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    EMBEDDING FIBER OPTIC CABLES IN ROTORCRAFT COMPOSITES
    2.
    发明申请
    EMBEDDING FIBER OPTIC CABLES IN ROTORCRAFT COMPOSITES 有权
    旋转复合材料嵌入式光纤电缆

    公开(公告)号：US20150370030A1

    公开(公告)日：2015-12-24

    申请号：US14310172

    申请日：2014-06-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Drew Sutton ,  Brian Tucker ,  Troy Schank

    IPC: G02B6/46 ,  G02B6/44

    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。

    AMORPHOUS METAL ROTOR BLADE ABRASION STRIP
    3.
    发明申请
    AMORPHOUS METAL ROTOR BLADE ABRASION STRIP 审中-公开
    非晶金属转子叶片磨损条

    公开(公告)号：US20140271214A1

    公开(公告)日：2014-09-18

    申请号：US13829191

    申请日：2013-03-14

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Drew Sutton ,  Jeffrey P. Nissen ,  Andrew Haldeman

    IPC: F01D5/28 ,  B23P15/04 ,  B64C11/20

    CPC classification number: F01D5/282 ,  B23P15/04 ,  B64C11/205 ,  B64C27/473 ,  C22C45/00 ,  Y10T29/49337

    Abstract: A rotor blade abrasion strip and method to manufacturing the same. The abrasion strip being composed of a molded amorphous metal contoured to match a leading edge outer surface of the rotor blade. The abrasion strip being configured to removably attach to a leading edge of the rotor blade and configured to prevent damage to the leading edge during flight. The method includes molding the abrasion strip with the amorphous metal.

    Abstract translation: 转子叶片磨损条及其制造方法。 磨损条由成型的非晶金属组成，其形状匹配转子叶片的前缘外表面。 所述磨耗条构造成可拆卸地附接到所述转子叶片的前缘并且构造成防止在飞行期间损坏所述前缘。 该方法包括用无定形金属模制耐磨条。

    Removable Rotor Blade Tip
    4.
    发明申请
    Removable Rotor Blade Tip 审中-公开
    可拆卸转子叶片尖端

    公开(公告)号：US20140255201A1

    公开(公告)日：2014-09-11

    申请号：US13789265

    申请日：2013-03-07

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Drew Sutton ,  Tim Ledbetter

    IPC: F01D5/14

    CPC classification number: F01D5/147 ,  B64C27/463 ,  Y10T29/49337

    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.

    Abstract translation: 转子叶片具有翼展方向轴线，根部包括具有锚定表面的锚固件，锚固件表面构造成相对于翼展方向轴线形成相对于翼展方向轴线的法线角度和相对于翼展方向轴线的锐角中的至少一个，以及包括连接器 具有构造成补充锚固表面的连接器表面。

    ROTORCRAFT ROTOR BLADE ASSEMBLY
    7.
    发明申请
    ROTORCRAFT ROTOR BLADE ASSEMBLY 审中-公开
    滚子转子叶片组件

    公开(公告)号：US20170009588A1

    公开(公告)日：2017-01-12

    申请号：US14792263

    申请日：2015-07-06

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Paul K. Oldroyd ,  Drew Sutton ,  Andrew Maresh ,  Christopher Foskey

    IPC: F01D5/14

    CPC classification number: F01D5/147 ,  B64C27/473

    Abstract: A rotorcraft rotor blade assembly includes a stub spar extending less than a full span of the rotor blade assembly. An upper skin portion extends substantially the full span of the rotor blade assembly. A lower skin portion extends substantially the full span of the rotor blade assembly. The stub spar is positioned between the upper skin portion and the lower skin portion.

    Abstract translation: 旋翼飞船转子叶片组件包括延伸小于转子叶片组件的全跨度的短柱梁。 上皮肤部分基本上延伸到转子叶片组件的整个跨度。 较低的皮肤部分基本上延伸到转子叶片组件的整个跨度。 短柱梁定位在上皮肤部分和下皮肤部分之间。

    HYBRID SPHERICAL AND THRUST BEARING
    8.
    发明申请
    HYBRID SPHERICAL AND THRUST BEARING 有权
    混合轴承和轴承

    公开(公告)号：US20150211573A1

    公开(公告)日：2015-07-30

    申请号：US14661007

    申请日：2015-03-18

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Drew Sutton ,  Frank B. Stamps

    IPC: F16C27/06 ,  F16C33/20 ,  F16C33/74 ,  F16C17/10

    CPC classification number: F16C27/063 ,  B64C27/54 ,  B64C27/605 ,  F16C11/0614 ,  F16C11/083 ,  F16C17/10 ,  F16C33/201 ,  F16C33/74 ,  F16C2326/43 ,  F16F1/393 ,  Y10T29/4971

    Abstract: According to one embodiment, a bearing features an elastomeric portion having an opening therethrough, a member disposed within the opening of the elastomeric portion, and a separation feature disposed between the member and the elastomeric portion. The member comprises a conical body portion arranged such that an interior diameter of the conical body portion is smaller than an exterior diameter of the conical body portion. The separation feature prevents contact between the member and the elastomeric portion.

    Abstract translation: 根据一个实施例，轴承的特征在于具有穿过其中的开口的弹性体部分，设置在弹性体部分的开口内的部件以及设置在该部件和弹性体部分之间的分离部件。 该构件包括锥形主体部分，其被布置成使得锥形主体部分的内径小于圆锥形主体部分的外径。 分离特征防止构件和弹性体部分之间的接触。

    ROTOR HUB FOR A ROTORCRAFT
    9.
    发明申请
    ROTOR HUB FOR A ROTORCRAFT 有权
    用于转子的转子座

    公开(公告)号：US20150175259A1

    公开(公告)日：2015-06-25

    申请号：US14135941

    申请日：2013-12-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Christopher Foskey ,  Drew Sutton ,  Frank B. Stamps

    IPC: B64C27/72

    CPC classification number: B64C27/72 ,  B64C27/001 ,  B64C27/35 ,  B64C27/37 ,  B64C2027/003 ,  B64C2027/004 ,  B64C2027/7216

    Abstract: A rotor hub can include a yoke, a mast, and one or more radially oriented actuators. The first radial actuator and the second radial actuator each have a piston configured to impart a translation of the yoke relative to the mast. The radial actuators are configured to attenuate in-plane whirling vibrations. The rotor hub can also have actuators coupled between the mast and the yoke for attenuating flapping and vertical vibrations.

    Abstract translation: 转子毂可以包括轭，桅杆和一个或多个径向定向的致动器。 第一径向致动器和第二径向致动器各自具有构造成赋予轭相对于桅杆平移的活塞。 径向致动器构造成衰减飞机内的旋转振动。 转子轮毂还可以具有联接在桅杆和轭架之间的致动器，用于衰减振荡和垂直振动。

    Composite Rotor System Using Two Race Track Style Cantilevered Yokes
    10.
    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。

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