In this paper, efficient reduced order model (ROM) is established for flutter analysis including geometric nonlinearities. 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 finite-state inflow aerodynamics to geometrical nonlinear flutter analysis. Accuracy of ROM has been validated compared to nonlinear FEM. The results show that both static and dynamic response analysis of wing based on structure ROM can achieve a good agreement compared to analysis based on the nonlinear finite element method (FEM). Plunging and pitching motion of airfoil section can be expressed with modal basis functions chosen in nonlinear ROM and amplitudes. Meanwhile, a wind tunnel test is completed to validate the nonlinear flutter analysis results.
展开▼
