Optimization Design of an Aircraft Wing Structure based on Response Surface Method

Abstract

Wing is the most critical part of an aircraft whose structural weight holds prime importance. It is always desirable to reduce the weight of an aircraft. In this work, a detailed analysis of wing is carried out and results pertaining to stress distribution are recorded. Commercial software ANSYS is used to perform simulations related to stress, strain and displacement distributions. Moreover, the optimization design of an aircraft wing was conducted using design of experiments (DOE) and response surface method (RSM) technique for the reduction of computational cost. The aircraft wing is efficiently optimized by changing thickness under the same loading and flight conditions. Results show that this optimization technique is useful to reduce stresses as well as overall weight of the structure with minor variation in thickness of components.