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    Multilink Constant Velocity Joint
    71.
    发明申请
    Multilink Constant Velocity Joint 有权
    多连续恒速接头

    公开(公告)号：US20140274427A1

    公开(公告)日：2014-09-18

    申请号：US13828509

    申请日：2013-03-14

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Christopher Foskey ,  Frank B. Stamps ,  Richard Rauber

    IPC: F16D3/60

    CPC classification number: F16D3/60 ,  B64C27/37 ,  B64C2027/125 ,  Y10T29/49643

    Abstract: An apparatus comprising a rotor hub system comprising a floating plate, a plurality of drive link trunnions each comprising a pivoting arm and positioned radially about the floating plate, wherein each drive link trunnion is coupled to the floating plate via the pivoting arm, and a housing disposed about the floating plate, coupled to each of the drive link trunnions, and configured to couple to a mast. Included is an apparatus comprising a floating plate, a plurality of drive link trunnions each comprising a pivoting arm and positioned radially about the floating plate, wherein each drive link trunnion is coupled to the floating plate via the pivoting arm, and wherein the drive link trunnions are configured to move the floating plate in response to a force applied to the drive link trunnions, and a housing disposed about the floating plate and coupled to each of the drive link trunnions.

    Abstract translation: 一种包括转子轮毂系统的装置，包括浮动板，多个驱动连杆耳轴，每个包括枢转臂并围绕浮动板径向定位，其中每个驱动连杆耳轴经由枢转臂连接到浮动板， 围绕浮动板设置，耦合到每个驱动链节耳轴，并且被配置成耦合到桅杆。 包括一种包括浮动板，多个驱动连杆耳轴的装置，每个驱动连杆耳轴包括枢转臂并且围绕浮动板径向地定位，其中每个驱动连杆耳轴经由枢转臂联接到浮动板，并且其中驱动连杆耳轴 构造成响应于施加到驱动连杆耳轴的力而移动浮板，以及围绕浮动板设置并联接到每个驱动连杆耳轴的壳体。

    Rotor Hub Elastomeric Bearings
    72.
    发明申请
    Rotor Hub Elastomeric Bearings 有权
    转子毂弹性轴承

    公开(公告)号：US20140270610A1

    公开(公告)日：2014-09-18

    申请号：US13800440

    申请日：2013-03-13

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Emily Schofield ,  Chad Jarrett ,  Dan Sottiaux ,  Frank B. Stamps

    IPC: F16C27/06

    CPC classification number: B64C27/35 ,  B23P19/04 ,  B64C27/41 ,  F16C7/04 ,  F16C11/083 ,  F16C27/063 ,  F16C2326/43 ,  F16D3/62 ,  F16F1/3863 ,  Y10T29/49643 ,  Y10T29/4984

    Abstract: An apparatus comprising a drivelink comprising a housing including a socket, wherein the socket comprises a cross-sectional area, and a bearing cartridge disposed within the socket, wherein a cross-sectional area of the cartridge is less than the cross-sectional area of the socket. An apparatus comprising a drivelink comprising a housing having a socket, and a bearing cartridge positioned within the socket and comprising a first portion and a second portion, wherein the first portion is configured to undergo compression when a load is applied to the drivelink, and wherein the second portion is configured to not be in tension when the load is applied to the drivelink.

    Abstract translation: 一种包括驱动装置的装置，包括壳体，该壳体包括插座，其中所述插座包括横截面区域，以及设置在所述插座内的轴承盒，其中所述盒的横截面积小于所述插座的横截面积 插座。 一种包括驱动装置的装置，包括具有插座的壳体和定位在所述插座内并包括第一部分和第二部分的轴承盒，其中所述第一部分构造成在负载施加到所述传动装置时经受压缩，并且其中 第二部分被配置为当负载施加到驱动器时​​不处于张力。

    Rotor System Shear Bearing
    74.
    发明申请
    Rotor System Shear Bearing 有权
    转子系统剪切轴承

    公开(公告)号：US20140241886A1

    公开(公告)日：2014-08-28

    申请号：US13778803

    申请日：2013-02-27

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Drew Sutton ,  Frank B. Stamps

    IPC: B64C27/46

    CPC classification number: B64C27/48 ,  B64C27/33 ,  B64C27/35

    Abstract: A shear bearing for a rotor system has a four bar linkage and a grip configured to retain a flexural yoke and the grip is connected between a first set of opposing links of the four bar linkage. A rotor system has a flexural yoke and a shear bearing configured to perform at least one of transmitting forces to the yoke and receiving forces from the yoke, wherein the yoke is free of cavities for receiving the shear bearing. A rotational system has a flexural yoke and a damper disposed on a surface of the yoke.

