CRAIG L. BROOKS
Over thirty
years experience with Original Equipment Manufacturers in the development and
application of fatigue and fracture life prediction methodologies. The areas of
focus have been establishing engineering applications of theories and
incorporating processes to assess the static, durability, and damage tolerance
capabilities of structure. This experience base is supported by knowledge of
multiple engineering disciplines and an understanding of structural integrity
philosophies for the design, manufacturing, and maintenance of aircraft,
engines, structures, and other aerospace products.
Present
Position & Responsibilities
Officer and
Chief Engineer for Analytical Processes / Engineered Solutions, APES, Inc. a
Missouri Corporation and a "Small Business", established in early
1997. APES is presently under contract with the USAF to research and develop
analytical predictive techniques that assess the interaction of operational
cycles and time based age degradation (such as corrosion) on the service life
capability of structure. These contracts involve 1) providing the analytical
tools to perform the assessments, 2) formulating the “integration” concepts and
plans for the many disparate user communities, and 3) assisting in research and
data acquisition to expand the models to many field applications. APES also
provides advanced stress analyses solutions, linear and non-linear, 2- and
3-dimensional, and fracture mechanics capabilities. Other expert services
include load and environmental spectrum evaluations, acoustic and buffet
interaction solutions, holistic life assessments, and advanced analytical
failure analyses. APES’s policy is to provide Analytical Processes in
conjunction with the Engineered Solutions to meet customer challenges.
Experience History
1992
- 1997 Advanced Methods and Special
Problems : McDonnell Douglas
Corp. St.Louis MO.
·
Provided engineering
solutions and support to all enterprise programs in addressing structural
problems, conducting product integrity assessments, directing advances in life
prediction methods and procedures, promoting cost efficient changes and
enhancements in products, and stimulating technology advances.
·
Program Independent
Assessments of F/A-18 aircraft to determine levels of risk and provide recommendations
to program office to mitigate risk and improve product quality
·
Implemented advanced
analytical procedures to improve F-15 depot inspection intervals
·
Performed complex
failure analyses for C-17 Full Scale Fatigue Test , F-15, T-45, F/A-18, and
SLAM missiles cracks resulting in a process and procedure being documented for
an standard industry approach
·
Determined the role
of microstructure in fatigue behavior to enable material substitutions to solve
manufacturing problems in coordination with establishing a process to ensure
product integrity
·
Formulated approach
for designing Joint Strike Fighter to meet service life requirements under new
joint aircraft specifications
·
Tailoring and
implementation of “Critical Component Selection” process across enterprise
1987 - 1991 Structural Integrity Process Development : McDonnell
Douglas Corp.
·
Developed design and
assembly process to optimize integrity, weight, and cost for transport aircraft
lower wing structure
·
Established
procedures for implementing ENSIP, MECSIP, and AVIP with subcontractors
·
Conducted F/A-18
Damage Tolerance Assessment for Swiss applications and provided necessary
design changes to aircraft to meet service life requirements
·
Fatigue and fracture
enterprise processes and procedures development; database, modeling,
benchmarking, etc.
1984 - 1986 Large Aircraft, Commercial Aircraft, and
Fixed Structures:
Boeing Aircraft, Seattle WA; CASA Madrid Spain; and Sverdrup
Technology, Tullahoma TN
·
Evaluation of fatigue
techniques and methodology improvements for B-2 applications with Boeing
·
Lead first
certification of commercial aircraft under new FAA FAR and JAR damage tolerance
specs
·
Damage Tolerance
analysis of NASA-Lewis Wind tunnel for continued service of non-stress relieved
welded steel structure
1979 - 1983 Fighter Aircraft Airframe Applications:
McDonnell Aircraft St. Louis MO
·
Analyst for F-15
Damage Tolerance Assessment and Reliability Centered Maintenance Programs
·
Constructed F-15 Aft
Fuselage finite element model, and performed salvages and repairs for
production
·
Extensive failure
analyses and Solutions; F-15 Upper Wing Spar cracking, Rudder Cable , Jet Fuel
Starter Turbine Disk, Inlet Duct Buffet cracking, F/A-18 Bulkhead cracking,
etc.
1975 - 1978 Turbine Engine and Rocket Applications:
Pratt & Whitney Aircraft WPB, FL
·
Analyst for the
Damage Tolerance Assessment of the PWA F100 Engine
·
Developed
multi-parameter interpolative crack growth rate relationship models using
Hyperbolic sine and double hyperbolic sine algorithms for : R-ratio, frequency,
temperature, and environment
·
Established design
criteria for Damage Tolerance of Engine Disks and broach slot modeling
·
Failure analysis
solutions for high frequency fatigue and fracture of fan and turbine blades
1970 - 1975 Fatigue and Fracture Research: Pratt
& Whitney Aircraft R&D Center FL
·
Established test
facilities and procedures for fatigue and fracture testing
·
Developed fracture
mechanics and damage tolerance concepts for engine industry, which subsequently
resulted in the Equivalent Initial Flaw Size concept and Retirement for Cause
·
Performed elevated
temperature testing and modeling for thermal mechanical fatigue approximations
·
Created method of
strain range partitioning for temperature creep and dwell effects
·
Conducted high
pressure hydrogen evaluations and assessment for pressure vessels
Education:
Graduate from Georgia Institute of Technology - Mechanical
Engineering, Atlanta GA 1973
Co-op Training in many engineering disciplines at Pratt
& Whitney Aircraft 1968 -1972
6 years in Engine and Space Applications with Pratt &
Whitney Aircraft
1 year in Structures with Sverdrup Technologies and Boeing
Aircraft
2 years in commercial certification of aircraft for CASA in
Madrid, Spain
15 years in multiple engineering disciplines and systems
McDonnell Douglas
Papers and Presentations
(since 1990)
1. “An
Engineering Procedure to Select and Prioritize Component Evaluation Under USAF
Structural Integrity Requirements”,
USAF Structural Integrity Conference, 1990
2. “Results From
Two MECSIP Studies” USAF
Structural Integrity Conference, 1991
3. “New Aircraft
Lower Wing Skin Trade Study” USAF
Structural Integrity Program Conference, 1992 and AIAA/ASME/ASCE/AHS/ASC
Conference, 1995.
