Outcomes of Nonlinear Static Aeroelasticity for Wing Stress and Buckling Applied to a Transport Aircraft

Abstract

© 2024 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.This work presents a decade of outcomes of Static Aeroelasticity of high aspect ratio wings for the Structures technology. There are considerable improvements in Aeroelasticity field by incorporating structural geometric nonlinearity to understand high span wing behavior. However, there is a lack of investigation on how the Aeroelasticity outcomes influences Structures technology, their interface information, and methodologies. Thus, this paper presents the high-fidelity methodology E2-FSI&SS as means to expose the chain of effects culminating in a different structural sizing concerning stress and buckling at limit static load. Here high flexibility is considered by adding structural geometric nonlinearity in the static aeroelasticity, to obtain follower loads, and in the sizing of the structure itself. The method is applied to a very flexible wing of a transport aircraft from 50 to 150 passengers. The differences found by considering and not considering the static aeroelasticity of high flexibility wings in limit flight loads are 14% in internal load, up to 82% in stress and 30% in buckling load factor.