Patent ID: 9452828
Filing Date: 2016-09-27
CPC Classification: B64C

Claim Text:
1. A vibration attenuator for an aircraft, the vibration attenuator comprising: an unbalance assembly with a base structure adapted to be mounted to a first member of the aircraft, the unbalance assembly being adapted to be rotatable about a first axis of rotation; a first weight coupled to the base structure and adapted to be rotatable about the first axis of rotation; a second weight coupled to the base structure and configured to be selectively positioned relative to the base structure and the first weight, the second weight selectively positioned relative to the first weight, wherein the second weight is selectively movable for changing the unbalance assembly center-of-mass relative to the first axis of rotation; and a motor configured to rotate the unbalance assembly about the first axis of rotation at a selected speed during operation; wherein during operation the second weight is positioned relative to the first weight so as to vary the unbalance assembly center-of-mass and create vibratory forces along the first axis of rotation for attenuation of rotor-induced vibrations having a selected frequency; and wherein the second weight is selectively movable for changing the unbalance assembly center-of-mass relative to the first axis of rotation.