The use of composite pressure vessels particularly in the aerospace industry is escalating rapidly because of their superiority in strength and colossal weight advantage.The present work elucidates the procedure to optimize the lay-up sequence and calculate the relative weight saving, compared with the reference metallic pressure vessel.The determination of a proper winding angle and thickness is very important to decrease manufacturing difficulties and to increase structural efficiency.The design of the composite laminate is based on the Tsai-Wu failure criterion for first-ply failure (FPF).Balanced symmetric laminates are to be considered of three candidate composite materials S-glass/epoxy, Kevlar/epoxy and carbon/epoxy.Netting analysis is carried out to find the winding angles and hoop/helical layers role for optimum structural performance and higher efficiencies.An in-house code is developed in MATLAB using the classical lamination theory (CLT) incorporating various other failure criteria.Finite element analysis (FEA) of the composite pressure vessel is performed by using commercial FEA code ANSYS and utilizing the capabilities of ANSYS Parametdc Design Language (APDL) to automate common tasks.