Search Results

A finite element model for progressive in-plane damage and interfacial delamination was presented for cross-ply composite laminates. The commercial finite element software ABAQUS/STANDARD was used for this study. Each composite lamina was modeled as layers of shell elements based on Mindlin's plate theory. Displacement continuity was established across the layers of shell elements. Interlaminar stresses were recovered at the interface with the use of multi-point constraints. Several material constitutive relations were developed to simulate in-plane damage, such as fiber breakage, matrix cracking and in-plane shear failure. Delamination was simulated by removing the displacement constraints. Cross-ply composite laminates were subjected to impact loading. The results from the finite element analysis compared well with the experimental results.