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    PRESSURE FUSELAGE OF AN AIRCRAFT WITH A FUSELAGE SHELL AND A PRESSURE BULKHEAD DISPOSED THEREIN
    1.
    发明申请
    PRESSURE FUSELAGE OF AN AIRCRAFT WITH A FUSELAGE SHELL AND A PRESSURE BULKHEAD DISPOSED THEREIN 有权
    具有熔断壳的飞机的压力熔断器和其中的压力容器

    公开(公告)号：US20150008285A1

    公开(公告)日：2015-01-08

    申请号：US14491251

    申请日：2014-09-19

    Applicant: AIRBUS OPERATIONS GMBH

    Inventor： M. Ichwan Zuardy ,  Karim Grase ,  Carsten Rowedder ,  Claas DeJong ,  Markus Mueller ,  Mathias Jessrang

    IPC: B64C1/10

    CPC classification number: B64C1/10

    Abstract: A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells.

    Abstract translation: 具有机身壳体和压力舱壁的飞机的压力舱壁优选地设置在后部区域中，用于形成机身内部压力区域，该压力舱壁附接在机身壳体内部的边缘上，其中压力舱壁 具有透镜状横截面和夹层结构，其包括夹在两个相对的外壳之间的泡沫芯。

    Attachment arrangement and installation method
    2.
    发明申请
    Attachment arrangement and installation method 有权
    附件安排和安装方法

    公开(公告)号：US20140158279A1

    公开(公告)日：2014-06-12

    申请号：US14096970

    申请日：2013-12-04

    Applicant: Airbus Operations GmbH

    Inventor： Cihangir Sayilgan ,  Markus Mueller ,  Henrik Linnemann

    IPC: F16B2/12

    CPC classification number: F16B2/12 ,  F16L3/02 ,  H02G3/32 ,  Y10T403/20

    Abstract: An arrangement for attaching a system to a structure having a base element to retain the system, a positioning element to position the base element at a location on the structure and a fixation device to fix the base element at the location on the structure. The base element has a section for holding the system and a section for being clamped to the structure. The clamping section has an element for alignment on the positioning element. The positioning element has a surface for being bonded to the structure and a positioning section for acting together with the alignment element. The fixation device has a counter element with a clamping area for being positioned on an opposite side of the structure from the clamping section and a fastener for clamping the base element and the counter element to the structure. An installation method for such an attachment arrangement is provided.

    Abstract translation: 一种用于将系统附接到具有用于保持系统的基座元件的结构的装置，定位元件将基座元件定位在结构上的位置处，以及固定装置，以将基座元件固定在结构上的位置。 基座元件具有用于保持系统的部分和用于夹紧到结构的部分。 夹紧部分具有用于在定位元件上对准的元件。 定位元件具有用于结合到结构的表面和用于与对准元件一起作用的定位部。 固定装置具有一个具有夹紧区域的对置元件，该夹持区域位于与夹紧部分相对的结构的相对侧上，以及紧固件，用于将基座元件和对置元件夹紧到结构体上。 提供了这种附接装置的安装方法。

    SHELL SEGMENT OF AN AIRCRAFT AND A PRODUCTION METHOD
    6.
    发明申请
    SHELL SEGMENT OF AN AIRCRAFT AND A PRODUCTION METHOD 有权
    飞机的壳段和生产方法

    公开(公告)号：US20140377501A1

    公开(公告)日：2014-12-25

    申请号：US14287625

    申请日：2014-05-27

    Applicant: Airbus Operations GmbH

    Inventor： Paul Joern ,  Markus Mueller

    IPC: B64C1/06 ,  B32B7/08 ,  B32B37/00

    CPC classification number: B64C1/06 ,  B29C65/48 ,  B29C65/562 ,  B29C65/62 ,  B29C65/72 ,  B29C66/1122 ,  B29C66/474 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/73752 ,  B29C70/24 ,  B29D99/0014 ,  B29L2031/3076 ,  B32B7/08 ,  B32B37/00 ,  B32B2038/0052 ,  B32B2038/008 ,  B64C1/12 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T428/24281 ,  B29K2307/04

    Abstract: A segment and a method for producing such a segment, in particular for an aircraft, having a skin field and a skin field stiffening structure. The skin field and stiffening structure are made from fiber-reinforced plastic materials. The stiffening structure is bonded to an inner surface of the skin field and comprises a multiplicity of first stiffeners and mounts which are formed integrally with the first stiffeners and extend in a transverse direction of the first stiffeners for the connection of second stiffeners to form an integral lattice structure. Reinforcement elements are provided for mechanically fixing the mounts to the skin field. Each reinforcement element has a connection section and a blocking section having an extension in a direction inclined to the connection section. The connection section penetrates the skin field and the mounts, and the blocking section is in contact with an outer surface of the skin field.

