| 考虑性能约束的航天器近距离悬停控制 |
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| 引用本文： | 张博翔,王理想,王辉,张彦鑫.考虑性能约束的航天器近距离悬停控制[J].南京气象学院学报,2021,13(1):93-101. |
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| 作者姓名： | 张博翔 王理想 王辉 张彦鑫 |
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| 作者单位： | 上海航天技术研究院 毫米波遥感技术重点实验室, 上海, 201109;哈尔滨工业大学 航天学院, 哈尔滨, 150001,哈尔滨工业大学 航天学院, 哈尔滨, 150001,上海航天技术研究院 毫米波遥感技术重点实验室, 上海, 201109,哈尔滨工业大学 航天学院, 哈尔滨, 150001 |
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| 基金项目： | 国家自然科学基金（61833009，11972130，61690212）；黑龙江省头雁计划（黑龙江省创新团队计划（2019）） |
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| 摘 要： | 本文主要研究了考虑预设性能的航天器交会对接中的近距离悬停控制问题.针对追踪航天器近距离悬停控制问题,首先基于追踪航天器的姿轨耦合模型设计了线性滑模控制器实现了近距离悬停任务.在此基础上,为对系统收敛过程中系统状态的暂态性能进行约束,设计了基于预设性能的滑模控制器.同时,为减少系统状态的收敛时间,针对预设性能中的性能函数,采用了一种有限时间收敛的性能函数代替传统的性能函数,并改进了滑模控制器的结构.最后通过仿真进行验证,并对比三种控制策略,结果表明所设计的航天器交会对接预设性能滑模控制律具有理想的控制性能.
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| 关 键 词： | 交会对接 姿轨耦合控制 滑模控制 预设性能控制 |
| 收稿时间： | 2020/11/2 0:00:00 |
Short-range hover control for spacecraft rendezvous and docking with prescribed performance |
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| ZHANG Boxiang,WANG Lixiang,WANG Hui and ZHANG Yanxin.Short-range hover control for spacecraft rendezvous and docking with prescribed performance[J].Journal of Nanjing Institute of Meteorology,2021,13(1):93-101. |
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| Authors: | ZHANG Boxiang WANG Lixiang WANG Hui and ZHANG Yanxin |
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| Institution: | Key Laboratory of Millimeter Wave Remote Sensing Technology, Shanghai Academy of Spaceflight Technology, Shanghai 201109;School of Astronautics, Harbin Institute of Technology, Harbin 150001,School of Astronautics, Harbin Institute of Technology, Harbin 150001,Key Laboratory of Millimeter Wave Remote Sensing Technology, Shanghai Academy of Spaceflight Technology, Shanghai 201109 and School of Astronautics, Harbin Institute of Technology, Harbin 150001 |
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| Abstract: | For the short-range hover control of tracking spacecraft during rendezvous and docking,a linear sliding mode control law is designed based on the coupled attitude and orbit dynamics.To constrain the system state during the system convergence,an attitude and orbit coupled controller is developed with prescribed performance.Furthermore,a new finite time convergence performance function is used in the design of prescribed performance control law,and the sliding mode controller is improved in structure,with the purpose to reduce the system state convergence time.Finally,simulations and comparisons are given to verify the effectiveness of the designed spacecraft control law. |
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| Keywords: | rendezvous and docking attitude and orbit coupled control sliding mode control prescribed performance control |
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