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公开(公告)号：US10232932B2
公开(公告)日：2019-03-19
申请号：US15466825
申请日：2017-03-22
Applicant: Bell Helicopter Textron Inc.
Abstract: A high stiffness hub assembly for a proprotor system operable to rotate with a mast of a tiltrotor aircraft having helicopter and airplane flight modes. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has four blade arms each adapted to hold a proprotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, four drive links and four pillow blocks. The trunnion assembly is coupled to the mast and has four outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate with two connection members that extend through the yoke and the pillow block.
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公开(公告)号：US20190002078A1
公开(公告)日：2019-01-03
申请号：US15638345
申请日：2017-06-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Clement Parham, Jr. , Jeffrey Bosworth , Gary Miller , Frank Bradley Stamps , Jouyoung Jason Choi , Paul K. Oldroyd , Richard Erler Rauber , Michael Scott Seifert
Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes an outer skin and a damping sublayer, the damping sublayer interposed between the outer skin and the wing airframe core assembly. The tiltrotor aircraft includes a pylon assembly subject to aeroelastic movement during forward flight. The wing is subject to deflection in response to the aeroelastic movement of the pylon assembly. The damping sublayer reduces the deflection of the wing, thereby stabilizing the wing during forward flight
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公开(公告)号：US20180273160A1
公开(公告)日：2018-09-27
申请号：US15466825
申请日：2017-03-22
Applicant: Bell Helicopter Textron Inc.
IPC: B64C11/34 , B64C29/00 , B64C11/00 , B64C27/605
CPC classification number: B64C11/34 , B64C11/008 , B64C27/605 , B64C29/0033
Abstract: A high stiffness hub assembly for a proprotor system operable to rotate with a mast of a tiltrotor aircraft having helicopter and airplane flight modes. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has four blade arms each adapted to hold a proprotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, four drive links and four pillow blocks. The trunnion assembly is coupled to the mast and has four outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate with two connection members that extend through the yoke and the pillow block.
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公开(公告)号：US20180162520A1
公开(公告)日：2018-06-14
申请号：US15375394
申请日：2016-12-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Frank Bradley Stamps , Jouyoung Jason Choi , Thomas Clement Parham, JR. , Gary Miller , Richard Erler Rauber
Abstract: A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of blade support assemblies coupling the proprotor blades with the hub. Each blade support assembly includes a flapping bearing coupled to the hub and a yoke having first and second longitudinal sections with outboard grip members and an inboard arcuate section connecting the first and second longitudinal sections and coupled to the flapping bearing. A lead-lag damper is coupled between the hub and an inboard station of the respective proprotor blade. A twist shank is coupled between the outboard grip members of the yoke and an outboard station of the respective the proprotor blade. The twist shank defines a virtual lead-lag hinge outboard of the yoke and coincident with the respective pitch change axis.
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公开(公告)号：US10392098B2
公开(公告)日：2019-08-27
申请号：US16289438
申请日：2019-02-28
Applicant: Bell Helicopter Textron Inc.
IPC: B63H1/06 , B64C11/34 , B64C29/00 , B64C27/605 , B64C27/41 , B64C11/00 , F16D3/62 , B64C27/473
Abstract: A high stiffness hub assembly for a rotor system operable to rotate with a mast of a rotorcraft. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has a plurality of blade arms each configured to hold a rotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, a plurality of drive links and a plurality of pillow blocks. The trunnion assembly is coupled to the mast and has a plurality of outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate.
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Patent Agency Ranking
公开(公告)号：US20190193836A1
公开(公告)日：2019-06-27
申请号：US16289438
申请日：2019-02-28
Applicant: Bell Helicopter Textron Inc.
IPC: B64C11/34 , B64C27/605 , B64C29/00 , B64C11/00
CPC classification number: B64C11/34 , B64C11/008 , B64C27/41 , B64C27/605 , B64C29/0033 , B64C2027/4736
Abstract: A high stiffness hub assembly for a rotor system operable to rotate with a mast of a rotorcraft. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has a plurality of blade arms each configured to hold a rotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, a plurality of drive links and a plurality of pillow blocks. The trunnion assembly is coupled to the mast and has a plurality of outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate.
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公开(公告)号：US20180162526A1
公开(公告)日：2018-06-14
申请号：US15375367
申请日：2016-12-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Clement Parham, JR. , Jouyoung Jason Choi , Gary Miller , Frank Bradley Stamps , Richard Erler Rauber
CPC classification number: B64C29/0033 , B64C27/41 , B64C27/51 , B64C27/54
Abstract: A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub about a flapping axis and independently change pitch about a pitch change axis. The proprotor blades have a first in-plane frequency less than 1.0/rev.
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公开(公告)号：US20180162519A1
公开(公告)日：2018-06-14
申请号：US15375385
申请日：2016-12-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Clement Parham, JR. , Jouyoung Jason Choi , Gary Miller , Frank Bradley Stamps , Richard Erler Rauber
Abstract: A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of loop yokes, each coupling one of the proprotor blades with the hub and each including first and second longitudinal sections extending between inboard and outboard arcuate sections and a bearing assembly disposed between the inboard and outboard arcuate sections of each loop yoke. Each bearing assembly includes a flapping bearing disposed generally within the inboard arcuate section of the respective loop yoke and coupled to the hub, a lead-lag damper coupled to the hub, a centrifugal force bearing disposed generally within the outboard arcuate section of the respective loop yoke and a blade anchor coupled between the lead-lag damper and the centrifugal force bearing. The blade anchor is also coupled to the respective proprotor blade.
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公开(公告)号：US20180162518A1
公开(公告)日：2018-06-14
申请号：US15375356
申请日：2016-12-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Clement Parham, JR. , Jouyoung Jason Choi , Gary Miller , Frank Bradley Stamps , Richard Erler Rauber
Abstract: A yoke for providing a centrifugal force retention load path between a proprotor blade and a hub of a soft-in-plane proprotor system operable for use on a tiltrotor aircraft. The yoke includes a continuous loop having a longitudinal axis and first and second longitudinal sections extending between inboard and outboard arcuate sections. A flapping bearing receiving region is disposed at least partially within the inboard arcuate section to an interior of the continuous loop. A centrifugal force bearing receiving region is disposed at least partially within the outboard arcuate section to the interior of the continuous loop. The continuous loop is formed from a composite material having a plurality of double bias material plies and a plurality of unidirectional material plies such that the number of unidirectional material plies is greater than the number of double bias material plies.
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公开(公告)号：US20180141654A1
公开(公告)日：2018-05-24
申请号：US15355347
申请日：2016-11-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Gary Miller , Richard Erler Rauber , Thomas Clement Parham, JR. , Alan Carl Ewing , Frank Bradley Stamps
IPC: B64C29/00 , B64C27/41 , B64C27/54 , B64C27/473
Abstract: A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.
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