Behavior of single-lap bolted joint subjected to dynamic transverse load
Résumé
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 examines the dynamic behavior of a simple bolted joint assembly subjected to a rapidly varying transverse load, which induces bending of the jointed plates. The approach adopted is based on a finite element method, with a coupled bolt model and a penalty friction model, and implicit time simulation. Numerical result sets are presented and discussed.