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为有效抑制二元机翼颤振现象,采用Lyapunov稳定性理论设计了一种改进状态相关黎卡提方程(SDRE)的非线性鲁棒控制律。将含前/后缘双控制面的二元机翼模型以状态空间形式描述并将该模型转化成输入矩阵B为行满秩的形式,进而解决了基于SDRE的非线性控制方法不能直接应用于二元机翼颤振主动抑制的问题。仿真结果表明,在阵风干扰和控制面存在偏转角限制的情况下,闭环系统能快速达到稳定状态,颤振现象得到有效抑制。通过调节权重矩阵Q和R,能够减小控制输入幅值。
In order to effectively suppress the flutter of binary airfoils, a nonlinear robust control law is proposed by using Lyapunov stability theory to improve the state-dependent Riccati equation (SDRE). The dual wing model with front / rear dual control surfaces is described in state space and converted into an input matrix B in the form of full rank. Thus, the nonlinear control method based on SDRE can not be directly applied to Active suppression of binary wing flutter. The simulation results show that the closed-loop system can reach steady state quickly and the flutter phenomenon can be effectively suppressed under the gust disturbance and control surface deflection limit. By adjusting the weight matrix Q and R, the control input amplitude can be reduced.