4. “Durability
Versus Damage Tolerance: A Discussion of the US Navy and US Air force
Philosophies”,1993
5. “A Probabilistic Strategy for Aircraft Fleet
Inspection Considering Unanticipated Environments” USAF Structural Integrity Program Conference, 1993.
6. “Fatigue
Methods Used in Life Prediction of Navy Aircraft: Current and Future”, USN ONR Fatigue Structural Reliability Workshop, 1994.
7. “Striation
Counting & Marker Band Recognition Applied to Aircraft Test Failures”, ASTM Conference & Symposium, 1994.
8. “Spectrum
Loads Development for Joint Aircraft Structures - Service Life Technology
Considerations” USN-ONR
Fatigue Structural Reliability Workshop, 1995
9. “Understanding
Fatigue Failure Analyses Under Random Spectrum Loading Using a C-17 Test
Article Failure”, ICAF
95-International Committee of Aeronautical Fatigue, Australia,1995 & USAF
Structural Integrity Program Conference, 1995
10. “Approach for
Determining the Economic Life of the F-15 Aircraft” USAF Air Logistic Command’s USAF Structural Integrity
Conference, 1995
11. “The Impact on
Total Life of Corrosion/Fatigue Interaction - An Engineering Approach”, USAF 4th Aging Aircraft Conference, 1996
12. “Cyclic
Relaxation in Compression-Dominated Structure” Engineering Foundation Conference for Fatigue Damage in
Structural Materials, 1996. Published in International
Journal of Fatigue: Volume 19 1997.
13. “Analytical
Process Framework for Aging Aircraft”, ASM
AEROMAT, 1997
14. “Damage
Accumulation and Spectrum Editing”, USAF
Structural Integrity Program Conference, 1997.
15. “Modeling
Corrosion Morphology and Effect of Initial Quality State” presentation located on www.nci.com and
www.APESolutions.com, 4 May 1998.
16. “Tailoring the
Structural Integrity Process to Meet the Challenges of Aging Aircraft” Presented at the Fatigue Damage of Structural Materials II,
Cape Cod, Massachusetts, September 1998.
17. “Corrosion is
a Structural and Economic Problem: Transforming Metrics to a Life Prediction
Method” Presented at the
NATO RTO’s Workshop 2 on Fatigue in the Presence of Corrosion, Corfu, Greece,
October 1998.
18. “Integrating
Real Time Age Degradation into the Structural Integrity Process” NATO RTO’s Workshop 2 on Fatigue in the Presence of
Corrosion, Corfu, Greece, October 1998.
19. “Determining
the Initial Quality State for Materials”,
USAF Aircraft Structural Integrity Program Conference, 1998.
20. “ECLIPSE-Environmental
and Cyclic Life Interaction Prediction Software” ASM AEROMAT, 1999.
21. “Predictive
Modeling for Corrosion Management: Modeling Fundamentals” Third Joint NASA/FAA/DoD Conference on Aging Aircraft,
1999.
22. “Correlation of
Life Prediction Methods with Corrosion-Related Tests” USAF Aircraft Structural Integrity Program Conference, San
Antonio, Texas, 1999.
23. “Case Studies
for Corrosion/Fatigue Life Assessments”
Fourth Joint NASA/FAA/DoD Conference on Aging Aircraft, St. Louis, Missouri,
May 2000.
24. “The
Application of p-version Finite
Element Methods to Fracture-Dominated Problems Encountered in Engineering
Practice” p and hp Finite Element Methods: Mathematics
and Engineering Practice Conference (p-FEM2000), St. Louis, Missouri, May 2000.
25. “Using
Holistic Life Predictions to Focus NDI Requirements” Presented at the 2000 USAF Aircraft Structural Integrity
Program Conference, San Antonio, Texas, December 2000.
26. “Monitoring the Robustness of
Corrosion & Fatigue Prediction Models” Presented at
the 2001 USAF Aircraft Structural Integrity Program Conference, Williamsburg,
Virginia, December 2001.
27. “Managing damage in the wing: modeling the
interaction of exfoliation with static and fatigue loads” Presented at the Sixth Joint FAA/DoD/NASA Conference on
Aging Aircraft, San Francisco, California, September 2002.