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    Composite Flexure for Tiltrotor Rotor System
    21.
    发明申请
    Composite Flexure for Tiltrotor Rotor System 有权
    用于倾斜转子转子系统的复合挠曲

    公开(公告)号：US20150034772A1

    公开(公告)日：2015-02-05

    申请号：US13958192

    申请日：2013-08-02

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Christopher Foskey ,  Frank B. Stamps ,  Joel McIntyre ,  Gary Miller

    IPC: B64C27/33 ,  B64C27/52 ,  B64C27/28

    CPC classification number: B64C27/33 ,  B64C27/48 ,  B64C29/0033

    Abstract: According to one embodiment, a composite flexure may secure a rotor blade to a yoke in a tiltrotor rotor system. The composite flexure includes a composite body, a first end configured to couple the composite member to the yoke, and a second end configured to couple the composite member to the rotor blade.

    Abstract translation: 根据一个实施例，复合挠曲件可将转子叶片固定在倾斜转子转子系统中的轭。 复合挠曲件包括复合体，构造成将复合构件耦合到轭的第一端，以及构造成将复合构件耦合到转子叶片的第二端。

    Rotor assembly with high lock-number blades
    22.
    发明授权
    Rotor assembly with high lock-number blades 有权

    公开(公告)号：US10472057B2

    公开(公告)日：2019-11-12

    申请号：US15432910

    申请日：2017-02-14

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Gary Miller ,  Frank B. Stamps ,  Jouyoung Jason Choi ,  Thomas C. Parham, Jr. ,  Alan Ewing ,  Richard E. Rauber

    IPC: B64C27/635 ,  B64C27/605 ,  B64C27/72

    Abstract: An aircraft rotor assembly has a central hub and a plurality of rotor blades coupled to the hub for rotation with the hub about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is formed by a flexure coupling the associated blade to the hub. Each pivot is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the hub, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Elastic deformation of the flexure produces a biasing force for biasing the associated blade toward the neutral position, and the biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.

    Vibration Attenuator
    23.
    发明申请
    Vibration Attenuator 审中-公开

    公开(公告)号：US20190263512A1

    公开(公告)日：2019-08-29

    申请号：US16284931

    申请日：2019-02-25

    Applicant: Bell Helicopter Textron Inc.

    Inventor： David Heverly ,  Frank Bradley Stamps ,  Gary Miller ,  Richard E. Rauber ,  Thomas C. Parham, JR. ,  Michael R. Smith ,  Michael Scott Seifert ,  Jouyoung Jason Choi

    IPC: B64C27/00 ,  B06B1/16

    Abstract: A vibration attenuator for a rotor is rotatable about a mast axis and has a frame configured for rotation about the mast axis relative to the rotor. A first mass is axially translatable in a first direction relative to the frame parallel to a first axis, and a first biasing force urges the first mass toward a first-mass rest position in which the first mass is symmetric about the mast axis. A second mass is axially translatable in a second direction relative to the frame parallel to a second axis, and a second biasing force urges the second mass toward a second-mass rest position in which the second mass is symmetric about the mast axis. A selected first or second mass moves radially outward from the rest position to oppose vibrations in the rotor.

    Soft-in-Plane Proprotor Systems
    25.
    发明申请
    Soft-in-Plane Proprotor Systems 审中-公开

    公开(公告)号：US20180162519A1

    公开(公告)日：2018-06-14

    申请号：US15375385

    申请日：2016-12-12

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Thomas Clement Parham, JR. ,  Jouyoung Jason Choi ,  Gary Miller ,  Frank Bradley Stamps ,  Richard Erler Rauber

    IPC: B64C11/06 ,  B64C29/00

    Abstract: A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of loop yokes, each coupling one of the proprotor blades with the hub and each including first and second longitudinal sections extending between inboard and outboard arcuate sections and a bearing assembly disposed between the inboard and outboard arcuate sections of each loop yoke. Each bearing assembly includes a flapping bearing disposed generally within the inboard arcuate section of the respective loop yoke and coupled to the hub, a lead-lag damper coupled to the hub, a centrifugal force bearing disposed generally within the outboard arcuate section of the respective loop yoke and a blade anchor coupled between the lead-lag damper and the centrifugal force bearing. The blade anchor is also coupled to the respective proprotor blade.

    Loop Yoke for Proprotor Systems
    26.
    发明申请
    Loop Yoke for Proprotor Systems 审中-公开

    公开(公告)号：US20180162518A1

    公开(公告)日：2018-06-14

    申请号：US15375356

    申请日：2016-12-12

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Thomas Clement Parham, JR. ,  Jouyoung Jason Choi ,  Gary Miller ,  Frank Bradley Stamps ,  Richard Erler Rauber

    IPC: B64C11/04 ,  B64C29/00 ,  B29C70/32

    Abstract: A yoke for providing a centrifugal force retention load path between a proprotor blade and a hub of a soft-in-plane proprotor system operable for use on a tiltrotor aircraft. The yoke includes a continuous loop having a longitudinal axis and first and second longitudinal sections extending between inboard and outboard arcuate sections. A flapping bearing receiving region is disposed at least partially within the inboard arcuate section to an interior of the continuous loop. A centrifugal force bearing receiving region is disposed at least partially within the outboard arcuate section to the interior of the continuous loop. The continuous loop is formed from a composite material having a plurality of double bias material plies and a plurality of unidirectional material plies such that the number of unidirectional material plies is greater than the number of double bias material plies.

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