Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator

This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system....
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Autor*in:	Nguyen Xuan-Mung [verfasserIn] Mehdi Golestani [verfasserIn] Huu Tiep Nguyen [verfasserIn] Ngoc Anh Nguyen [verfasserIn] Afef Fekih [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2023

Schlagwörter:	spacecraft attitude system output feedback practical predefined-time stability back-stepping control anti-windup compensator

Übergeordnetes Werk:	In: Mathematics - MDPI AG, 2013, 11(2023), 9, p 2149
Übergeordnetes Werk:	volume:11 ; year:2023 ; number:9, p 2149

Links:	Link aufrufen Link aufrufen Link aufrufen Journal toc

DOI / URN:	10.3390/math11092149

Katalog-ID:	DOAJ090353102

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allfields	10.3390/math11092149 doi (DE-627)DOAJ090353102 (DE-599)DOAJ98d9b392b03445a4a4631cd1a900d895 DE-627 ger DE-627 rakwb eng QA1-939 Nguyen Xuan-Mung verfasserin aut Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system. All states of the new converted system are measurable and available for feedback; however, the system contains mismatched uncertainty resulting from the coordinate transformation. Then, an adaptive nonsingular back-stepping control with practical predefined-time convergence is designed. To resolve the problem of input saturation, an anti-windup compensator is developed. It is analytically proved that the spacecraft attitude and angular velocity are practical predefined-time stable, such that the convergence time is a given tunable constant. The simulation results reveal that the proposed control framework provides rapid attitude maneuver and actuator saturation elimination. spacecraft attitude system output feedback practical predefined-time stability back-stepping control anti-windup compensator Mathematics Mehdi Golestani verfasserin aut Huu Tiep Nguyen verfasserin aut Ngoc Anh Nguyen verfasserin aut Afef Fekih verfasserin aut In Mathematics MDPI AG, 2013 11(2023), 9, p 2149 (DE-627)737287764 (DE-600)2704244-3 22277390 nnns volume:11 year:2023 number:9, p 2149 https://doi.org/10.3390/math11092149 kostenfrei https://doaj.org/article/98d9b392b03445a4a4631cd1a900d895 kostenfrei https://www.mdpi.com/2227-7390/11/9/2149 kostenfrei https://doaj.org/toc/2227-7390 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2111 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 11 2023 9, p 2149
spelling	10.3390/math11092149 doi (DE-627)DOAJ090353102 (DE-599)DOAJ98d9b392b03445a4a4631cd1a900d895 DE-627 ger DE-627 rakwb eng QA1-939 Nguyen Xuan-Mung verfasserin aut Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system. All states of the new converted system are measurable and available for feedback; however, the system contains mismatched uncertainty resulting from the coordinate transformation. Then, an adaptive nonsingular back-stepping control with practical predefined-time convergence is designed. To resolve the problem of input saturation, an anti-windup compensator is developed. It is analytically proved that the spacecraft attitude and angular velocity are practical predefined-time stable, such that the convergence time is a given tunable constant. The simulation results reveal that the proposed control framework provides rapid attitude maneuver and actuator saturation elimination. spacecraft attitude system output feedback practical predefined-time stability back-stepping control anti-windup compensator Mathematics Mehdi Golestani verfasserin aut Huu Tiep Nguyen verfasserin aut Ngoc Anh Nguyen verfasserin aut Afef Fekih verfasserin aut In Mathematics MDPI AG, 2013 11(2023), 9, p 2149 (DE-627)737287764 (DE-600)2704244-3 22277390 nnns volume:11 year:2023 number:9, p 2149 https://doi.org/10.3390/math11092149 kostenfrei https://doaj.org/article/98d9b392b03445a4a4631cd1a900d895 kostenfrei https://www.mdpi.com/2227-7390/11/9/2149 kostenfrei https://doaj.org/toc/2227-7390 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2111 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 11 2023 9, p 2149
