Reduced order modeling analysis for flexible wing using a co-rotational beam element

An accurate method for large deformation structural modeling is fundamental to geometrically nonlinear aeroelasticity analysis. This paper develops a nonlinear reduced order modeling method suitable for aeroelastic analysis with high efficiency and sufficient fidelity. The structural reduced order modeling method is based on equations derived from the Galerkin approach to solve the geometric nonlinear dynamics in a weak form, in which the explicit calculation of nonlinear stiffness is not practical. Based on dynamic response data samples, nonlinear stiffness coefficients in structural dynamics equation are identified based on the fast Fourier transform and the Harmonic Balance nonlinearity identification technique. Co-Rotational finite element method is adopted for the structural simulation of a wing model to provide dynamic response data. ...