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THE development and implementation of passive and active feedback control capabilities in aerospace are current topics of research with many practical applications. In particular, active flutter suppression mechanisms are recently emerging as promising technologies aimed at providing solution for a large class of problems for aeronautical and aerospace flight vehicles that are prone to aeroelastic instabilities. Such instabilities can yield instantaneous catastrophic failure, eg, flutter, or structural fatigue failure, due to persistent oscillations, eg, limit cycle oscillations (LCOs)[1]. Dynamic aeroelastic effects may provide critical constraints on the flight vehicle performance, therefore, control strategies need to be implemented to safely perform maneuvers at the limit of the flight envelope. While aeroelastic instabilities can be postponed, providing an expansion of the flight envelope, by increasing the stiffness of the

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