Abstract
Laminated composite panels are presently being used in wider applications in automotive, aerospace, defence and civil type of industries. It has various advantages over conventional materials with superior specific stiffness & strength, fatigue and corrosion resistance with energy absorption feature comparing others. Optimal design of composite laminates regarding change in ply angles to increase the strength is obligatory to realize the complete potentiality of fibre reinforced particles/materials. The above epistemology is applied to the multi-objective design optimization technique of fibre-reinforced solid rocket motor composite cylindrical skirt of space vehicle is analyzed. In that solid rocket motor, a skirt is defined as a feasible component for weight diminution which leads to reduction of entire weight. Due to its significance, it is recommended to optimize the both weight and expense of the fibre reinforced composite (FRC) cylindrical shape skirt affected to overstressing strength and buckling strength at the combined conditions of aerodynamic torque and thrust in axial direction. In this paper, the failure principle of Tsai-wu is applied to determine the first ply catastrophe. Failure strength and Buckling strength of the skirt is depicts by using overstressing load level factor and buckling load factor. Various material combinations such as Graphite/Epoxy & Glass/Epoxy, have been used to find the optimal values. Laminated composite skirts are fabricated with glass-epoxy if cost is the criteria and graphite-epoxy if weight comes into an account
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