Reliability Analysis of Fatigue-Sensitive Aircraft Structures Under Random Loading and Periodic Inspection
Technical rept. Oct 1973-Jan 1974
AIR FORCE MATERIALS LAB WRIGHT-PATTERSON AFB OH
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A reliability analysis of fatigue-sensitive structures, based on the application of random vibration theory, is presented. The fatigue process involved here consists of crack initiation, crack propagation and strength degradation. After a fatigue crack is initiated, fracture mechanics is applied to predict crack propagation under random loading. The aircraft structure is subjected to periodic inspection in service. When a fatigue crack is detected during inspection, the implicated component is either repaired or replaced. Such a renewal process is taken into account in the present analysis. Taking into account all the random variables as well as the random loadings, the solution for the probability of first failure in a fleet of aircraft is derived.
- Metallurgy and Metallography
- Solid State Physics