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公开(公告)号：US20230194312A1
公开(公告)日：2023-06-22
申请号：US17555104
申请日：2021-12-17
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas Cravener , Patrick Smith , Troy Cyril Schank , Brady Garrett Atkins , Kynn Jerald Schulte
IPC: G01D5/16
Abstract: A rotor-hub-flap anisotropic-sensor system includes a rotor hub, a plurality of anisotropic-sensor arrangements interoperably coupled to the rotor hub and operable to measure flapping of the rotor hub, a plurality of rotor blades connected to the rotor hub, and at least one flight control computer interoperably coupled to the plurality of anisotropic-sensor arrangements.
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公开(公告)号：US20230118750A1
公开(公告)日：2023-04-20
申请号：US17503736
申请日：2021-10-18
Applicant: Bell Textron Inc.
Inventor： Bryan Kenneth Baskin , Kyle Thomas Cravener , Andrew Ryan Maresh
Abstract: A teeter flap lock for an aircraft may include at least one pair of diametrically positioned teeter flap lock plates extending from a rotor teetering hinge, spaced apart from a rotor mast of the aircraft. A teeter flap lock block is positioned about the rotor mast and is configured to fit between the teeter flap lock plates and the rotor mast. The teeter flap lock block fits between and contacts the teeter flap lock plates in an engaged position, and is movable between the engaged position and a disengaged position relative to the teeter flap lock plates. The teeter flap lock enables flapping of rotors coupled to the rotor mast via the teetering hinge when the teeter flap lock block is in the disengaged position and disables flapping of the rotors when the teeter flap lock block is in the engaged position.
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公开(公告)号：US11511848B2
公开(公告)日：2022-11-29
申请号：US16879114
申请日：2020-05-20
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas Cravener , Andrew Ryan Maresh , Brady Garrett Atkins , Kynn J. Schulte , Troy Schank
Abstract: Embodiments are directed to a blade lock comprising a fold lock adapted to prevent folding of a rotor blade in a fold-lock position and to allow folding of the rotor blade in a pitch-lock position. The blade lock further comprises a pitch lock adapted to allow pitch movement of a rotor blade in a fold-lock position and to prevent pitch movement of the rotor blade in the pitch-lock position. A spring-loaded link pivotally connects both the fold lock and the pitch lock and is adapted to provide passive, overcenter locking in the fold-lock position. An actuator is coupled to the pitch lock and is adapted to move the pitch lock and the fold lock between the fold-lock and pitch-lock positions.
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公开(公告)号：US20210371094A1
公开(公告)日：2021-12-02
申请号：US17396095
申请日：2021-08-06
Applicant: Bell 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：US20210269148A1
公开(公告)日：2021-09-02
申请号：US16804357
申请日：2020-02-28
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas Cravener
Abstract: Embodiments are directed to a propulsion assembly for an aircraft. The propulsion assembly comprises a mast, a hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast, the hub assembly having an inner hub wall spaced part from the mast, a gimbal lock positioned about the mast, the gimbal lock configured to fit between the inner hub wall and the mast in an engaged position, and an over-center locking mechanism coupled to the gimbal lock. The gimbal lock is movable between a disengaged position and the engaged position relative to the 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 over-center locking mechanism is configured to move the gimbal lock between the engaged position and the disengaged position.
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Patent Agency Ranking
公开(公告)号：US11591069B1
公开(公告)日：2023-02-28
申请号：US17554949
申请日：2021-12-17
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas Cravener
Abstract: A system for retaining a folded proprotor blade in flight. The system includes a rotary actuator mechanism operable to generate torque via a shaft that rotates about an axis generally parallel to a chordwise direction of the folded proprotor blade, a pair of clamping arms movable in a direction generally parallel to a beamwise direction of the folded proprotor blade, a pair of linkage arms interoperably responsive to the rotary actuator mechanism and coupled between the rotary actuator mechanism and the pair of clamping arms, and a first guide rod extending between the pair of clamping arms in the direction generally parallel to the beamwise direction.
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公开(公告)号：US11414185B2
公开(公告)日：2022-08-16
申请号：US16804357
申请日：2020-02-28
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas Cravener
Abstract: Embodiments are directed to a propulsion assembly for an aircraft. The propulsion assembly comprises a mast, a hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast, the hub assembly having an inner hub wall spaced part from the mast, a gimbal lock positioned about the mast, the gimbal lock configured to fit between the inner hub wall and the mast in an engaged position, and an over-center locking mechanism coupled to the gimbal lock. The gimbal lock is movable between a disengaged position and the engaged position relative to the 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 over-center locking mechanism is configured to move the gimbal lock between the engaged position and the disengaged position.
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公开(公告)号：US20210354815A1
公开(公告)日：2021-11-18
申请号：US16874084
申请日：2020-05-14
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas Cravener
IPC: B64C27/605 , B64C27/48
Abstract: Embodiments are directed to a pitch horn assembly for an aircraft comprising a pitch horn rotatably coupled to a connector pin along a first axis using a first set of spherical bearings. The connector pin is rotatably coupled to a housing along a second axis using a second set of spherical bearings. A crank is fixedly coupled to the connector pin, wherein the pitch horn and the crank are configured to commonly rotate relative to the housing.
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公开(公告)号：US11142300B2
公开(公告)日：2021-10-12
申请号：US16655400
申请日：2019-10-17
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas Cravener , Andrew Maresh , Chyausong Tzeng
Abstract: An exemplary length adjustable link includes a tube having an internal bore and internal surface, a first rod end having a first shaft disposed in a first end of the internal bore, a second rod end having a second shaft disposed in a second end of the internal bore, and a member threadably connecting the first rod end to the second rod end.
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公开(公告)号：US11052993B2
公开(公告)日：2021-07-06
申请号：US16599483
申请日：2019-10-11
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas Cravener , Christopher Edward Foskey , Andrew Maresh
IPC: B64C27/57 , F16F3/02 , B64C11/28 , B64C29/00 , B64C27/80 , B64C27/605 , B64C11/38 , B64C27/59 , B64C11/32 , B64C27/64
Abstract: An exemplary spring-loaded link for an aircraft including a spring interposed between a first and a second rod, the spring, when compressed, urging the first rod and the second rod away from each other.
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