| 引用本文: | 尤浩,常新龙,赵久奋,等.带落角约束的新型领弹-从弹固定时间协同制导律.[J].国防科技大学学报,2024,46(6):64-76.[点击复制] |
| YOU Hao,CHANG Xinlong,ZHAO Jiufen,et al.Novel leader-following missiles fixed-time cooperative guidance law with impact angle constraints[J].Journal of National University of Defense Technology,2024,46(6):64-76[点击复制] |
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| 带落角约束的新型领弹-从弹固定时间协同制导律 |
| 尤浩,常新龙,赵久奋,马峰 |
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(火箭军工程大学 导弹工程学院, 陕西 西安 710025)
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| 摘要: |
| 针对多导弹以期望角度协同攻击机动目标问题,提出了一种新型领弹-从弹固定时间协同制导律。根据弹目相对运动关系建立了领弹-从弹协同制导模型；基于固定时间滑模控制理论设计了视线法向上的制导律,实现了领弹和从弹以期望的攻击角度对机动目标进行精准打击。在从弹视线方向上,基于一致性误差函数和固定时间滑模趋近律,设计了一种从弹视线方向制导律,充分利用了导弹间的信息交互,实现了从弹与领弹的剩余时间在固定时间内快速趋于一致。数值仿真和对比试验结果表明:所提制导律对时间协同和角度约束的控制精度高,避免了奇异和抖振现象,收敛速度快且收敛时间上界与初始状态无关,充分地验证了所提制导律的有效性和优越性。 |
| 关键词: 落角约束 领弹-从弹 固定时间 滑模控制 信息交互 机动目标 一致性误差函数 |
| DOI：10.11887/j.cn.202406007 |
| 投稿日期：2022-06-30 |
| 基金项目:国家自然科学基金资助项目(12171481) |
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| Novel leader-following missiles fixed-time cooperative guidance law with impact angle constraints |
| YOU Hao, CHANG Xinlong, ZHAO Jiufen, MA Feng |
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(College of Missile Engineering, Rocket Force University of Engineering, Xi′an 710025, China)
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| Abstract: |
| To deal with the problem that multiple missiles cooperatively attack maneuvering targets with impact angle constraints, a novel leader-following missiles fixed-time cooperative guidance law was proposed. The leader-following missiles cooperative guidance model was established according to the relative motion between the target and missiles. Based on the fixed-time sliding mode control theory, the guidance law in the directions normal to the LOS(line-of-sight) was designed, so that the leader and followers could accurately attack the maneuvering target from the desired impact angles. Based on the consistency error function and the fixed-time sliding mode reaching law, the guidance law in the LOS direction of the followers was designed, which fully utilized the information exchange between missiles, and the time-to-go of the followers could quickly achieve consensus with that of the leaders in fixed time. Simulations and comparison verification indicate that the designed guidance law has higher control accuracy for time and angle constraints, no singularity and chattering phenomenon, faster convergence speed and the convergence time bound is independent of the initial states, which fully verifies the effectiveness and superiority of the proposed guidance law. |
| Keywords: impact angle constraint leader-following missiles fixed time sliding mode control information exchange maneuvering targets consistency error function |
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