Adaptive variable structure controller for spacecraft vibration reduction

Qinglei Hu; Guangfu Ma

doi:10.1109/TAES.2008.4655349

Adaptive variable structure controller for spacecraft vibration reduction

Qinglei Hu^*
, Guangfu Ma

^*Corresponding author for this work

Harbin Institute of Technology

Research output: Contribution to journal › Article › peer-review

42 Scopus citations

Abstract

A hybrid control scheme to vibration reduction of flexible spacecraft is presented by using a variable structure technique for attitude control and piezoelectric materials for active vibration suppression. The attitude controller consists of a linear feedback term and a discontinuous feedback ones. An adaptive version of the proposed attitude controller is also achieved through releasing the limitation of knowing the bounds of the lumped perturbations in advance. An additional independent control system acting on the flexible parts can be designed for further vibration suppression. Simulation results have shown the theoretical and practical merit of this approach.

Original language	English
Pages (from-to)	861-876
Number of pages	16
Journal	IEEE Transactions on Aerospace and Electronic Systems
Volume	44
Issue number	3
DOIs	https://doi.org/10.1109/TAES.2008.4655349
State	Published - 2008
Externally published	Yes

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10.1109/TAES.2008.4655349

Cite this

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title = "Adaptive variable structure controller for spacecraft vibration reduction",

abstract = "A hybrid control scheme to vibration reduction of flexible spacecraft is presented by using a variable structure technique for attitude control and piezoelectric materials for active vibration suppression. The attitude controller consists of a linear feedback term and a discontinuous feedback ones. An adaptive version of the proposed attitude controller is also achieved through releasing the limitation of knowing the bounds of the lumped perturbations in advance. An additional independent control system acting on the flexible parts can be designed for further vibration suppression. Simulation results have shown the theoretical and practical merit of this approach.",

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year = "2008",

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language = "英语",

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AU - Ma, Guangfu

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N2 - A hybrid control scheme to vibration reduction of flexible spacecraft is presented by using a variable structure technique for attitude control and piezoelectric materials for active vibration suppression. The attitude controller consists of a linear feedback term and a discontinuous feedback ones. An adaptive version of the proposed attitude controller is also achieved through releasing the limitation of knowing the bounds of the lumped perturbations in advance. An additional independent control system acting on the flexible parts can be designed for further vibration suppression. Simulation results have shown the theoretical and practical merit of this approach.

AB - A hybrid control scheme to vibration reduction of flexible spacecraft is presented by using a variable structure technique for attitude control and piezoelectric materials for active vibration suppression. The attitude controller consists of a linear feedback term and a discontinuous feedback ones. An adaptive version of the proposed attitude controller is also achieved through releasing the limitation of knowing the bounds of the lumped perturbations in advance. An additional independent control system acting on the flexible parts can be designed for further vibration suppression. Simulation results have shown the theoretical and practical merit of this approach.

UR - https://www.scopus.com/pages/publications/55349097516

U2 - 10.1109/TAES.2008.4655349

DO - 10.1109/TAES.2008.4655349

M3 - 文章

AN - SCOPUS:55349097516

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SP - 861

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JO - IEEE Transactions on Aerospace and Electronic Systems

JF - IEEE Transactions on Aerospace and Electronic Systems

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Adaptive variable structure controller for spacecraft vibration reduction

Abstract

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