摘要
针对某型机翼振动响应较大的问题,运用压电纤维复合材料作为控制器,采用PID、LQR和LMS三种控制律方法和设计的实验方案进行振动主动控制的仿真模拟研究。仿真结果表明,所采用的控制律方法和设计的实验方案对机翼结构进行振动主动控制是可行的,同时得出了LMS方法是三种控制方法中控制效果最好,PID方法的收敛时间最短。
The PID,LQR and LMS control methods,with the optimized parameters of the three methods,were used to perform the simulate experiment of active vibration control of the aircraft,which used Macro Fiber Composites( MFC) as control device. It was used to validate the feasibility of the active vibrate from simulate experiment. Come to the conclusion that the amplitude response from the simulate experiment has been suppressed well,and the control effect of LMS is better and the convergence time of PID is shorter.
出处
《飞机设计》
2016年第2期53-56,共4页
Aircraft Design
基金
中航工业集团技术创新项目2009F63080
