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Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults / Boyan Jiang; Qinglei Hu; Michael Friswell

IEEE Transactions on Control Systems Technology, Volume: 24, Issue: 5, Pages: 1892 - 1898

Swansea University Author: Michael, Friswell

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Abstract

This brief investigates the finite-time control problem associated with attitude stabilization of a rigid spacecraft subject to external disturbance, actuator faults, and input saturation. More specifically, a novel fixed-time sliding mode surface is developed, and the settling time of the defined s...

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Published in: IEEE Transactions on Control Systems Technology
ISSN: 1063-6536 1558-0865
Published: 2016
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URI: https://cronfa.swan.ac.uk/Record/cronfa30889
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last_indexed 2018-02-09T05:17:14Z
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spelling 2016-11-01T09:29:00.6417574 v2 30889 2016-11-01 Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false 2016-11-01 EEN This brief investigates the finite-time control problem associated with attitude stabilization of a rigid spacecraft subject to external disturbance, actuator faults, and input saturation. More specifically, a novel fixed-time sliding mode surface is developed, and the settling time of the defined surface is shown to be independent of the initial conditions of the system. Then, a finite-time controller is derived to guarantee that the closed-loop system is stable in the sense of the fixed-time concept. The actuator-magnitude constraints are rigorously enforced and the attitude of the rigid spacecraft converges to the equilibrium in a finite time even in the presence of external disturbances and actuator faults. Numerical simulations illustrate the spacecraft performance obtained using the proposed controller. Journal Article IEEE Transactions on Control Systems Technology 24 5 1892 1898 1063-6536 1558-0865 30 9 2016 2016-09-30 10.1109/TCST.2016.2519838 COLLEGE NANME Engineering COLLEGE CODE EEN Swansea University 2016-11-01T09:29:00.6417574 2016-11-01T09:27:54.3878540 College of Engineering Engineering Boyan Jiang 1 Qinglei Hu 2 Michael Friswell 3
title Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults
spellingShingle Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults
Michael, Friswell
title_short Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults
title_full Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults
title_fullStr Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults
title_full_unstemmed Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults
title_sort Fixed-Time Attitude Control for Rigid Spacecraft With Actuator Saturation and Faults
author_id_str_mv 5894777b8f9c6e64bde3568d68078d40
author_id_fullname_str_mv 5894777b8f9c6e64bde3568d68078d40_***_Michael, Friswell
author Michael, Friswell
author2 Boyan Jiang
Qinglei Hu
Michael Friswell
format Journal article
container_title IEEE Transactions on Control Systems Technology
container_volume 24
container_issue 5
container_start_page 1892
publishDate 2016
institution Swansea University
issn 1063-6536
1558-0865
doi_str_mv 10.1109/TCST.2016.2519838
college_str College of Engineering
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hierarchy_top_id collegeofengineering
hierarchy_top_title College of Engineering
hierarchy_parent_id collegeofengineering
hierarchy_parent_title College of Engineering
department_str Engineering{{{_:::_}}}College of Engineering{{{_:::_}}}Engineering
document_store_str 0
active_str 0
description This brief investigates the finite-time control problem associated with attitude stabilization of a rigid spacecraft subject to external disturbance, actuator faults, and input saturation. More specifically, a novel fixed-time sliding mode surface is developed, and the settling time of the defined surface is shown to be independent of the initial conditions of the system. Then, a finite-time controller is derived to guarantee that the closed-loop system is stable in the sense of the fixed-time concept. The actuator-magnitude constraints are rigorously enforced and the attitude of the rigid spacecraft converges to the equilibrium in a finite time even in the presence of external disturbances and actuator faults. Numerical simulations illustrate the spacecraft performance obtained using the proposed controller.
published_date 2016-09-30T03:48:48Z
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score 10.7876