrated safety program. One such system, the antiskid system, has repeatedly used the integrated safety program as a primary design tool and is a particularly satisfying example of what DAC calls 'Design for Safety'. Author (AIAA) Aircraft Safety; Systems Integration; Failure Modes; Fault Trees; Aircraft Design
199g0207345 Safety assessment of aireraR mou_lted systems Trotta, Luigi, Alenia Aerospazio, Italy; Buffardi, Riccardo, Alenia Aerospazio, Italy; Querzoli, Rodolfo, Alenia Aerospazio, Italy; Sep. 1998; In English Report No.(s): ICAS Paper 98-6,7,3; Copyright; Avail: Aeroplus Dispatch This contribution highlights methodology to assess the safety aspects of military aircraft systems, a part of a fly-by-wire A/C. The correlations between FMECA and Safety Assessment will be shown to identify all possible hazards caused by single failures. A tool using fault tree analysis approach, to assess from a quantitative and qualitative point of view the discovered hazards, identifies the minimal cut sets and critical items in the system configuration. Zonal hazard analysis is used to show how to identify the hazards due to the physical location of the system components and the possible effects due to component failures, disadvantageous operating conditions, maintenance errors, and environment induced faults. Software safety assessment is performed to analyze and assess the safety of the software configuration items of a system and ensure that a risk classification is allocated appropriate to the severity of hazard which could be caused by a software error. These results lead to a definition of
2
the critical areas and the possible requirements. Author (AIAA) Military
Aircraft;
Aircraft
corrective
actions, providing
Safety; Fly by Wire Control;
a compliance
statement
Fault Trees; Software
_99g02_0315 Brookhaven National Lab., Upton, NY USA ()_ the safety of aircraft system,s: A case study Martinez_Guridi, G., Brookhaven National Lab., USA; Hall,
for system qualification
Development
R. E., Brookhaven
and airworthiness
Tools
National
Lab.,
USA;
Fullwood,
R. R.,
Brookhaven National Lab., USA; May 14, 1997; 45p; In English Contract(s)/Grant(s): DE-AC02-76CH-00016; 95-G-039 Report No.(s): BNL-64946; DE98-002766; No Copyright; Avail: Issuing Activity (Natl Technical Information Service (NTIS)), Hardcopy, Microfiche An airplane is a highly engineered system incorporating control- and feedback-loops which often, and realistically, are non-linear because the equations describing such feedback contain products of state variables, trigonometric or square-root functions, or other types of non-linear terms. The feedback provided by the pilot (crew) of the airplane also is typically non-linear because it has the same mathematical characteristics. An airplane is designed with systems to prevent and mitigate undesired events. If an undesired triggering event occurs, an accident may process in different ways depending on the effectiveness of such systems. In addition, the progression of some accidents requires that the operating crew take corrective action(s), which may modify the configuration of some systems. The safety assessment of an aircraft system typically is carried out using ARP (Aerospace Recommended Practice) 4761 (SAE, 1995) methods, such as Fault Tree Analysis (FTA) and Failure Mode and Effects Analysis (FMEA). Such methods may be called static because they model an aircraft system on its nominal configuration during a mission time, but they do not incorporate the action(s) taken by the operating crew, nor the dynamic behavior (non-linearities) of the system (airplane) as a function of time. Probabilistic Safety Assessment (PSA), also known as Probabilistic Risk Assessment (PRA), has been applied to highly engineered systems, such as aircraft and nuclear power plants. PSA encompasses a wide variety of methods, including event tree analysis (ETA), FTA, and common-cause analysis, among others. PSA should not be confused with ARP 4761's proposed PSSA (Preliminary System Safety Assessment); as its name implies, PSSA is a preliminary assessment at the system level consisting of FTA and FMEA. DOE Failure
Analysis;
Safety Factors;
Feedback
Control;
Aeronautics
05 AIRCRAFT
DESIGN,
TESTING
AND PERFORMANCE
Includes all stages of design of aircraft and aircraft structures and systems. Also includes aircraft testing, performance, and evaluation, and aircraft and flight simulation technology. For related information, see also 18 Spacecraft Design, Testing and Performance and 39 Structural Mechanics. For land transportation vehicles, see 85 Technology Utilization and Surface Transportation.
