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    Over-centering blade lock
    1.
    发明授权
    Over-centering blade lock 有权

    公开(公告)号：US11535370B2

    公开(公告)日：2022-12-27

    申请号：US16599471

    申请日：2019-10-11

    Applicant: Bell Textron Inc.

    Inventor： Kyle Thomas Cravener ,  Andrew Maresh

    IPC: B64C29/00 ,  B64C11/20

    Abstract: An exemplary blade lock for a tiltrotor aircraft to enable and disable a folding degree of freedom and a pitching degree of freedom of a rotor blade assembly includes a link pivotally connected to a lever and a bellcrank, where the link is in a center position when the lever is in a locked position disabling the folding degree of freedom and the lever is secured in the locked position when the link is positioned in an over-center position.

    SINGLE HOOKE'S JOINT WITH SPHERICAL MAST ATTACHMENT
    2.
    发明申请
    SINGLE HOOKE'S JOINT WITH SPHERICAL MAST ATTACHMENT 有权

    公开(公告)号：US20210291960A1

    公开(公告)日：2021-09-23

    申请号：US16821266

    申请日：2020-03-17

    Applicant: Bell Textron Inc.

    Inventor： Andrew Ryan Maresh ,  Kyle Thomas Cravener

    IPC: B64C11/02 ,  B64C29/00 ,  B64C27/35

    Abstract: Embodiments are directed to a rotor hub assembly comprising a yoke configured to attach rotor blades thereto, a single Hooke's joint configured to attach to, and transmit forces between, a mast and the yoke, and a spherical bearing coupled between the yoke and the mast. Two pillow blocks couple the single Hooke's joint to the yoke. An adapter sleeve is attached to the pillow blocks and is positioned to surround the spherical bearing. The adapter sleeve extends between the single Hooke's joint and the mast. A hub lock extension is attached to the yoke. The hub lock extension is configured to receive a hub lock that prevents gimballing of the yoke when engaged.

    Teeter flap lock
    3.
    发明授权
    Teeter flap lock 有权

    公开(公告)号：US11891167B2

    公开(公告)日：2024-02-06

    申请号：US17503736

    申请日：2021-10-18

    Applicant: Bell Textron Inc.

    Inventor： Bryan Kenneth Baskin ,  Kyle Thomas Cravener ,  Andrew Ryan Maresh

    IPC: B64C27/32 ,  B64C29/00

    CPC classification number: B64C27/322 ,  B64C29/0033

    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.

    PITCH-FOLD LOCK
    5.
    发明申请
    PITCH-FOLD LOCK 有权

    公开(公告)号：US20210362837A1

    公开(公告)日：2021-11-25

    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

    IPC: B64C11/28 ,  B64C11/06

    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.

    Elastomeric pitch lock restraint
    6.
    发明授权
    Elastomeric pitch lock restraint 有权

    公开(公告)号：US10994837B1

    公开(公告)日：2021-05-04

    申请号：US16655855

    申请日：2019-10-17

    Applicant: Bell Textron Inc.

    Inventor： Kyle Thomas Cravener ,  Andrew Maresh ,  Mark Adam Wiinikka

    IPC: B64C11/32 ,  B64C27/57 ,  B64C29/00 ,  B64C27/80 ,  B64C11/28 ,  B64C27/605

    Abstract: An exemplary pitch lock for a tiltrotor aircraft to enable and disable a pitching degree of freedom of a rotor blade assembly includes a first tab coupled to a blade stop assembly, the first tab having a first ramp surface, a second tab coupled to a blade cuff, the second tab having a second ramp surface, a hasp having a central opening to receive the first and the second tab and rollers rotatably coupled to the hasp on opposite sides of the central opening, where the rollers engage the first and second ramp surfaces and retain the first and the second tabs in the central opening.

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