现代防御技术 ›› 2018, Vol. 46 ›› Issue (5): 39-45.DOI: 10.3969/j.issn.1009-086x.2018.05.07

• 导航、制导与控制 • 上一篇    下一篇

滑翔飞行器反逆轨拦截突防制导律研究

刘开封, 孟海东, 王长江, 李军营, 陈颖   

  1. 火箭军研究院 第六研究所,北京 100094
  • 收稿日期:2017-11-10 修回日期:2018-01-24 出版日期:2018-10-30 发布日期:2020-11-25
  • 作者简介:刘开封(1984-),男,湖北竹山人。助理研究员,博士,主要研究方向为飞行器飞行动力学及制导原理。通信地址:100094 北京海淀区北清路109号96901部队26分队

Anti-Head-on Interception Penetration Guidance Law for Slide Vehicle

LIU Kai-feng, MENG Hai-dong, WANG Chang-jiang, LI Jun-ying, CHEN Ying   

  1. The Sixth Research Institute of Academy of the Rocket Force,Beijing 100094,China
  • Received:2017-11-10 Revised:2018-01-24 Online:2018-10-30 Published:2020-11-25

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。

关键词: 高超声速, 滑翔飞行器, 反逆轨, 逃逸, 突防, 制导律

Abstract: 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.

Key words: hypersonic, slide vehicle, anti-head-on, escape, penetration, guidance law

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