姿态脉冲控制技术在导弹设计中的应用与研究基于大气层内飞行目标姿态脉冲控制技术,设计利用姿态脉冲发动机产生的脉冲推力实现对导弹攻角的控制。采用相平面方法给出了不同飞行环境下脉冲发动机周期性点火的工作过程以及对导弹运动姿态的控制结果,推导出计算脉冲发动机数量的解析公式;同时对脉冲发动机快速建立攻角和周期性点火保持稳态攻角的两个工作阶段进行数值计算与仿真分析,实验结果表明该控制技术的可行性,为导弹姿态控制设计提出一种快速、高效的解决方法。

The research and application of pulse attitude control technology in missile design was based on the attitude pulse control technique of flight target within the atmosphere, and the design used pulse thrust generated by attitude pulse engine to control the attack angle of missile. The phase plane method was used to give the working process of the periodic ignition of pulse engine in different flight environments and the control results of missile motion attitude, and the analytical formula for calculating the number of pulse engine was derived. Meanwhile, the numerical calculation and simulation analysis were carried out on two stages of the pulse engine, which were establishing angle of attack quickly and keeping angle of attack steady in periodic ignition process. The experimental results show that the control technology is feasible, which provide a fast and efficient solution for the design of missile attitude control.