Finite-time active fault-tolerant attitude control for flexible spacecraft with vibration suppression and anti-unwinding
In this paper, a finite-time active fault-tolerant control scheme is designed for a flexible spacecraft’s attitude control experiencing inertial parametric variations, external disturbances, multiple actuator faults, and estimation errors while suppressing the flexible appendages’ vibrations without...
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| Published in | Advances in space research Vol. 71; no. 9; pp. 3644 - 3660 |
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| Main Authors | , , |
| Format | Journal Article |
| Language | English |
| Published |
Elsevier B.V
01.05.2023
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| Subjects | |
| Online Access | Get full text |
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| Abstract | In this paper, a finite-time active fault-tolerant control scheme is designed for a flexible spacecraft’s attitude control experiencing inertial parametric variations, external disturbances, multiple actuator faults, and estimation errors while suppressing the flexible appendages’ vibrations without using smart vibration suppression actuators. First, relative attitude dynamics of a flexible spacecraft with multiple actuator faults are outlined, and a sliding mode observer is designed to estimate flexible appendages-related vibrations. The proposed fault detection and identification (FDI) strategy can efficiently detect actuator faults, avoiding the false alarms caused by uncertainties and disturbances, and accurately estimate the cumulative fault effects on the spacecraft via Chebyshev neural network (CNN) based estimator. Based on a novel fast nonsingular terminal sliding mode surface, a finite-time, unwinding-free, and adaptive fault-tolerant attitude controller is designed to acclimatize the detected faults and uncertainties effectively, also heeding the errors in the estimation of flexible modes and faults. The spacecraft can carry out the coveted control objective in a definable time, and the stability of the proposed controller is corroborated via Lyapunov techniques. Finally, a comparative simulation analysis with the existing results elucidated the proposed scheme’s efficacy. |
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| AbstractList | In this paper, a finite-time active fault-tolerant control scheme is designed for a flexible spacecraft’s attitude control experiencing inertial parametric variations, external disturbances, multiple actuator faults, and estimation errors while suppressing the flexible appendages’ vibrations without using smart vibration suppression actuators. First, relative attitude dynamics of a flexible spacecraft with multiple actuator faults are outlined, and a sliding mode observer is designed to estimate flexible appendages-related vibrations. The proposed fault detection and identification (FDI) strategy can efficiently detect actuator faults, avoiding the false alarms caused by uncertainties and disturbances, and accurately estimate the cumulative fault effects on the spacecraft via Chebyshev neural network (CNN) based estimator. Based on a novel fast nonsingular terminal sliding mode surface, a finite-time, unwinding-free, and adaptive fault-tolerant attitude controller is designed to acclimatize the detected faults and uncertainties effectively, also heeding the errors in the estimation of flexible modes and faults. The spacecraft can carry out the coveted control objective in a definable time, and the stability of the proposed controller is corroborated via Lyapunov techniques. Finally, a comparative simulation analysis with the existing results elucidated the proposed scheme’s efficacy. |
| Author | Qin, Shiyin Hasan, Muhammad Noman Haris, Muhammad |
| Author_xml | – sequence: 1 givenname: Muhammad Noman surname: Hasan fullname: Hasan, Muhammad Noman email: noman@buaa.edu.cn organization: School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China – sequence: 2 givenname: Muhammad surname: Haris fullname: Haris, Muhammad organization: School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China – sequence: 3 givenname: Shiyin surname: Qin fullname: Qin, Shiyin organization: School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China |
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| Keywords | Fault detection and identification Flexible spacecraft Active fault-tolerant control Actuator faults Finite-time control Chebyshev neural network Anti-unwinding |
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| SubjectTerms | Active fault-tolerant control Actuator faults Anti-unwinding Chebyshev neural network Fault detection and identification Finite-time control Flexible spacecraft |
| Title | Finite-time active fault-tolerant attitude control for flexible spacecraft with vibration suppression and anti-unwinding |
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