Efficient aeroelastic response analysis including geometric nonlinearities based on structural Rom

In this paper, efficient reduced order model (ROM) is established for nonlinear aeroelastic response analysis. The method can be used to solve the aeroelastic response problems of wing containing geometric nonlinearities. Traditional methods of aeroelastic analysis can’t reflect the nonlinear characteristics of structures. And their results can’t satisfy the precision demand of engineering analysis. The approach for structure modeling presented here is based on a combined modal/finite element (MFE) approach that describes the stiffness nonlinearities. We apply that structure modeling method as ROM coupled with nonlinear unsteady vortex lattice method (UVLM) to aeroelastic response analysis. The results show that aeroelastic response analysis of wing based on structure ROM can achieve a good agreement compared to analysis based on the nonlinear finite element method (FEM). The method in this paper is suitable for the preliminary design and the aeroelastic response analysis of the large-aspect-ratio wing efficiently.