A three layer [0/90/0] graphite-epoxy composite laminate subjected to an axial load will be examined. A finite element model will be constructed using Abaqus/CAE 6.10 where the principal stresses in the respective plies will be analyzed.

Since the laminate shown in Figure 1 consists of ply drop-offs, the lumped shell finite element model will be constructed using three sections (Figure 2). The respective material properties for the model are shown in Table 1.