Failure analysis of single lap composite laminate bolted joints: Comparison of experimental and numerical tests

Carbon fiber reinforced plastics (CFRP) are widely used in aircraft industry because of their high mechanical properties. However these properties considerably drop when composite materials are drilled and bolted. Thus, it is important to master the composite bolted joint behavior to avoid a structural failure. Experimental test on single lap bolted joints with various end distance have been led. The failed specimens are analysed thanks to XR computed tomography (XR-CT) and digital image correlation (DIC). The results are compared with a three dimensional finite element model involving a progressive damage model for the composite material. It is based on a progressive damage model of the composite material. The global behavior and the damages computed are in good agreement with the experimental results. But, contrary to the experimental observations, the computed damage scenarios are the same for all the tested end distance.