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    Proprotor lockout systems for tiltrotor aircraft
    2.
    发明授权
    Proprotor lockout systems for tiltrotor aircraft 有权

    公开(公告)号：US11964757B2

    公开(公告)日：2024-04-23

    申请号：US17825278

    申请日：2022-05-26

    Applicant: Textron Innovations Inc.

    Inventor： Grant Michael Beall ,  Kyle Thomas Cravener ,  Brady Garrett Atkins ,  Gilberto Morales

    IPC: B64C29/00 ,  B64C11/28 ,  B64D35/00 ,  F16D71/00

    CPC classification number: B64C29/0033 ,  B64C11/28 ,  B64D35/00 ,  F16D71/00

    Abstract: A lockout system for an aircraft having a rotor assembly. The lockout system includes a drive shaft coupled to and rotatable with the rotor assembly, a nonrotating airframe structure disposed proximate the drive shaft and a lock assembly having first and second lock members. The first lock member is rotatable with the drive shaft and includes a plurality of bearing assemblies. The second lock member is coupled to the nonrotating airframe structure and includes a cradle having a plurality of asymmetric slots each with a leading ramp and a trailing stop. The lock assembly has a disengaged position in which rotation of the drive shaft is allowed and an engaged position in which each of the bearing assemblies is seated within one of the asymmetric slots to prevent rotation of the drive shaft. The lock assembly is actuatable between the engaged and disengaged positions.

    Proprotor Lockout Systems for Tiltrotor Aircraft
    4.
    发明公开
    Proprotor Lockout Systems for Tiltrotor Aircraft 审中-公开

    公开(公告)号：US20230406492A1

    公开(公告)日：2023-12-21

    申请号：US17825278

    申请日：2022-05-26

    Applicant: Textron Innovations Inc.

    Inventor： Grant Michael Beall ,  Kyle Thomas Cravener ,  Brady Garrett Atkins ,  Gilberto Morales

    IPC: B64C29/00 ,  B64C13/28 ,  B64C11/28

    CPC classification number: B64C29/0033 ,  B64C11/28 ,  B64C13/28

    Abstract: A lockout system for an aircraft having a rotor assembly. The lockout system includes a drive shaft coupled to and rotatable with the rotor assembly, a nonrotating airframe structure disposed proximate the drive shaft and a lock assembly having first and second lock members. The first lock member is rotatable with the drive shaft and includes a plurality of bearing assemblies. The second lock member is coupled to the nonrotating airframe structure and includes a cradle having a plurality of asymmetric slots each with a leading ramp and a trailing stop. The lock assembly has a disengaged position in which rotation of the drive shaft is allowed and an engaged position in which each of the bearing assemblies is seated within one of the asymmetric slots to prevent rotation of the drive shaft. The lock assembly is actuatable between the engaged and disengaged positions.

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

    公开(公告)号：US20230101186A1

    公开(公告)日：2023-03-30

    申请号：US18059002

    申请日：2022-11-28

    Applicant: Textron Innovations 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.

    Over-centering blade lock
    6.
    发明授权
    Over-centering blade lock 有权

    公开(公告)号：US11975831B2

    公开(公告)日：2024-05-07

    申请号：US17994289

    申请日：2022-11-26

    Applicant: Textron Innovations Inc.

    Inventor： Kyle Thomas Cravener ,  Andrew Maresh

    IPC: B64C29/00 ,  B64C11/20

    CPC classification number: B64C29/0033 ,  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.

    Inboard bearing assemblies with anti-rotation features
    8.
    发明授权
    Inboard bearing assemblies with anti-rotation features 有权

    公开(公告)号：US10514060B2

    公开(公告)日：2019-12-24

    申请号：US15698796

    申请日：2017-09-08

    Applicant: Textron Innovations Inc.

    Inventor： Glenn Alan Shimek ,  Amarjit Olenchery Kizhakkepat ,  Ken Shundo ,  Michael Dean Dearman ,  Kyle Thomas Cravener ,  Michael Christopher Burnett

    IPC: B64C27/33 ,  F16C27/06 ,  B64C29/00 ,  B64C27/39 ,  B64C27/605

    Abstract: A bearing assembly for coupling a proprotor blade to a yoke in a proprotor system. The bearing assembly is positionable within an inboard pocket of a blade arm of the yoke. The proprotor system is operable for use on a tiltrotor aircraft having helicopter and airplane flight modes. The bearing assembly includes a centrifugal force bearing and a shear bearing having an inboard beam coupled therebetween. The centrifugal force bearing has a mating surface, a lateral movement constraint feature and at least one radially extending anti-rotation feature. The inboard beam has a mating surface in a contact relationship with the mating surface of the centrifugal force bearing, a lateral movement constraint feature operably associated with the lateral movement constraint feature of the centrifugal force bearing and at least one radially extending anti-rotation feature that corresponds with the at least one radially extending anti-rotation feature of the centrifugal force bearing.

    BLADE POSITION CONTROL SYSTEM
    9.
    发明申请
    BLADE POSITION CONTROL SYSTEM 有权

    公开(公告)号：US20250100680A1

    公开(公告)日：2025-03-27

    申请号：US18472933

    申请日：2023-09-22

    Applicant: Textron Innovations Inc.

    Inventor： Lancer Drake Halcom ,  Kyle Thomas Cravener

    IPC: B64C27/72 ,  B64C27/50

    Abstract: An aircraft that has a blade position control system (BPCS). The BPCS includes an actuator, a multilobe component configured for at least one of longitudinal movement along a mast axis as a function of actuation of the actuator and rotational movement relative to the mast axis as a function of actuation of the actuator. Movement of the multilobe component selectively restricts at least one of pitch movement and folding of a plurality of rotor blades.

    Pitch-fold lock
    10.
    发明授权
    Pitch-fold lock 有权

    公开(公告)号：US12214860B2

    公开(公告)日：2025-02-04

    申请号：US18059002

    申请日：2022-11-28

    Applicant: Textron Innovations Inc.

    Inventor： Kyle Thomas Cravener ,  Andrew Ryan Maresh ,  Brady Garrett Atkins ,  Kynn J. Schulte ,  Troy Schank

    IPC: B64C11/28 ,  B64C11/06 ,  B64C29/00

    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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