Structural design of a UAV wing using finite element method

Abstract

This paper presents the structural design methodology for the wing of an Unmanned Aerial Vehicle. In this study, the application of computational methods in design is successfully explored. The strength and stiffness analysis of the UAV wing was performed using an FEA software ANSYS. The available CAD model and aerodynamic CFD analysis of the vehicle were used as design input. The aerodynamic loads were applied on the structure as pressure functions using a novel approach employing Artificial Neural Networks. Effects of variability in geometry, material and lay-up were also analyzed to find the best possible combination with optimal strength and stiffness amid minimum weight and cost. The finally designed wing has two spars and used an all composite structure. The wing is lighter in weight as compared to a similar wing made from Aluminum, and sufficiently strong enough to meet all in-flight load conditions and factor of safety. Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc.