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

School of Astronautics

Northwestern Polytechnical University Xian

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

3 Scopus citations

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.

Original language	English
Title of host publication	2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009
Pages	3900-3904
Number of pages	5
DOIs	https://doi.org/10.1109/ICMA.2009.5244894
State	Published - 2009
Event	2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009 - Changchun, China Duration: 9 Aug 2009 → 12 Aug 2009

Publication series

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

Conference

Conference	2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009
Country/Territory	China
City	Changchun
Period	9/08/09 → 12/08/09

Keywords

Attitude control
Sliding mode
Spring-eject separation
Variable structure control

Access to Document

10.1109/ICMA.2009.5244894

Cite this

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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",

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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. in 2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009., 5244894, 2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009, pp. 3900-3904, 2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009, Changchun, China, 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. p. 3900-3904 5244894 (2009 IEEE International Conference on Mechatronics and Automation, ICMA 2009).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

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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DO - 10.1109/ICMA.2009.5244894

M3 - 会议稿件

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

SP - 3900

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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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Keywords

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