Robust Control Design in a Non-Smooth H_{\inftny} / µ Setting for Spacecraft Microvibration Attenuation

Abstract : The paper addresses the problem of mixed active-passive microvibration mitigation solution able to attenuate the vibrations generated by reaction wheels to the satellite structure. From an uncertain Linear Fractional Transformation (LFT) satellite model, preliminary results obtained to the aforementionned issue are introduced. The design of the microvibration mitigation solution is formulated into the H_{\inftny}/µ framework leading to a robust H_{\inftny} control strategy capable of achieving active attenuation performance across a wide range of reaction wheel speeds. An analysis procedure based on the structured singular value µ is used to assess the robust stability and nominal performance of the microvibration itigation strategy. Time domain simulations based on a representative benchmark provided by the European Space Agency (ESA) and Airbus Defence and Space are included to highlight the potential of the proposed solution.
Type de document :
Communication dans un congrès
10th International ESA Conference on Guidance, Navigation & Control Systems, May 2017, Salzburg, Austria. 2017
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https://hal.archives-ouvertes.fr/hal-01491173
Contributeur : Jérome Cieslak <>
Soumis le : jeudi 16 mars 2017 - 14:36:39
Dernière modification le : mercredi 28 mars 2018 - 13:20:02

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  • HAL Id : hal-01491173, version 1

Citation

Valentin Preda, Jérôme Cieslak, David Henry, Samir Bennani, Alexandre Falcoz. Robust Control Design in a Non-Smooth H_{\inftny} / µ Setting for Spacecraft Microvibration Attenuation. 10th International ESA Conference on Guidance, Navigation & Control Systems, May 2017, Salzburg, Austria. 2017. 〈hal-01491173〉

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