Robust fixed-time attitude stabilization control of flexible spacecraft with actuator uncertainty
Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Cao, Lu [verfasserIn] |
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| Format: |
Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2020 |
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| Schlagwörter: |
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| Anmerkung: |
© Springer Nature B.V. 2020 |
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| Übergeordnetes Werk: |
Enthalten in: Nonlinear dynamics - Springer Netherlands, 1990, 100(2020), 3 vom: 22. Apr., Seite 2505-2519 |
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volume:100 ; year:2020 ; number:3 ; day:22 ; month:04 ; pages:2505-2519 |
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| DOI / URN: |
10.1007/s11071-020-05596-5 |
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OLC2051145938 |
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| 520 | |a Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily proposed by introducing a time-varying gain into the conventional fixed-time stability method. This gain improves the convergence rate. Then, a fixed-time observer is proposed to estimate the uncertain torque induced by disturbance, uncertain parameters of inertia, and actuator uncertainty. Fixed-time stability is ensured for the estimation error. Using this estimated knowledge and the full-states’ measurements, a nonsingular terminal sliding controller is finally synthesized. This is achieved via a nonsingular and faster terminal sliding surface with faster convergence rate. The closed-loop attitude stabilization system is proved to be fixed-time stable with the convergence time independent of initial states. The attitude stabilization performance is robust to disturbance and uncertainties in inertia and actuators. Simulation results are also shown to validate the attitude stabilization performance of this control approach. | ||
| 650 | 4 | |a Flexible spacecraft | |
| 650 | 4 | |a Fixed-time stability | |
| 650 | 4 | |a Attitude stabilization | |
| 650 | 4 | |a Actuator uncertainty | |
| 650 | 4 | |a Uncertain inertia | |
| 650 | 4 | |a Robust control | |
| 700 | 1 | |a Xiao, Bing |4 aut | |
| 700 | 1 | |a Golestani, Mehdi |4 aut | |
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10.1007/s11071-020-05596-5 doi (DE-627)OLC2051145938 (DE-He213)s11071-020-05596-5-p DE-627 ger DE-627 rakwb eng 510 VZ 11 ssgn Cao, Lu verfasserin aut Robust fixed-time attitude stabilization control of flexible spacecraft with actuator uncertainty 2020 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Springer Nature B.V. 2020 Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily proposed by introducing a time-varying gain into the conventional fixed-time stability method. This gain improves the convergence rate. Then, a fixed-time observer is proposed to estimate the uncertain torque induced by disturbance, uncertain parameters of inertia, and actuator uncertainty. Fixed-time stability is ensured for the estimation error. Using this estimated knowledge and the full-states’ measurements, a nonsingular terminal sliding controller is finally synthesized. This is achieved via a nonsingular and faster terminal sliding surface with faster convergence rate. The closed-loop attitude stabilization system is proved to be fixed-time stable with the convergence time independent of initial states. The attitude stabilization performance is robust to disturbance and uncertainties in inertia and actuators. Simulation results are also shown to validate the attitude stabilization performance of this control approach. Flexible spacecraft Fixed-time stability Attitude stabilization Actuator uncertainty Uncertain inertia Robust control Xiao, Bing aut Golestani, Mehdi aut Enthalten in Nonlinear dynamics Springer Netherlands, 1990 100(2020), 3 vom: 22. Apr., Seite 2505-2519 (DE-627)130936782 (DE-600)1058624-6 (DE-576)034188126 0924-090X nnns volume:100 year:2020 number:3 day:22 month:04 pages:2505-2519 https://doi.org/10.1007/s11071-020-05596-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY SSG-OLC-CHE SSG-OLC-MAT SSG-OPC-MAT AR 100 2020 3 22 04 2505-2519 |
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10.1007/s11071-020-05596-5 doi (DE-627)OLC2051145938 (DE-He213)s11071-020-05596-5-p DE-627 ger DE-627 rakwb eng 510 VZ 11 ssgn Cao, Lu verfasserin aut Robust fixed-time attitude stabilization control of flexible spacecraft with actuator uncertainty 2020 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Springer Nature B.V. 2020 Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily proposed by introducing a time-varying gain into the conventional fixed-time stability method. This gain improves the convergence rate. Then, a fixed-time observer is proposed to estimate the uncertain torque induced by disturbance, uncertain parameters of inertia, and actuator uncertainty. Fixed-time stability is ensured for the estimation error. Using this estimated knowledge and the full-states’ measurements, a nonsingular terminal sliding controller is finally synthesized. This is achieved via a nonsingular and faster terminal sliding surface with faster convergence rate. The closed-loop attitude stabilization system is proved to