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    END-EFFECTOR BODY FOR A FIXTURE DEVICE
    61.
    发明公开
    END-EFFECTOR BODY FOR A FIXTURE DEVICE 审中-公开
    ENDEFFEKTORKÖRPERFÜREINE ARMATURVORRICHTUNG

    公开(公告)号：EP3046725A1

    公开(公告)日：2016-07-27

    申请号：EP13893483.1

    申请日：2013-09-16

    Applicant: SAAB AB

    Inventor： ENMAR, Mats

    IPC: B23Q3/06 ,  B25B11/02 ,  B64F5/00

    CPC classification number: B23Q3/103 ,  B23Q1/5456 ,  B25B11/02 ,  B64F5/10

    Abstract: The invention relates to an end-effector body (210, 252, 310) for a fixture device comprising a first fixing point (218, 262, 318) for attachment to an article (270, 370, 470), wherein the end-effector body (210, 252, 310) comprises a second fixing point (220, 262, 320) for article (270, 370, 470) attachment. The fixing points (218, 220, 262, 318, 320) are arranged to face away from the end-effector body (210, 252, 310) in different directions. The invention also regards an adjustable fixture device (400) comprising such end-effector body (210, 252, 310).

    Abstract translation: 用于固定装置的末端执行器主体。 末端执行器主体包括第一固定点，第二固定点和附接到物品的第三固定点。 固定点被布置为在不同方向上远离末端执行器主体。 而且，一种包括末端执行器主体的可调节固定装置。

    AIRCRAFT WING PANEL ASSEMBLY AND METHOD OF MANUFACTURING
    62.
    发明授权
    AIRCRAFT WING PANEL ASSEMBLY AND METHOD OF MANUFACTURING 有权
    弗吉尼亚州弗吉尼亚州赫尔辛基

    公开(公告)号：EP2668092B1

    公开(公告)日：2016-07-27

    申请号：EP12702072.5

    申请日：2012-01-26

    Applicant: Airbus Operations Limited

    Inventor： DOUGLAS, Paul ,  PETIT, David Patrick Stephane

    IPC: B64C1/06 ,  B64D37/00 ,  B64C3/34 ,  B64C3/26

    CPC classification number: B64C3/26 ,  B29C33/505 ,  B29C70/446 ,  B29C70/865 ,  B29D99/0003 ,  B64C3/182 ,  B64C3/34 ,  B64D37/005 ,  B64F5/10 ,  F16L3/26 ,  Y02T50/43 ,  Y02T50/44 ,  Y10T156/10 ,  Y10T428/24612

    Abstract: Embodiments of the invention relate to a stringer (108) adapted to transport fluid in an aircraft wing (100). For example, the stringer may be adapted to provide venting to one or more fuel tanks (111) in the aircraft wing, or may be adapted to provide fuel to the one or more fuel tanks. To perform this function, the stringer comprises a duct member (120) providing a duct and a structural member (121) providing an attachment surface for attachment of the stringer to a wing panel (112). Typically, the stringer is formed from a composite material such as carbon fibre reinforced plastic. A method of manufacturing the stringer is also disclosed.

    Abstract translation: 本发明的实施例涉及一种适于在飞机机翼（100）中输送流体的纵梁（108）。 例如，桁条可以适于提供到飞机机翼中的一个或多个燃料箱（111）的通风，或者可以适于向一个或多个燃料箱提供燃料。 为了执行该功能，桁条包括提供管道的管道构件（120）和提供用于将桁条附接到翼板（112）的附接表面的结构构件（121）。 通常，桁条由诸如碳纤维增强塑料的复合材料形成。 还公开了制造桁条的方法。

    Mobile automated overhead assembly tool for aircraft structures
    64.
    发明公开
    Mobile automated overhead assembly tool for aircraft structures 审中-公开
    手机自动化ÜberkopfmontagewerkzeugfürFlugzeugstrukturen

    公开(公告)号：EP2939796A3

    公开(公告)日：2016-06-01

    申请号：EP14196483.3

    申请日：2014-12-05

    Applicant: The Boeing Company

    Inventor： Desjardien, Matthew Ray ,  Reid, Eric M ,  Best, Steven A ,  Martin, Daniel Saeil

    IPC: B25J5/00 ,  B25J9/02 ,  B25J15/04 ,  B25J9/00 ,  B25J11/00

    CPC classification number: B64F5/10 ,  B25J5/007 ,  B25J9/0018 ,  B25J9/026 ,  B25J11/007 ,  B25J15/0491 ,  B66C5/02 ,  B66C19/005 ,  Y10T29/49622

    Abstract: A method and apparatus for performing an operation (111) on a work surface (116) (116) of a structure (106). The apparatus may comprise a motion platform (122) and an overhead support system (118). The motion platform (122) may be configured to be positioned above the work surface (116) (116) of the structure (106) to perform the operation (111) on the work surface (116) (116). The overhead support system (118) may be configured to carry the motion platform (122) across a floor (107) of a manufacturing environment (100) from a first location (117) to a second location (121).

    Abstract translation: 一种用于在结构（106）的工作表面（116）（116）上执行操作（111）的方法和装置。 该装置可以包括运动平台（122）和架空支撑系统（118）。 运动平台（122）可以被配置为定位在结构（106）的工作表面（116）（116）上方，以在工作表面（116）（116）上执行操作（111）。 架空支撑系统（118）可以被配置成将运动平台（122）从制造环境（100）的第一位置（117）运送到第二位置（121）。

    METHOD FOR PRODUCING REINFORCING STRUCTURE
    65.
    发明公开
    METHOD FOR PRODUCING REINFORCING STRUCTURE 审中-公开
    VERFAHREN ZUR HERSTELLUNG EINERVERSTÄRKUNGSSTRUKTUR

    公开(公告)号：EP3020540A1

    公开(公告)日：2016-05-18

    申请号：EP14823339.8

    申请日：2014-06-26

    Applicant: Mitsubishi Heavy Industries, Ltd.

