研究了一种基于LQG自校正器的机翼颤振主动抑制设计方法.以带有后缘控制面的柔性机翼为研究对象,采用在线辨识来获取系统的时变参数,利用Kalman滤波器重构状态,通过求解离散时间代数Riccati方程得出机翼颤振主动控制律.在Simulink仿真平台上实现了上述方法,仿真结果表明,该控制器能够有效抑制机翼颤振的发生并具有一定的鲁棒性. This paper studies a design method of active suppression of wing flutter based on LQG self-calibrator. Taking the flexible wing with trailing edge control surface as the research object, the time-varying parameters of the system are obtained by on-line identification. The Kalman filter State, and obtain the flutter active control law by solving the discrete-time algebraic Riccati equation. The above method is implemented on the Simulink simulation platform. The simulation results show that this controller can effectively suppress the flutter of the wing and has certain Robustness.