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论文:2020,Vol:38,Issue(6):1257-1265 |
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引用本文： |
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郭正玉, 王超磊, 钱航, 韩治国, 张婧娴. 带有攻击角约束的大机动目标协同攻击制导律[J]. 西北工业大学学报 |
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GUO Zhengyu, WANG Chaolei, QIAN Hang, HAN Zhiguo, ZHANG Jingxian. Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint[J]. Northwestern polytechnical university |
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| 带有攻击角约束的大机动目标协同攻击制导律 |
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| 郭正玉1,2, 王超磊1, 钱航3, 韩治国4, 张婧娴4 |
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1. 中国空空导弹研究院, 河南 洛阳 471009;
2. 航空制导武器航空科技重点实验室, 河南 洛阳 471009;
3. 北京宇航系统工程研究所, 北京 100076;
4. 西北工业大学 航天学院, 陕西 西安 710072 |
| 摘要: |
| 针对三维空间内多枚空空导弹协同攻击高速大机动目标末制导问题，提出了一种分布式有限时间协同制导律设计方法。视线方向加速度根据有限时间一致性理论设计了基于积分滑模面的自适应制导律，保证了在末制导过程所有导弹能够同时达到目标；视线纵向和视线侧向的加速度均采用基于快速终端滑模面的制导律，同时对末端攻击角进行约束，使得末端攻击角能够在有限时间达到期望值。仿真算例验证了所提出的制导律能够实现对机动目标的协同攻击。 |
| 关键词:
三维空间
协同制导
机动目标
攻击角约束
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| Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint |
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| GUO Zhengyu1,2, WANG Chaolei1, QIAN Hang3, HAN Zhiguo4, ZHANG Jingxian4 |
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1. China Airborne Missile Academy, Luoyang 471009, China;
2. Aviation Key Laboratory of Science and Technology on Airborne Guided Weapons, Luoyang 471009, China;
3. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China;
4. School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| A distributed multi-missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three-dimensional multi-missiles cooperative interception of large maneuvering target. According to the finite time consistency theory, an adaptive guidance law based on the integral sliding mode is designed to ensure that all missiles can reach the target at the same time in the terminal guidance process. The longitudinal and lateral acceleration of the line of sight are based on the guidance law of the fast terminal sliding mode surface. The terminal attack angle is constrained, so that the terminal attack Angle can reach the expected value in finite time. The simulation results show that the designed guidance law can achieve the cooperative attack on the maneuvering targets. |
| Key words:
three-dimension
coordination guidance
maneuvering target
impact angle constraint
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| 收稿日期: 2020-05-14
修回日期:
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| DOI: 10.1051/jnwpu/20203861257 |
| 基金项目: 航空科学基金项目（20180153002）资助 |
| 通讯作者:
Email： |
| 作者简介: 郭正玉(1982-),中国空空导弹研究院高级工程师,主要从事空空导弹总体设计和制导控制技术研究。
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