be fixed-time stable with the convergence time independent of initial states. The attitude stabilization performance is robust to disturbance and uncertainties in inertia and actuators. Simulation results are also shown to validate the attitude stabilization performance of this control approach. Flexible spacecraft Fixed-time stability Attitude stabilization Actuator uncertainty Uncertain inertia Robust control Xiao, Bing aut Golestani, Mehdi aut Enthalten in Nonlinear dynamics Springer Netherlands, 1990 100(2020), 3 vom: 22. Apr., Seite 2505-2519 (DE-627)130936782 (DE-600)1058624-6 (DE-576)034188126 0924-090X nnns volume:100 year:2020 number:3 day:22 month:04 pages:2505-2519 https://doi.org/10.1007/s11071-020-05596-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY SSG-OLC-CHE SSG-OLC-MAT SSG-OPC-MAT AR 100 2020 3 22 04 2505-2519 |
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10.1007/s11071-020-05596-5 doi (DE-627)OLC2051145938 (DE-He213)s11071-020-05596-5-p DE-627 ger DE-627 rakwb eng 510 VZ 11 ssgn Cao, Lu verfasserin aut Robust fixed-time attitude stabilization control of flexible spacecraft with actuator uncertainty 2020 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Springer Nature B.V. 2020 Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily proposed by introducing a time-varying gain into the conventional fixed-time stability method. This gain improves the convergence rate. Then, a fixed-time observer is proposed to estimate the uncertain torque induced by disturbance, uncertain parameters of inertia, and actuator uncertainty. Fixed-time stability is ensured for the estimation error. Using this estimated knowledge and the full-states’ measurements, a nonsingular terminal sliding controller is finally synthesized. This is achieved via a nonsingular and faster terminal sliding surface with faster convergence rate. The closed-loop attitude stabilization system is proved to be fixed-time stable with the convergence time independent of initial states. The attitude stabilization performance is robust to disturbance and uncertainties in inertia and actuators. Simulation results are also shown to validate the attitude stabilization performance of this control approach. Flexible spacecraft Fixed-time stability Attitude stabilization Actuator uncertainty Uncertain inertia Robust control Xiao, Bing aut Golestani, Mehdi aut Enthalten in Nonlinear dynamics Springer Netherlands, 1990 100(2020), 3 vom: 22. Apr., Seite 2505-2519 (DE-627)130936782 (DE-600)1058624-6 (DE-576)034188126 0924-090X nnns volume:100 year:2020 number:3 day:22 month:04 pages:2505-2519 https://doi.org/10.1007/s11071-020-05596-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY SSG-OLC-CHE SSG-OLC-MAT SSG-OPC-MAT AR 100 2020 3 22 04 2505-2519 |
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10.1007/s11071-020-05596-5 doi (DE-627)OLC2051145938 (DE-He213)s11071-020-05596-5-p DE-627 ger DE-627 rakwb eng 510 VZ 11 ssgn Cao, Lu verfasserin aut Robust fixed-time attitude stabilization control of flexible spacecraft with actuator uncertainty 2020 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Springer Nature B.V. 2020 Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily proposed by introducing a time-varying gain into the conventional fixed-time stability method. This gain improves the convergence rate. Then, a fixed-time observer is proposed to estimate the uncertain torque induced by disturbance, uncertain parameters of inertia, and actuator uncertainty. Fixed-time stability is ensured for the estimation error. Using this estimated knowledge and the full-states’ measurements, a nonsingular terminal sliding controller is finally synthesized. This is achieved via a nonsingular and faster terminal sliding surface with faster convergence rate. The closed-loop attitude stabilization system is proved to be fixed-time stable with the convergence time independent of initial states. The attitude stabilization performance is robust to disturbance and uncertainties in inertia and actuators. Simulation results are also shown to validate the attitude stabilization performance of this control approach. Flexible spacecraft Fixed-time stability Attitude stabilization Actuator uncertainty Uncertain inertia Robust control Xiao, Bing aut Golestani, Mehdi aut Enthalten in Nonlinear dynamics Springer Netherlands, 1990 100(2020), 3 vom: 22. Apr., Seite 2505-2519 (DE-627)130936782 (DE-600)1058624-6 (DE-576)034188126 0924-090X nnns volume:100 year:2020 number:3 day:22 month:04 pages:2505-2519 https://doi.org/10.1007/s11071-020-05596-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY SSG-OLC-CHE SSG-OLC-MAT SSG-OPC-MAT AR 100 2020 3 22 04 2505-2519 |
