Computational Aeroelasticity Using Modal-Based Structural Nonlinear Analysis

Abstract

This paper presents the development of an aeroelastic analysis formulation for the dynamic response of a flexible wing. The geometrically nonlinear structure is represented by a reduced-order model that accounts for the large-deformation effects on the inertia and stiffness terms. It is based on a system identification of a built-up finite element model and does not rely on a geometric nonlinear beam-based model as most of the state-of-the-art nonlinear aeroelastic frameworks do. The complexity of the wing structural layout is captured in the built-up finite element model as in traditional industry applications. To preserve a small number of states to represent the structural dynamics of the system, a modal approach is used in a nonlinear sense. Moreover, this approach is easily linked to computational fluid dynamics. For this study, the structural reduced-order model framework is integrated within the aeroelastic framework of the code CFL3D. Using this integrated solution, the aeroelastic response of a high-aspect-ratio wing is investigated.