Abstract
The research work considered in this paper draws expertise from the European Space Agency, Airbus Defence & Space and the IMS laboratory, on mixed active-passive control strategy for mitigating the micro-vibrations induced by the reaction wheels in a flexible spacecraft structure. High frequency disturbances are handled using passive isolation, based on elastomer devices, while an active control strategy is used to mitigate the micro-vibrations, in the low frequency range. The control strategy proposed in this paper, is based on H∞ LPV synthesis and handles robust stability and performance specifications. Different LPV synthesis approaches are also investigated. The results are compared by means of different H∞-oriented criteria and simulation results demonstrate the potential of the proposed methods.
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