:19720011367 University of Southern California, Inst. of Aerospace Safety and Management., Los Angeles, CA, USA A_a/ytieal techniques for effective ma_ntena_lee Hall, D. S., University of Southern California, USA; Holt, E. L., University of Southern California, USA; Jan 1, 1971; 14p; In English; 7th; Ann. Intern. Aviation Maintenance Symp., 7-9 Dec. 1971, Oklahoma City; Avail: CASI; A03, Hardcopy; A01, Microfiche Systems analysis techniques are applied to aircraft maintenance to achieve aviation safety. The failure mode analysis method is discussed along with the fault tree analysis method. It is concluded: (1) The maintenance manager needs to know how to make decisions and that these decisions affect the safety and efficiency of his operation. (2) Many of these decisions can be made in advance when time or other pressure is not a factor. (3) Greater knowledge of the implications of a decision is available to the individual who approaches each problem systematically. (4) Systematic and analytical decision making is within the capability of today's maintenance activity. CASI Aircraft
Maintenance;
Aircraft
Safety; Failure
Analysis;
Systems
Analysis
19760057 _60 Seeking _i_are-free systems Merkling, R.E.,USAF, USA;Air Activity The need for developing and costs. Fault tree analysis AIAA Accident
Prevention;
University
Review;
failure-free
systems
is described
and applied
Aircraft Accidents;
Aug 1, 1976; 27, pp. July-Aug;
for USAF aircraft is advocated,
Fail-Safe
to fire threat and prevention
Systems;
In English; 1976, p. 41-50; Avail: Issuing
with figures relating
major aircraft accidents
on fighter aircraft.
Fighter Aircraft; Fire Prevention
1989OO59099 Probabiiistie a_alysis of aircraft structure Zielinski, Paul A., Boeing Military Airplane
Co., USA; Jan 1, 1989; 6p; In English;
Annual
Reliability
and Maintainability
Symposium, Jan. 24-26, 1989, Atlanta, GA, USA; See also A89-46451 20-38; Copyright; Avail: Issuing Activity Probabilistic structural mechanics (PSM) has been promoted for use in the design of products. The author presents the practical methods for applying PSM to critical aircraft component fanlt-tree analysis. The B-1B Common Strategic Rotary Launcher (CSRL) fault-tree analysis is used as a demonstative example of mechanical component failure probabilities calculated using PSM. The CSRL components per flight hour, material properties, AIAA Aircraft
Structures;
Failure
demonstrate how this methodology accounts and stress analysis or structural test results.
Analysis;
Fault Trees; Probability
Theory;
for aircraft limit loads, limit load exceedances
Stress Analysis;
Structural
Reliability
19980117945 The service
reliability
a_mlysis
_i_r the brake
_n_t _ff a certain
m_del
Fu, Changan, Air Force Aero College No. 2, China; Wang, Yuanda, English; Copyright; Avail: Aeroplus Dispatch
aircraft
Air Force Aero College
No. 2, China;
1995, pp. 79-82;
In
When aircraft of certain models land and the pilots brake, the service tire skidding and tire blowout are frequently occurring faults, endangering the landing safety. After having investigated and analyzed such incidents, the departments concerned think the fault is mainly caused by the improper brake operation when the aircraft lands. Using the fault tree analysis method, the paper first discusses the causes which result in severe tire skidding and blowout when the aircraft is braked, then presents some factors which the pilots and the ground crew should pay attention to in the actual use and maintenance work. Finally, improvements in the structure of the decelostat are proposed. Author (AIAA) Service Life; Reliability Analysis; Aircraft Brakes; Aircraft
19980139
Models;
Fault Trees; Skidding
_ 58
Heavy transport aircraft reliability study Chiesa, S., Torino, Politecnico, Italy; Gianotti, R, Torino, Politecnico, 682-690; In English; Copyright; Avail: AIAA Dispatch
Italy; Maggiore,
R, Torino,
Politecnico,
Italy;
1996, pp.