    Inventor： YAMAMORI Taku

    IPC: B29C70/06 ,  B64C1/00 ,  B64C3/34 ,  B64D45/02 ,  B64F5/00

    CPC classification number: B64C1/12 ,  B29C70/06 ,  B29C70/882 ,  B29K2105/08 ,  B29K2307/04 ,  B29K2995/0005 ,  B29L2031/3085 ,  B64C1/064 ,  B64C2001/0072 ,  B64D45/02 ,  B64F5/10 ,  Y02T50/43

    Abstract: This method for producing a reinforcing structure comprises: a step for preparing a stringer that has a fiber exposed surface; a step for arranging a conductive protective material so as to cover at least a part of the fiber exposed surface; a step for arranging the stringer on a skin that has an uncured resin component; and a step for curing the skin after the step for arranging the stringer. The conductive protective material contains a composite material that is obtained by combining a resin component and a conductive fiber component. The step for curing the skin comprises a step wherein the skin and the conductive protective material are cured at the same time. This method for producing a reinforcing structure is able to prevent edge growth without increasing the number of production steps.

    Abstract translation: 该加强结构体的制造方法包括：制造具有纤维露出面的纵梁的工序; 布置导电保护材料以覆盖所述纤维暴露表面的至少一部分的步骤; 将桁条布置在具有未固化的树脂成分的皮肤上的步骤; 以及在用于布置桁条的步骤之后固化皮肤的步骤。 导电保护材料包含通过组合树脂组分和导电纤维组分而获得的复合材料。 固化皮肤的步骤包括其中皮肤和导电保护材料同时固化的步骤。 这种增强结构的制造方法能够在不增加制造工序的情况下防止边缘生长。

    BRAIDED COMPOSITE SPAR
    69.
    发明公开
    BRAIDED COMPOSITE SPAR 有权
    UMFLOCHTENER HOLM AUS VERBUNDWERKSTOFF

    公开(公告)号：EP2986439A1

    公开(公告)日：2016-02-24

    申请号：EP14719819.6

    申请日：2014-04-17

    Applicant: Airbus Operations Limited

    Inventor： FONG, Tony ,  AXFORD, Timothy

    IPC: B29C70/22 ,  B64C3/16 ,  B64C23/06

    CPC classification number: B64C3/185 ,  B29C70/222 ,  B29C70/30 ,  B29C70/32 ,  B29L2031/3085 ,  B32B38/1866 ,  B32B2305/72 ,  B64C23/069 ,  B64F5/10 ,  Y02T50/164 ,  Y02T50/43

    Abstract: A winglet comprising a tubular main spar with forward and aft main spar webs joined by upper and lower main spar caps; a front spar with a front spar web, an upper front spar cap, and a lower front spar cap; an upper skin joined to the upper main spar cap and the upper front spar cap; and a lower skin joined to the lower main spar cap and the lower front spar cap. The winglet is manufactured by co-curing the upper skin to the upper main spar cap and the upper front spar cap; and co-curing the lower skin to the lower main spar cap and the lower front spar cap.

    Abstract translation: 小翼包括具有由上和下主翼梁连接的前和后主翼梁的管状主翼梁; 具有前翼梁腹板的前翼梁，上前翼梁帽和下前翼梁盖; 连接到上主翼梁帽和上前翼梁帽的上皮; 以及连接到下主翼梁帽和下前翼梁帽的下皮。 小翼通过将上部皮肤与上部主翼梁帽和上部前翼梁帽共同固化来制造; 并将下部皮肤与下部主翼梁帽和下部前翼梁帽共同固化。

    CELLULAR CORE COMPOSITE AIRFOILS
    70.
    发明公开
    CELLULAR CORE COMPOSITE AIRFOILS 审中-公开
    VERBUNDSCHAUFELN MIT ZELLIGEM KERN

    公开(公告)号：EP2981407A1

    公开(公告)日：2016-02-10

    申请号：EP13881178.1

    申请日：2013-09-02

    Applicant: Rodman, William L.

    Inventor： Rodman, William L.

    IPC: B29C70/40

    CPC classification number: B64F5/0009 ,  B29C70/44 ,  B29D99/0025 ,  B64C3/24 ,  B64C2003/147 ,  B64D45/02 ,  B64F5/10 ,  Y02T50/43 ,  Y10T156/10

    Abstract: A complex-shaped, three-dimensional fiber reinforced composite trailing edge structure may be formed by using counteracting pressures applied to a structural lay-up of wetted fibers placed onto pressurizable members to form continuous fore and aft loops. In turn, the loops may be structurally functional to transfer loads from the trailing edge structure to a wing center section. The trailing structure may include may include fillers and/or a metallic insert, wherein the metallic insert may provide a lightening strike capability for the trailing edge structure.

    Abstract translation: 复杂形状的三维纤维增强复合材料后缘结构可以通过使用施加到放置在可加压构件上的润湿纤维的结构层叠上的抵消压力来形成连续的前后环来形成。 反过来，环可以在结构上起作用以将负载从后缘结构传递到翼中心部分。 拖尾结构可以包括填充物和/或金属插入物，其中金属插入物可以为后缘结构提供减轻打击能力。

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