    Abstract translation: 特别是用于生产具有皮肤区域和皮肤场加强结构的这种特别是飞行器的区段和方法。 皮肤区域和加强结构由纤维增强塑料制成。 加强结构结合到皮肤区域的内表面并且包括多个第一加强件和安装件，其与第一加强件一体地形成并且在第一加强件的横向方向上延伸以连接第二加强件以形成整体 晶格结构。 提供增强元件用于将安装件机械地固定到皮肤区域。 每个加强元件具有连接部分和阻挡部分，其在与连接部分倾斜的方向上具有延伸部。 连接部分穿透皮肤区域和安装件，并且阻挡部分与皮肤区域的外表面接触。

    Method and a device for the manufacturing of a lightweight structure, and also a lightweight structure
    7.
    发明申请
    Method and a device for the manufacturing of a lightweight structure, and also a lightweight structure 审中-公开
    用于制造轻质结构的方法和装置，以及轻质结构

    公开(公告)号：US20130337207A1

    公开(公告)日：2013-12-19

    申请号：US13918318

    申请日：2013-06-14

    Applicant: Airbus Operations GmbH

    Inventor： Markus Mueller ,  Paul Joern ,  Tobias Stroehlein ,  Steffen Niemann ,  Christian Huehne ,  Markus Kleineberg

    IPC: B64C1/06 ,  B32B38/00

    CPC classification number: B64C1/068 ,  B29C70/083 ,  B29C70/30 ,  B29C70/326 ,  B29C70/545 ,  B29C70/56 ,  B29L2031/3082 ,  B32B38/0012 ,  Y02T50/43 ,  Y10T156/1002 ,  Y10T428/1372 ,  Y10T428/24124 ,  Y10T428/24479 ,  Y10T428/24612

    Abstract: A method for the manufacture of an integrally reinforced lightweight structure with a fiber-reinforced plastic by a molding tool, the structure having stiffening ribs crossing one another at node points and a skin attached to the stiffening ribs. The molding tool has channel-type depressions for creating the stiffening ribs. The steps include laying down into the depressions at least one intermediate layer and at least one reinforcement layer, repeating the laying down until the depressions are at least partially filled with intermediate layers and reinforcement layers to form the stiffening ribs with integral connecting feet, populating the molding tool with intermediate layers and reinforcement layers for manufacturing the skin, and curing and/or solidifying the intermediate layers and reinforcement layers. A resulting lightweight structure and a device for the manufacture of the lightweight structure are also disclosed.

    Abstract translation: 一种用于通过模制工具制造具有纤维增强塑料的整体增强轻质结构的方法，所述结构具有在节点处彼此交叉的加强筋和附着在加强肋上的皮肤。 模制工具具有用于形成加强肋的通道型凹陷。 这些步骤包括将至少一个中间层和至少一个加强层铺设在凹陷中，重复放置，直到凹陷至少部分地填充有中间层和加强层，以形成具有整体连接脚的加强肋， 具有用于制造皮肤的中间层和加强层的模制工具，以及固化和/或固化中间层和加强层。 还公开了所得到的轻质结构和用于制造轻量结构的装置。

    Method And Needle for Reinforcing Cellular Materials
    10.
    发明申请
    Method And Needle for Reinforcing Cellular Materials 审中-公开

    公开(公告)号：US20170151729A1

    公开(公告)日：2017-06-01

    申请号：US15355299

    申请日：2016-11-18

    Applicant: Airbus Operations GmbH

    Inventor： Paul Joern ,  Markus Mueller

    IPC: B29C70/08 ,  B29C65/54 ,  D05B85/00

    CPC classification number: B29C70/088 ,  B29C65/54 ,  B29C70/086 ,  B29C70/24 ,  B29L2031/3097 ,  D05B85/006

    Abstract: A method for reinforcing a cellular material includes producing a through-hole in the cellular material that extends from a first surface of the cellular material to a second surface of the cellular material; reaching through the through-hole from the first surface of the cellular material to the second surface of the cellular material; taking hold of at least one fiber bundle at the second surface of the cellular material; and pulling the at least one fiber bundle into the through-hole in the cellular material. Producing the through-hole in the cellular material includes perforating the cellular material with a rotating and/or oscillating needle.

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