A computational damage mechanics approach for laminates: Identification and comparison with experimental results

International audienceThe present study concerns finite element predictions of carbon-fiber/epoxy-resin composite coupon delamination tests up to fracture. For these predictions, a previously-defined damage mesomodel of composite laminates is used and implemented in a tridimensional F.E. code. This F.E. software includes the interlaminar interfacial deterioration as well as the main inner layer damage mechanisms. This code is able to predict at any time and at any point the "intensities" of the different damage mechanisms up to fracture. However herein, attention is being focused on the identification and comparison of F.E. predictions with M55J/M18 carbon/epoxy experimental results obtained from the AEROSPATIALE company