The analysis of safety and reliability is of primary importance during the design of a modern, large complex aircraft. On the other other hand, the intrinsic complexity of large, multiple-redundant systems usually impose severe limitations on both the depth and the extension of this analysis. In this work, a computer program for the reliability analysis of a generic system is presented, underlining the advantages of a computer-based approach to the problem. The philosophy which stands behind such an approach consists of a tailoring of well-known Failure Modes and Effect Analysis and Fault Tree Analysis techniques. The results of the automatic analysis include symbolic and sensitivity analysis. Author (AIAA) Transport
4
Aircraft;
Aircraft
evaluation
Reliability;
Aircraft
of fault and functional
Design;
Expert
trees, minimal-paths
Systems;
Fault Trees
and minimal
cut sets determination,
AVIONICS
06 AND AIRCRAFT
INSTRUMENTATION
Includes all stages of design of aircraft and aircraft structures and systems. Also includes aircraft testing, performance, and evaluation, and aircraft and flight simulation technology. For related information, see also 18 Spacecraft Design, Testing and Performance and 39 Structural Mechanics. For land transportation vehicles, see 85 Technology Utilization and Surface Transportation.
19940034825 NASA Ames Research Center, Moffett Field, CA, USA A quantitative a_a_ys_s (_f the Flg flight eontro_ system Doyle, Stacy A., Duke Univ., USA; Dugan, Joanne B., Virginia Univ., USA; Patterson Hine, Ann, NASA Ames Research Center, USA; In: AIAA Computing in Aerospace Conference, 9th, San Diego, CA, Oct. 19-21, 1993, Technical Papers. Pt. 1 (A94-11401 01-62); 1993, pp. 668-675.; In English; See also A94-11401 Contract(s)/Grant(s): NCA2-617 Report No.(s): AIAA PAPER 93-4574; Copyright; Avail: Issuing Activity This paper presents an informal quantitative analysis of the F18 flight control system (FCS). The analysis technique combines a coverage model with a fault tree model, to demonstrate the method's extensive capabilities, we replace the fault tree with a digraph model of the F18 FCS, the only model available to us. The substitution shows that while digraphs have primarily been used for qualitative analysis, they can also be used for quantitative analysis. Based on our assumptions and the particular failure rates assigned to the F18 FCS components, we show that coverage does have a significant effect on the system's reliability and thus it is important to include coverage in the reliability analysis. Control Systems Design; F-18 Aircraft; Failure Modes; Fault Trees; Flight Control; Reliability Analysis
19980147707 Dynamic
fault
tree analysis
fl_r the Digital FlyqSy-W_re
Flight
Contrail
System
Yao, Yiping, Beijing Univ. of Aeronautics and Astronautics, China; Yang, Xiaojun, Beijing Univ. of Aeronautics and Astronautics, China; Li, Peiqiong, Beijing Univ. of Aeronautics and Astronautics, China; 1996, pp. 479-484; In English; Copyright; Avail: AIAA Dispatch The Digital Fly-By-Wire (FBW) FCS is designed to a achieve high level of reliability, and frequently employs high level of redundancy. The dynamic redundancy employed in the FBW system can realize complex fault and error diagnosis, recovery, and reconfignration. It is very difficult to analyze the reliability of the FBW system by traditional methods, such as fault tree analysis (FTA) or network analysis. This paper describes dynamic fanlt-tree modeling techniques for handling these difficulties and provides a Markov chain generation modeling method for converting the dynamic fault tree to the Markov chain. The software failure of the FBW system can also be considered in the model. An example of a quadruple FBW redundant system and a Markov state transition chain software package is given. Author (AIAA) Fault Trees; Fly by Wire Control; Digital Systems; Dynamic Models
AIRCRAFT
07 PROPULSION
AND POWER
Includes prime propulsion systems and systems components, e.g., gas turbine engines and compressors; and onboard auxiliary power plants for aircraft. For related information see also 20 Spacecraft Propulsion and Power, 28 Propellants and Fuels, and 44 Energy Production and Conversion.
