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公开(公告)号：US11001369B2
公开(公告)日：2021-05-11
申请号：US15942707
申请日：2018-04-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Tyler Wayne Baldwin , Michael Dearman
IPC: B64C11/04 , F16D3/60 , F16D1/10 , B64F5/10 , B64C29/00 , B29C70/84 , B29L31/00 , B22D25/02 , B29K705/00
Abstract: A light weight hybrid torque transfer joint trunnion has an integral metal hub spline fitting oriented on a center axis. This integral metal hub spline fitting may be made of steel, aluminum, titanium, or the like and may be generally cylindrical. The integral metal hub spline fitting defines an integral central internally-splined mast or driveshaft coupling opening centered about the center axis. A composite material body centrally retains, and is cured to, the metal hub spline fitting. Torque transfer joint link attachment pins extend from the composite material body and are rigidly linked to the metal hub spline fitting. In an example constant-velocity joint, a plurality of pivoting linkages may each be rotatably coupled to the torque transfer joint link attachment pins, and each of the plurality of pivoting linkages may, in turn be secured to a rotor yoke configured to mount a plurality of rotorcraft blades.
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公开(公告)号：US10556676B2
公开(公告)日：2020-02-11
申请号：US15881980
申请日：2018-01-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Tyler Wayne Baldwin , Kyle Thomas Cravener
Abstract: A hybrid yoke including a center and yoke arms connected to flexure arms. An inboard centrifugal force bearing assembly connects to the yoke arm and a grip and an outboard shear bearing assembly connects to the flexure arm and the grip. In use, the center and yoke arms carry the centrifugal force at a position inboard of the flexure arm.
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公开(公告)号：US20200039633A1
公开(公告)日：2020-02-06
申请号：US16055121
申请日：2018-08-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Kyle Thomas Cravener , Tyler Wayne Baldwin , Jared Mark Paulson
Abstract: A rotor blade locking assembly for locking a rotor blade in a deployed position. The rotor blade locking assembly comprises a locking mechanism configured to be coupled to a blade grip. The locking mechanism comprises a latch and an actuator configured to cause the latch to move between an unlocked position and a locked position. The assembly comprises a locking plate configured to be coupled to the rotor blade. The locking plate comprises a bearing surface configured to bear against a contact surface of the latch, when the latch is in the locked position.
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公开(公告)号：US10543913B2
公开(公告)日：2020-01-28
申请号：US15882287
申请日：2018-01-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Tyler Wayne Baldwin , Kyle Thomas Cravener , Andrew Maresh
Abstract: A tri-hybrid yoke including a center ring connected to a CF fitting connected to flexure arms. An inboard centrifugal force bearing assembly connects to the CF fitting and a grip. An outboard shear bearing assembly connects to the flexure arm and the grip. In use, the center ring and the CF fittings carry the centrifugal force at a position inboard of the flexure arm.
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公开(公告)号：US20190185142A1
公开(公告)日：2019-06-20
申请号：US15845967
申请日：2017-12-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Tyler Wayne Baldwin , Kyle Thomas Cravener
Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
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Patent Agency Ranking
公开(公告)号：US20170217595A1
公开(公告)日：2017-08-03
申请号：US15409971
申请日：2017-01-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Tyler Wayne Baldwin , John Elton Brunken, JR. , Matthew Carl VanBuskirk , Bart Marcus Shafer , Bruce Bennett Bacon
CPC classification number: B64D27/26 , B64C27/28 , B64C29/0033 , B64D27/12 , B64D2027/262
Abstract: An engine mount assembly for coupling an engine to an airframe includes a torsion bar, a lateral movement control assembly and a vertical movement control assembly. The torsion bar has a torsional stiffness and is coupled between the engine and the airframe such that torsional movement of the engine causes torsion in the torsion bar. The lateral movement control assembly has a lateral stiffness and is coupled between the torsion bar and the airframe such that lateral movement of the engine causes rotation of the torsion bar which reacts on lateral movement control assembly. The vertical movement control assembly has a vertical stiffness and is coupled between the engine and the airframe such that vertical movement of the engine reacts on the vertical movement control assembly. The engine mount assembly, thereby enables torsional, lateral and vertical movement of the engine to be independently controlled.
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公开(公告)号：US11097837B2
公开(公告)日：2021-08-24
申请号：US16004689
申请日：2018-06-11
Applicant: Bell Helicopter Textron Inc.
Inventor： Tyler Wayne Baldwin , Kyle Thomas Cravener
Abstract: A gimbal joint may employ a plurality of wear sleeves, each disposed between a pin or pin receptive bore of a first structure and a corresponding bore or pin of a second structure and between another pin or bore of the second structure and a corresponding bore or pin of a third structure. Each of these structures may be adapted to rotate in a single plane, with one structure adapted to also tilt about a first axis, and one other structure adapted to tilt about a second axis. Each integral flanged wear sleeve may comprise a right circular hollow cylindrical body portion, which may be interiorly sized to be retained on one of the pins and externally sized to be retained in one of the pin receptive bores, and a flange portion may radiate from one end of the cylindrical body portion.
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公开(公告)号：US11009080B2
公开(公告)日：2021-05-18
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
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.
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公开(公告)号：US10703460B2
公开(公告)日：2020-07-07
申请号：US15845967
申请日：2017-12-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Tyler Wayne Baldwin , Kyle Thomas Cravener
Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
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公开(公告)号：US10472059B2
公开(公告)日：2019-11-12
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
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.
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