Service Life Modelling of Single Lap Joint Subjected to Cyclic Bending Load

Bonded joints used in wing sections and frames of aircraft structures are mostly exposed to cyclic loadings instead static ones during their services. Bending types dynamic encountered. In this study, the fatigue response a single lap joint (SLJ) bending loading was studied with developed advanced finite-element (FE) model. The cohesive zone model describing behaviour adhesive layer damage mechanism, where damages were linked each other; i.e., total accumulated because material deterioration plastic separation. This enabled us predict characteristics including finite life, crack propagation rate using Paris law. implemented via user-defined UMAT subroutine offered ABAQUS-Standard. numerical validated by experiments available literature. performance an SLJ subjected investigated for different configurations. A smaller load, thicker adherend or longer overlap length (OL) led enhanced life. For instance, life observed increase up 50 times 66% OL.