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    COMPOSITE STRUCTURAL COMPONENT WITH TENSION/COMPRESSION MECHANICAL JOINT
    2.
    发明公开
    COMPOSITE STRUCTURAL COMPONENT WITH TENSION/COMPRESSION MECHANICAL JOINT 审中-公开

    公开(公告)号：EP3382220A1

    公开(公告)日：2018-10-03

    申请号：EP17164437.0

    申请日：2017-03-31

    Applicant: Crompton Technology Group Limited

    Inventor： BEALE, Tom

    IPC: F16C3/02

    CPC classification number: E04B1/185 ,  B62D29/048 ,  B64C1/06 ,  B64C2001/0072 ,  E04B1/30 ,  F16C3/026 ,  F16C2240/30

    Abstract: A composite structural component 2 comprises an elongate member made of a polymer matrix composite material, the elongate member generally extending along an axis of the composite structural component 2 from an end portion 5 thereof. The composite structural component 2 also comprises an end fitting 8 that forms a mechanical joint with the end portion 5. The elongate member comprises a first member 4 extending from the end portion 5 along the axis of the composite structural component 2 and a second member 3 extending from the end portion 5 along the axis of the composite structural component 2. The end fitting 8 is constrained in the end portion 5 by the first and second members 4,3 such that the first member 4 is preloaded with a compressive stress in the axial direction and the second member 3 is preloaded with a tensile stress in the axial direction.

    DAMAGE VISUALIZATION
    5.
    发明公开
    DAMAGE VISUALIZATION 审中-公开
    损伤可视化

    公开(公告)号：EP3292993A1

    公开(公告)日：2018-03-14

    申请号：EP16187764.2

    申请日：2016-09-08

    Applicant: Airbus Operations GmbH

    Inventor： Benthien, Hermann ,  Hegenbart, Matthias

    IPC: B29C70/56

    CPC classification number: B64C1/061 ,  B29C70/56 ,  B64C2001/0072 ,  B64G1/10 ,  B64G1/22

    Abstract: The present disclosure relates to a structural member (10, 10', 10") for an aircraft (50) or spacecraft, the structural member (10, 10', 10") comprising at least one fibre plastic composite (11), the fibre plastic composite (11) having at least one or a plurality of plies (12). The structural member (10, 10' 10") comprises at least one pre-stressing means (20) providing internal stresses to the fibre plastic composite (11) and that the fibre plastic composite (11) and the pre-stressing means (20) are configured and arranged to form a balanced system the internal stresses of which are essentially balanced to zero in a cured state of the said system. The balanced system of the structural member (10, 10' 10") is able to counteract loading stresses exerted to the airframe (52) in service such, that a damage caused by the loading stress is easily detectable visually.

    Abstract translation: 本公开涉及用于飞机（50）或航天器的结构构件（10,10'，10“），所述结构构件（10,10'，10”）包括至少一个纤维塑料复合材料（11），所述 纤维塑料复合物（11）具有至少一个或多个层（12）。 结构构件（10,10'，10“）包括至少一个为纤维塑料复合材料（11）提供内部应力的预应力装置（20），并且纤维塑料复合材料（11）和预应力装置 ）被构造和布置成形成平衡系统，该平衡系统的内部应力在所述系统的固化状态下基本平衡为零。结构构件（10,10'''''）的平衡系统能够抵消加载应力 在使用中施加到机身（52），使得由加载应力引起的损坏容易在视觉上检测到。

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