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针对高超声速飞行器包线范围广、参数变化大的控制需求,应用保护映射理论提出一种高超声速飞行器的自适应控制律设计方法。首先建立整个飞行包线内的线性变参数(LPV)模型,在参数变化边界点设计一个初始的控制结构和参数,然后基于保护映射理论分析初始控制结构使闭环系统稳定的参数范围,通过迭代自动获取整个包线内满足性能指标的控制参数,进而通过多项式拟合设计出高超声速飞行器自适应控制律。所提出的方法能够根据初始控制结构自动寻找一系列满足性能要求的控制器参数,并确定这些控制参数满足闭环系统稳定的设计范围。仿真结果表明,所设计的自适应控制律能够确保高超声速飞行器大包线的设计要求,实现闭环系统的鲁棒稳定。
Aiming at the control demand of hypersonic vehicle with a wide range of envelope and large parameter variation, an adaptive control law design method for hypersonic vehicle is proposed based on the theory of conservation mapping. Firstly, the linear variable parameter (LPV) model of the entire flight envelope is established. An initial control structure and parameters are designed at the boundary of the parameter variation. Based on the protection mapping theory, the initial control structure is used to analyze the parameter range of the closed-loop system. The control parameters satisfying the performance index are obtained in the whole envelope, and the hypersonic vehicle adaptive control law is designed by polynomial fitting. The proposed method can automatically find a series of controller parameters satisfying the performance requirements according to the initial control structure and determine that the control parameters satisfy the stable design range of the closed-loop system. The simulation results show that the designed adaptive control law can ensure the design requirements of the hypersonic aircraft large envelope and realize the robust stability of the closed-loop system.