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弹箭与制导学报 >

2014 , Vol. 34 >Issue 3: 25 - 28

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2014.03.036

导弹与制导技术

滑翔弹头末段俯冲导引律设计与仿真

  • 刘开封 ,
  • 陈颖 ,
  • 梁立威 ,
  • 孟海东
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  • 1 第二炮兵工程大学, 西安 710025
    2 第二炮兵装备研究院, 北京 100085

刘开封(1984-),男,湖北竹山人,助理工程师,博士研究生,研究方向:飞行器飞行动力学及制导。

收稿日期: 2013-06-01

  网络出版日期: 2025-05-30

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Design and Simulation of Diving Guidance Law for Terminal Phase Trajectory of Glide-warhead

  • LIU Kaifeng ,
  • CHEN Ying ,
  • LIANG Liwei ,
  • MENG Haidong
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  • 1 The Second Artillery Engineering University, Xi'an 710025, China
    2 The Second Artillery Equipment Academy, Beijing 100085, China

Received date: 2013-06-01

  Online published: 2025-05-30

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摘要

滑翔弹头长期飞行在气动环境较为复杂的临近空间,再入精度难以保证。为实现滑翔弹头精确打击并考虑攻击角度的战术使用需求,文中在目标坐标系中建立了滑翔弹头质心运动方程,推导了基于扩展比例导引的带落速方向控制的末段俯冲导引规律。仿真结果表明,在合理的俯冲起点参数要求范围内,采用文中制导规律,能够实现对落点和攻击角度的精确控制。

关键词： 滑翔弹头; 俯冲; 扩展比例导引; 落速方向控制

本文引用格式

刘开封 , 陈颖 , 梁立威 , 孟海东 . 滑翔弹头末段俯冲导引律设计与仿真[J]. 弹箭与制导学报, 2014 , 34(3) : 25 -28 . DOI: 10.15892/j.cnki.djzdxb.2014.03.036

Abstract

Glide-warhead long flies in near space where aerodynamic environment is complicated, so the entry precision can not be guaranteed. In order to realize accurate attack and considering the demand for attack angle control, the motion equation of glide warhead at terminal phase was built in target coordinates, the dive guidance law based on expanded proportion guidance with terminal-velocity direction control was derived. Simulation results show that when parameters at the dive beginning point are reasonable, method in this paper performs efficiently to control the precision of attack angle.

Key words： glide-warhead; dive; expanded proportion guidance; terminal-velocity direction control

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参考文献

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