高超声速飞行器再入段RCS姿态控制

摘要

为满足反作用控制系统(reaction control system，RCS)姿态控制需求，对高超声速飞行器再入段的姿态控制进行研究。以X-34的RCS系统为对象，建立了RCS的数字模型，设计了RCS姿态控制率与PWPE脉冲调制器，利用非线性描述函数法分析姿态控制系统的稳定性，并通过 Matlab 仿真验证了所设计的 RCS 姿态控制系统性能。仿真结果表明：该PWPF脉冲调制可以满足RCS姿态控制的需要，同时与传统的PWM脉冲调制相比，可以较大地降低RCS消耗的流量与开启次数，可为高超声速飞行器再入段RCS姿态控制系统设计提供参考。%In order to meet the attitude control requirement of reaction control system (RCS), research on attitude control of reaction control system for hypersonic vehicle. Taking the RCS of X-34 as object, establish RCS mathematical model, design RCS attitude control rate and PWPE pulse modulator. Analysis the stabilization of RCS attitude control system using nonlinearity describing function method, and validate RCS attitude control performance through Matlab. The simulation results show that the PWPF modulator not only can meet RCS attitude control’s requirement, but also can reduce RCS flow consumption and jet times compared with traditional PWM pulse modulation. The method can offer reference for attitude control of reaction control system for hypersonic vehicle.