Ground flutter simulation test of wing with control surface

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. Taking the wing model with control surface as the research object, a time-domain reconstruction method based on two-stage reduced-order modeling of unsteady aerodynamic forces is employed. With the objective of minimizing the difference in flutter characteristics before and after reduction, a global optimization of aerodynamic force loading points and response measurement points is carried out, yielding a high-fidelity reduced-order aerodynamic force 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 surface under wind-off conditions. Studies have shown that the experimental results of linear ground flutter simulation test demonstrate agreement with numerical simulations within 7%, and the experimental results of nonlinear ground flutter simulation test demonstrate agreement with numerical simulations about 10%, validating the feasibility of the proposed ground flutter simulation test methodology for wing with control surface.