A time domain adaptive control algorithm is developed to reduce hub vibration of a dissimilar rotor. The control strategy can be implemented using smart material actuated on-blade trailing edge flaps. Each flap is controlled individually, optimally taking into account blade dissimilarities and damages. The controller is tested using a comprehensive rotor aeroelastic analysis. The analysis includes dissimilar blade modeling and accounts for aerodynamic and inertial effects of trailing edge flaps. The controller successfully reduces all harmonics of the hub loads arising out of blade dissimilarities. Significant improvements in vibration reduction are predicted using the present individual control method as coin-pared to a classical control method. A 98% reduction is achieved for a. single targeted load, and at least 40% for all six hub vibratory loads for a combined objective function. In all cases, trailing edge flap deflections are limited to +-4°.
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