[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]
导弹与制导技术

基于终端角约束的动能拦截器滑模导引律设计

  • 聂闯 ,
  • 舒健生 ,
  • 孟少飞
展开
  • 第二炮兵工程大学,西安 710025

聂闯(1990-),男,辽宁沈阳人,硕士研究生,研究方向:飞行动力与制导。

收稿日期: 2014-10-29

  网络出版日期: 2025-05-28

Design of EKV Sliding Mode Guidance Law Based on Terminal Angle Limit

  • NIE Chuang ,
  • SHU Jiansheng ,
  • MENG Shaofei
Expand
  • The Second Artillery Engineering University, Xi'an 710025, China

Received date: 2014-10-29

  Online published: 2025-05-28

摘要

研究了一种带有终端角约束的导引方法。推导得到了视线坐标系下目标速度方向与视线转率的关系,建立了基于终端角约束的拦截模型,并进一步设计了基于拦截模型非线性的双环滑模导引率,同时合理选择了滑模趋近率。仿真结果表明了这种导引方法能有效减小攻击角,减小脫靶量,很好的实现顺轨或逆轨拦截的目的。

本文引用格式

聂闯 , 舒健生 , 孟少飞 . 基于终端角约束的动能拦截器滑模导引律设计[J]. 弹箭与制导学报, 2015 , 35(5) : 22 -24,29 . DOI: 10.15892/j.cnki.djzdxb.2015.05.006

Abstract

A guidance method based on terminal angle limit was researched. By deduction, the relationship between target velocity direction and LOS angle velocity was found in LOS coordinate system, and intercept model based on terminal angle limit was built. Furthermore, on the basis of model nonlinearity, the double ring sliding mode guidance law was designed and sliding mode approach rate was also chosen reasonably. The simulation result explained the effect of this method could reduce attack angle and target-missing quality, the aim of direct rail or reverse course interceptor effectively was targeted.

[an error occurred while processing this directive]

参考文献

[1]
马丹山, 王明海, 鲜勇, 等. 逆轨道拦截卫星轨道设计与优化[J]. 飞行力学, 2009. 27 (5): 63-65.
[2]
田源, 任章. 大气层外动能拦截器末段导引规律设计[J]. 宇航学报, 2009, 30 (2): 474-479.
[3]
杨洁, 王庆林, 李原. 滑模变结构控制研究综述[C]// 第13届中国控制会议论文集:B卷, 2012.
[4]
刘金琨, 孙富春. 滑模变结构控制理论及其算法研究与进展[J]. 控制理论与应用, 2007, 24 (3): 407-418.
[5]
罗生, 张文山, 王纪兵. 最优滑模制导律设计与仿真[J]. 航空兵器, 2012 (1): 34-37.
[6]
李广华. 近旁飞越航天器末制导方法研究[D].长沙: 国防科技大学, 2011.
文章导航

/

[an error occurred while processing this directive]