Aero-Structural Optimization of Aircraft Wing by Finite Element Method

New and innovative designs must be explored to meet the aircraft requirements lower weight and more cost effective structure for future airplanes. For these reasons, present study aims to deals with the structural analysis for predicting the structural behavior of aircraft wing with ribs and stringers. With an helpful of aerodynamic principles, aircraft wing with ribs and stringers were analyzed by considering two criteria, one is varying load conditions and the other method is varying structural materials. For structural and aero–elastic response analysis, finite element method is used in ANSYS software with efficient computation. Wing behavior of total deformation (δ) , equivalent (von Mises) stress (σv), equivalent elastic strain (ε), ultimate tensile stress (UTS) and wing twist to be simulated. From the computational results, better performance aircraft structure material, in terms of light weight, low fuel consumption and cost-benefit to save economy is identified.