旋转弹头直接力姿态控制研究

Research on Attitude Control of Rotating Warhead Under Direct Force

以某旋转导弹弹头为研究对象,脉冲姿控发动机安装于弹头尾部,呈"×"字型排列。姿控发动机所产生的直接力经脉冲宽度调制后作用于旋转弹头,忽略空气动力对旋转弹头的影响,只考虑直接力对弹头的影响。分析了旋转导弹控制力产生的原理,推导和建立了直接力作用下旋转导弹单通道控制的弹体动力学模型和运动学模型。并进行了动态分析,同时设计了旋转弹头姿态稳定控制系统,仿真结果表明,针对旋转弹头单通道控制提出相应的PID控制器,能满足控制系统对稳定性和快速性的要求,并为旋转弹头大回路仿真分析提供了理论依据。

This paper takes a rotating missile warheads as the object of study.and the pulse attitude control engine is installed in the tail of the warhead.The direct force generated by the attitude control engine is modulated by the pulse width.The influence of the aerodynamic force on the rotating warhead is ignored,and only considering the effect of direct force on rotating warhead.In this paper,the process of the control force generation of the missile is analyzed.