Abstract
Fatigue life can be divided into crack initiation life and crack propagation life in fatigue damage process. Fatigue crack comes of the initial discontinuity states （IDS） of material, and goes through short crack , long crack and rupture failure. A estimation model based on fracture theory is built, in which includes of IDS, short crack, long crack and rupture failure. A fatigue holistic life (including fatigue life, the residual life and the calendar life ) estimation model was built on the basis of IDS in which the aircraft structures had not been corrosion damage. A lot of fatigue tests with different stress level and different stress ratio are carried out to validate the model. The results demonstrate that the approach is reasonable and feasible.
Published Version
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