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    High Stiffness Hub Assembly for Proprotor Systems
    12.
    发明申请
    High Stiffness Hub Assembly for Proprotor Systems 审中-公开

    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.

    Inventor： Tyler Wayne Baldwin ,  Jouyoung Jason Choi ,  Richard Erler Rauber ,  Frank Bradley Stamps

    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.

    Engine mount assemblies for aircraft
    14.
    发明授权
    Engine mount assemblies for aircraft 有权

    公开(公告)号：US10384790B2

    公开(公告)日：2019-08-20

    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

    IPC: B64D27/26 ,  B64C29/00 ,  B64D27/12 ,  B64C27/28

    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.

    MULTI-PIECE INBOARD-BEAM
    15.
    发明申请
    MULTI-PIECE INBOARD-BEAM 审中-公开

    公开(公告)号：US20190233097A1

    公开(公告)日：2019-08-01

    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 ,  B64C27/50

    CPC classification number: B64C27/33 ,  B64C27/50 ,  B64C29/0033

    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.

    Hub Bolt Supported Inboard Bearing Assemblies
    18.
    发明申请
    Hub Bolt Supported Inboard Bearing Assemblies 审中-公开

    公开(公告)号：US20190016458A1

    公开(公告)日：2019-01-17

    申请号：US15990625

    申请日：2018-05-26

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Amarjit Olenchery Kizhakkepat ,  Robert Patrick Wardlaw ,  John Richard McCullough ,  Frank Bradley Stamps ,  Tyler Wayne Baldwin

    IPC: B64C29/00 ,  B64C11/06 ,  F16C17/10 ,  F16C33/06

    Abstract: A proprotor system for a tiltrotor aircraft having helicopter and airplane flight modes includes a yoke having a plurality of blade arms each having an inboard pocket. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets with each bearing assembly including a bearing cage, a shear bearing and a centrifugal force bearing. Each of a plurality of inboard beams is disposed at least partially between one of the centrifugal force bearings and one of the shear bearings. Each of a plurality of proprotor blades is coupled to one of the inboard beams. Hub bolts couple each of the bearing cages to the yoke such that the hub bolts provide centrifugal force load paths between the bearing assemblies and the yoke inboard of the inboard pockets.

    DRIVE LINK MOUNTED FLAPPING SENSOR SYSTEMS
    20.
    发明申请
    DRIVE LINK MOUNTED FLAPPING SENSOR SYSTEMS 审中-公开

    公开(公告)号：US20190329901A1

    公开(公告)日：2019-10-31

    申请号：US15967007

    申请日：2018-04-30

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Kyle T. Cravener ,  Tyler Wayne Baldwin

    IPC: B64D45/00 ,  B64C29/00

    Abstract: A rotor system is provided in one example embodiment and may include a rotor system may be provided and may include a drive link associated with a rotor hub of the rotor system, the drive link comprising an inner member and an outer member; and a sensor system mounted to the drive link, the sensor system to accommodate motions of the drive link to track rotor hub flapping. The sensor system for the rotor system may further include a sensor, the sensor comprising a sensor arm, wherein the sensor is mounted proximate to the inner member of the drive link; and a sensor link, the sensor link comprising a first end portion moveably coupled to the sensor arm, a second end portion coupled to the outer member of the drive link, and an angled portion between the first end portion and the second end portion.

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