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

Abstract

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.