大气层外拦截弹中段耗尽关机制导律  

A Midcourse Guidance Law for an Exo-Atmospheric Interceptor with Fuel Exhaustion Shutoff Motor

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,湖南长沙410073

出　　处：《飞行力学》2005年第1期54-57,共4页Flight Dynamics

摘　　要：针对采用燃料耗尽方式关机且具有持续定常推力的大气层外拦截弹设计了中段制导律。假设拦截弹在关机后的无控滑行段中与目标相对距离不大,拦截弹与目标的引力加速度差近似为零,则拦截弹中制导的终端约束条件为视线转率为零。根据终端约束推导了推力定向解析表达式,分析了推力定向计算过程中存在的问题,并做了相应的改进。仿真表明,这种制导律具有计算简单、计算无奇异的特点,且在拦截近程弹道导弹时精度较高且鲁棒性好。A midcourse guidance law for an exo-atmospheric interceptor with constant sustaining thrust shut-off by fuel exhaustion is proposed. Suppose that the relative distance between the interceptor and the target is not great during the coast phase of the interceptor after burnout, and the gravitational difference between the two is nearly zero, then the terminal restriction of the midcourse guidance is that the line-of-sight rate is zero. The analytical solution of the direction of the thrust is deduced according to the restriction, the oddity when calculating the direction is analyzed and the corresponding improvement is made. Simulations have shown that the guidance is simple with no computational oddity, and when applied to short range ballistic missile interception, perfect accuracy and robustness could be expected.

关 键 词：大气层外拦截弹 耗尽关机 中制导律 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] TJ761.7