北京航空航天大学学报 ›› 2015, Vol. 41 ›› Issue (2): 343-350.doi: 10.13700/j.bh.1001-5965.2014.0127

• 论文 • 上一篇    下一篇

基于扩张状态观测器的导弹滑模制导律

张尧, 郭杰, 唐胜景, 马悦悦, 商巍   

  1. 北京理工大学 宇航学院, 飞行器动力学与控制教育部重点实验室, 北京 100081
  • 收稿日期:2014-03-17 出版日期:2015-02-20 发布日期:2015-03-12
  • 通讯作者: 郭杰(1981—), 男, 陕西渭南人, 讲师, guojie1981@bit.edu.cn, 主要研究方向为飞行动力学与控制. E-mail:guojie1981@bit.edu.cn
  • 作者简介:张尧(1991—), 男, 陕西西安人, 硕士生, 2220130035@bit.edu.cn
  • 基金资助:

    国家自然科学基金资助项目(11202024); 航空科学基金资助项目(2012ZA720002)

Missile sliding mode guidance law based on extended state observer

ZHANG Yao, GUO Jie, TANG Shengjing, MA Yueyue, SHANG Wei   

  1. Key Laboratory of Dynamics and Control of Flight Vehicle of Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
  • Received:2014-03-17 Online:2015-02-20 Published:2015-03-12

摘要:

针对导弹拦截机动目标的问题,基于扩张状态观测器(ESO,Extended State Observer)设计了一种全新的导弹滑模制导律.考虑拦截时的弹目相对运动关系,通过ESO对目标加速度进行实时的观测和动态补偿,有效地解决了导弹拦截末端所需过载过大的问题,使导弹能够以更小的脱靶量拦截目标.同时在仿真中考虑自动驾驶仪的二阶动态特性,分别以不同的初始航迹角对周期性机动目标和非周期性机动目标进行拦截打击仿真,并与基于有限时间收敛理论提出的滑模制导律对迎击拦截、追击拦截和前向拦截3种方式进行仿真对比,仿真结果表明了基于ESO的滑模制导律在拦截末制导过程中的鲁棒性和优越性.

关键词: 扩张状态观测器, 滑模控制, 观测, 有限时间收敛, 导弹制导, 拦截

Abstract:

Based on the technology of extended state observer (ESO), a novel missile sliding mode guidance law was derived to intercept maneuvering target. According to relative movement between missile and target in the process of interception, the difficult question was effectively settled that too large overload was required during terminal intercepting phase, which was addressed by currently estimating and dynamically compensating to target acceleration via ESO. Thus, the goal of precision against target was achieved. Moreover, accounting for the autopilot as second-order dynamics in simulation, three simulation experiments of different interception strategies, which included head-on interception, tail-chase interception and head-pursuit interception, were investigated in the two kinds of cases of intercepting periodic maneuvering target and aperiodic maneuvering target. Compared with sliding mode guidance law based on finite time convergence, the results show the strong robustness and validities of the proposed sliding mode guidance law based on ESO in the terminal interception guidance.

Key words: extended state observer, sliding mode control, observation, finite time convergence, missile guidance, interception

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