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Fixed-time fault-tolerant attitude control for flexible spacecraft without angular velocity sensor.
Hasan, Muhammad Noman; Chen, Yong; Liang, Jiongjiong; Wen, An.
Afiliación
  • Hasan MN; Yangtze Delta Region Institute of University of Electronic Science and Technology (UESTC), Huzhou, Zhejiang, 313001, China. Electronic address: nomi.iiee@gmail.com.
  • Chen Y; Yangtze Delta Region Institute of University of Electronic Science and Technology (UESTC), Huzhou, Zhejiang, 313001, China; School of Automation Engineering, University of Electronic Science and Technology of China, Chengdu 611731, China. Electronic address: ychencd@uestc.edu.cn.
  • Liang J; Yangtze Delta Region Institute of University of Electronic Science and Technology (UESTC), Huzhou, Zhejiang, 313001, China. Electronic address: liangjiongjiong@163.com.
  • Wen A; Yangtze Delta Region Institute of University of Electronic Science and Technology (UESTC), Huzhou, Zhejiang, 313001, China. Electronic address: wa66@csj.uestc.edu.cn.
ISA Trans ; 146: 87-98, 2024 Mar.
Article en En | MEDLINE | ID: mdl-38129245
ABSTRACT
This paper deals with the appealing problem of fixed-time fault-tolerant attitude control, using attitude-information-only, for a flexible spacecraft under the influence of inertial parametric variations, external disturbances, and multiple actuator faults while suppressing the flexible appendages' vibrations without using additional sensors or smart vibration suppression actuators. First, an adaptive fixed-time model-free observer (AFTMFO) is designed, using the attitude information, for rapid estimation of unavailable angular velocity. A novel adaptive continuous control is then synthesized based on an anti-unwinding fast fixed-time nonsingular sliding surface (AFFTNSS), utilizing variable gains in both the control law and sliding surface; that simultaneously alleviates the chattering but also improves the convergence speed when compared to existing fixed-time approaches. The proposed scheme offers superior performance characteristics such as velocity sensor-free fixed-time attitude maneuvering with high pointing accuracy, fault tolerance, vibration suppression, nonsingular and chattering-free control. The spacecraft can carry out the coveted control objective in a predeterminable time independent of the knowledge of initial states while overcoming the unwinding effect to reduce the control effort and time. The fixed-time closed-loop stability of the proposed scheme is corroborated via Lyapunov techniques. Finally, a comparative simulation analysis with the existing results elucidated the proposed scheme's efficacy.
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Texto completo: 1 Colección: 01-internacional Base de datos: MEDLINE Idioma: En Revista: ISA Trans Año: 2024 Tipo del documento: Article Pais de publicación: Estados Unidos
Texto completo
Añadir a Mi BVS
Imprimir
XML
PubMed Links
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Texto completo: 1 Colección: 01-internacional Base de datos: MEDLINE Idioma: En Revista: ISA Trans Año: 2024 Tipo del documento: Article Pais de publicación: Estados Unidos