摘要
针对动能拦截器逆轨拦截情形,分析了高超声速滑翔飞行器利用空气动力机动突防的可能性,并从逃逸机动拦截范围的角度,根据动能拦截器助推分离时刻的状态参数推导了突防制导律。仿真结果表明,在动能拦截器初始拦截条件与理想拦截条件存在一定程度偏差时,推导的突防制导律能够有效逃逸机动拦截范围。
Aimed at head-on interception situation of kinetic kill vehicle,the possibility of penetration using aerodynamics for hypersonic slide vehicle is analyzed,and the penetration guidance law is deduced perspective from maneuver interception scale escape according to the parameters at boost separating time of kinetic kill vehicle. Simulation result shows that the guidance law takes effect to escape maneuver interception scale while there is deviation between real initial interception condition and realistic interception condition.
作者
刘开封
孟海东
王长江
李军营
陈颖
LIU Kai-feng;MENG Hai-dong;WANG Chang-jiang;LI Jun-ying;CHEN Ying(The Sixth Research Institute of Academy of the Rocket Force,Beijing 100094,China)
出处
《现代防御技术》
2018年第5期39-45,共7页
Modern Defence Technology
关键词
高超声速
滑翔飞行器
反逆轨
逃逸
突防
制导律
hypersonic
slide vehicle
anti-head-on
escape
penetration
guidance law
