The variable structure control of spacecraft during spring-eject separation

Zhanxia Zhu; Wei Jin; Wei Zhang

doi:10.1109/ICMA.2009.5244894

The variable structure control of spacecraft during spring-eject separation

Zhanxia Zhu, Wei Jin, Wei Zhang

航天学院

Northwestern Polytechnical University Xian

科研成果: 书/报告/会议事项章节 › 会议稿件 › 同行评审

3 引用（Scopus）

摘要

This paper aims to the control problems of spacecraft when a small flyer separated from a main spacecraft in orbit. Firstly, the kinetic model is established and disturbance of spring-eject separation on the main spacecraft is analyzed. Secondly, we choose the variable structure control method to control the main spacecraft attitude because the whole system is complex nonlinear coupling system during separation. Concretely, we design sliding mode control law to solve this problem through choosing reasonable sliding surface and its update law. Finally, simulation results indicate the validity of the designed sliding mode control law.

源语言	英语
主期刊名	2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009
页	3900-3904
页数	5
DOI	https://doi.org/10.1109/ICMA.2009.5244894
出版状态	已出版 - 2009
活动	2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009 - Changchun, 中国期限: 9 8月 2009 → 12 8月 2009

出版系列

姓名	2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009

会议

会议	2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009
国家/地区	中国
市	Changchun
时期	9/08/09 → 12/08/09

访问文件

10.1109/ICMA.2009.5244894

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引用此

@inproceedings{45c9a0936e374286a90ea7a6411bfaa9,

title = "The variable structure control of spacecraft during spring-eject separation",

abstract = "This paper aims to the control problems of spacecraft when a small flyer separated from a main spacecraft in orbit. Firstly, the kinetic model is established and disturbance of spring-eject separation on the main spacecraft is analyzed. Secondly, we choose the variable structure control method to control the main spacecraft attitude because the whole system is complex nonlinear coupling system during separation. Concretely, we design sliding mode control law to solve this problem through choosing reasonable sliding surface and its update law. Finally, simulation results indicate the validity of the designed sliding mode control law.",

keywords = "Attitude control, Sliding mode, Spring-eject separation, Variable structure control",

author = "Zhanxia Zhu and Wei Jin and Wei Zhang",

year = "2009",

doi = "10.1109/ICMA.2009.5244894",

language = "英语",

isbn = "9781424426935",

series = "2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009",

pages = "3900--3904",

booktitle = "2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009",

note = "2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009 ; Conference date: 09-08-2009 Through 12-08-2009",

}

Zhu, Z, Jin, W & Zhang, W 2009, The variable structure control of spacecraft during spring-eject separation. 在 2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009., 5244894, 2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009, 页码 3900-3904, 2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009, Changchun, 中国, 9/08/09. https://doi.org/10.1109/ICMA.2009.5244894

The variable structure control of spacecraft during spring-eject separation. / Zhu, Zhanxia; Jin, Wei; Zhang, Wei.
2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009. 2009. 页码 3900-3904 5244894 (2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009).

科研成果: 书/报告/会议事项章节 › 会议稿件 › 同行评审

TY - GEN

T1 - The variable structure control of spacecraft during spring-eject separation

AU - Zhu, Zhanxia

AU - Jin, Wei

AU - Zhang, Wei

PY - 2009

Y1 - 2009

N2 - This paper aims to the control problems of spacecraft when a small flyer separated from a main spacecraft in orbit. Firstly, the kinetic model is established and disturbance of spring-eject separation on the main spacecraft is analyzed. Secondly, we choose the variable structure control method to control the main spacecraft attitude because the whole system is complex nonlinear coupling system during separation. Concretely, we design sliding mode control law to solve this problem through choosing reasonable sliding surface and its update law. Finally, simulation results indicate the validity of the designed sliding mode control law.

AB - This paper aims to the control problems of spacecraft when a small flyer separated from a main spacecraft in orbit. Firstly, the kinetic model is established and disturbance of spring-eject separation on the main spacecraft is analyzed. Secondly, we choose the variable structure control method to control the main spacecraft attitude because the whole system is complex nonlinear coupling system during separation. Concretely, we design sliding mode control law to solve this problem through choosing reasonable sliding surface and its update law. Finally, simulation results indicate the validity of the designed sliding mode control law.

KW - Attitude control

KW - Sliding mode

KW - Spring-eject separation

KW - Variable structure control

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U2 - 10.1109/ICMA.2009.5244894

DO - 10.1109/ICMA.2009.5244894

M3 - 会议稿件

AN - SCOPUS:77449159996

SN - 9781424426935

T3 - 2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009

SP - 3900

EP - 3904

BT - 2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009

T2 - 2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009

Y2 - 9 August 2009 through 12 August 2009

ER -

The variable structure control of spacecraft during spring-eject separation

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