公开(公告)号：US10450059B2

公开(公告)日：2019-10-22

申请号：US15882573

申请日：2018-01-29

Applicant: Bell Helicopter Textron Inc.

Inventor： Kyle Thomas Cravener ,  Tyler Wayne Baldwin ,  Nicholas Allen Torske

IPC: B64C27/33 ,  B64C27/35 ,  B64C27/48 ,  B64C27/32 ,  B64C27/50 ,  B64C29/00

Abstract: A multi-piece inboard beam assembly for use in a rotor blade assembly of a rotorcraft. The inboard beam assembly includes an inboard beam connected to an inboard beam fitting with an anti-rotational connection. The inboard beam is connected to a yoke via bearings and the inboard beam fitting is connected to a grip in a double shear condition. In use, the grip, the inboard beam fitting with the double shear connection, the inboard beam, a centrifugal force bearing held by the inboard beam, and the yoke carry the centrifugal force created upon rotation of the rotor blade assembly.

公开(公告)号：US20190277343A1

公开(公告)日：2019-09-12

申请号：US15916134

申请日：2018-03-08

Applicant: Bell Helicopter Textron Inc.

Inventor： Tyler Wayne Baldwin ,  Ryan T. Ehinger ,  Jared Mark Paulson ,  Michael Christopher Burnett ,  Kyle Thomas Cravener

IPC: F16D3/62 ,  B64C11/02 ,  F16C7/04

Abstract: A link includes an outer composite portion substantially encircling at least two bearing pockets and a central substantially incompressible portion disposed between the at least two bearing pockets.

公开(公告)号：US20190017543A1

公开(公告)日：2019-01-17

申请号：US15698796

申请日：2017-09-08

Applicant: Bell Helicopter Textron Inc.

Inventor： Glenn Alan Shimek ,  Amarjit Olenchery Kizhakkepat ,  Ken Shundo ,  Michael Dean Dearman ,  Kyle Thomas Cravener ,  Michael Christopher Burnett

IPC: F16C27/06 ,  B64C29/00

Abstract: A bearing assembly for coupling a proprotor blade to a yoke in a proprotor system. The bearing assembly is positionable within an inboard pocket of a blade arm of the yoke. The proprotor system is operable for use on a tiltrotor aircraft having helicopter and airplane flight modes. The bearing assembly includes a centrifugal force bearing and a shear bearing having an inboard beam coupled therebetween. The centrifugal force bearing has a mating surface, a lateral movement constraint feature and at least one radially extending anti-rotation feature. The inboard beam has a mating surface in a contact relationship with the mating surface of the centrifugal force bearing, a lateral movement constraint feature operably associated with the lateral movement constraint feature of the centrifugal force bearing and at least one radially extending anti-rotation feature that corresponds with the at least one radially extending anti-rotation feature of the centrifugal force bearing.

公开(公告)号：US20190016454A1

公开(公告)日：2019-01-17

申请号：US15648650

申请日：2017-07-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Kyle Thomas Cravener ,  Amarjit Kizhakkepat ,  Ken Shundo ,  Jared Mark Paulson ,  Tyler Wayne Baldwin

IPC: B64C29/00 ,  F16C23/04 ,  F16C27/02 ,  F16C33/20

CPC classification number: B64C29/0033 ,  B64C27/35 ,  B64C27/54 ,  F16C23/045 ,  F16C27/02 ,  F16C27/063 ,  F16C33/203 ,  F16C33/22 ,  F16C2326/43

Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a yoke having a plurality of blade arms with inboard pockets. A centrifugal force and shear bearing assembly is disposed in each of the inboard pockets of the yoke. Each of a plurality of proprotor blades is coupled to the yoke by one of the bearing assemblies such that each proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point. Each bearing assembly includes a centrifugal force bearing coupled to the yoke, a shear bearing coupled to the yoke and an inboard beam coupled between the centrifugal force bearing and the shear bearing. Each inboard beam is coupled to a respective proprotor blade.

公开(公告)号：US20180155015A1

公开(公告)日：2018-06-07

申请号：US15372072

申请日：2016-12-07

Applicant: Bell Helicopter Textron Inc.

Inventor： Terry K. Thompson ,  Kyle Thomas Cravener

IPC: B64C27/00 ,  B64C27/57

CPC classification number: B64C27/008 ,  B64C27/57

Abstract: The present invention includes an apparatus and method for automatically adjusting the tracking of one or more blades comprising: a blade tracking adjustment mechanism connected to one or more blades of an aircraft; a blade tracking measurement system that measures the tracking of the one or more blades; and a computer that receives an output from the blade tracking measurement system with tracking information for each of the one or more blades; wherein the computer outputs instructions for the blade tracking adjustment mechanism to change a pitch of one or more of the blades to correct blade tracking.