Abstract
Fiber metal laminates (FMLs) commonly occur in airplane structures and are of great interest in the aerospace industry due to their superior properties. This study simulates fracture behavior in a FMLs specimen subjected to quasi-static loading conditions by a 3D elastic-plastic finite element model in ABAQUS. Cohesive elements are used to model the interlaminar delamination, and the ABAQUS damage model for fiber-reinforced materials is used to predict behavior of the fiber-reinforced epoxy layer. The materials strength can be predicted by the simplified 3D elastic-plastic finite element model. Predictions accuracy of model are tested by the experimental results and good consistency acquired. The models presented in this study can shorten the period of new style FMLs research and the cost cut down largely.