On the fatigue crack growth analysis of spliced aircraft wing panels under sequential axial and shear loads

The spliced wing panels on a surveillance aircraft are subject to sequentially applied axial and shear load cycles. This paper aims to propose an approach to address the fatigue crack growth under this scenario. Current understanding on fatigue crack growth behaviours was reviewed, focusing on crack surface interferences and fatigue crack growth mechanisms under non-proportional mixed-mode loads. A generic spliced plate was analysed using...