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    SOFT IN-PLANE AND STIFF OUT-OF-PLANE ROTOR SYSTEM
    5.
    发明申请
    SOFT IN-PLANE AND STIFF OUT-OF-PLANE ROTOR SYSTEM 有权
    软平面和平坦的平面转子系统

    公开(公告)号：US20140271182A1

    公开(公告)日：2014-09-18

    申请号：US13804832

    申请日：2013-03-14

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Ken Shundo ,  Mithat Yuce ,  Frank B. Stamps

    IPC: B64C27/80 ,  B64C11/02 ,  B64C11/48 ,  B64C27/51

    CPC classification number: B64C27/80 ,  B64C11/02 ,  B64C11/48 ,  B64C27/10 ,  B64C27/322 ,  B64C27/35 ,  B64C27/48 ,  B64C27/51 ,  B64C27/52

    Abstract: A rotor assembly includes a yoke operably associated with a rotor blade. The yoke includes a first device and a second device that attach the rotor blade to the yoke. The first device is configured to allow transverse movement of the rotor blade about a chord axis and rotational movement about a pitch-change axis. The second device is configured to allow rotational movement of the rotor blade solely about the pitch-change axis. The method includes rotating rotor assembly about a first plane of rotation, while retaining a relatively stiff out-of-plane rotation and a relatively soft in-plane rotation during flight.

    Abstract translation: 转子组件包括与转子叶片可操作地相关联的轭。 轭包括第一装置和将转子叶片附接到轭架的第二装置。 第一装置被构造成允许转子叶片围绕弦轴线的横向运动和围绕俯仰变化轴线的旋转运动。 第二装置构造成仅允许转子叶片围绕俯仰变化轴线的旋转运动。 该方法包括围绕第一旋转平面旋转转子组件，同时在飞行期间保持相对刚性的平面外旋转和相对柔软的平面内旋转。

    Soft in-plane and stiff out-of-plane rotor system
    6.
    发明授权
    Soft in-plane and stiff out-of-plane rotor system 有权

    公开(公告)号：US10543916B2

    公开(公告)日：2020-01-28

    申请号：US15603019

    申请日：2017-05-23

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Ken Shundo ,  Mithat Yuce ,  Frank B. Stamps

    IPC: B64C27/80 ,  B64C27/52 ,  B64C27/10 ,  B64C27/32 ,  B64C27/35 ,  B64C27/48 ,  B64C27/51

    Abstract: A rotor assembly includes a yoke operably associated with a rotor blade. The yoke includes a first device and a second device that attach the rotor blade to the yoke. The first device is configured to allow transverse movement of the rotor blade about a chord axis and rotational movement about a pitch-change axis. The second device is configured to allow rotational movement of the rotor blade solely about the pitch-change axis. The method includes rotating rotor assembly about a first plane of rotation, while retaining a relatively stiff out-of-plane rotation and a relatively soft in-plane rotation during flight.

    ADJUSTABLE BLADE-TO-HUB LEAD-LAG DAMPER ATTACHMENT
    8.
    发明申请
    ADJUSTABLE BLADE-TO-HUB LEAD-LAG DAMPER ATTACHMENT 有权
    可调节叶片到屋顶导杆阻尼器附件

    公开(公告)号：US20150336664A1

    公开(公告)日：2015-11-26

    申请号：US14283515

    申请日：2014-05-21

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Richard E. Rauber ,  Mithat Yuce ,  Thomas C. Parham, JR. ,  Thomas J. Newman ,  Mark A. Wiinikka

    IPC: B64C27/54 ,  B64C27/51

    CPC classification number: B64C27/54 ,  B64C27/51 ,  B64C27/58 ,  B64C27/59 ,  B64C27/635 ,  F16C11/045 ,  F16C11/0614 ,  F16C11/0695 ,  F16C23/02 ,  F16C2326/43

    Abstract: An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.

    Abstract translation: 飞机包括转子叶片和转子轮毂系统。 转子毂系统包括具有杆端并与转子叶片可操作地相关联的前导滞后阻尼器; 具有第一臂和相对的第二臂的刀片适配器; 由刀片适配器承载并被构造成经由第一臂和第二臂固定就位的销; 以及致动器，其固定到所述销并且构造成调节所述牵引杆延伸杆端部相对于所述第一臂和所述第二臂的位置。

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