Application of the F/A-22 Full-Scale Test for Durability Verification
Speaker: Tom Brussat
Lockheed Martin Aeronautics
The F/A-22 Full-Scale Durability Test completed 2.68 test lifetimes without catastrophic failure. This paper assesses the approach for application of the test results and the durability analysis for verifying the life of the F/A-22 airframe structure. The verification approach is complicated by the fact that 3 different loading spectra were involved. The design analysis for drawing release of the test aircraft was based on the Design Loading Spectrum; the Test Spectrum was based on an updated and more severe spectrum; and the durability verification is evaluated against an updated “Verification Spectrum” that is even more severe than the test spectrum. Consequently
The predicted life for some areas of the structure was less than 2 lifetimes of the Test Spectrum.
Many areas of the structure required significantly more than two lifetimes of testing to demonstrate a two-lifetime capability for the Verification Spectrum.
Due to design updates, several structural details on the durability article had been improved on Production aircraft.
Dr. Brussat has 38 years of experience in fatigue and fracture mechanics, including 20 years of research and development, and the past 18 years as Technical Lead for Durability and Damage Tolerance for the F/A-22 "Raptor." He has published numerous technical papers and has taught crack growth analysis applied to metallic aircraft structure in an annual UCLA short course since 1975.
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February 22 , 2005
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