Numerical and experimental studies on the joint performance of fastened, bonded, and hybrid thin metal joints used in aircraft structures

Abstract

Static strength of mechanically fastened, bonded, and hybrid double lap joints are investigated in this study. Aerospace grade 7075-T6 aluminium alloy was chosen for the adherend as it is a widely used primary aircraft structure material. Mechanical fasteners were arranged in square array patterns to resemble typical rivet arrangements in airframes. The aim was to compare the joint performance of three distinct joining/repairing mechanisms: purely riveted, purely bonded, and a hybrid of both rivets and adhesive bonding. Finite element analysis (FEA) verification of the riveted configuration static strength indicated accurate prediction of both joint strength and failure mode. Detailed results will be reported in the paper. This paper presents the first stage of a systematic research program assessing the damage tolerance behaviour of crack growth, and design assessment of adhesive bonded/hybrid metallic joints under static and fatigue loadings, to achieve the optimum joint design for applications.