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An understanding of the failure mechanisms of the adhesive layer is decisive in interpreting theperformance of a particular adhesive joint because the delamination is one of the most common failure modes of thelaminated composites such as the fiber metal laminates. The interface between different materials, which is the casebetween the metal and the composite layers in this study, can be loaded through a combination of fracture modes. Allloads can be decomposed into peel stresses, perpendicular to the interface, and two in-plane shear stresses, leading tothree basic fracture mode I, II and III. To determine the load causing the delamination growth, the energy release rateshould be identified in corresponding criterion involving the critical energy release rate ( G C ) of the material. Thecritical energy release rate based on these three modes will be G IC , G IIC and G IIIC . In this study, to evaluate the fracturebehaviors in the fracture mode I and II of the adhesive layer in fiber metal laminates, the double cantilever beam andthe end-notched flexure tests were performed using the reference adhesive joints. Furthermore, it is confirmed that theexperimental results of the adhesive fracture toughness can be applied by the comparison with the finite elementanalysis using cohesive zone model.

Evaluation of Fracture Behavior of Adhesive Layer in Fiber Metal Laminates using Cohesive Zone Models