The bolt-connected structure of lug

widely used in aviation industry

is prone to fracture under frequent loading

making the analysis of its tensile and fatigue performance crucial. In this paper

the tensile test parameters of lugconnected structure were designed based on theoretical calculations

and the low-cycle fatigue test was designed by the tensile displacement–load curve. The static-load failure and low-cycle fatigue failure of 7050–T7451 aluminum alloy lugconnected structure were investigated using experiments and finite element simulations. The results demonstrated that the double lug structure completely fractured after 7686 cycles

and the crack propagation a–N curve was close to that of the fatigue life simulation results. The results provide a reliable theoretical basis for evaluating the safety of lug-connected structure and selection of lug-connected part.