摘要
基于理想二体下的弹道方程解析式和Taylor线性化方法,忽略重力在拦截末段对拦截器和目标运动状态的影响,推导了空间拦截初始制导偏差与零控脱靶量之间的近似计算公式.测试结果表明该近似算法得到的零控脱靶量与真实值比较接近,在较小初始偏差条件下,简化的近似计算公式能给出满意的结果,所得零控脱靶量可用于空间动能拦截制导系统的初步设计与分析.
Based on the trajectory equation for restricted two-body problem and Taylor series linearization method, the approximate function between the initial guidance errors and the end zero effort miss vector was proposed for space interception by neglecting the effect of gravity on motion state of interceptor and target. Experimental results show that the zero effort miss vector calculated by using approximate formulas is close to the real miss vector. Under the conditions of small initial errors, the satisfied results can be obtained by approximate function. The zero effort miss vector obtained can be used for the preliminary design and analysis of kinetic interceptor guidance.
出处
《弹道学报》
EI
CSCD
北大核心
2007年第3期62-64,72,共4页
Journal of Ballistics
关键词
弹道方程
初始偏差
动能拦截
零控脱靶量
trajectory equations
initial errors
kinetic interception
zero effort miss vector
作者简介
周须峰（1976-），男，博士生，研究方向为飞行器动力学控制．
