Optimization of Ply Orientation of Different Composite Materials for Aircraft Wing

Abstract

The target of this paper is to build up an exact model for ideal plan through outline the structure of wing that consolidate the composite (Skins) and isotropic materials (every single other structure) and contrast this and a similar wing made by changing the materials and the orientation of composite ply in skin.The ideal plan for each wing with various materials and different ply orientation can be obtained by comparing the displacement and stress on the wing. The structural design of the wing is finished with the assistance of CATIA V5, every parts modelled independently and collected in the IGS file. By using the IGS file as geometry, the Finite element modeling is completed in ANSYS and the Static analysis was done using ANSYS. In this analysis, the boundary conditions of inertia force of 1Kg and the lift force is used to simulate the wing loading on the wings. From this study, the Optimum design of the wing was found from the comparisons of stress and displacement of each material and ply combination. Keywords-Composite Wing, Modeling in CATIA V5, Finite element Analysis in ANSYS, Optimum ply orientation and material.