两种方法在机翼振动主动控制中的应用研究

针对机翼振动响应较大问题,研究了PID和LMS两种控制律方法在真实机翼上实现振动主动控制技术的可行性。仿真模拟实验中,采用Patran进行结构建模和压电力等效,通过Matlab的Simulink模块搭建控制仿真模型;机上地面实验中,设计了以压电纤维复合材料作为控制器,激振台作为激振器的地面试验方案。结果表明,通过优化参数,PID和LMS两种控制律方法在仿真模拟和地面试验中均较好地抑制了振动响应,从而在机翼上实现主动控制技术,同时LMS方法比PID方法的控制效果更佳。

Study of two control methods on application of theActive vibration control used to the wing

In order to reduce the large amplitude response of the wing-vibration, The LMS and PID control methods have been used to validate the feasibility of the active vibrate to the true wing. In the simulation study, the experimental model is made up of two components, one is the Patran which builds the FEM of the wing and plays the role of the Piezoelectric force, and the other is the Simulink tool of Matlab software. In the ground test study, a new experimental scheme is designed which uses the vibration exciter as the exciting device, the Macro Fiber Composites (MFC) as the control device. The results show that the PID and the LMS control methods, by tuning an optimized parameters, have successfully suppressed the amplitude response of the wing-vibration in both simulation and ground test studies, which reveals that the PID and LMS control methods have the potential to implement the active control technology of the true wing, and the result of LMS is more optimum.