Structural optimization of a light aircraft composite wing

Abstract

This paper presents the results of structural optimization of a two-spar composite wing for a light aircraft. Different lay-up structures of power components such as spars, ribs and skin panels was considered. The problem of optimization was solved using Pareto optimization method with two criteria: Minimal wing weight and minimal wing deflection under aerodynamic load. The angle of ply orientation and power components thicknesses were considered as the optimization parameters. It was shown that the use of the optimized wing from carbon composite could reduce up to 60% of the wing weight comparing with aluminium one. The stress-strain and buckling analysis of the wing and its power components were carried out in FEMAP software package.