航天器有限时间输出反馈姿态控制

电子与自动控制

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航天器有限时间输出反馈姿态控制

高岱¹, 吕建婷², 王本利¹

1. 哈尔滨工业大学卫星技术研究所, 黑龙江哈尔滨 150080;
2. 黑龙江大学数学科学学院, 黑龙江哈尔滨 150080

收稿日期:2011-11-17 修回日期:2012-01-16 出版日期:2012-11-25 发布日期:2012-11-22
通讯作者: 吕建婷 E-mail:lvjianting@gmail.com
基金资助:
黑龙江省教育厅科学技术研究项目(12511402)

Finite-time Output Feedback Attitude Control of Spacecraft

GAO Dai¹, LU Jianting², WANG Benli¹

1. Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150080, China;
2. School of Mathematical Sciences, Heilongjiang University, Harbin 150080, China

Received:2011-11-17 Revised:2012-01-16 Online:2012-11-25 Published:2012-11-22
Supported by:
Scientific Research Fund of Heilongjiang Provincial Education Department (12511402)

摘要/Abstract

摘要： 研究在角速度不可测时航天器的有限时间姿态控制问题。基于有限时间控制技术,提出了由修正Rodrigues参数进行姿态描述的航天器输出反馈姿态控制算法。首先设计了单个航天器的输出反馈姿态控制器,在没有角速度反馈时也能够保证航天器姿态在有限时间内调节到期望姿态。之后,设计了无需绝对角速度和相对角速度信息的多航天器分布式输出反馈姿态控制器。使用Lyapunov理论和图论,对闭环系统全局有限时间稳定性进行了严格的证明。最后对提出的控制算法进行了数值仿真,其结果验证了所设计的航天器输出反馈控制算法的可行性和有效性。

关键词: 航天器, 姿态控制, 有限时间控制, 输出反馈控制, 分布式控制

Abstract: This paper discusses the finite-time attitude control problem for spacecraft without angular velocity measurements. Based on the finite-time control technique, output feedback attitude control algorithms are proposed for spacecraft with attitudes represented by the modified Rodrigues parameter. First, an output feedback attitude controller of a single spacecraft is proposed, which guarantees the finite-time reachability of the given desired attitude of a rigid spacecraft without angular velocity feedback. Secondly, a distributed output feedback coordinated attitude controller for multiple spacecraft is proposed without the requirement of absolute angular velocities and relative angular velocities, which guarantees the coordinated attitude regulation in finite time. Rigorous proof is given by using the Lyapunov theory and graph theory. Finally, numerical simulation and verification are performed for the proposed control schemes. The results show that the proposed output feedback attitude control algorithms are feasible and effective.

Key words: spacecraft, attitude control, finite-time control, output feedback control, distributed control

中图分类号:

V448.2

高岱, 吕建婷, 王本利. 航天器有限时间输出反馈姿态控制[J]. 航空学报, 2012, 33(11): 2074-2081.

GAO Dai, LU Jianting, WANG Benli. Finite-time Output Feedback Attitude Control of Spacecraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(11): 2074-2081.

参考文献

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

航天器有限时间输出反馈姿态控制

Finite-time Output Feedback Attitude Control of Spacecraft

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