    Abstract translation: 用于转子系统的剪切轴承具有四杆连杆和构造成保持弯曲轭的夹持件，并且把手连接在四杆连杆的第一组相对的连杆之间。 转子系统具有弯曲轭和剪切轴承，该剪力轴承构造成执行向轭的传递力和从轭的接收力中的至少一个，其中轭没有用于接收剪切轴承的空腔。 旋转系统具有设置在轭的表面上的弯曲轭和阻尼器。

    Constant-velocity drive system for gimbaled rotor hubs
    75.
    发明授权
    Constant-velocity drive system for gimbaled rotor hubs 有权
    用于万向转子轮毂的恒速驱动系统

    公开(公告)号：US08590833B2

    公开(公告)日：2013-11-26

    申请号：US13677146

    申请日：2012-11-14

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Richard Rauber ,  Frank B. Stamps ,  James Lee Braswell, Jr.

    IPC: B64D35/00 ,  B64C29/00

    CPC classification number: B64C27/41 ,  B64C27/52 ,  B64C29/0033 ,  F16C1/04

    Abstract: An aircraft rotor constant-velocity drive system having a differential mechanism that includes a drive disk configured to be integral in rotation with a mast, an upper member at least partially located above the drive disk, a lower member at least partially located below the drive disk, and at least one link connecting the upper member and the lower member to the drive disk such that the drive disk drives the upper member and the lower member in rotation with the drive disk and that the upper member and the lower member are allowed to rotate differently with respect to the drive disk. The link having opposing end joints and a central joint that pivotally engages the drive disk. The system also having a gimbal device configured to drive a rotor hub and to allow gimbaling of the rotor hub with respect to a mast.

    Abstract translation: 一种具有差速机构的飞行器转子恒速驱动系统，该差速机构包括构造成与桅杆一体旋转的驱动盘，至少部分地位于驱动盘上方的上部构件，至少部分地位于驱动盘下方的下部构件 以及将上部构件和下部构件连接到驱动盘的至少一个链节，使得驱动盘驱动上部构件和下部构件与驱动盘一起旋转，并且上部构件和下部构件被允许旋转 与驱动盘不同。 该连杆具有相对的端部接头和枢转地接合驱动盘的中心接头。 该系统还具有构造成驱动转子轮毂并允许转子轮毂相对于桅杆展开平衡的万向架装置。

    Rotorcraft anti-torque system
    77.
    发明授权
    Rotorcraft anti-torque system 有权

    公开(公告)号：US10940945B2

    公开(公告)日：2021-03-09

    申请号：US15796910

    申请日：2017-10-30

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Levi C. Hefner ,  Frank B. Stamps

    IPC: B64C27/82 ,  B64C27/12

    Abstract: There is provided a rotorcraft, including a body, including a front portion and a tail portion; a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body; and an anti-torque system coupled to the tail portion of the body, the anti-torque system including a primary tail rotor system and a secondary tail rotor system; wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force. In other aspects, there are methods of providing anti-torque force in a rotorcraft.

    Multirotor aircraft with collective for autorotation
    78.
    发明授权
    Multirotor aircraft with collective for autorotation 有权

    公开(公告)号：US10829200B2

    公开(公告)日：2020-11-10

    申请号：US15807843

    申请日：2017-11-09

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Eric R. Gonzalez ,  Frank B. Stamps

    IPC: B64C11/30 ,  B64D45/00 ,  B64C27/54 ,  B64C27/28 ,  B64C29/00

    Abstract: A multirotor aircraft comprises at least three proprotors. Each proprotor has a plurality of rotor blades pivotably attached to a mast assembly. When a rotor blade pitch angle is changed for a proprotor, all rotor blades on the proprotor change to a same pitch angle. The proprotors are configured to spin freely when a power source is disengaged or fails. In various embodiments, one or more engines provides power to each proprotor, or at least one engine provides power to two or more proprotors. A rotor blade control system is configured to control a collective rotor blade pitch angle on each proprotor independently of the rotor blade pitch on the other proprotors. The rotor blade control system is configured to set a negative collective rotor blade pitch angle on an unpowered proprotor, such as in response to manual inputs by a pilot or in response to current engine conditions.

    Low moment rotor hub
    80.
    发明授权
    Low moment rotor hub 有权

    公开(公告)号：US10597143B2

    公开(公告)日：2020-03-24

    申请号：US15683621

    申请日：2017-08-22

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Andrew Paul Haldeman ,  Frank B. Stamps ,  James Donn Hethcock

    IPC: B64C11/02 ,  B64C27/35 ,  B64C11/04 ,  B64C11/06 ,  B64C27/39 ,  B64C27/12 ,  B64C27/32 ,  B64C27/59 ,  B64C27/78

    Abstract: In one embodiment, a rotor hub comprises a hub body, and a plurality of blade grips configured for attaching a plurality of rotor blades. The rotor hub further comprises a plurality of centrifugal force bearings coupled to the plurality of blade grips, wherein a focus of the plurality of centrifugal force bearings is aligned with a centerline of a rotor mast. The rotor hub further comprises a plurality of drive links configured to transfer torque to the plurality of rotor blades, wherein the plurality of drive links is positioned to correspond with a leading edge side of the plurality of rotor blades. The rotor hub further comprises a plurality of pitch horns configured to adjust a pitch of the plurality of rotor blades.

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