Nonlinear aeroelasticity and ground flutter simulation test of a supersonic panel

The extensive utilization of high-speed aircraft has motivated considerable research on supersonic panel flutter, while research on the nonlinear aeroelastic behavior of panels subjected to non-classical boundary constraints remains limited, and an effective ground simulation test system for supersonic panel flutter is lacking. To elucidate the nonlinear flutter mechanism and parameter influences in supersonic rectangular panels under non-classical boundary conditions, a nonlinear aeroelastic model is developed employing the von-Karman plate theory, first-order piston theory, and the assumed-mode method. The accuracy of the model is validated through comparison with finite element method (FEM) results. Numerical integration reveals that reducing the length-width ratio slightly delays the onset of flutter while significantly lowering the threshold for complex dynamic responses. Phase diagrams, Poincare maps and spectral diagrams are employed to trace the system's transition from ordered to chaotic motion. Furthermore, a second-order reduction and reconstruction method for distributed aerodynamics is proposed, tailored for the ground flutter simulation test of supersonic panels. A multi-input multi-output (MIMO) excitation force controller is designed, resulting in a comprehensive ground flutter simulation test system. Experimental results show good agreement with theoretical predictions, and the controller demonstrates effective real-time tracking of excitation forces, confirming the feasibility of the proposed test approach and its substantial value for engineering applications. This work addresses the challenge of performing aeroelastic tests under coupled multi-physical ground conditions, thereby overcoming a key bottleneck in evaluating the dynamic strength of supersonic/hypersonic panels, providing a novel methodology for the design and assessment of advanced thin-walled structures in next-generation high-speed aircraft.