XFEM and CZM modeling to predict the repair damage by composite patch of aircraft structures: Debonding parameters

In this work, a model based on the combination of two approaches XFEM and CZM, has been used to predict damage repairs by composite patch (patch/adhesive/plate assembly). This degradation is analyzed in terms adhesive considering both initiation propagation interfacial debonding. The cohesive zone patch/adhesive/plate system defined its properties resistance debonding estimated from displacement-load curves. study highlights, as function plate/patch interface, competition between mechanisms: (through mechanism plate) plate phenomenon crack emanating notch). It also depending nature four physical parameters: bending deflection repaired plate, displacement path patch-reinforced shear stresses, characteristic joint their interactions with interface. originality study. Results show that simulations CZM allow adequate prediction assemblies.