Structural optimization of a light aircraft composite wing

Author:

Aung Phyo Wai,Tatarnikov Oleg,Aung Naing Lin

Abstract

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.

Publisher

IOP Publishing

Subject

General Medicine

Reference8 articles.

1. A Layout Optimization Method of Composite Wing Structures Based on Carrying Efficiency Criterion Chinese;Qun;Journal of Aeronautics,2011

2. Optimization of aircraft wing with composite material;Shabeer;International Journal of Innovative Research in Science Engineering and Technology,2013

3. Global/Local Multidisciplinary Design Optimization of Subsonic Wing;Liu,2014

4. Structural-Optimization Strategy for Composite Wing Based on Equivalent Finite Element Model;Wang;Journal of Aircraft,2016

5. Three-Level Design of Composite Structures;Tatarnikov,2012

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