CPC B64C 27/001 (2013.01) [B64C 2027/003 (2013.01); B64C 2027/005 (2013.01)] | 14 Claims |
1. A vibration attenuator for an aircraft having a rotor rotatable about a mast axis, the attenuator comprising:
upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis, the weight assemblies being configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis; and
a first motor configured for selective translation of one of the weight assemblies relative to the other of the weight assemblies along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.
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