[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

带落角约束的非奇异变结构导引律设计

  • 尹高扬 ,
  • 周绍磊 ,
  • 薛于廷
展开
  • 海军航空工程学院,山东烟台 264001

尹高扬(1987-),男,湖南湘潭人,硕士研究生,研究方向:导航、制导与控制。

收稿日期: 2011-01-12

  网络出版日期: 2025-05-30

The Design of Nonsingular Variable Structure GuidanceLaw with Falling Angle Constraint

  • YIN Gaoyang ,
  • ZHOU Shaolei ,
  • XUE Yuting
Expand
  • Naval Aeronautical and Astronautical University, Shandong Yantai 264001, China

Received date: 2011-01-12

  Online published: 2025-05-30

摘要

基于变结构控制理论,针对反舰导弹打击水面机动目标的导引问题,设计了非奇异变结构导引律。基于零化相对航向误差角的导引律适用于任意初始导弹弹道角和目标航向角,文中选择了相对航向误差角作为导引律设计中将要被控制到零的输出,同时把命中落角作为系统的终端约束条件。仿真结果证明,在导弹任意初始航向角下,采用所设计的带落角约束的非奇异变结构导引律均能够满足脱靶量和落角约束要求。

本文引用格式

尹高扬 , 周绍磊 , 薛于廷 . 带落角约束的非奇异变结构导引律设计[J]. 弹箭与制导学报, 2011 , 31(6) : 62 -65 . DOI: 10.15892/j.cnki.djzdxb.2011.06.042

Abstract

A nonsingular variable structure guidance law for anti-ship missile against maneuvering warship was designed based on variable structure control theory. The guidance law based on the so-called relative heading error angle between the relative velocity vector and the line of sight that to be controlled to zero was suitable for random original line throwing and target heading angle, the so-called relative heading error angle between the relative velocity vector and the line of sight was chosen as the output to be controlled to zero. Meanwhile, the falling angle constraint was chosen to be terminal constraint condition in this article. Simulation results show that the miss distance and the falling angle constraint are well satisfied by using the designed guidance law in any original heading angle.

[an error occurred while processing this directive]

参考文献

[1]
Gerard L A nonlinear Inverse Approach[J]. Journal of Guidance, Control, and Dynamics, 1998, 21(5):742-746.
[2]
Ha JJ, Chong S Design of a CLOS guidance law via feedback linearization[J]. IEEE Transaction on Aerospace and Elec-tronic System, 1992,28(1):51-62.
[3]
Bezick S, Rusnak I, Gray W S Guidance of a homing missile via nonlinear geometric control methods[J]. Journal of Guid-ance, Control, and Dynamics, 1995, 18(3):441-448.
[4]
余文学, 周凤岐, 周军 非线性变结构制导律[J]. 宇航学报,2003,24(6):638-641.
[5]
林嘉新, 赵永涛, 胡云安 基于零化相对速度偏角的变结构末制导律设计[J]. 海军航空工程学院学报,2009,24(6):646-650.
文章导航

/

[an error occurred while processing this directive]