摘要
针对当前弹道导弹采用单一制导方式带来的制导精度不高的现状,提出了利用激光导引头进行末制导的方案。以最优控制理论和飞行力学原理为基础,考虑导弹速度大小和方向变化,推导了适应弹道导弹末制导段的导引律。提出了实现该制导律必须满足的几个条件,对激光导引头进行了初步建模研究。为后续设计提供了理论基础。
The ballistic missile adopts the single guidance style that results the low accuracy.This paper presents a pro- ject that the missile terminal guidance is introduced through using the laser seeker.Based on the optimal control theory and the flighting dynamic principle the guidance law is derivated which takes into account the velocity and its direction of missile.The factors to realize this guidance law are presented.The models of this laser seeker are built.This paper can provide a reference for the future design.
出处
《弹箭与制导学报》
CSCD
北大核心
2005年第S2期302-305,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
激光导引头
弹道导弹
末制导
制导律
laser seeker
ballistic missile
terminal guidance
guidance law
