Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism

Qian Sun; Yingmin Jia

doi:10.1007/978-981-19-6203-5_81

Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism

Qian Sun
, Yingmin Jia^*

^*Corresponding author for this work

School of Automation Science and Electrical Engineering

Beihang University

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

Abstract

In this paper, the attitude and orbit coupled control problem is studied for distributed spacecraft formation. Firstly, a compact integrated attitude-orbit relative motion model of the spacecrafts in the formation is proposed based on dual quaternion. Correspondingly, by virtue of the nonsingular fast terminal sliding mode (NFTSM) technique, a robust control strategy is designed to realize the attitude and position tracking control simultaneously considering the bounded external disturbances. Meanwhile, an event-triggered condition (ETC) is applied in the controller design to eliminate communication burden among the spacecrafts. Finally, numerical simulations demonstrate the validity and robustness of the developed control scheme.

Original language	English
Title of host publication	Proceedings of 2022 Chinese Intelligent Systems Conference - Volume I
Editors	Yingmin Jia, Weicun Zhang, Yongling Fu, Shoujun Zhao
Publisher	Springer Science and Business Media Deutschland GmbH
Pages	815-824
Number of pages	10
ISBN (Print)	9789811962028
DOIs	https://doi.org/10.1007/978-981-19-6203-5_81
State	Published - 2022
Event	18th Chinese Intelligent Systems Conference, CISC 2022 - Beijing, China Duration: 15 Oct 2022 → 16 Oct 2022

Publication series

Name	Lecture Notes in Electrical Engineering
Volume	950 LNEE
ISSN (Print)	1876-1100
ISSN (Electronic)	1876-1119

Conference

Conference	18th Chinese Intelligent Systems Conference, CISC 2022
Country/Territory	China
City	Beijing
Period	15/10/22 → 16/10/22

Keywords

Dual quaternion
Event-triggered control
Integrated attitude-orbit control
Spacecraft formation

Access to Document

10.1007/978-981-19-6203-5_81

Cite this

Sun, Q., & Jia, Y. (2022). Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism. In Y. Jia, W. Zhang, Y. Fu, & S. Zhao (Eds.), Proceedings of 2022 Chinese Intelligent Systems Conference - Volume I (pp. 815-824). (Lecture Notes in Electrical Engineering; Vol. 950 LNEE). Springer Science and Business Media Deutschland GmbH. https://doi.org/10.1007/978-981-19-6203-5_81

Sun, Qian ; Jia, Yingmin. / Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism. Proceedings of 2022 Chinese Intelligent Systems Conference - Volume I. editor / Yingmin Jia ; Weicun Zhang ; Yongling Fu ; Shoujun Zhao. Springer Science and Business Media Deutschland GmbH, 2022. pp. 815-824 (Lecture Notes in Electrical Engineering).

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title = "Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism",

abstract = "In this paper, the attitude and orbit coupled control problem is studied for distributed spacecraft formation. Firstly, a compact integrated attitude-orbit relative motion model of the spacecrafts in the formation is proposed based on dual quaternion. Correspondingly, by virtue of the nonsingular fast terminal sliding mode (NFTSM) technique, a robust control strategy is designed to realize the attitude and position tracking control simultaneously considering the bounded external disturbances. Meanwhile, an event-triggered condition (ETC) is applied in the controller design to eliminate communication burden among the spacecrafts. Finally, numerical simulations demonstrate the validity and robustness of the developed control scheme.",

keywords = "Dual quaternion, Event-triggered control, Integrated attitude-orbit control, Spacecraft formation",

author = "Qian Sun and Yingmin Jia",

note = "Publisher Copyright: {\textcopyright} 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.; 18th Chinese Intelligent Systems Conference, CISC 2022 ; Conference date: 15-10-2022 Through 16-10-2022",

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language = "英语",

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publisher = "Springer Science and Business Media Deutschland GmbH",

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Sun, Q & Jia, Y 2022, Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism. in Y Jia, W Zhang, Y Fu & S Zhao (eds), Proceedings of 2022 Chinese Intelligent Systems Conference - Volume I. Lecture Notes in Electrical Engineering, vol. 950 LNEE, Springer Science and Business Media Deutschland GmbH, pp. 815-824, 18th Chinese Intelligent Systems Conference, CISC 2022, Beijing, China, 15/10/22. https://doi.org/10.1007/978-981-19-6203-5_81

Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism. / Sun, Qian; Jia, Yingmin.
Proceedings of 2022 Chinese Intelligent Systems Conference - Volume I. ed. / Yingmin Jia; Weicun Zhang; Yongling Fu; Shoujun Zhao. Springer Science and Business Media Deutschland GmbH, 2022. p. 815-824 (Lecture Notes in Electrical Engineering; Vol. 950 LNEE).

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

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N2 - In this paper, the attitude and orbit coupled control problem is studied for distributed spacecraft formation. Firstly, a compact integrated attitude-orbit relative motion model of the spacecrafts in the formation is proposed based on dual quaternion. Correspondingly, by virtue of the nonsingular fast terminal sliding mode (NFTSM) technique, a robust control strategy is designed to realize the attitude and position tracking control simultaneously considering the bounded external disturbances. Meanwhile, an event-triggered condition (ETC) is applied in the controller design to eliminate communication burden among the spacecrafts. Finally, numerical simulations demonstrate the validity and robustness of the developed control scheme.

AB - In this paper, the attitude and orbit coupled control problem is studied for distributed spacecraft formation. Firstly, a compact integrated attitude-orbit relative motion model of the spacecrafts in the formation is proposed based on dual quaternion. Correspondingly, by virtue of the nonsingular fast terminal sliding mode (NFTSM) technique, a robust control strategy is designed to realize the attitude and position tracking control simultaneously considering the bounded external disturbances. Meanwhile, an event-triggered condition (ETC) is applied in the controller design to eliminate communication burden among the spacecrafts. Finally, numerical simulations demonstrate the validity and robustness of the developed control scheme.

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KW - Spacecraft formation

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Sun Q, Jia Y. Nonsingular Fast Terminal Sliding Mode Control for Integrated Attitude-Orbit Spacecraft Formation with Event-triggered Mechanism. In Jia Y, Zhang W, Fu Y, Zhao S, editors, Proceedings of 2022 Chinese Intelligent Systems Conference - Volume I. Springer Science and Business Media Deutschland GmbH. 2022. p. 815-824. (Lecture Notes in Electrical Engineering). doi: 10.1007/978-981-19-6203-5_81