Patent ID: 9139296
Filing Date: 2015-09-22
Classification: B64C

Abstract:
1. A vibration attenuator for a rotor hub of an aircraft, the vibration attenuator comprising: a weight adapted to be mounted to a non-rotating member of the rotor hub of the aircraft, each weight also being adapted to be rotatable about a weight axis of rotation which is perpendicular to a rotor mast axis, wherein the weight is selectively movable for changing a distance between a center of mass of the weight and the weight axis of rotation; and a motor configured to rotate the weight about the axis of rotation at a selected speed during operation; wherein during operation the weight is driven in rotation for creating oscillatory vertical forces along the rotor mast axis for attenuation of rotor-induced vibrations having a selected frequency; and wherein the non-rotating member is stationary relative to an airframe of the aircraft.