19800072732 Science Applications, Inc., Palo Alto, CA, USA Fm_lt tree analysis for reliability prediction of gas turMne type power plants_ Volume 2: Appendixes Final R_Tort Kelly, J. E., Science Applications, Inc., USA; Erdmann, R. C., Science Applications, Inc., USA; Gilbert, K., Science Applications, Inc., USA; Jun 1, 1978; 85p; In English; Sponsored by EPRI Report No.(s): EPRI-AF-811-VOL-2-APP; Avail: CASI; A05, Hardcopy, Microfiche No abstract. Electric
Power Plants; Fault Trees; Gas Turbines;
Performance
Prediction;
Systems
Analysis
19950004033 Rolls-Royce Ltd.,Industrial andMarineGasTurbines., Coventry, WestMidlands, UK Thereliabilityofaero-derived marinegas turbines Moore, Tim C., Rolls-Royce Ltd., UK; Wilkinson, Craft Conference, Jan. 1992, London, UK
Brian, Rolls-Royce
Ltd., UK; Jan l, 1992; 17p; In English; High Speed Surface
Report No.(s): PNR-90982; Copyright; Avail: Issuing Activity (European Space Agency (ESA)), Unavall. Microfiche; Limited Reproducibility: More than 20% of this document may be affected by microfiche quality An overview of work carried out to assess the safety and reliability of the Marine Spey, a marine propulsion gas turbine unit, is reported. The question of the limit of safety inherent in reliability of an aeroengine is considered. Failure probabilities are defined both qualitatively and quantitatively, and it is shown how the combination of failure effect category and probability rank defines the risk level. Means of assessing the capability of a design to comply to the reliability standards are addressed. These can take the form of a Failure Mode Effects Analysis (FMEA), Failure Mode Effect Criticality Analysis (FMECA), or a Failure Mode Effect Systems Analysis (EMESA). The latter investigates the significance of a system or subsystem failure on the operation of the overall plant. The use of FMESA studies on aero derived marine gas turbines is considered, and the safety and reliability in fast ferries is discussed. Modem FEA techniques, which include the Fault Tree Analysis (ETA) used to assess safety, control and protection system reliability, are considered. ESA Engine Design;
Engine Failure; Failure
Analysis;
Gas Turbine
Engines; Marine Propulsion;
Reliability;
System Failures
09 RESEARCH
AND SUPPORT
FACILITIES
(AIR)
Includes airports, runways, hangars, and aircraft repair and overhaul facilities/wind tunnels, water tunnels, and shock tubes/flight simulators; and aircraft engine test stands. Also includes airport ground equipment and systems. For airport ground operations see 03 Air Transportation and SafeO/.For astronautical facilities see 14 Ground Support Systems and Facilities (Space). 19840068890 Minority Enterprise Service Associates, Large-coil_test facility face, t-tree a_mlysis May 31, 1982; 168p; In English Contract(s)/Grant(s): DE-AC01-81ER-52074 Report No.(s): DE83-002783; No abstract. Cryogenics;
DOE/ER-52074-T1;
Fault Trees; Parameter
Identification;
Orem, UT, USA
Avail: CASI; A08, Hardcopy,
Microfiche
Safety; Systems
19690031585 Battelle Northwest Labs., Pacific Northwest Lab., Richland, WA, USA Preliminary fa_dt tree analysis for the FFTF Mc Laughlin, M. A., Battelle Northwest Labs., USA; May 1, 1969; 37p; In English Contract(s)/Grant(s): AT/45-1/- 1830 Report No.(s): BNWL-874; Avail: CASI; A03, Hardcopy; A01, Microfiche Preliminary fault tree analysis for FFTF CASI Failure
Analysis;
Nuclear Research
and Test Reactors;
Reactor
Safety;
Trees (Mathematics)
12 ASTRONAUTICS
(GENERAL)
Includes general research topics related to space flight and manned and unmanned space vehicles, platforms or objects launched into, or assembled in, outer space; and related components and equipment. Also includes manufacturing and maintenance of such vehicles or platforms. For specific topics in astronautics see categories 13 through 20. For extraterrestrial exploration, see 91 Lunar and Planetary Science and Exploration. 19920073157 NASA Goddard Space Flight Center, Greenbelt, MD, USA Maki_g the H_bWe Space Te|escope servici_g mission safe Bahr, N. J., NASA Goddard Space Flight Center, USA; Depalo, S. V., Hemandez English Contract(s)/Grant(s): NAS5-30917
