北京航空航天大学学报 ›› 2017, Vol. 43 ›› Issue (8): 1693-1704.doi: 10.13700/j.bh.1001-5965.2016.0630

• 论文 • 上一篇    下一篇

考虑导弹自动驾驶仪动态特性的新型制导律

张凯1,2, 杨锁昌1, 张宽桥1, 张永伟1, 陈鹏1,3   

  1. 1. 军械工程学院导弹工程系, 石家庄 050003;
    2. 中国华阴兵器试验中心制导武器试验鉴定仿真技术重点实验室, 华阴 714200;
    3. 军械技术研究院, 石家庄 050003
  • 收稿日期:2016-07-27 修回日期:2016-11-08 出版日期:2017-08-20 发布日期:2017-08-29
  • 通讯作者: 杨锁昌 E-mail:yangsuochang_jx@sina.com
  • 作者简介:张凯,男,硕士研究生。主要研究方向:精确制导理论与技术;杨锁昌,男,博士,教授,博士生导师。主要研究方向:精确制导理论与技术;张宽桥,男,博士研究生。主要研究方向:精确制导理论与技术;张永伟,男,博士研究生。主要研究方向:弹箭智能化与信息化技术;陈鹏,男,博士,工程师。主要研究方向:弹箭智能化与信息化技术。
  • 基金资助:
    国家自然科学基金(61501493,51177174);武器装备军内科研项目(ZS2015070132A12012)

Novel guidance law accounting for dynamics of missile autopilot

ZHANG Kai1,2, YANG Suochang1, ZHANG Kuanqiao1, ZHANG Yongwei1, CHEN Peng1,3   

  1. 1. Department of Missile Engineering, Ordnance Engineering College, Shijiazhuang 050003, China;
    2. Key Laboratory of Guided Weapons Test and Evaluation Simulation Technology, China Huayin Ordnance Test Center, Huayin 714200, China;
    3. Ordnance Technology Research Institute, Shijiazhuang 050003, China
  • Received:2016-07-27 Revised:2016-11-08 Online:2017-08-20 Published:2017-08-29
  • Supported by:
    National Natural Science Foundation of China (61501493,51177174);Weapon and Equipment Military Science Projects (ZS2015070132A12012)

摘要: 针对拦截空中飞行目标需要满足零脱靶量和攻击角约束提高导弹制导性能等问题,首先,利用考虑噪声干扰的扩张状态观测器对目标加速度进行估计,其次,改进一种非奇异终端滑模面,将自动驾驶仪视为理想环节,然后,基于终端滑模控制理论和有限时间收敛理论推导一种滑模制导律,最后,考虑自动驾驶仪二阶动态特性,将得到的滑模制导律结合动态面控制法提出一种新型制导律。分别以不同的攻击角对机动飞行和匀速飞行的目标进行拦截,大量仿真表明,所提制导律具有良好的制导性能,能够保证导弹在零脱靶量击中目标的同时达到期望攻击角。

关键词: 自动驾驶仪, 攻击角约束, 制导律, 动态面控制, 非奇异终端滑模控制

Abstract: Interception of air targets requires zero miss-distance and impact angle constraint to improve the missile guidance performance. First, the acceleration of the target was estimated by extended disturbance observer which also considered the noise interference. Second, a nonsingular terminal sliding mode surface was improved, which considered autopilot ideally. Third, a sliding-mode guidance law was designed based on the terminal sliding mode control theory and the theory of finite time convergence. Finally, considering the second-order dynamic characteristics of autopilot, the novel guidance law was developed combining both sliding-mode guidance law and dynamic surface control method. In simulation experiments, both maneuvering targets and constant velocity targets were intercepted with different impact angle. A large number of simulation results demonstrate that the proposed guidance law canguarantee that the missile hits the target and at the same time achieves a desired angle of impact, which performs well.

Key words: autopilot, impact angle constraint, guidance law, dynamic surface control, nonsingular terminal sliding mode control

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