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Constrained Nonsingular Terminal Sliding Mode Attitude Control for Spacecraft: A Funnel Control Approach

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)

  • Sung Kyung Hong

    (Faculty of Mechanical and Aerospace Engineering, Sejong University, Seoul 05006, Republic of Korea
    Department of Convergence Engineering for Intelligent Drone, Sejong University, Seoul 05006, Republic of Korea)

Abstract

This paper presents an adaptive constrained attitude control for uncertain spacecraft. Inspired by the concept of nonsingular terminal sliding mode control and funnel control for nonlinear systems, a novel adaptive attitude control is introduced which contains a time-varying gain to handle the constraints imposed on the spacecraft attitude. Indeed, when the attitude trajectory approaches the boundary of the constraint set, the control effort as well as the time-varying gain will increase in order to preclude the trajectory from intersecting the boundary. Then, it is analytically proved that the system trajectories converge to an arbitrary small region around the origin within a fixed time where the smallest upper bound of the convergence time is determined as an independent parameter in the controller. Further, the proposed control scheme is nonsingular without having to use any piecewise continuous function which simplifies stability analysis. These properties distinguish the proposed control scheme from the existing finite/fixed-time attitude controls. Finally, several simulation results confirm the robustness and performance of the proposed control framework.

Suggested Citation

  • 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.
    • Handle: RePEc:gam:jmathe:v:11:y:2023:i:1:p:247-:d:1023720
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    References listed on IDEAS

    as
    1. Qijia Yao & Hadi Jahanshahi & Irene Moroz & Naif D. Alotaibi & Stelios Bekiros, 2022. "Neural Adaptive Fixed-Time Attitude Stabilization and Vibration Suppression of Flexible Spacecraft," Mathematics, MDPI, vol. 10(10), pages 1-17, May.
    2. Qijia Yao & Hadi Jahanshahi & Stelios Bekiros & Sanda Florentina Mihalache & Naif D. Alotaibi, 2022. "Indirect Neural-Enhanced Integral Sliding Mode Control for Finite-Time Fault-Tolerant Attitude Tracking of Spacecraft," Mathematics, MDPI, vol. 10(14), pages 1-18, July.
    3. Amin Najafi & Mai The Vu & Saleh Mobayen & Jihad H. Asad & Afef Fekih, 2022. "Adaptive Barrier Fast Terminal Sliding Mode Actuator Fault Tolerant Control Approach for Quadrotor UAVs," Mathematics, MDPI, vol. 10(16), pages 1-22, August.
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    Cited by:

    1. 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.

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