基于拦截点的大气层外拦截弹中制导  

Midcourse Guidance Based on the Interception Point for Exoatmospheric Interceptor

作　　者：刘世勇[1] 吴瑞林[1] 周伯昭[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《航天控制》2005年第2期54-58,共5页Aerospace Control

摘　　要：针对拦截点给定的情况讨论了大气层外拦截弹中制导律的设计。证明显式制导的最优性,推导出常值引力场与平方反比引力场假设下拦截弹需要速度的表达式,分析了采用显式制导时推力方向在邻近关机时变化剧烈的原因,并通过构造需要速度的虚拟映射进行了改进。仿真表明,采用改进的显式制导,发动机工作时间有所增加,但邻近关机时推力方向平稳。The design of midcourse guidance law for an exo-atmospheric interceptor with known interception point is discussed. The optimality of the explicit guidance is proved, then the expression of the required velocity of the interceptor under constant gravitation model and square inverse gravitation model is deduced. Rapid change of direction of the thrust near shutoff is analyzed, and improvement is gained by introducing a virtual mapping of the required velocity. Simulations show that using the improved explicit guidance, the working time of the engine is increased while the direction of the thrust near shutoff keeps stable.

关 键 词：大气层外拦截弹 拦截点 中程制导 

分 类 号：TJ761.7[兵器科学与技术—武器系统与运用工程] V448.232[航空宇航科学与技术—飞行器设计]