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Composite materials are ideal for structural application where high strength-to-weight and high stiffness-to-weight ratios are required. In particular, Aircraft and Spacecraft are the typical weight-sensitive structures in which composite material are cost-effective. A major purpose of lamination is to tailor the directional dependence of strength and stiffness of a composite material to match the loading environment on the structural element. Since the fiber orientation enables the optimization of the mechanical behavior along a specific direction, the study has been made to analyze the behavior of the laminate properties and strength based on the fiber orientation.

Finite Element Modeling and Analysis of Skin Panel Based On the Fiber Orientation and Stacking Sequence