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

Author

Listed:
  • Nguyen Xuan-Mung

    (Faculty of Mechanical and Aerospace Engineering, Sejong University, Seoul 05006, Republic of Korea)

  • Mehdi Golestani

    (Department of Electrical Engineering, Iran University of Science and Technology, Tehran 16844, Iran)

  • Huu Tiep Nguyen

    (Department of Quantum and Nuclear Engineering, Sejong University, Seoul 05006, Republic of Korea)

  • Ngoc Anh Nguyen

    (Faculty of Fundamental Science, PHENIKAA University, Hanoi 12116, Vietnam
    PHENIKAA Research and Technology Institute (PRATI), A&A Green Phoenix Group JSC, No. 167 Hoang Ngan, Trung Hoa, Cau Giay, Hanoi 11313, Vietnam)

  • Afef Fekih

    (Department of Electrical and Computer Engineering, University of Louisiana at Lafayette, Lafayette, LA 70504, USA)

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.

Suggested Citation

  • Nguyen Xuan-Mung & Mehdi Golestani & Huu Tiep Nguyen & Ngoc Anh Nguyen & Afef Fekih, 2023. "Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator," Mathematics, MDPI, vol. 11(9), pages 1-17, May.
    • Handle: RePEc:gam:jmathe:v:11:y:2023:i:9:p:2149-:d:1138972
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    References listed on IDEAS

    as
    1. Nguyen Xuan-Mung & Mehdi Golestani & Sung Kyung Hong, 2023. "Constrained Nonsingular Terminal Sliding Mode Attitude Control for Spacecraft: A Funnel Control Approach," Mathematics, MDPI, vol. 11(1), pages 1-23, January.
    2. Nguyen Xuan-Mung & Mehdi Golestani & Sung-Kyung Hong, 2022. "Tan-Type BLF-Based Attitude Tracking Control Design for Rigid Spacecraft with Arbitrary Disturbances," Mathematics, MDPI, vol. 10(23), pages 1-21, December.
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    Cited by:

    1. Jiao Xu & Tao Song & Jiaxin Wang, 2024. "Finite-Time Fuzzy Fault-Tolerant Control for Nonlinear Flexible Spacecraft System with Stochastic Actuator Faults," Mathematics, MDPI, vol. 12(4), pages 1-25, February.

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