摘要
本文对运用速度增益制导实现对目标卫星的拦截方法进行了研究。其特点是在拦截器运动参数初值及目标轨道参数给定的条件下,首先确定考虑地球扁率J_2项影响下的拦截目标的预测命中点,然后采用Lambert方法确定给定碰撞时间下拦截器的需要速度,最后实现对目标的拦截。用该方法可保证向未制导转换时有较高精度的转换条件。
This paper is about the study of realization of the target satellite interception method with velocity gain guidance. The characteristics are the following: based on the given conditions of the interceptor's initial motion parameters and the target's trajectory parameters, firstly the predictive point of impact intercepting the target under the influence of J2 item of the earth oblatness is determined,then the interceptor's velocity required during the collision time using Lambert method is decided, at last, the target interception with velocity gain guidance method is realized. A transform condition with higher precision to the terminal guidance by using this method is guaranteed.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
1992年第2期72-77,共6页
Journal of National University of Defense Technology
关键词
拦截
弹道
速度增益制导
目标卫星
interception, trajectory, velocity gain guidance
