带操纵面机翼的颤振地面模拟试验方法OA

Control surfaces,being critical components of aircraft,exhibit significant sensitivity in their flutter character-istics to design parameters and are prone to flutter instability,making them a critical focus in aeroelastic design.Tak-ing 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 differ-ence 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 un-steady aerodynamic forces induced by wing motion,thereby enabling ground simulation of flutter stability and subcriti-cal limit cycle for the wing model with control surface under wind-off conditions.Studies have shown that the experi-mental 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.