The evaluation of the fatigue quality of an aircraft is discussed. The steps involved are as follows: (1) determination of the fatigue load environment, (2) response of the aircraft structure, (3) internal load distributions, and (4) estimation of the fatigue properties. The fatigue properties comprise fatigue life, crack propagation, and residual strength. The latter two items together with inspection procedures are qualifications for fail safe conditions. The influences of these factors on design efforts calculations, testing, inspections, and fatigue load monitoring are analyzed. (Author)
Aspects of Aeronautical Fatigue
1973
29 pages
Report
No indication
English
International Committee on Aeronautical Fatigue
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