6
Engineering,
Inc., USA; Aug l, 1992; 12p; In
Report No.(s):IAFPAPER 92-0380; Copyright; Avail:Issuing Activity Theimplementation oftheHSTsystem safety program isdetailed. Numerous safety analyses areconducted through various phases ofdesign, test,andfabrication, andresults arepresented toNASAmanagement fordiscussion duringdedicated safety reviews. Attention isgiventothesystem safety assessment andriskanalysis methodologies used, i.e.,hazard analysis, faulttree analysis, andfailuremodes andeffects analysis, andtohowtheyarecoupled withengineering andtestanalysis fora'synergistic picture'ofthesystem. Some preliminary safety analysis results, showing therelationship between hazard identification, control orabatement, andfinallycontrol verification, arepresented asexamples ofthissafety process. AIAA FlightSafety; Hubble Space Telescope; NASASpace Programs; OrbitalServicing; Space Shuttle Missions 14 GROUND
SUPPORT
SYSTEMS
AND FACILITIES
(SPACE)
Includes launch complexes, research and production facilities; ground support equipment, e.g., mobile transporters; and test chambers and simulators. Also includes extraterrestrial bases and supporting equipment. For related information see also 09 Research and Support Facilities (Air). 99g0_73949 Dynamic rca/4_mc _'ad_oscopy o:f Space Shuttle reusable _(_l_d rocket motor durirlg static fir_ng Rogerson, D. J., U.S. Navy, Naval Air Warfare Center, USA; Jul. 1995; In English Report No.(s): AIAA Paper 95-2727; Copyright; Avail: Aeroplus Dispatch In 1993, engineers were tasked to investigate the cause of the pressure perturbations occurring in the Reusable Solid Rocket Motor (RSRM) following the deviation in the predicted pressure trace in STS-54. An initial fault tree analysis indicated that the most probable source for pressure perturbation in the RSRM was the expulsion of aluminum oxide slag accumulated between the submerged portion of the nozzle and the motor aft dome. Three static firings were completed using real-time radioscopy (RTR). The dynamic data from the RTR system, in conjunction with data from other instrumentation, strongly supported slag expulsion as the primary cause for pressure perturbations in the RSRM. Author (AIAA) Real Time Operation; Space Shuttles; Solid Propellant Rocket Engines; Rocket Firing; Reusable Rocket Engines; X Ray Imagery
18 SPACECRAFT
DESIGN,
TESTING
AND PERFORMANCE
Includes satellites; space platforms; space stations; spacecraft systems and components such as thermal and environmental controls; and spacecraft control and stability characteristics. For life support systems, see 54 Man/System Technology and Life Support. For related information, see also 05 Aircraft Design, Testing and Performance, 39 Structural Mechanics, and 16 Space Transportation and Safety. 19930016042 NASA, Washington, DC, USA 3k_thered S_teH_tc System Cont_ngency h_vesfigafio_ Bo_rd Final Rep_rg Nov 6, 1992; 51p; In English Report No.(s): NASA-TM-108704; NAS 1.15:108704; Avail: CASI; A04, Hardcopy; A01, Microfiche The Tethered Satellite System (TSS-1) was launched aboard the Space Shuttle Atlantis (STS-46) on July 31, 1992. During the attempted on-orbit operations, the Tethered Satellite System failed to deploy successfully beyond 256 meters. The satellite was retrieved successfully and was returned on August 6, 1992. The National Aeronautics and Space Administration (NASA) Associate Administrator for Space Flight formed the Tethered Satellite System (TSS-1) Contingency Investigation Board on August 12, 1992. The TSS-1 Contingency Investigation Board was asked to review the anomalies which occurred, to determine the probable cause, and to recommend corrective measures to prevent recurrence. The board was supported by the TSS Systems Working group as identified in MSFC-TSS-11-90, 'Tethered Satellite System (TSS) Contingency Plan'. The board identified five anomalies for investigation: initial failure to retract the U2 umbilical; initial failure to flyaway; unplanned tether deployment stop at 179 meters; unplanned tether deployment stop at 256 meters; and failure to move tether in either direction at 224 meters. Initial observations of the returned flight hardware revealed evidence of mechanical interference by a bolt with the level wind mechanism travel as well as a helical shaped wrap of tether which indicated that the tether had been unwound from the reel beyond the travel by the level wind mechanism. Examination of the detailed mission events from flight data and mission logs related to the initial
