ABSTRACT
A load is applied to a curved (C-Spar) hybrid composite that attempts to unfold the laminate, causing various damages. This damage can result in a reduction in the strength and stiffness of the laminated composite. In addition, cracks in the matrix and fibers play an important role in the failure of a curved hybrid laminate. In this chapter, a hybrid composite was designed according to the stacking order [0°/30°/−30°/0°/45°/−45°/−45°/−45°/−45°]S. Using the commercial software ABAQUS, a pullout simulation was carried out using the plane stress and plane strain model to determine the load-carrying capacity of a curved hybrid laminate. The built-in Hashin failure criteria were applied to predict the various damages such as fiber damage and matrix damage. Further, the cohesive elements were inserted between the interfaces (delamination) of the laminate. Here the onset of delamination is based on the traction-separation law and propagates under mixed loading. The predicted failure load in the case of plane stress and plane strain model showed a deviation of 2.4% and 1.5%, respectively, compared to the values already reported in the literature, and showed good agreement.
