滑翔式高超声速飞行器大包线状态反馈控制

State Feedback Control for Gliding Hypersonic Vehicle in Wide Flight Envelope

研究了基于状态反馈的滑翔式高超声速飞行器控制系统设计方法。首先建立了滑翔式高超声速飞行器的动力学模型并对其耦合特性进行了分析,然后考虑到该飞行器再入过程中存在的扰动、参数大范围变化和强耦合情况,针对一类抗扰动鲁棒控制系统,在采用伺服补偿器和基于特征根配置设计的镇定补偿器的基础上,引入状态反馈解耦控制器实现输入输出的近似解耦,得到了一种改进的控制系统结构,设计了滑翔式高超声速飞行器的控制系统。最后,通过定点仿真、参数拉偏仿真及大包线全轨迹飞行仿真,对控制系统的性能进行了检验,校验了控制系统设计方法的有效性。

A state feedback-based method is proposed tor design a gliding hypersonic vehicle control system. After establishing the dynamics model tor the gliding hypersonic vehicle, the features of its strong coupling is analyzed. Then, an improved gliding hypersonic vehicle control system is eonsidered for solving the problems such as external disturbance, wide parameter variation range and strong coupling during the reentry of the gliding hypersonic vehicle. The robust control system composed of servo compensator and pole assignment-based stable compensator is improved by adding a state teedback-based decoupled structure to approximately decouple inputs and outputs of the gliding hypersonic vehicle. Simulation results of tracking attitude angle commands after random variation of parameters and trajectory commands in wide flight enveh）pe validate the control ability of/he control system, also demonstrate the validity of the design method for the control system of gliding hypersonic vehicle.