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    HELICOPTER TAIL ROTOR BLADE WITH COMPOSITE YOKE FITTING
    1.
    发明公开
    HELICOPTER TAIL ROTOR BLADE WITH COMPOSITE YOKE FITTING 有权
    HECKROTORBLATTANORDUNG旋翼机及其制造方法

    公开(公告)号：EP3072814A1

    公开(公告)日：2016-09-28

    申请号：EP15188195.0

    申请日：2015-10-02

    Applicant: Bell Helicopter Textron Inc.

    Inventor： HALDEMAN, Andrew ,  STAMPS, Frank Bradley ,  SUTTON, Drew

    IPC: B64C27/48 ,  B64C27/473

    CPC classification number: B64C27/46 ,  B64C27/48 ,  B64C2027/4736

    Abstract: A rotor blade assembly includes a rotor blade (504) comprising an inboard end (506) and an outboard end (508). A composite yoke fitting (502) made from a composite material is attached to the rotor blade (504). The composite yoke fitting (502) includes an outboard portion (510) inserted into the inboard end (506) of the rotor blade (504), an inboard portion (512), and a flexure region (514) about which the rotor blade (504) is configured to flex. The inboard portion (512) and the flexure region (514) are outside the rotor blade (504).

    EMBEDDING FIBER OPTIC CABLES IN ROTORCRAFT COMPOSITES
    3.
    发明公开
    EMBEDDING FIBER OPTIC CABLES IN ROTORCRAFT COMPOSITES 有权
    嵌入式光纤光缆在转子复合材料中的应用

    公开(公告)号：EP2957884A1

    公开(公告)日：2015-12-23

    申请号：EP15172054.7

    申请日：2015-06-15

    Applicant: Bell Helicopter Textron Inc.

    Inventor： SUTTON, Drew ,  TUCKER, Brian ,  SCHANK, Troy

    IPC: G01M11/08 ,  G02B6/00

    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 (306) in laminate structures and to terminate the fiber optic cables (306) on the surface of the laminate for robust and easily-repairable connections can be implemented in rotorcraft composites (302). To position a cable (306) in the rotorcraft composite (302), a length of a fiber optic cable (306) is embedded between layers of a composite rotorcraft material (300). The length of the fiber optic cable (306) is oriented in a substantially S-shape between the layers. An end of the length of the substantially S-shaped fiber optic cable (306) is extended to an edge of the composite rotorcraft material (300). The end of the length of the substantially S-shaped fiber optic cable (306) is terminated at the edge of the composite rotorcraft material (300) in either a storage area or easily machinable embedded connection.

    Abstract translation: 可以在旋翼飞行器复合材料（302）中实施以经济有效的方式将光纤电缆（306）嵌入到层压结构中并且将层压材料的表面上的光纤电缆（306）端接以便鲁棒且容易修复的连接的技术的一些示例， 。 为了将电缆（306）定位在旋翼飞行器复合材料（302）中，将一段光缆（306）嵌入复合旋翼飞行器材料（300）的层之间。 光纤电缆（306）的长度在层之间以大致S形定向。 大致S形光缆（306）的长度的一端延伸到复合旋翼飞机材料（300）的边缘。 基本上S形的光纤电缆（306）的长度的末端在复合旋翼飞机材料（300）的边缘处在存储区域或易于机械加工的嵌入连接处终止。

    ROTORCRAFT ROTOR BLADE ASSEMBLY
    6.
    发明公开
    ROTORCRAFT ROTOR BLADE ASSEMBLY 审中-公开
    ROTORBLATTANORDNUNG EINESDREHFLÜGELFLUGZEUGS

    公开(公告)号：EP3127808A1

    公开(公告)日：2017-02-08

    申请号：EP16172820.9

    申请日：2016-06-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： SUTTON, Drew ,  OLDROYD, Paul K. ,  BRASWELL, Jr., James ,  WOLTHUIS, Scott ,  SHERRILL, Paul

    IPC: B64C27/473

    CPC classification number: B64C27/473 ,  B64C2027/4736

    Abstract: A rotorcraft rotor blade assembly (100) includes an upper skin portion (104) extending substantially a full span of the rotor blade assembly (100) and a lower skin portion (106) extending substantially the full span of the rotor blade assembly (100). Each of the upper skin portion (104) and the lower skin portion (106) is configured to carry at least substantially 30% of rotor blade assembly (100) loads.

    Abstract translation: 旋翼航空器转子叶片组件（100）包括基本上延伸的转子叶片组件（100）的整个跨度的上部皮肤部分（104）和基本上延伸到转子叶片组件（100）的整个跨度的下部皮肤部分（106） 。 上皮肤部分（104）和下皮肤部分（106）中的每一个构造成承载至少大约30％的转子叶片组件（100）的载荷。

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