Variable thickness design for composite materials using curvilinear fiber paths

Abstract Carbon fiber reinforced plastic (CFRP) laminates are often used in a quasi-isotropic manner, such as cross-ply lamination; thus, the mechanical properties of CFRP cannot be fully exploited. In this study, we proposed carbon design method, which uses orientation and thickness lamination parameters, where is determined using principal stress direction by iterative calculations maximum theory bisection method. The method also accounts for manufacturability considering bundles modifies accordingly. As result implementing weight wing plate model was reduced approximately 5% with failure index 0.7 compared that constant linear model. Thus, can while maintaining strength, may useful further reduction conventional parts.