导弹与制导技术

反导制导滤波技术研究

  • 张文山 ,
  • 王文 ,
  • 李铮 ,
  • 罗生 ,
  • 刘世前
展开
  • 1 上海交通大学航空航天学院,上海 200240
    2 中国空空导弹研究院,河南洛阳 471009

张文山(1974-),男,河南洛阳人,高级工程师,硕士,研究方向:导航制导与控制。

收稿日期: 2011-06-06

  网络出版日期: 2025-05-29

基金资助

航空基金

The Study on Filter Technologies of Anti-missile Guidance

  • ZHANG Wenshan ,
  • WANG Wen ,
  • LI Zheng ,
  • LUO Sheng ,
  • LIU Shiqian
Expand
  • 1 School of Aeronautics and Astronautics, Shanghai Jiaotong University, Shanghai 200240, China
    2 China Airborne Missile Academy, Henan Luoyang 471009, China

Received date: 2011-06-06

  Online published: 2025-05-29

摘要

为了实现对下落段速度大、螺旋机动的弹道导弹的有效拦截,反导导弹必须有针对性的进行制导滤波技术的研究。文中创新性的采用拉普拉斯变换方法进行4态滤波设计,对目标加速度、加速度一阶导、加速度二阶导同时进行在线估计,滤波结果与3态滤波结果比具有延迟小、精度高的特点;同时结合已有Weave制导律,通过和3态滤波+比例导引、3态滤波+最优导引进行对比,得出4态滤波+Weave导引具有脱靶量小的优点。

本文引用格式

张文山 , 王文 , 李铮 , 罗生 , 刘世前 . 反导制导滤波技术研究[J]. 弹箭与制导学报, 2012 , 32(2) : 19 -21,28 . DOI: 10.15892/j.cnki.djzdxb.2012.02.030

Abstract

For effective interception of ballistic missiles with large velocity and screw maneuverability in their falling course, focused research should be carried out on guidance filter techniques. In this paper, a novel Laplace transform was used to design a four-state filter and the target acceleration, first and second derivatives of acceleration were estimated. The results are more accurate with short latency compared with three-state filter estimation. Meantime, combined with the given Weave guidance law, the four-state filter with weave guidance law is proved to have advantages in smaller miss distance compared with the three-state filter with proportional guidance law and three-state filter with optimal guidance law.

参考文献

[1]
Golan O M, Shima T. Head pursuit guidance for hypervelocity interception[M]. : , 2004.
[2]
O Golan, T Shima. Precursor interceptor guidance using sliding mode approach[M]. : , 2005.
[3]
侯明善. 适用于大离轴角度发射的非线性最优制导律[J]. 航空兵器, 1999 (3): 9- 12.
[4]
周荻, 邹昕光, 孙德波. 导弹机动突防滑模制导律[J]. 宇航学报, 2006 27 (2): 213- 216.
[5]
赵振昊. 基于变结构控制的前向拦截导引方法[J]. 宇航学报, 2007 28 (4): 835- 839.
[6]
Kliger I. A simple derivation of certain optimal control laws[M]. Bedford, MA: Raytheon, 1980.
[7]
P Zarchan. Tactical and strategic missile guidance[M]. 4th ed Virginia: American Institute of Aeronautics and Astronautics Inc., 2002.
[8]
Kuo CY, Chiou Y C. Geometric analysis of missile guidance command[J]. IEE Proceedings: Control Theory and Applications, 2000 147 (2): 205- 211.
文章导航

/