A mathematic rotating blade model is established with periodic time-varying aerodynamic load, which is simulated by Beddoes-Leishman dynamic stall model. The consequent aeroelastic model is utilized to analyze blade dynamics and design control strategy for blade flutter suppression application. Aeroelastic stability of rotating blade is indicated by open-loop simulation test for critical flutter speed study. It was found that designed Adaptive Controller is capable of restraining flutter vibration with trailing-edge flap, and its robustness and effectiveness are shown by closed-loop tests with a wide range of aerodynamic loads. The stability analysis presents that the stability of the given Adaptive Controller, proved theoretically by Adaptive Stability Theorem.
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