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10.1007/s11071-020-05596-5 doi (DE-627)OLC2051145938 (DE-He213)s11071-020-05596-5-p DE-627 ger DE-627 rakwb eng 510 VZ 11 ssgn Cao, Lu verfasserin aut Robust fixed-time attitude stabilization control of flexible spacecraft with actuator uncertainty 2020 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Springer Nature B.V. 2020 Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily proposed by introducing a time-varying gain into the conventional fixed-time stability method. This gain improves the convergence rate. Then, a fixed-time observer is proposed to estimate the uncertain torque induced by disturbance, uncertain parameters of inertia, and actuator uncertainty. Fixed-time stability is ensured for the estimation error. Using this estimated knowledge and the full-states’ measurements, a nonsingular terminal sliding controller is finally synthesized. This is achieved via a nonsingular and faster terminal sliding surface with faster convergence rate. The closed-loop attitude stabilization system is proved to be fixed-time stable with the convergence time independent of initial states. The attitude stabilization performance is robust to disturbance and uncertainties in inertia and actuators. Simulation results are also shown to validate the attitude stabilization performance of this control approach. Flexible spacecraft Fixed-time stability Attitude stabilization Actuator uncertainty Uncertain inertia Robust control Xiao, Bing aut Golestani, Mehdi aut Enthalten in Nonlinear dynamics Springer Netherlands, 1990 100(2020), 3 vom: 22. Apr., Seite 2505-2519 (DE-627)130936782 (DE-600)1058624-6 (DE-576)034188126 0924-090X nnns volume:100 year:2020 number:3 day:22 month:04 pages:2505-2519 https://doi.org/10.1007/s11071-020-05596-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-PHY SSG-OLC-CHE SSG-OLC-MAT SSG-OPC-MAT AR 100 2020 3 22 04 2505-2519 |
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Robust fixed-time attitude stabilization control of flexible spacecraft with actuator uncertainty |
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Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily proposed by introducing a time-varying gain into the conventional fixed-time stability method. This gain improves the convergence rate. Then, a fixed-time observer is proposed to estimate the uncertain torque induced by disturbance, uncertain parameters of inertia, and actuator uncertainty. Fixed-time stability is ensured for the estimation error. Using this estimated knowledge and the full-states’ measurements, a nonsingular terminal sliding controller is finally synthesized. This is achieved via a nonsingular and faster terminal sliding surface with faster convergence rate. The closed-loop attitude stabilization system is proved to be fixed-time stable with the convergence time independent of initial states. The attitude stabilization performance is robust to disturbance and uncertainties in inertia and actuators. Simulation results are also shown to validate the attitude stabilization performance of this control approach. © Springer Nature B.V. 2020 |
| abstractGer |
Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily proposed by introducing a time-varying gain into the conventional fixed-time stability method. This gain improves the convergence rate. Then, a fixed-time observer is proposed to estimate the uncertain torque induced by disturbance, uncertain parameters of inertia, and actuator uncertainty. Fixed-time stability is ensured for the estimation error. Using this estimated knowledge and the full-states’ measurements, a nonsingular terminal sliding controller is finally synthesized. This is achieved via a nonsingular and faster terminal sliding surface with faster convergence rate. The closed-loop attitude stabilization system is proved to be fixed-time stable with the convergence time independent of initial states. The attitude stabilization performance is robust to disturbance and uncertainties in inertia and actuators. Simulation results are also shown to validate the attitude stabilization performance of this control approach. © Springer Nature B.V. 2020 |
| abstract_unstemmed |
Abstract A robust fixed-time control framework is presented to stabilize flexible spacecraft’s attitude system with external disturbance, uncertain parameters of inertia, and actuator uncertainty. As a stepping stone, a nonlinear system having faster fixed-time convergence property is preliminarily proposed by introducing a time-varying gain into the conventional fixed-time stability method. This gain improves the convergence rate. Then, a fixed-time observer is proposed to estimate the uncertain torque induced by disturbance, uncertain parameters of inertia, and actuator uncertainty. Fixed-time stability is ensured for the estimation error. Using this estimated knowledge and the full-states’ measurements, a nonsingular terminal sliding controller is finally synthesized. This is achieved via a nonsingular and faster terminal sliding surface with faster convergence rate. The closed-loop attitude stabilization system is proved to be fixed-time stable with the convergence time independent of initial states. The attitude stabilization performance is robust to disturbance and uncertainties in inertia and actuators. Simulation results are also shown to validate the attitude stabilization performance of this control approach. © Springer Nature B.V. 2020 |
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Robust fixed-time attitude stabilization control of flexible spacecraft with actuator uncertainty |
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https://doi.org/10.1007/s11071-020-05596-5 |
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Xiao, Bing Golestani, Mehdi |
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10.1007/s11071-020-05596-5 |
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