failuretoflyaway andthefailuretomove ineither direction at224meters, together withknownpreflight concerns regarding slack tether, focused theassessment ofthese anomalies ontheuppertethercontrolmechanism. Afterthesecond meeting, theboard requested theworkinggrouptocomplete andvalidate adetailed integrated mission sequence tofocusthefaulttreeanalysis on astuckU2umbilical, levelwindmechanical interference, andslacktetherinuppertethercontrolmechanism andtoprepare a detailed planforhardware inspection, test,andanalysis including anyappropriate hardware disassembly. Author FailureAnalysis; Space Shuttle Payloads; Spaceborne Experiments; Tethered Satellites; Tethering 19940021785 NASAAmesResearch Center,
Moffett Field, CA, USA Simulation modelh_g _r hmg durafios spacecraft control systems Boyd, Mark A., NASA Ames Research Center, USA; Bavuso, Salvatore J., NASA Langley Research Center, USA; NASA. Langley Research Center, Selected Topics in Robotics for Space Exploration; Dec 1, 1993, pp. p 213-221; In English; See also N94-26278 07-12; Avail: CASk A02, Hardcopy; A03, Microfiche The use of simulation is described and it is contrasted to analytical solution techniques for evaluation of analytical reliability models. The role importance sampling plays in simulation of models of this type was also discussed. The simulator tool used for our analysis is described. Finally, the use of the simulator tool was demonstrated by applying it to evaluate the reliability of a fault tolerant hypercube multiprocessor intended for spacecraft designed for long duration missions. The reliability analysis was used to highlight the advantages and disadvantages offered by simulation over analytical solution of Markovian and non-Markovian reliability models. Author (revised) Fault Tolerance; Fault Trees; Hypercube Multiprocessors; Long Duration Space Flight; Mathematical Models; Reliability Analysis 19960047793 Naval Postgraduate School, Monterey, CA USA Critical Failure Mode Analysis of The Petite Amate_r Navy Sate|/_te (FANSAT) Alldridge, David W., Naval Postgraduate School, USA; Sep. 1995; 174p; In English Report No.(s): AD-A303881; No Copyright; Avail: CASI; A08, Hardcopy; A02, Microfiche System reliability analysis is an essential element is the design process. A reliability study should proceed from system inception through final deployment. As the PANSAT project approaches the final design stage and begins initial flight production, the absence of any significant reliability analysis becomes increasingly troubling. This thesis initiates the program's reliability analysis obligation by investigating spacecraft failure modes. Typically referenced as critical failure modes, these events will cause complete and permanent system failure. A reliability analysis tool, called Fault Tree Analysis (FTA), is used to conduct a systematic review of current hardware design architecture to expose potential critical failure points or weak links. The analytical result is a Boolean logic tree that describes critical failure events and all the potential causes. This causal output relationship describes each component failure (i.e., single point failures), or component failure combinations (i.e., multi-point failures), which could cause the undesirable failure event, or Top Event. The fault tree will provide design engineers and management personnel with an effective tool and reference point from which to implement design modifications to circumvent potential problems. DTIC Systems
Analysis;
Reliability
Analysis;
Deployment;
SPACECRAFT
Failure Modes;
20 PROPULSION
System
Failures;
Logic
AND POWER
