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.
Fatigue Behaviors of 2024 Aluminum Alloy under Aviation Load Spectrum
2016
Article (Journal)
Electronic Resource
Unknown
Metadata by DOAJ is licensed under CC BY-SA 1.0
Notch Size Effects in 2024-T351 Aluminum Alloy Under Fatigue Spectrum Loading
Online Contents | 1998
|Notch Size Effects in 2024-T351 Aluminum Alloy Under Fatigue Spectrum Loading
British Library Online Contents | 1998
|