US 11,724,800 B2
Vibration attenuator
Frank Bradley Stamps, Colleyville, TX (US); David Heverly, Arlington, TX (US); Michael R. Smith, Colleyville, TX (US); Michael Scott Seifert, Southlake, TX (US); Thomas C Parham, Jr., Colleyville, TX (US); Gary Miller, North Richland Hills, TX (US); Jouyoung Jason Choi, Southlake, TX (US); and Richard E. Rauber, Colleyville, TX (US)
Assigned to Textron Innovations Inc., Providence, RI (US)
Filed by Textron Innovations Inc., Providence, RI (US)
Filed on Jan. 3, 2022, as Appl. No. 17/567,874.
Application 17/567,874 is a division of application No. 16/197,761, filed on Nov. 21, 2018, granted, now 11,214,361.
Prior Publication US 2022/0126989 A1, Apr. 28, 2022
Int. Cl. B64C 27/00 (2006.01)
CPC B64C 27/001 (2013.01) [B64C 2027/003 (2013.01); B64C 2027/005 (2013.01)] 14 Claims
OG exemplary drawing
 
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.