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Attitude Control of a Flexible Spacecraft via Fuzzy Optimal Variance Technique

Author

Listed:
  • Chokri Sendi

    (Department of Mechanical Engineering, College of Engineering, University of Alaska Anchorage, Anchorage, AK 99508, USA)

Abstract

This paper investigates the performance of a fuzzy optimal variance control technique for attitude stability and vibration attenuation with regard to a spacecraft made of a rigid platform and multiple flexible appendages that can be retargeted to the line of sight. The proposed technique addresses the problem of actuators’ amplitude and rate constraints. The fuzzy model of the spacecraft is developed based on the Takagi-Sugeno(T-S) fuzzy model with disturbances, and the control input is designed using the Parallel Distributed Compensation technique (PDC). The problem is presented as an optimization problem in the form of Linear Matrix Inequalities (LMIs). The performance and the stability of the proposed controller are investigated through numerical simulation.

Suggested Citation

  • Chokri Sendi, 2022. "Attitude Control of a Flexible Spacecraft via Fuzzy Optimal Variance Technique," Mathematics, MDPI, vol. 10(2), pages 1-17, January.
    • Handle: RePEc:gam:jmathe:v:10:y:2022:i:2:p:179-:d:719751
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    Citations

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    Cited by:

    1. Stepan Tkachev & Alexey Shestoperov & Anna Okhitina & Anna Nuralieva, 2023. "Attitude Stabilization of a Satellite with Large Flexible Elements Using On-Board Actuators Only," Mathematics, MDPI, vol. 11(24), pages 1-24, December.
    2. 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.

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