Terminal sliding mode attitude control for satellite

Guangfu Ma; Yueyong Lv; Qinglei Hu; Chuanjiang Li

doi:10.1109/WCICA.2010.5553962

Terminal sliding mode attitude control for satellite

Guangfu Ma^*
, Yueyong Lv
, Qinglei Hu
, Chuanjiang Li

^*Corresponding author for this work

Harbin Institute of Technology

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

2 Scopus citations

Abstract

A finite time control method based on terminal sliding mode (TSM) is presented for satellite attitude control system in this paper. Using the concepts of finite time stability and TSM, a finite time stable sliding mode is designed, and then a continuous TSM finite time controller using the inverse dynamic method is designed for the second-order dynamic system of the satellite. In order to eliminate the oscillation, a new type of saturation function is also designed to replace the conventional symbolic function. The validity for the proposed algorithm is testified through simulations.

Original language	English
Title of host publication	2010 8th World Congress on Intelligent Control and Automation, WCICA 2010
Pages	3372-3376
Number of pages	5
DOIs	https://doi.org/10.1109/WCICA.2010.5553962
State	Published - 2010
Externally published	Yes
Event	2010 8th World Congress on Intelligent Control and Automation, WCICA 2010 - Jinan, China Duration: 7 Jul 2010 → 9 Jul 2010

Publication series

Name	Proceedings of the World Congress on Intelligent Control and Automation (WCICA)

Conference

Conference	2010 8th World Congress on Intelligent Control and Automation, WCICA 2010
Country/Territory	China
City	Jinan
Period	7/07/10 → 9/07/10

Keywords

Attitude control
Finite time
Terminal sliding mode

Access to Document

10.1109/WCICA.2010.5553962

Cite this

@inproceedings{5a91af1a609f4a8e8a4b31bf991c3ab1,

title = "Terminal sliding mode attitude control for satellite",

abstract = "A finite time control method based on terminal sliding mode (TSM) is presented for satellite attitude control system in this paper. Using the concepts of finite time stability and TSM, a finite time stable sliding mode is designed, and then a continuous TSM finite time controller using the inverse dynamic method is designed for the second-order dynamic system of the satellite. In order to eliminate the oscillation, a new type of saturation function is also designed to replace the conventional symbolic function. The validity for the proposed algorithm is testified through simulations.",

keywords = "Attitude control, Finite time, Terminal sliding mode",

author = "Guangfu Ma and Yueyong Lv and Qinglei Hu and Chuanjiang Li",

year = "2010",

doi = "10.1109/WCICA.2010.5553962",

language = "英语",

isbn = "9781424467129",

series = "Proceedings of the World Congress on Intelligent Control and Automation (WCICA)",

pages = "3372--3376",

booktitle = "2010 8th World Congress on Intelligent Control and Automation, WCICA 2010",

note = "2010 8th World Congress on Intelligent Control and Automation, WCICA 2010 ; Conference date: 07-07-2010 Through 09-07-2010",

}

Ma, G, Lv, Y, Hu, Q & Li, C 2010, Terminal sliding mode attitude control for satellite. in 2010 8th World Congress on Intelligent Control and Automation, WCICA 2010., 5553962, Proceedings of the World Congress on Intelligent Control and Automation (WCICA), pp. 3372-3376, 2010 8th World Congress on Intelligent Control and Automation, WCICA 2010, Jinan, China, 7/07/10. https://doi.org/10.1109/WCICA.2010.5553962

Terminal sliding mode attitude control for satellite. / Ma, Guangfu; Lv, Yueyong; Hu, Qinglei et al.
2010 8th World Congress on Intelligent Control and Automation, WCICA 2010. 2010. p. 3372-3376 5553962 (Proceedings of the World Congress on Intelligent Control and Automation (WCICA)).

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

TY - GEN

T1 - Terminal sliding mode attitude control for satellite

AU - Ma, Guangfu

AU - Lv, Yueyong

AU - Hu, Qinglei

AU - Li, Chuanjiang

PY - 2010

Y1 - 2010

N2 - A finite time control method based on terminal sliding mode (TSM) is presented for satellite attitude control system in this paper. Using the concepts of finite time stability and TSM, a finite time stable sliding mode is designed, and then a continuous TSM finite time controller using the inverse dynamic method is designed for the second-order dynamic system of the satellite. In order to eliminate the oscillation, a new type of saturation function is also designed to replace the conventional symbolic function. The validity for the proposed algorithm is testified through simulations.

AB - A finite time control method based on terminal sliding mode (TSM) is presented for satellite attitude control system in this paper. Using the concepts of finite time stability and TSM, a finite time stable sliding mode is designed, and then a continuous TSM finite time controller using the inverse dynamic method is designed for the second-order dynamic system of the satellite. In order to eliminate the oscillation, a new type of saturation function is also designed to replace the conventional symbolic function. The validity for the proposed algorithm is testified through simulations.

KW - Attitude control

KW - Finite time

KW - Terminal sliding mode

UR - https://www.scopus.com/pages/publications/77958146856

U2 - 10.1109/WCICA.2010.5553962

DO - 10.1109/WCICA.2010.5553962

M3 - 会议稿件

AN - SCOPUS:77958146856

SN - 9781424467129

T3 - Proceedings of the World Congress on Intelligent Control and Automation (WCICA)

SP - 3372

EP - 3376

BT - 2010 8th World Congress on Intelligent Control and Automation, WCICA 2010

T2 - 2010 8th World Congress on Intelligent Control and Automation, WCICA 2010

Y2 - 7 July 2010 through 9 July 2010

ER -

Terminal sliding mode attitude control for satellite

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Keywords

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