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    Removable rotor blade tip
    11.
    发明授权
    Removable rotor blade tip 有权

    公开(公告)号：US11261735B2

    公开(公告)日：2022-03-01

    申请号：US13789265

    申请日：2013-03-07

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Drew Sutton ,  Tim Ledbetter

    IPC: F01D5/14 ,  B64C27/46

    Abstract: A rotor blade has a spanwise axis, a root comprising an anchor having an anchor surface configured to form at least one of a normal angle relative to the spanwise axis and an acute angle relative to the spanwise axis, and a selectively removable tip comprising a connector having a connector surface configured to complement the anchor surface.

    Composite rotor system using two race track style cantilevered yokes
    12.
    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。

    Flexing clevis arrangement bolted joint attachment for flexible rotor hub with high offset and high flapping
    13.
    发明授权
    Flexing clevis arrangement bolted joint attachment for flexible rotor hub with high offset and high flapping 有权
    弯曲U形夹配置螺栓连接附件，用于具有高偏移和高拍打的柔性转子毂

    公开(公告)号：US09505489B2

    公开(公告)日：2016-11-29

    申请号：US13801965

    申请日：2013-03-13

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Drew Sutton ,  Frank B. Stamps ,  Patrick Ryan Tisdale ,  Paul Oldroyd

    IPC: B64C27/33 ,  B64C27/48 ,  B64C11/02 ,  B64C27/32

    CPC classification number: B64C27/33 ,  B64C11/02 ,  B64C27/32 ,  B64C27/48 ,  Y10T29/49316

    Abstract: A flexible joint assembly for providing flexure to a rotor blade comprising an upper hub plate and a lower hub plate configured to secure a rotor blade yoke via a bolted joint located radially outward of a mast; and an upper flexure assembly connected to the upper hub plate and a lower flexure assembly connected to the lower hub plate, wherein the upper flexure assembly and lower flexure assembly are configured to promote flapping of the rotor blade yoke about a flapping hinge located radially outward of the bolted joint.

    Abstract translation: 一种用于向转子叶片提供挠曲的柔性接头组件，包括上轮毂板和下轮毂板，所述上轮毂板和下轮毂板被构造成通过位于桅杆的径向外侧的螺栓接头固定转子叶片翼片; 以及连接到上轮毂板的上挠性组件和连接到下轮毂板的下挠曲组件，其中上弯曲组件和下挠曲组件构造成促使转子叶片轭绕着位于径向向外的振动铰链 螺栓接头。

    Embedding fiber optic cables in rotorcraft composites
    14.
    发明授权
    Embedding fiber optic cables in rotorcraft composites 有权
    在旋翼飞机复合材料中嵌入光纤电缆

    公开(公告)号：US09500561B2

    公开(公告)日：2016-11-22

    申请号：US14310172

    申请日：2014-06-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Drew Sutton ,  Brian Tucker ,  Troy Schank

    IPC: G02B6/34 ,  G01M11/08 ,  G02B6/00 ,  B64C27/00 ,  B64C27/33 ,  G01D5/353 ,  G02B6/12 ,  B64D45/00

    CPC classification number: G01M11/086 ,  B64C27/007 ,  B64C27/33 ,  B64D2045/0085 ,  G01D5/3537 ,  G01D5/35374 ,  G02B6/00 ,  G02B2006/12138 ,  Y10T156/1002

    Abstract: Some examples of techniques to cost-effectively embed fiber optic cables in laminate structures and to terminate the fiber optic cables on the surface of the laminate for robust and easily-repairable connections can be implemented in rotorcraft composites. To position a cable in the rotorcraft composite, a length of a fiber optic cable is embedded between layers of a composite rotorcraft material. The length of the fiber optic cable is oriented in a substantially S-shape between the layers. An end of the length of the substantially S-shaped fiber optic cable is extended to an edge of the composite rotorcraft material. The end of the length of the substantially S-shaped fiber optic cable is terminated at the edge of the composite rotorcraft material in either a storage area or easily machinable embedded connection.

    Abstract translation: 将成本有效地将光纤电缆嵌入层压结构中的技术的一些实例并且终止层压板表面上的光纤电缆用于坚固且容易修理的连接可以在旋翼航空器复合材料中实现。 为了将电缆定位在旋翼航空器复合材料中，光纤电缆的长度被嵌入在复合旋翼航空器材料的层之间。 光纤电缆的长度在层之间取向为大致S形。 基本上S形的光纤电缆的长度的一端延伸到复合旋翼航空器材料的边缘。 基本上S形的光纤电缆的长度的端部终止于复合旋翼航空器材料在存储区域或易于加工的嵌入式连接中的边缘。

    Rotor system shear bearing
    15.
    发明授权
    Rotor system shear bearing 有权
    转子系统剪切轴承

    公开(公告)号：US09457897B2

    公开(公告)日：2016-10-04

    申请号：US13778803

    申请日：2013-02-27

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Drew Sutton ,  Frank B. Stamps

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

    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。

    Gimbaled Tail Rotor Hub with Spherical Elastomeric Centrifugal Force Bearing for Blade Retention and Pitch Change Articulation
    16.
    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。

    Rotor System Shear Bearing
    17.
    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。

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