allfields_unstemmed	10.3390/math11092149 doi (DE-627)DOAJ090353102 (DE-599)DOAJ98d9b392b03445a4a4631cd1a900d895 DE-627 ger DE-627 rakwb eng QA1-939 Nguyen Xuan-Mung verfasserin aut Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system. All states of the new converted system are measurable and available for feedback; however, the system contains mismatched uncertainty resulting from the coordinate transformation. Then, an adaptive nonsingular back-stepping control with practical predefined-time convergence is designed. To resolve the problem of input saturation, an anti-windup compensator is developed. It is analytically proved that the spacecraft attitude and angular velocity are practical predefined-time stable, such that the convergence time is a given tunable constant. The simulation results reveal that the proposed control framework provides rapid attitude maneuver and actuator saturation elimination. spacecraft attitude system output feedback practical predefined-time stability back-stepping control anti-windup compensator Mathematics Mehdi Golestani verfasserin aut Huu Tiep Nguyen verfasserin aut Ngoc Anh Nguyen verfasserin aut Afef Fekih verfasserin aut In Mathematics MDPI AG, 2013 11(2023), 9, p 2149 (DE-627)737287764 (DE-600)2704244-3 22277390 nnns volume:11 year:2023 number:9, p 2149 https://doi.org/10.3390/math11092149 kostenfrei https://doaj.org/article/98d9b392b03445a4a4631cd1a900d895 kostenfrei https://www.mdpi.com/2227-7390/11/9/2149 kostenfrei https://doaj.org/toc/2227-7390 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2111 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 11 2023 9, p 2149
allfieldsGer	10.3390/math11092149 doi (DE-627)DOAJ090353102 (DE-599)DOAJ98d9b392b03445a4a4631cd1a900d895 DE-627 ger DE-627 rakwb eng QA1-939 Nguyen Xuan-Mung verfasserin aut Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system. All states of the new converted system are measurable and available for feedback; however, the system contains mismatched uncertainty resulting from the coordinate transformation. Then, an adaptive nonsingular back-stepping control with practical predefined-time convergence is designed. To resolve the problem of input saturation, an anti-windup compensator is developed. It is analytically proved that the spacecraft attitude and angular velocity are practical predefined-time stable, such that the convergence time is a given tunable constant. The simulation results reveal that the proposed control framework provides rapid attitude maneuver and actuator saturation elimination. spacecraft attitude system output feedback practical predefined-time stability back-stepping control anti-windup compensator Mathematics Mehdi Golestani verfasserin aut Huu Tiep Nguyen verfasserin aut Ngoc Anh Nguyen verfasserin aut Afef Fekih verfasserin aut In Mathematics MDPI AG, 2013 11(2023), 9, p 2149 (DE-627)737287764 (DE-600)2704244-3 22277390 nnns volume:11 year:2023 number:9, p 2149 https://doi.org/10.3390/math11092149 kostenfrei https://doaj.org/article/98d9b392b03445a4a4631cd1a900d895 kostenfrei https://www.mdpi.com/2227-7390/11/9/2149 kostenfrei https://doaj.org/toc/2227-7390 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2111 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 11 2023 9, p 2149
allfieldsSound	10.3390/math11092149 doi (DE-627)DOAJ090353102 (DE-599)DOAJ98d9b392b03445a4a4631cd1a900d895 DE-627 ger DE-627 rakwb eng QA1-939 Nguyen Xuan-Mung verfasserin aut Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system. All states of the new converted system are measurable and available for feedback; however, the system contains mismatched uncertainty resulting from the coordinate transformation. Then, an adaptive nonsingular back-stepping control with practical predefined-time convergence is designed. To resolve the problem of input saturation, an anti-windup compensator is developed. It is analytically proved that the spacecraft attitude and angular velocity are practical predefined-time stable, such that the convergence time is a given tunable constant. The simulation results reveal that the proposed control framework provides rapid attitude maneuver and actuator saturation elimination. spacecraft attitude system output feedback practical predefined-time stability back-stepping control anti-windup compensator Mathematics Mehdi Golestani verfasserin aut Huu Tiep Nguyen verfasserin aut Ngoc Anh Nguyen verfasserin aut Afef Fekih verfasserin aut In Mathematics MDPI AG, 2013 11(2023), 9, p 2149 (DE-627)737287764 (DE-600)2704244-3 22277390 nnns volume:11 year:2023 number:9, p 2149 https://doi.org/10.3390/math11092149 kostenfrei https://doaj.org/article/98d9b392b03445a4a4631cd1a900d895 kostenfrei https://www.mdpi.com/2227-7390/11/9/2149 kostenfrei https://doaj.org/toc/2227-7390 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2111 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 11 2023 9, p 2149
language	English
source	In Mathematics 11(2023), 9, p 2149 volume:11 year:2023 number:9, p 2149
sourceStr	In Mathematics 11(2023), 9, p 2149 volume:11 year:2023 number:9, p 2149
format_phy_str_mv	Article
institution	findex.gbv.de
