Abstract: Control surfaces, being critical components of aircraft, exhibit significant sensitivity in their flutter characteristics to design parameters and are prone to flutter instability, making them a critical focus in aeroelastic design. This study investigates a wing model with control surface and employs a time-domain reconstruction method based on reduced-order modeling of unsteady aerodynamic forces. With the objective of minimizing the differences in flutter characteristics before and after reduction, a global optimization of aerodynamic loading points and response measurement points is carried out, yielding a high-fidelity reduced-order unsteady aerodynamic model in the time domain. A ground simulation test platform for a wing with control surface is established, incorporating a multi-input multi-output (MIMO) robust controller. Electromagnetic exciters are utilized to equivalently simulate the distributed unsteady aerodynamic forces induced by wing motion, thereby enabling ground simulation of flutter stability and subcritical limit cycle for the wing model with control surfaces under wind-off conditions. Studies have shown that the linear experimental results demonstrate agreement with numerical simulations within 7%, and the nonlinear experimental results demonstrate agreement with numerical simulations about 10%, validating the feasibility of the proposed ground flutter simulation test methodology for wing with control surface.

Key words: Control surface flutter, Ground flutter simulation test, Reduced-order modeling of unsteady aerodynamics, Time-domain reconstruction of aerodynamics, Freeplay nonlinearity