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- W4313592395 abstract "AbstractIn this article, we are concerned with a viscoelastic flexible spacecraft subject to undesirable vibrations during attitude maneuvering. The system is composed of a centre body and two symmetric flexible appendages. The problem can be modelled by a set of partial differential equations taking into account therefore the dynamic boundary condition. Under a suitable control force applied at the center body of the spacecraft system, we shall attenuate these vibrations in a fast manner. Namely, we prove the arbitrary stabilisation of the system under appropriate assumptions imposed on the relaxation function. Finally, numerical examples illustrate the effectiveness of the proposed control scheme.Keywords: Vibration controlflexible spacecraft systemviscoelastic dampingPDEsdynamic boundary conditionEuler–Bernoulli beamAMS CLASSIFICATIONS: 35L2093D1593D20 Disclosure statementNo potential conflict of interest was reported by the author(s).Additional informationFundingThis work was supported by the Directorate General for Scientific Research and Technological Development [grant number C00L03UN440120220001]." @default.
- W4313592395 created "2023-01-06" @default.
- W4313592395 creator A5019831900 @default.
- W4313592395 creator A5056919402 @default.
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- W4313592395 date "2023-08-14" @default.
- W4313592395 modified "2023-10-05" @default.
- W4313592395 title "Vibration control of a flexible satellite system with viscoelastic damping" @default.
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- W4313592395 doi "https://doi.org/10.1080/00207179.2023.2165163" @default.
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