Static and fatigue testing bolted, bonded and hybrid step lap joints of thick carbon fibre/epoxy laminates used on aircraft structures

摘要

Fibre reinforced polymer matrix composites are being increasingly used for aircraft structures because of their superior structural performance, such as high strength, high stiffness, long fatigue life, and low density. This study is targeted towards the repair of thicker composite step lap joint configurations. The aim is to compare the static strength and fatigue resistance of a hybrid joint consisting of both bonding and bolting, a purely fastened joint and a purely bonded joint. Parameters such as fastener array, bond strength and the influence of initial defects are investigated.