Design, Optimization and Analysis of Aircraft Composite Wing for Aerospace Application

Abstract

The objective of this research is to develop an accurate model for an optimized wing design by configuring the arrangement of compound materials (skins) and isotropic materials. A comparison is made between optimized wing and another wing created by adjusting parameters such as skin thickness, number of ribs, rib positions, spar measurements, and more, in order to achieve the best possible results. After evaluating the different properties of composite materials for wing structures that satisfy desired requirements and criteria by referring the previously designed wing structures available, analysis of the same was done by using isotropic as well as composite material and results were noted. During the analysis phase, various structural parameters of the aircraft wing, such as total deformation, Von-Mises stress (also known as equivalent stress), shear stress, and shear intensity on the wing's skin, were determined. Simultaneously, an optimization process was conducted to refine the wing design. This involved making changes to parameters like skin thickness, number of ribs, rib positions, spar dimensions, and other relevant factors, in order to achieve the most favorable outcomes. The objective was to find the optimal configuration that would yield the best results for the wing design. After optimization, the best configuration was selected and analysis report for best composite material that can be used for future wing design is generated. Validation of results obtained was done by hand calculation by using formulae of simplified beam theory. The result was expected to have 35-45% weight saving using composites for wing design compared to isotropic materials.