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    PLANKING PANEL FOR A STRUCTURAL COMPONENT, FLOW BODY COMPRISING SUCH A PLANKING PANEL AND DEVICE FOR MONITORING MATERIAL DAMAGE ON SUCH A PLANKING PANEL
    5.
    发明申请
    PLANKING PANEL FOR A STRUCTURAL COMPONENT, FLOW BODY COMPRISING SUCH A PLANKING PANEL AND DEVICE FOR MONITORING MATERIAL DAMAGE ON SUCH A PLANKING PANEL 审中-公开
    用于结构构件的平面板，包含这样的平面板的流动体和用于监测这样的平面板上的材料损坏的装置

    公开(公告)号：US20140000381A1

    公开(公告)日：2014-01-02

    申请号：US13743767

    申请日：2013-01-17

    Applicant: Airbus Operations GmbH

    Inventor： Ichwan Zuardy ,  Pierre Zahlen ,  Axel Siegfried Herrmann

    IPC: G01N19/08

    CPC classification number: B64C1/12 ,  B32B3/02 ,  B32B3/06 ,  B32B3/08 ,  B32B3/28 ,  B32B3/30 ,  B32B5/18 ,  B32B7/04 ,  B32B2266/0214 ,  B32B2266/04 ,  B32B2266/045 ,  B32B2307/102 ,  B32B2307/54 ,  B32B2307/5825 ,  B32B2605/18 ,  B32B2607/00 ,  B64C3/20 ,  B64C3/26 ,  B64D45/00 ,  B64D2045/0085 ,  G01N19/08 ,  Y10T428/239 ,  Y10T428/24 ,  Y10T428/24322 ,  Y10T428/249923

    Abstract: The invention pertains to a planking panel (B) for a structural component (1) that is realized in the form of a sandwich component in its inner region (BI) that extends in a planar fashion and features a first skin section (11), a second skin section (12) and a core section (13) that is situated between these two skin sections, wherein the core section (13) connects the first and the second skin sections (11, 12) to one another in a planar fashion, with the invention being characterized in that a plurality of monitoring lines (14) is provided that extend over a planar section of the core section (13) to be monitored in order to detect damage in the core section (13) and respectively feature a first connection point (15) on a first end (14a) and a second connection point (16) on a second end (16a) in order to apply a monitoring signal (UK), wherein the monitoring lines (14) have a tear strength that lies in the range between 50% and 100% of the tear strength of the core section (13).

    Abstract translation: 本发明涉及一种用于结构部件（1）的板条板（B），其在其内部区域（BI）中以三明治部件的形式实现，其以平面方式延伸并且具有第一皮肤部分（11）， 第二皮肤部分（12）和位于这两个皮肤部分之间的芯部分（13），其中，芯部分（13）以平面方式彼此连接第一和第二皮肤部分（11,12） 本发明的特征在于，提供了多个监测线（14），其在待监测的芯部分（13）的平面部分上延伸，以便检测芯部分（13）中的损伤，并且分别具有 为了施加监测信号（UK），第一端（14a）上的第一连接点（15）和第二端（16a）上的第二连接点（16），其中监测线（14）具有撕裂强度 其位于芯部（13）的撕裂强度的50％至100％的范围内。

    Aircraft structural component
    6.
    发明授权
    Aircraft structural component 有权

    公开(公告)号：US10377461B2

    公开(公告)日：2019-08-13

    申请号：US14747707

    申请日：2015-06-23

    Applicant: Airbus Operations GmbH

    Inventor： Paul Jörn ,  Pierre Zahlen ,  Markus Müller ,  Ichwan Zuardy ,  Claus Hanske

    IPC: B64C1/12 ,  B64C1/06

    Abstract: An aircraft structural component having a skin element, including an inner surface, a multitude of transverse stiffening elements, which lie against the inner surface of the skin element, and a multitude of longitudinal stiffening elements, perpendicular to the transverse stiffening elements against the inner surface of the skin element, wherein between a first and a second transverse stiffening element and also between a first and a second longitudinal stiffening element, a first skin section is defined. An aircraft structural component is provided with the quantity of the longitudinal stiffening elements reduced. A first applied reinforcement includes a core layer having a contour line running along the circumference of the skin element, the first applied reinforcement including a face sheet surrounding the core layer on the side thereof which faces away from the skin element, which face sheet is connected to the skin element along the core layer contour line.

    Pressurized airplane fuselage, comprising a pressure bulkhead
    7.
    发明授权
    Pressurized airplane fuselage, comprising a pressure bulkhead 有权

    公开(公告)号：US10099766B2

    公开(公告)日：2018-10-16

    申请号：US13970656

    申请日：2013-08-20

    Applicant: Airbus Operations GmbH

    Inventor： Karim Grase ,  Ichwan Zuardy ,  Henning Scheel ,  Dieter Hachenberg ,  B. Claudio Vultaggio

    IPC: B64C1/10

    Abstract: A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area, wherein the edge of the pressure bulkhead is circumferentially attached to the fuselage structure by fastening means, wherein the fastening means include a pair of ring-shaped attachment frames made of an open or hollow profile, which are disposed at each side of the pressure bulkhead respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.

    Panel member for an airframe
    10.
    发明授权
    Panel member for an airframe 有权

    公开(公告)号：US10814957B2

    公开(公告)日：2020-10-27

    申请号：US14304252

    申请日：2014-06-13

    Applicant: AIRBUS OPERATIONS GMBH

    Inventor： Ichwan Zuardy ,  Oliver Bullinger ,  Claudio Vultaggio

    IPC: B64C3/20 ,  B64C1/12 ,  B64D45/02 ,  B32B38/08 ,  B32B38/18 ,  B64C1/00 ,  B64G1/22

    Abstract: The disclosure relates to a composite panel member for an airframe of an aircraft or spacecraft, the composite panel member having a laminated or sandwich structure including: a first outer layer extending over a first side of the panel member; a second outer layer extending over a second side of the panel member; a core layer between the first and second outer layers; and at least one support element configured as an electrical conductor and provided within the core layer between the first and second outer layers. In this regard, the at least one support element extends within the core layer substantially parallel to the first and second outer layers.

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