Rotor hub vibration attenuator

Details Rotor hub vibration attenuator Rotor hub vibration attenuator

B - Operations, Transporting

64

C

B64C 27/32 (2006.01) B64C 27/00 (2006.01) F16F 15/10 (2006.01) F16F 15/20 (2006.01) F16F 15/28 (2006.01) F16F 15/36 (2006.01)

Patent

CA 2685025

A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency.

L'atténuateur de vibrations selon l'invention, destiné à un avion, possède au moins un poids monté dans un système de rotation d'un moyeu de rotor de l'avion, chaque poids pouvant tourner autour d'un axe de rotation du moyeu par rapport au moyeu et à chaque autre poids. Des moyens d'entraînement sont prévus afin de faire tourner chaque poids autour de l'axe de rotation à une vitesse choisie afin de créer des forces de cisaillement oscillatoires qui s'opposent et atténuent les vibrations induites par le rotor ayant une fréquence choisie.

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