Behavior of Single-Lap Bolted Joint Subjected to Dynamic Transverse Load

Bolted joints used in aeronautical structures are subject to vibrations, which can result in critical damage either from self-loosening or from fatigue. This study is devoted to the examination of the dynamic behavior of a simple bolted joint assembly subjected to quickly varying transverse load, which induces bending of the jointed plates. The adopted approach is based on finite element method, with a coupled bolt model and a penalty friction model, and implicit time simulation. Numerical result sets are presented and discussed.