Vibration Suppression of a Flexible Appendage and Pitch Angle Fuzzy Regulation of a Spacecraft

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Authors Abstract
Content
In this work, the large-angle rotational movement and vibration suppression of a flexible spacecraft are carried out based on an adjustable system. First the spacecraft model is transformed into a canonical affine control form, then two fuzzy systems are used: The first (of Takagi–Sugeno type) estimates the feedback linearization control law as a whole, while the second (of Mamdani type) adjusts and stabilizes the control parameters using the gradient descent technique and based on the minimization of the control error rather than the tracking error. Stability results are presented in terms of Lyapunov’s theory, and simulation tests illustrate the significant transient robustness of the closed-loop system against perturbations, the accurate trajectory control, and vibration suppression of the flexible spacecraft. Consequently, as will be shown later, the error will stay confined and converges quickly to zero, confirming the smoothing property of the proposed method using fuzzy logic systems.
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DOI
https://doi.org/10.4271/01-18-01-0004
Pages
10
Citation
Bahita, M., "Vibration Suppression of a Flexible Appendage and Pitch Angle Fuzzy Regulation of a Spacecraft," SAE Int. J. Aerosp. 18(1):47-56, 2025, https://doi.org/10.4271/01-18-01-0004.
Additional Details
Publisher
Published
Feb 05
Product Code
01-18-01-0004
Content Type
Journal Article
Language
English