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    High flapping yoke hub assembly using a cylindrical elastomeric attachment to avoid holes
    3.
    发明授权
    High flapping yoke hub assembly using a cylindrical elastomeric attachment to avoid holes 有权

    公开(公告)号：US10336445B2

    公开(公告)日：2019-07-02

    申请号：US13797334

    申请日：2013-03-12

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Andrew Maresh ,  Frank Bradley Stamps ,  Andrew Haldeman

    IPC: B64C27/33 ,  B64C27/48 ,  B64C27/35 ,  B64C11/02

    Abstract: An apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein a center portion of each longitudinal side portion comprises a build-up of material that is configured to accommodate a yoke hub clamp. Included is an apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions. Also included is a method of coupling aircraft blades comprising providing a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions.

    Composite rotor system using two race track style cantilevered yokes
    4.
    发明授权
    Composite rotor system using two race track style cantilevered yokes 有权
    复合转子系统采用两种跑道式悬臂式轭铁

    公开(公告)号：US09505490B2

    公开(公告)日：2016-11-29

    申请号：US13801733

    申请日：2013-03-13

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Andrew Maresh ,  Frank Bradley Stamps ,  Patrick Ryan Tisdale ,  Robert Wardlaw ,  Andrew Haldeman ,  Drew Sutton

    IPC: B64C27/35 ,  B64C27/48 ,  B64C27/33

    CPC classification number: B64C27/33 ,  B64C11/02 ,  B64C11/12 ,  B64C27/35 ,  B64C27/48

    Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.

    Abstract translation: 毂系统包括至少一个轭，至少一个剪切轴承和至少一个桅杆适配器。 所述至少一个桅杆适配器构造成支撑所述至少一个轭和所述至少一个剪切轴承，并且所述至少一个轭具有与所述至少一个剪切轴承的扑动铰链不重合的扑动铰链。 另一个集线器系统包括堆叠的轭和桅杆适配器。 桅杆适配器被配置为将旋转从转子桅杆传递到轮毂系统，以围绕中心旋转轴线旋转轮毂系统。 桅杆适配器还被配置为支撑堆叠的轭架，使得堆叠的轭架中的每个轭架构造成适应围绕垂直于或大致垂直于中心旋转轴线的轴线的至少一定量的旋转。

    Gimbaled Tail Rotor Hub with Spherical Elastomeric Centrifugal Force Bearing for Blade Retention and Pitch Change Articulation
    5.
    发明申请
    Gimbaled Tail Rotor Hub with Spherical Elastomeric Centrifugal Force Bearing for Blade Retention and Pitch Change Articulation 有权
    具有球形弹性离心力的平衡尾部转子毂用于刀片保持和间距变化铰接

    公开(公告)号：US20140271180A1

    公开(公告)日：2014-09-18

    申请号：US13800174

    申请日：2013-03-13

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Andrew Haldeman ,  Frank Bradley Stamps ,  Drew Sutton ,  James Donn Hethcock

    IPC: F01D7/00

    CPC classification number: B64C27/35 ,  B64C27/32 ,  B64C27/41 ,  B64C27/48 ,  B64C27/52 ,  B64C27/78 ,  B64C27/82 ,  B64C29/0033 ,  F01D7/00

    Abstract: A rotor hub comprises a gimbal assembly and an elastomeric centrifugal force bearing. The gimbal assembly is configured to transfer rotational movement of a mast to the rotor hub and to enable the rotor hub to flap relative to the mast. The elastomeric centrifugal force bearing is configured to withstand centrifugal force of a rotor blade when the mast is rotated and is configured to accommodate pitch changes of the rotor blade. A method comprises designing a gimbal assembly that enables a tail rotor hub to flap relative to a tail rotor mast. A centrifugal force bearing is selected that enables tail rotor blades to withstand centrifugal force and that allows for tail rotor blade pitch change articulation. Then, instructions are provided to use the gimbal assembly and the centrifugal force bearing in an in-plane tail rotor assembly.

    Abstract translation: 转子毂包括万向节组件和弹性离心力轴承。 万向节组件构造成将桅杆的旋转运动传递到转子轮毂，并且使得转子轮毂能够相对于桅杆折叠。 弹性体离心力轴承构造成当桅杆旋转时承受转子叶片的离心力，并且构造成适应转子叶片的桨距变化。 一种方法包括设计一个万向架组件，其使得尾部转子毂能相对于尾部转子桅杆折叠。 选择离心力轴承，使离合力叶片能够承受离心力，并允许尾部转子叶片间距改变铰接。 然后，提供说明书以在平面内转子组件中使用万向架组件和离心力轴承。

    Composite Rotor System Using Two Race Track Style Cantilevered Yokes
    7.
    发明申请
    Composite Rotor System Using Two Race Track Style Cantilevered Yokes 有权
    复合转子系统使用两个赛道式悬臂式轭

    公开(公告)号：US20140271222A1

    公开(公告)日：2014-09-18

    申请号：US13801733

    申请日：2013-03-13

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Andrew Maresh ,  Frank Bradley Stamps ,  Patrick Ryan Tisdale ,  Robert Wardlaw ,  Andrew Haldeman ,  Drew Sutton

    IPC: B64C27/39

    CPC classification number: B64C27/33 ,  B64C11/02 ,  B64C11/12 ,  B64C27/35 ,  B64C27/48

    Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.

    Abstract translation: 毂系统包括至少一个轭，至少一个剪切轴承和至少一个桅杆适配器。 所述至少一个桅杆适配器构造成支撑所述至少一个轭和所述至少一个剪切轴承，并且所述至少一个轭具有与所述至少一个剪切轴承的扑动铰链不重合的扑动铰链。 另一个集线器系统包括堆叠的轭和桅杆适配器。 桅杆适配器被配置为将旋转从转子桅杆传递到轮毂系统，以围绕中心旋转轴线旋转轮毂系统。 桅杆适配器还被配置为支撑堆叠的轭架，使得堆叠的轭架中的每个轭架构造成适应围绕垂直于或大致垂直于中心旋转轴线的轴线的至少一定量的旋转。

    High Flapping Yoke Hub Assembly Using a Cylindrical Elastomeric Attachment to Avoid Holes
    8.
    发明申请
    High Flapping Yoke Hub Assembly Using a Cylindrical Elastomeric Attachment to Avoid Holes 审中-公开
    使用圆柱形弹性连接件避免孔的高振动式轭架组件

    公开(公告)号：US20140271199A1

    公开(公告)日：2014-09-18

    申请号：US13797334

    申请日：2013-03-12

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Andrew Maresh ,  Frank Bradley Stamps ,  Andrew Haldeman

    IPC: B64C27/32

    CPC classification number: B64C27/33 ,  B64C11/02 ,  B64C27/35 ,  B64C27/48 ,  Y10T29/49316

    Abstract: An apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein a center portion of each longitudinal side portion comprises a build-up of material that is configured to accommodate a yoke hub clamp. Included is an apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions. Also included is a method of coupling aircraft blades comprising providing a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions.

    Abstract translation: 一种包括转子轭的装置，包括由两个外侧部分相互连接的两个纵向侧部分，其中每个纵向侧部分的中心部分包​​括被构造成容纳轭架式夹持器的材料的积聚。 包括一种装置，其包括转子轭，该转子轭包括通过两个外侧部分互连的两个纵向侧部，其中没有孔穿过两个纵向侧部和两个外侧部。 还包括联接飞行器叶片的方法，包括提供转子轭，转子轭包括通过两个外侧部分互连的两个纵向侧部，其中没有孔穿过两个纵向侧部和两个外侧部。

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