一种考虑直升机状态矩阵摄动的改进LMI设计方法

Improved LMI Design Method Considering Helicopter State Matrix Perturbation

基于线性矩阵不等式(Linear matrix inequality,LMI)的鲁棒控制方法在直升机飞控系统设计中得到了广泛的应用,现有方法在设计中仅考虑了阵风和噪声等外界干扰引起的控制对象模型不确定性,未考虑直升机飞行状态变化引起的状态矩阵摄动。本文发展了一种能够同时考虑直升机外界扰动和状态矩阵摄动的改进LMI方法,并基于Z-11直升机,针对姿态指令姿态保持(Attitude command attitude hold,ACAH)响应类型进行设计。最后在Matlab/Simulink环境下进行了仿真验证。结果表明基于本文设计方法得到的控制律具有较高的控制精度,同时具有增强的鲁棒性。

The linear matrix inequality（LMI） robust control method is widely used in the design of helicopter flight control system. Current methods only consider the model uncertainty caused by gust and noise etc. The perturbation of state matrix due to flight state variation is neglected. In the paper, an improved LMI method considering both external disturbances and state matrix perturbation is established. The flight control law for attitude command attitude hold （ACAH） of Z-11 helicopter using the developed method is implemented. Finally, the simulation is carried out under the Matlab/Simulink environment. The results show that the control law designed by using the developed method has good performance and the improved robustness.