摘要
为减小由弹上计算机的速度限制和制导方法误差导致的弹头落点偏差,研究了一种用小推力发动机在主发动机关机后沿空间某方向工作一定时间以减小误差的方法。根据椭圆弹道条件下推力的作用,给出了小推力发动机的工作方向和时间的计算模型。仿真计算结果表明:该法可有效减小导弹的落点偏差。
To reduce the landing error caused by capacity limitation of the missile s computer and the guidance method error,a method that a little thruster worked with a given direction and given time after the main engine of ballistic missile shut down was put forward in this paper.The algorithm of the operation direction and time for the little thruster was given out based on the thruster in a elliptical trajectory.The computation result showed that this method could decrease the landing error of ballistic missile.
出处
《上海航天》
北大核心
2008年第3期16-18,22,共4页
Aerospace Shanghai
关键词
弹道导弹
制导
落点偏差
末速修正
小推力发动机
Ballistic missile
Guidance
Landing error
Terminal velocity correction
Little thruster
