操纵面作为飞行器的重要部件之一，其颤振特性对设计参数较敏感，容易发生颤振失稳，成为飞行器气动弹性设计重点关注的问题之一。以带操纵面的机翼模型为研究对象，采用非定常气动力二次降阶时域重构的方法，以降阶前后颤振特性差异最小为目标，对气动力加载点和响应测量点进行全局优化，获得高精度的降阶时域气动力模型。搭建了带操纵面机翼地面模拟试验平台，设计了多输入多输出（Multi-Input Multi-Output, MIMO）鲁棒控制器，并利用电磁激振器等效施加机翼结构运动所诱导的分布式非定常气动力，从而实现无风条件下带操纵面机翼模型颤振稳定性与亚临界极限环颤振的地面模拟。研究表明，线性颤振地面模拟试验结果与数值仿真结果误差在7%以内，非线性颤振试验结果与数值仿真结果误差在10%左右，验证了本文所提出的带操纵面机翼颤振地面模拟试验流程及方法的有效性。
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.
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