带矢量喷管的高超声速飞行器的跟踪控制

基于跟踪控制理论，本文研究了具有矢量喷管的吸气式高超声速飞行器的控制问题．首先本文建立了基于矢量喷管的吸气式高超声速飞行器的动力学模型．该模型表现为矢量喷管推力对飞行器纵向力矩的作用很大，而对速度的影响很小．在相同的控制参数下，本文给出了飞行器的三种不同的跟踪控制模式．基于极点配置和Youla参数化方法设计切换的跟踪控制律，实现了不同控制模式之间的平滑切换，并且保证切换过程中闭环系统的稳定性．最后，通过对仿真结果的分析验证了矢量喷管技术在吸气式高超声速飞行器控制中的优势，并且指出多种控制方式协调配合对高超声速飞行器的姿态控制具有重要意义．

Tracking control for a hypersonic air-breathing vehicle with thrust vectoring nozzles

Based on the tracking control theory, this paper investigates the control problems of hypersonic air-breathing vehicle with thrust vectoring nozzles. First of all, dynamic model of hypersonic air-breathing vehicle with thrust vectoring nozzles is constructed. And the thrust vectoring nozzles have significant contribution on longitudinal torque, whereas, they have little effect on speed in this model. For the same control parameters, three different tracking control modes are given in detail. The tracking control laws with the switch are designed by means of the pole placement and Youla parameters, which can ensure smooth transition between different control modes, and the stability of closed-loop system. Numerical results show that the thrust vectoring nozzles have certain advantages in the control of hypersonic vehicle. And it is concluded that it is of significance for the attitude control of hypersonic air-breathing vehicle to coordinate many kinds of control modes.