高超声速飞行器线性变参数一体化式控制律设计

Linear Parameter-Varying Integrated Control Law Design for a Hypersonic Vehicle

针对高超声速飞行器的三维航迹控制问题,采用线性变参数(LPV)输出反馈控制和极点配置理论,基于高度-水平航迹控制概念,在马赫数包线内设计高超声速飞行器一体化式LPV控制律.该控制律不区分常规飞行控制律的内外控制回路,根据速度、高度、侧滑角和偏航角指令对飞行器纵向和横航向运动进行综合控制,在L_(2)诱导范数意义下实现飞行器三维航迹的鲁棒最优控制.在地心地固参考系内建立高超声速飞行器的数学模型,考虑地球自转、地球扁率、地球引力二阶简谐效应对飞行器运动特性的影响.通过数值仿真检验LPV控制律的控制性能,仿真结果表明:高超声速飞行器闭环系统具有D-稳定性,能够在典型机动中保持良好的航迹控制性能,并且在扰动和测量噪声下具有良好的鲁棒性.

A linear parameter-varying(LPV) integrated control law is designed for a hypersonic vehicle to achieve trajectory control based on an altitude-horizontal trajectory control concept. The LPV output-feedback control theory and pole placement techniques are employed to design parameters of the control law within a Mach number envelope. Such a control law performs integrated control for longitudinal and lateral-directional dynamics of the vehicle, free from the scheme of inner and outer control loops of classical flight controls and ensuring robust and optimal control performance in the sense of L_(2)-induced norm. A mathematical model of the hypersonic vehicle is developed in the Earth-centered-Earth-fixed reference frame. Earth rotation, Earth oblateness, and the second order harmonic perturbations of Earth are considered in the model. Numerical simulations are conducted to examine the performance of the LPV controller. The simulation results indicate that the closed-loop system of the hypersonic vehicle achieves D-stability. The LPV control law achieves a good performance in vehicle trajectory control and has sufficient robustness with respect to perturbations and sensor noise.