Fracture analysis of adhesively bonded single lap joint with four layered [+θ/-θ]_s adherents

The uses of Composite materials together with adhesive bonding have been increasing in aviation industry. The performance of adhesivebonded FRP composite joint is limited by the characteristics of the composite laminate and bimaterial interface. Both cohesive and adhesive failures are major threats to the adhesive bonded joint. In this paper adhesive bonded single lap joints (SLJs) with [+θ/-θ]s laminated FRP composite adherends having a failure at the interface of free edge of the loaded adherend and adhesive along the width of joint are analyzed by varying fiber angle (θ) to investigate the effects of fiber angle (θ) on distribution of SERRs along the delaminating front. Strain Energy Release Rates (SERRs) along the delamination front is calculated using Virtual Crack Closure Technique(VCCT) which is based upon Irwin's hypothesis that the energy absorbed during crack extension (Δc) is equal to the work done to close that crack by the same incremental amount. The problem is modeled and the results are obtained after proper validation of the method with the results available in literature.