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公开(公告)号：US11235858B2
公开(公告)日：2022-02-01
申请号：US16035397
申请日：2018-07-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Troy Cyril Schank , Andrew Ryan Maresh , Chyau-Song Tzeng
Abstract: A mechanism for folding a rotor blade that is rotatably coupled to a blade cuff about a blade-fold axis between an extended position and a folded position. The mechanism includes a swash plate configured to translate relative to a mast, a pitch link rotatably coupled to the swash plate, a pitch horn rotatably coupled to the pitch link, a crank coupled to the pitch horn, and a link rotatably coupled to the crank and rotatably coupled to the rotor blade. The pitch horn and the crank being configured to commonly rotate relative to the blade cuff about a crank axis in response to translation of the swash plate, wherein the crank axis passes through the blade cuff.
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公开(公告)号：US11623742B2
公开(公告)日：2023-04-11
申请号：US16372289
申请日：2019-04-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Ryan Maresh , Christopher Edward Foskey
Abstract: An elastomeric bearing assembly has a housing, a centrifugal force bearing axially captured relative to the housing, and a sliding cap disposed between the housing and the centrifugal force bearing.
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公开(公告)号：US10807705B2
公开(公告)日：2020-10-20
申请号：US15469463
申请日：2017-03-24
Applicant: Bell Helicopter Textron Inc.
Inventor： Drew A. Sutton , Mark E. Wasikowski , Andrew Ryan Maresh , Nolan B. Phillips
IPC: B64C27/00 , B64C27/473
Abstract: In one embodiment, a rotor blade may comprise a blade body, a spar structure, and a blade nose. The blade body may comprise a skin, wherein the skin is configured to form an airfoil shape, and wherein the airfoil shape comprises an inboard end, an outboard end, a leading edge, and a trailing edge. The spar structure may comprise a first spar cap and a second spar cap, wherein the first spar cap is coupled to an upper portion of the skin, and wherein the second spar cap is coupled to a lower portion of the skin. The blade nose may comprise a cavity, wherein the cavity is configured to house a plurality of modular weights at a plurality of radial blade locations, wherein the plurality of radial blade locations comprises a range of locations between the inboard end and the outboard end.
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公开(公告)号：US20190300164A1
公开(公告)日：2019-10-03
申请号：US16372289
申请日：2019-04-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Ryan Maresh , Christopher Edward Foskey
Abstract: An elastomeric bearing assembly has a housing, a centrifugal force bearing axially captured relative to the housing, and a sliding cap disposed between the housing and the centrifugal force bearing.
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Patent Agency Ranking
公开(公告)号：US20190077502A1
公开(公告)日：2019-03-14
申请号：US15699677
申请日：2017-09-08
Applicant: Bell Helicopter Textron Inc.
Inventor： Jason C. Owens , Frank B. Stamps , Andrew Paul Haldeman , Robert P. Wardlaw , John R. McCullough , Gary Miller , Andrew Ryan Maresh , Drew A. Sutton
Abstract: In one embodiment, a rotor hub comprises a hub plate, a yoke for attaching a plurality of rotor blades, a plurality of yoke support bearings, and a plurality of cushioned damper bearings for attaching a plurality of dampers.
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公开(公告)号：US20180273163A1
公开(公告)日：2018-09-27
申请号：US15469463
申请日：2017-03-24
Applicant: Bell Helicopter Textron Inc.
Inventor： Drew A. Sutton , Mark E. Wasikowski , Andrew Ryan Maresh , Nolan B. Phillips
IPC: B64C27/00 , B64C27/473
Abstract: In one embodiment, a rotor blade may comprise a blade body, a spar structure, and a blade nose. The blade body may comprise a skin, wherein the skin is configured to form an airfoil shape, and wherein the airfoil shape comprises an inboard end, an outboard end, a leading edge, and a trailing edge. The spar structure may comprise a first spar cap and a second spar cap, wherein the first spar cap is coupled to an upper portion of the skin, and wherein the second spar cap is coupled to a lower portion of the skin. The blade nose may comprise a cavity, wherein the cavity is configured to house a plurality of modular weights at a plurality of radial blade locations, wherein the plurality of radial blade locations comprises a range of locations between the inboard end and the outboard end.
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公开(公告)号：US20190047692A1
公开(公告)日：2019-02-14
申请号：US16051343
申请日：2018-07-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Troy Cyril Schank , Andrew Ryan Maresh , Chyau-Song Tzeng
Abstract: A propulsion assembly for a rotorcraft includes a mast and a proprotor hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast. The proprotor hub assembly includes a hook receiver. The propulsion assembly includes a gimbal lock positioned about the mast. The gimbal lock includes a locking ring and a gimbal lock hook. The gimbal lock is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. The gimbal lock enables the gimballing degree of freedom in the disengaged position and disables the gimballing degree of freedom in the engaged position. The gimbal lock hook is hooked to the hook receiver in the engaged position to secure the locking ring to the proprotor hub assembly.
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公开(公告)号：US20190047691A1
公开(公告)日：2019-02-14
申请号：US16051334
申请日：2018-07-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Troy Cyril Schank , Andrew Ryan Maresh , Chyau-Song Tzeng
Abstract: A propulsion assembly for a rotorcraft includes a mast and a proprotor hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast. The propulsion assembly includes a gimbal lock assembly positioned about the mast and including a plurality of radially outwardly extending and circumferentially distributed rollers. The gimbal lock assembly is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. In the disengaged position, the gimbal lock assembly enables the gimballing degree of freedom. In the engaged position, the rollers of the gimbal lock assembly contact the proprotor hub assembly to disable the gimballing degree.
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公开(公告)号：US20190016441A1
公开(公告)日：2019-01-17
申请号：US16035397
申请日：2018-07-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Troy Cyril Schank , Andrew Ryan Maresh , Chyau-Song Tzeng
Abstract: A mechanism for folding a rotor blade that is rotatably coupled to a blade cuff about a blade-fold axis between an extended position and a folded position. The mechanism includes a swash plate configured to translate relative to a mast, a pitch link rotatably coupled to the swash plate, a pitch horn rotatably coupled to the pitch link, a crank coupled to the pitch horn, and a link rotatably coupled to the crank and rotatably coupled to the rotor blade. The pitch horn and the crank being configured to commonly rotate relative to the blade cuff about a crank axis in response to translation of the swash plate, wherein the crank axis passes through the blade cuff.
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