航空学报 > 2014, Vol. 35 Issue (7): 1999-2010   doi: 10.7527/S1000-6893.2013.0498

带末端碰撞角约束的三维联合偏置比例制导律设计

闫梁1, 赵继广2, 沈怀荣1, 李辕1   

  1. 1. 装备学院 航天装备系, 北京 101416;
    2. 装备学院 科研部, 北京 101416
  • 收稿日期:2013-09-21 修回日期:2013-12-19 出版日期:2014-07-25 发布日期:2013-12-25
  • 通讯作者: 闫梁,Tel.:010-66364196E-mail:yanliangbj@163.com E-mail:yanliangbj@163.com
  • 作者简介:闫梁男,博士研究生。主要研究方向:航天发射总体。Tel:010-66364196E-mail:yanliangbj@163.com;赵继广男,博士,教授,博士生导师。主要研究方向:航天发射总体。Tel:010-66364196E-mail:haofangshi@163.com
  • 基金资助:

    国家“863”计划

Three-dimensional United Biased Proportional Navigation Guidance Law for Interception of Targets with Angular Constraints

YAN Liang1, ZHAO Jiguang2, SHEN Huairong1, LI Yuan1   

  1. 1. Department of Spaceflight Equipment, Academy of Equipment, Beijing 101416, China;
    2. Department of Scientific Research, Academy of Equipment, Beijing 101416, China
  • Received:2013-09-21 Revised:2013-12-19 Online:2014-07-25 Published:2013-12-25
  • Contact: 10.7527/S1000-6893.2013.0498 E-mail:yanliangbj@163.com
  • Supported by:

    National High-tech Research and Development Program of China

摘要:

可拦截高/低速目标并带有末端碰撞角约束的制导律设计是研究难点,为此,设计一种三维联合偏置比例制导(UBPN)律。该制导律采用时变偏置角速率和时变比例系数,结合顺轨、逆轨拦截模式的优点,使用负比例系数拦截高速目标(顺轨模式),使用正比例系数拦截低速目标(逆轨模式)。给出偏置角速率的解析形式及时变比例系数的奇点解决方法,及二维约束碰撞角到三维约束碰撞角的具体实现过程。与比例制导律、负比例制导律、偏置比例制导律进行了对比验证,结果表明脱靶量、碰撞角误差均满足制导精度要求。

关键词: 导弹, 目标跟踪, 制导律, 联合偏置比例制导, 比例导引, 偏置比例导引, 碰撞角, 高速目标

Abstract:

It is a challenging task to design a guidance law which can intercept not only high-speed targets, but also low-speed targets with impact angle constraints. In this paper, a new guidance law called united biased proportional navigation (UBPN) is proposed. The guidance law uses time-varying rate bias and navigation ratio and incorporates the advantages of head-on and head-pursuit engagement. UBPN can intercept low-speed targets with positive time-varying navigation ratios, which is head-on engagement, as well as high-speed targets with negative time-varying navigation ratios, which is head-pursuit engagement. The precise time-varying bias and solution to the singularity in time-varying navigation ratio are given, and the solution of how to use a 2D impact angle to derive a 3D impact angle is presented. Finally, the simulation results compared with proportional navigation, retro-proportional navigation and bias proportional navigation guidance law are shown, which demonstrate that the miss distance and impact angle error of this guidance law can meet the requirements.

Key words: missiles, target tracking, guidance law, united biased proportional navigation, proportional navigation, biased proportional navigation, impact angle, high-speed targets

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