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.

Improving the Flexibility of Ship Propellers Additively Manufactured from High-Density Polyethylene/Long Carbon Fiber Composites by Prepreg Coating

“…Furthermore, lighter structures for the same product can be achieved thanks to the material extrusion method, which allows for thicker and more flexible blades, improving hydrodynamic performance by raising cavitation inception speeds [26]. Most sustainable material research focuses on the structural design of a plate, beam, or aircraft wing [27,28] with a mechanical performance analysis [29], failure analysis [30], optimization [31], and impact damage assessment [32]. Research on 3DAM for wing structures is focused on aircraft wings [33][34][35][36] rather than ship propellers, whose geometry is more complicated.…”