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采用反作用喷气控制系统(RCS)对内装式空中发射运载火箭箭机分离阶段实施姿态控制的方案进行了研究。根据不同发射条件下的箭机分离运动,确定了RCS启控时运载火箭的飞行状态,设计了发动机点火前的运载火箭俯仰运动程序。在此基础上,给定标准弹道方案,并确定了RCS推力器组合方案。采用脉冲调宽调频(PWPF)调制方法,设计出适合于RCS推力器开关控制的控制器,通过仿真分析了运载火箭初始弹道飞行对RCS控制能力的需求。
The scheme of attitude control in the separation stage of the built-in airborne launch vehicle rocket motor was studied with the reaction jet control system (RCS). According to the separation of the arrow movement under different launching conditions, the flight status of the launch vehicle during RCS activation and control was determined, and the launch vehicle pitching motion program before the ignition of the engine was designed. On this basis, given the standard trajectory program, and determine the RCS thruster combination program. The pulse width modulated frequency modulation (PWPF) modulation method is used to design the controller which is suitable for the RCS thruster switch control. The simulation analysis of the initial launch of the rocket launcher for RCS control capability needs.