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