Research on the Mechanism of Vibration of the Helicopter in Low Advance Ratio
This paper addressed the mechanism of high vibration level of the helicopter in low ad-vance ratio.The blade-vortex interaction characteristics of the blade aerodynamics were obtained by free wake model.This paper derived the 4-DOF element matrixes of the blade structure for the blade modal analysis and parametric study,the blade flap dynamics was established based on the prescribed air loads.The results showed that the blade-vortex interaction was the external source of the vibration,and concentrated mass near the blade root was the inner root of the vibration.
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