公开(公告)号：US11724800B2

公开(公告)日：2023-08-15

申请号：US17567874

申请日：2022-01-03

Applicant: Textron Innovations Inc.

Inventor： Frank Bradley Stamps ,  David Heverly ,  Michael R. Smith ,  Michael Scott Seifert ,  Thomas C Parham, Jr. ,  Gary Miller ,  Jouyoung Jason Choi ,  Richard E. Rauber

IPC: B64C27/00

CPC classification number: B64C27/001 ,  B64C2027/003 ,  B64C2027/005

Abstract: A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has 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 are 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. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly 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.

公开(公告)号：US09878782B2

公开(公告)日：2018-01-30

申请号：US14623615

申请日：2015-02-17

Applicant: TEXTRON INNOVATIONS INC.

Inventor： Frank B. Stamps ,  Patrick R. Tisdale ,  Tom Donovan ,  Richard E. Rauber

IPC: B64C27/35 ,  B64C27/33 ,  B64C27/32 ,  B64C27/39 ,  B64C27/48

CPC classification number: B64C27/35 ,  B64C27/32 ,  B64C27/33 ,  B64C27/39 ,  B64C27/48

Abstract: A rotor assembly for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto. The arms provide for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing associated with each arm is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.

公开(公告)号：US20220126989A1

公开(公告)日：2022-04-28

申请号：US17567874

申请日：2022-01-03

Applicant: Textron Innovations Inc.

Inventor： Frank Bradley Stamps ,  David Heverly ,  Michael R. Smith ,  Michael Scott Seifert ,  Thomas C. Parham, JR. ,  Gary Miller ,  Jouyoung Jason Choi ,  Richard E. Rauber

IPC: B64C27/00

Abstract: A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has 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 are 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. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly 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.