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Rotor hub vibration attenuator

  • US 8,424,799 B2
  • Filed: 04/24/2007
  • Issued: 04/23/2013
  • Est. Priority Date: 04/24/2007
  • Status: Active Grant
First Claim
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1. A vibration attenuator for a rotor hub of an aircraft, the rotor hub being configured for being driven in rotation by a mast about an axis of rotation, the vibration attenuator comprising:

  • a first weight adapted to be mounted in a rotating system of a rotor hub of an aircraft, each the first weight also being adapted to be rotatable about an axis of rotation of the hub relative to the hub and motor means for rotating each the first weight about the axis of rotation at a selected speed during operation;

    wherein during operation each the first weight is driven in rotation for creating oscillatory shear forces for attenuation of rotor-induced vibrations having a selected frequency;

    wherein the location of the first weight is selectively movable between an inner radial position and an outer radial position, the location being between a center of mass of the first weight and the axis of rotation, the inner radial position providing minimal shear forces, the outer radial position providing maximum shear forces, the first weight positioned above the rotor hub and mounted on said motor means.

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