采用分布式压电驱动器升力面的颤振主动抑制  

FLUTTER SUPPRESSION USING DISTRIBUTED PIEZOELECTRIC ACTUATORS

作　　者：陈伟民[1] 管德[2] 诸德超[2] 李敏[3] 

机构地区：[1]北京大学力学与工程科学系,北京100871 [2]北京航空航天大学飞行器设计与应用力学系,北京100083 [3]中国科学院力学研究所,北京100080

出　　处：《力学学报》2002年第5期756-763,共8页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金重点项目(60034010);中国博士后基金项目资助.

摘　　要：对采用分布式压电驱动器升力面的颤振主动抑制进行了理论与试验研究.应用 LQG最优控制法设计了主动控制律,在控制律降阶时提出了平衡实现与LK法结合使用的新途径,在对不定常气动力进行有理函数拟合时对LS法进行了改进.试验中利用激光测速仪非接触测量模型的速度响应并在地面共振试验中用压电驱动器激振模型.颤振风洞试验结果表明,理论计算合理并与试验结果吻合良好.An analytical and experimental investigation of a lifting surface with distributed piezoeletric actuators for active flutter suppression is described.Equations such like structure dynamic equation, flutter equation and state space equation of piezoelectric laminated structure are developed, based on investigating mechanic-electric coupling.LQG control law was used for active flutter suppression. Random disturbance existing in measuring signal being considered, so Kalman filter was designed for states estimating. The order reduction of control law is discussed on two hands. First, the physical reduction of state-space equations, meanwhile the reduction of aerodynamic lag terms based upon modification of aerodynamic simulation; Second, after discussed balance realization and LK method, a combed balance realization and LK method was developed.Ground tests preparing for wind-tunnel test were implemented after manufacturing model. By non-contact exciting and non-contact laser measuring, the accuracy of vibration tests improved pretty well. The control laws were implemented using real time digital control computer, then the open-loop response of model-control system was tested.When wind-tunnel tests were conducted employing laser vibrameter and digital control computer, both of open-loop and close-loop velocity response was recorded in tests in order to compare them, additionally control voltage applied to piezoelectric actuators also recorded in close loop tests. Tests demonstrate that the test results agree well with that of analysis, and distributed piezoelectric actuators can be employed for flutter suppression with an increase in flutter speed of 12%.

关 键 词：分布式 压电驱动器 升力面 颤振主动抑制 风洞实验 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]