当高超声速飞行器改变飞行状态时, 若采用传统的状态反馈方法进行姿态控制系统设计, 为保持系统稳定, 需在不同的平衡点反复进行线性化计算, 计算过程十分复杂。另外, 在飞行器高速飞行的过程中存在输入约束, 还需考虑执行器饱和的问题。针对以上问题, 采用两步法进行控制系统的设计: 首先, 设计了基于线性变参数(LPV)系统的模型参考控制器, 采用奇异值分解与线性矩阵不等式计算得到控制器系统矩阵与反馈增益, 在飞行状态发生变化后, 实现对指令信号的跟踪响应;然后, 考虑到执行器饱和的情况, 引入抗饱和补偿器, 采用LQR最优控制理论计算补偿器增益, 实现对控制输入限幅约束。通过仿真表明, 设计的控制器超调量较小, 调节时间较短, 且有效地减小了控制器设计过程的计算量。

When hypersonic vehicle changes the flight state, the calculation process will be very complicated if the attitude control system is designed by using the traditional state feedback method, since the linearization calculation is repeated at different balance points to maintain the stability of the system.Besides, the actuator saturation should be taken into consideration due to the input constraint in high-speed flight.Aiming at the above problems, a two-step method was developed.Firstly, a model reference controller based on Linear Parameter Varying (LPV) system was designed.The system matrix and feedback gain of the controller were calculated by using singular value decomposition and linear matrix inequation, respectively.So the tracking response of the command signals could be realized after the flight state changes.Then, considering the case of actuator saturation, an anti-windup compensator was introduced, and LQR optimal control theory was used to calculate the compensator gain so as to limit the control input.Simulation result shows that:The designed controller has smaller overshoot and shorter adjustment time, and the calculation amount of the controller design is reduced effectively.