Weight minimization of blended composite structures under buckling lamination parameters layup design

Composite laminates have outstanding mechanical performance and many applications such as aerospace, automotive, marine, and civil industries. One of the most significant properties of the composite laminate fibers is the weight minimization of the composite structure under a certain load. In this study, an optimization of the stacking sequence of the composite material to reduce the weight making the optimized structure more manufacturable and improving its performance. Weight can be controlled or reduced by reducing the thickness of each laminate. Three-ply angles( 25, 50, 75 ) are used in this optimization. Using the classical theory of composite materials to know the properties of each laminate, Tsai–Hill failure theory used to test stiffness properties f the optimized laminate under a certainly designed load.