topic_facet	spacecraft attitude system output feedback practical predefined-time stability back-stepping control anti-windup compensator Mathematics
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container_title	Mathematics
authorswithroles_txt_mv	Nguyen Xuan-Mung @@aut@@ Mehdi Golestani @@aut@@ Huu Tiep Nguyen @@aut@@ Ngoc Anh Nguyen @@aut@@ Afef Fekih @@aut@@
publishDateDaySort_date	2023-01-01T00:00:00Z
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callnumber-first	Q - Science
author	Nguyen Xuan-Mung
spellingShingle	Nguyen Xuan-Mung misc QA1-939 misc spacecraft attitude system misc output feedback misc practical predefined-time stability misc back-stepping control misc anti-windup compensator misc Mathematics Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator
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topic_title	QA1-939 Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator spacecraft attitude system output feedback practical predefined-time stability back-stepping control anti-windup compensator
topic	misc QA1-939 misc spacecraft attitude system misc output feedback misc practical predefined-time stability misc back-stepping control misc anti-windup compensator misc Mathematics
topic_unstemmed	misc QA1-939 misc spacecraft attitude system misc output feedback misc practical predefined-time stability misc back-stepping control misc anti-windup compensator misc Mathematics
topic_browse	misc QA1-939 misc spacecraft attitude system misc output feedback misc practical predefined-time stability misc back-stepping control misc anti-windup compensator misc Mathematics
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title	Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator
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title_full	Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator
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title_sort	output feedback control for spacecraft attitude system with practical predefined-time stability based on anti-windup compensator
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title_auth	Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator
abstract	This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system. All states of the new converted system are measurable and available for feedback; however, the system contains mismatched uncertainty resulting from the coordinate transformation. Then, an adaptive nonsingular back-stepping control with practical predefined-time convergence is designed. To resolve the problem of input saturation, an anti-windup compensator is developed. It is analytically proved that the spacecraft attitude and angular velocity are practical predefined-time stable, such that the convergence time is a given tunable constant. The simulation results reveal that the proposed control framework provides rapid attitude maneuver and actuator saturation elimination.
abstractGer	This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system. All states of the new converted system are measurable and available for feedback; however, the system contains mismatched uncertainty resulting from the coordinate transformation. Then, an adaptive nonsingular back-stepping control with practical predefined-time convergence is designed. To resolve the problem of input saturation, an anti-windup compensator is developed. It is analytically proved that the spacecraft attitude and angular velocity are practical predefined-time stable, such that the convergence time is a given tunable constant. The simulation results reveal that the proposed control framework provides rapid attitude maneuver and actuator saturation elimination.
abstract_unstemmed	This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system. All states of the new converted system are measurable and available for feedback; however, the system contains mismatched uncertainty resulting from the coordinate transformation. Then, an adaptive nonsingular back-stepping control with practical predefined-time convergence is designed. To resolve the problem of input saturation, an anti-windup compensator is developed. It is analytically proved that the spacecraft attitude and angular velocity are practical predefined-time stable, such that the convergence time is a given tunable constant. The simulation results reveal that the proposed control framework provides rapid attitude maneuver and actuator saturation elimination.
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title_short	Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator
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Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator

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