三种方法在机翼振动主动控制中的仿真研究  

Simulation Study on Three Control Methods for Active Control in Wing Vibration

作　　者：朱江辉[1] 雷鸣[1] 孙勇军[1] 

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《工程与试验》2014年第4期1-4,72,共5页Engineering and Test

基　　金：中航工业集团技术创新项目2009F63080

摘　　要：针对某型机翼振动响应较大问题,研究了PID、LQR和LMS等3种控制律方法实现振动主动控制技术的可行性。在仿真试验中,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,使用设计出的试验方案进行。结果表明,通过优化参数,PID、LQR和LMS等3种控制律方法在仿真模拟中均较好地抑制了振动响应,在机翼上实现主动控制技术。LMS方法的控制效果更佳,PID方法的控制收敛时间更短。In order to reduce the large amplitude response of the wing vibration,the PID,LQR and LMS control methods have been used to validate the feasibility of the active vibrate.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 an important role in the piezoelectric force,and the other is the Simulink tool of Matlab software,then,a new experimental scheme is designed.The results show that the PID,LQR and LMS control methods,by tuning an optimized parameter,have successfully suppressed the amplitude response of the wing vibration in simulation studies,which reveals that the PID,LQR and LMS control methods have the potential to implement the active control technology,and the control effect of LMS is optimum,the convergence time of PID is optimum.

关 键 词：振动主动控制 仿真 压电力 抑制 

分 类 号：V216.21[航空宇航科学与技术—航空宇航推进理论与工程]