Abstract
An optimum design method of fibrous laminated composites is proposed. This method yields optimum laminate configuration with the maximum strength being subject to required in-plane stiffness under in-plane loading condition. Tsai-Wu criterion is used for determining a first-ply-failure strength, and the margin of safety is adopted as the objective function in optimizing process. The fiber orientation angles are 0°，±45°and 90°, which are usual for aircraft structures.
