Spacecraft attitude control using nonsingular finite-time convergence Terminal Sliding Mode

Zhiguo Han; Ke Zhang; Tianshe Yang

doi:10.1109/CGNCC.2016.7828857

Spacecraft attitude control using nonsingular finite-time convergence Terminal Sliding Mode

Zhiguo Han, Ke Zhang, Tianshe Yang

School of Astronautics

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

7 Scopus citations

Abstract

Finite-time convergence control strategies based on adaptive Nonsingular Terminal Sliding Mode are proposed for spacecraft attitude tracking control subject to external disturbances and actuator faults. The designed attitude tracking controller meets the multi-constraints, and has singularities avoidance attributes. It is further shown that the controller with parameter adaptations is independent from bound of external disturbances. The Lyapunov stability analysis shows that the controller designed in this paper can guarantee the fast convergence of the closed-loop system, and has a good fault tolerant performance on actuator faults under the multi-constraints on external disturbances and actuator faults. Numerical simulation verified the good performance of the controller in the attitude tracking control.

Original language	English
Title of host publication	CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	618-623
Number of pages	6
ISBN (Electronic)	9781467383189
DOIs	https://doi.org/10.1109/CGNCC.2016.7828857
State	Published - 20 Jan 2017
Event	7th IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2016 - Nanjing, Jiangsu, China Duration: 12 Aug 2016 → 14 Aug 2016

Publication series

Name	CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference

Conference

Conference	7th IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2016
Country/Territory	China
City	Nanjing, Jiangsu
Period	12/08/16 → 14/08/16

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10.1109/CGNCC.2016.7828857

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Han, Z., Zhang, K., & Yang, T. (2017). Spacecraft attitude control using nonsingular finite-time convergence Terminal Sliding Mode. In CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference (pp. 618-623). Article 7828857 (CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/CGNCC.2016.7828857

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title = "Spacecraft attitude control using nonsingular finite-time convergence Terminal Sliding Mode",

abstract = "Finite-time convergence control strategies based on adaptive Nonsingular Terminal Sliding Mode are proposed for spacecraft attitude tracking control subject to external disturbances and actuator faults. The designed attitude tracking controller meets the multi-constraints, and has singularities avoidance attributes. It is further shown that the controller with parameter adaptations is independent from bound of external disturbances. The Lyapunov stability analysis shows that the controller designed in this paper can guarantee the fast convergence of the closed-loop system, and has a good fault tolerant performance on actuator faults under the multi-constraints on external disturbances and actuator faults. Numerical simulation verified the good performance of the controller in the attitude tracking control.",

author = "Zhiguo Han and Ke Zhang and Tianshe Yang",

note = "Publisher Copyright: {\textcopyright} 2016 IEEE.; 7th IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2016 ; Conference date: 12-08-2016 Through 14-08-2016",

year = "2017",

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doi = "10.1109/CGNCC.2016.7828857",

language = "英语",

series = "CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference",

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Han, Z, Zhang, K & Yang, T 2017, Spacecraft attitude control using nonsingular finite-time convergence Terminal Sliding Mode. in CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference., 7828857, CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference, Institute of Electrical and Electronics Engineers Inc., pp. 618-623, 7th IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2016, Nanjing, Jiangsu, China, 12/08/16. https://doi.org/10.1109/CGNCC.2016.7828857

Spacecraft attitude control using nonsingular finite-time convergence Terminal Sliding Mode. / Han, Zhiguo; Zhang, Ke; Yang, Tianshe.
CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference. Institute of Electrical and Electronics Engineers Inc., 2017. p. 618-623 7828857 (CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference).

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

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AU - Han, Zhiguo

AU - Zhang, Ke

AU - Yang, Tianshe

PY - 2017/1/20

Y1 - 2017/1/20

N2 - Finite-time convergence control strategies based on adaptive Nonsingular Terminal Sliding Mode are proposed for spacecraft attitude tracking control subject to external disturbances and actuator faults. The designed attitude tracking controller meets the multi-constraints, and has singularities avoidance attributes. It is further shown that the controller with parameter adaptations is independent from bound of external disturbances. The Lyapunov stability analysis shows that the controller designed in this paper can guarantee the fast convergence of the closed-loop system, and has a good fault tolerant performance on actuator faults under the multi-constraints on external disturbances and actuator faults. Numerical simulation verified the good performance of the controller in the attitude tracking control.

AB - Finite-time convergence control strategies based on adaptive Nonsingular Terminal Sliding Mode are proposed for spacecraft attitude tracking control subject to external disturbances and actuator faults. The designed attitude tracking controller meets the multi-constraints, and has singularities avoidance attributes. It is further shown that the controller with parameter adaptations is independent from bound of external disturbances. The Lyapunov stability analysis shows that the controller designed in this paper can guarantee the fast convergence of the closed-loop system, and has a good fault tolerant performance on actuator faults under the multi-constraints on external disturbances and actuator faults. Numerical simulation verified the good performance of the controller in the attitude tracking control.

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DO - 10.1109/CGNCC.2016.7828857

M3 - 会议稿件

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T3 - CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference

SP - 618

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BT - CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference

PB - Institute of Electrical and Electronics Engineers Inc.

T2 - 7th IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2016

Y2 - 12 August 2016 through 14 August 2016

ER -

Han Z, Zhang K, Yang T. Spacecraft attitude control using nonsingular finite-time convergence Terminal Sliding Mode. In CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference. Institute of Electrical and Electronics Engineers Inc. 2017. p. 618-623. 7828857. (CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference). doi: 10.1109/CGNCC.2016.7828857

Spacecraft attitude control using nonsingular finite-time convergence Terminal Sliding Mode

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