采用捷联寻的和直接力控制的制导技术研究

Strapdown Homing Guided and Direct Force Control System Design for Low Altitude Interception Missile

以超低空拦截导弹为背景,提出了一种捷联寻的直接力控制的制导控制系统设计方法。根据直接力控制的导弹动力学特征,给出了导弹弹道倾角的实时估算方法,实现了捷联寻的拦截导弹的积分式比例导引。为达到精确控制的目的,基于冲量相等原则,提出了脉冲发动机的点火个数及点火角度的计算方法。仿真结果表明:提出的捷联寻的直接力控制的超低空拦截导弹的制导控制系统设计方法是正确可行的,系统控制精度较高,满足了武器系统反应快、成本低、精度高的要求。

A design method of strapdown homing guidance and direct force control system for low altitude interception missile was presented.An integral proportional navigation law for the missile was deduced by the estimated trajectory angle in real-time based on the kinetic features of the direct force control missile.In order to control the missile accurately,the calculating formulas of fire number and fire angle of impulse motors were deduced based on the principle of equaling impulse.The simulated results show that the design method is correct and feasible,the designed system can satisfy the requirements of the missile in respects of low cost,quick response and high accuracy.