Fatigue Behaviors of 2024 Aluminum Alloy under Aviation Load Spectrum

Abstract

The fatigue properties of 2024 aluminum alloy under the influence of TWIST on the aviation load spectrum were studied. The aircraft load spectrum was simplified, and the fatigue life of the aircraft was predicted by theoretical analysis, MATLAB program simulation and fatigue was test, and the failure mechanism was observed. The results show that the predicted values of fatigue life are 163800, 158280 and 134249 respectively. Aircraft cruise loads during actual gust load spectrum is simulated, the minimal fluctuation spectrum is ignored. The flight cycles are 92314 and 92321 times respectively. Crack initiation nucleation is originated in the test piece near the surface. Fatigue crack is propagated between intergranular and transcrystalline rupture. Instantaneous, rupture zone and crack propagation can be observed.

Keywords

• aluminum alloy
• aviation load spectrum
• fatigue life predict
• microscopic analysis