Includes main propulsion systems and components, e.g., rocket engines; and spacecraft auxiliary power sources. For related information, see also 07 Aircraft Propulsion and Power; 28 Propellants and Fuels; 15 Launch Vehicles and Launch Operations; and 44 Energy Production and Conversion. 1974O060462 The case for digit'M techniques applied to powerplant controls Evans, J. F. O., Smiths Industries, Ltd., UK; Jan 1, 1974; 20p; In English; Symposium on the Application of Electrical Control to Aircraft Propulsion Systems, February 20-21, 1974, London; See also A74-43201 22-28; Avail: Issuing Activity The present work argues for the application of digital computing techniques to on-line powerplant control in aircraft. The analysis is based on the cost effectiveness of digital control techniques and hardware solutions in the light of the particular problems associated with aircraft engine control. The use of digital systems with their ability to change programs easily and
8
cheaply during development permits important decisions to be delayed until the necessary data to base them on becomes available. The computer in a digital system can be employed for overall system check-out, thus avoiding the necessity for separate equipment at dispersed sites and additional connectors for ground check equipment. Digital systems reduce the number and frequency of control setting adjustments, thus improving aircraft availability and maintainability. The application of Fault Tree Analysis is illustrated for a hypothetical analysis of a VTOL aircraft. AIAA Aircraft Engines;
Digital Techniques;
Engine
Control;
Numerical
Control
19850010853 Naval Weapons Center, China Lake, CA, USA Caleu_afi_m through Fa_t Tree AnMysis of t_e probab_l_ty _f a warhead being armed pr_r to lmmch Stefan, G., Jr., Naval Weapons Center, USA; Spille, E, Naval Weapons Center, USA; APL The 1984 JANNAF Propulsion Systems Hazards Subcomm. Meeting, Vol. 1; Jun 1, 1984, pp. p 1-7; In English; See also N85-19162 10-28 Report No.(s): AD-P004339; Avail: Issuing Activity This paper is presented to illustrate the usefulness of Fault Tree Analysis (FTA), which, when quantified can yield the probability of occurrence of a given undesired event. A Fault Tree is a symbolic logic diagram which provides the deductive analytical means to identify failure modes contributing to the occurrence of the undesired event. As an illustrative example, an analysis was performed to assess the design safety of the MK 76 MOD 0 Safety-Arming (S-A) device, which is used on Standard Missile SM-1 Block VI. This analysis was performed with the primary intent of determining the various scenarios leading to an armed prior to launch event. These scenarios are made possible only by the assumed failure, or assumed bypassing, of the safety interlocks in the S-A device. DTIC Fault Trees; Fuses (Ordnance);
Warheads
19920066467 Tutorial (_n n_c/ear thermal prop_Mon safety _k_rMars Buden, David, Idaho National Engineering Laboratory, USA; Jul 1, 1992; 15p; In English Contract(s)/Grant(s): DE-AC07-76ID-O1570 Report No.(s): AIAA PAPER 92-3696; Avail: Issuing Activity A range of safety topics related to the use of nuclear thermal propulsion (NTP) are examined including risk and safety analysis methodologies, NERVA reliability, and life-cycle risk assessments. A list of goals for the safe use of NTP is given which includes low radiation levels, avoiding unplanned core destruction, and preventing inadvertent criticality. Safety analysis and failure-mode analysis for NTP are illustrated by means of the fault tree analysis, event tree analysis, failure modes and effects analysis, and preliminary hazards analysis. Data from the NERVA propulsion program show that safety requirements built into the NTP engine are important for diagnostic and preventive assessments. Other key issues affecting the safety of an NTP program encompass precautions at the launch pad, crew isolation from reactor radiation, flight operations safety, and final disposal of the NTP engines and wastes. AIAA Failure
Modes;
Flight Safety;
Mars (Planet);
Nuclear
Engine For Rocket
Vehicles; Nuclear
Propulsion;
Space Exploration
19930017833 NASA Lewis Research Center, Cleveland, OH, USA Re_abi_ty studies of _ntegrated modular e_gi_e system de_ign_ Hardy, Terry L., NASA Lewis Research Center, USA; Rapp, Douglas C., Sverdrup Technology, Inc., USA; Jun 1, 1993; 19p; In English; 29th; Joint Propulsion Conference and Exhibit, 28-30 Jun. 1992, Monterey, CA, USA; Sponsored by AIAA Contract(s)/Grant(s): RTOP 468-02-11 Report No.(s): NASA-TM-106178; E-7774; NAS 1.15:106178; AIAA PAPER 93-1886; Avail: CASI; A03, Hardcopy; A01, Microfiche A study was performed to evaluate the reliability of Integrated Modular Engine (IME) concepts. Comparisons were made between networked IME systems and non-networked discrete systems using expander cycle configurations. Both redundant and non-redundant systems were analyzed. Binomial approximation and Markov analysis techniques were employed to evaluate total system reliability. In addition, Failure Modes and Effects Analyses (FMEA), Preliminary Hazard Analyses (PHA), and Fault Tree
Analysis (FTA)wereperformed toallowdetailed evaluation oftheIMEconcept. A discussion ofthese system reliability concepts isalsopresented. Author EngineDesign;FailureAnalysis; FailureModes;FaultTrees;Modularity; Propulsion System Configurations; Reliability Analysis; Rocket Engine Design 19930065762 NASALewisResearch Center,
Cleveland, OH, USA Reliability studies of Integrated Mo(lular Engine system designs Hardy, Terry L., NASA Lewis Research Center, USA; Rapp, Douglas C., Sverdrup Technology, Inc., USA; Jun 1, 1993, pp. 18 p.; In English; 29th; AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, June 28-30, 1993, Monterey, CA, USA; Sponsored by AIAA; Previously announced in STAR as N93-27022 Report No.(s): AIAA PAPER 93-1886; Copyright; Avail: Issuing Activity A study was performed to evaluate the reliability of Integrated Modular Engine (IME) concepts. Comparisons were made between networked IME systems and non-networked discrete systems using expander cycle configurations. Both redundant and non-redundant systems were analyzed. Binomial approximation and Markov analysis techniques were employed to evaluate total system reliability. In addition, Failure Modes and Effects Analyses (FMEA), Preliminary Hazard Analyses (PHA), and Fault Tree Analysis (FTA) were performed to allow detailed evaluation of the IME concept. A discussion of these system reliability concepts is also presented. Engine Design; Failure Analysis; Failure Modes; Fault Trees; Modularity; Propulsion System Configurations; Reliability Analysis; Rocket Engine Design
19940024900 NASA Lewis Research Center, Cleveland, OH, USA Rocket engine system reliaMJ_ty m_alyses _s_ng probaMlistie and fuzzy logic techniques Hardy, Terry L., NASA Lewis Research Center, USA; Rapp, Douglas C., NASA Lewis Research Center, USA; Apr 1, 1994; 18p; In English; 30th; Joint Propulsion Conference, 27-29 Jun. 1994, Indianapolis, IN, USA; Sponsored by AIAA, ASME, SAE, and ASEE Contract(s)/Grant(s): RTOP 506-42-72 Report No.(s): NASA-TM-106519; E-8640; Microfiche
NAS
1.15:106519;
AIAA
PAPER 94-2750;
Avail:
CASI; A03, Hardcopy;
A01,
The reliability of rocket engine systems was analyzed by using probabilistic and fuzzy logic techniques. Fault trees were developed for integrated modular engine (IME) and discrete engine systems, and then were used with the two techniques to quantify reliability. The IRRAS (Integrated Reliability and Risk Analysis System) computer code, developed for the U.S. Nuclear Regulatory Commission, was used for the probabilistic analyses, and FUZZYFYA (Fuzzy Fault Tree Analysis), a code developed at NASA Lewis Research Center, was used for the fuzzy logic analyses. Although both techniques provided estimates of the reliability of the IME and discrete systems, probabilistic techniques emphasized uncertainty resulting from randomness in the system whereas fuzzy logic techniques emphasized uncertainty resulting from vagueness in the system. Because uncertainty can have both random and vague components, both techniques were found to be useful tools in the analysis of rocket engine system reliability. Author (revised) Engine Failure; Fault Trees; Fuzzy Systems; Probability Distribution Functions; Reliability; Reliability Analysis; Rocket Engines
19980025783 Current and emergi_lg teehn
