公开(公告)号：EP2448813B1

公开(公告)日：2014-05-21

申请号：EP10734190.1

申请日：2010-07-02

申请人： Airbus Operations

发明人： MOREAU, Dominique ,  MEYER, Cédric ,  GAUDIN, Jocelyn

IPC分类号： B64C1/12 ,  B64C1/06

CPC分类号： B64C1/064 ,  B64C1/069 ,  B64C1/12 ,  B64C2001/0081

公开(公告)号：EP2682340A2

公开(公告)日：2014-01-08

申请号：EP13173489.9

申请日：2013-06-25

申请人： The Boeing Company

发明人： Dopker, Bernhard ,  Chan, Wallace Chi-Hua ,  Ostroff, Henri Michael

IPC分类号： B64C1/06 ,  B64F5/00

CPC分类号： B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49826

摘要： A fuselage having a longitudinal window belt (58) has a composite outer skin including upper and lower composite skin sections (52, 54). The skin includes at least one window opening (70) located at the window belt (58). The upper and lower skin sections are joined together by a longitudinal splice joint (56) located at the window belt (58).

摘要翻译： 具有纵向窗口带（58）的机身具有包括上下复合皮肤部分（52,54）的复合外皮。 皮肤包括位于窗口带（58）处的至少一个窗口（70）。 上皮肤部分和下皮肤部分通过位于窗口带（58）处的纵向接合接头（56）连接在一起。

公开(公告)号：EP2650120A2

公开(公告)日：2013-10-16

申请号：EP13162774.7

申请日：2013-04-08

申请人： The Boeing Company

发明人： Griess, Kenneth Harlan ,  Georgeson, Gary E.

IPC分类号： B32B7/12 ,  B32B15/01 ,  B32B15/14 ,  B32B3/06 ,  B32B3/14 ,  B32B3/18 ,  B29C70/86 ,  B64C1/26 ,  B64C3/20 ,  B64C5/06 ,  B64C27/48 ,  B64C27/473

CPC分类号： B29C70/86 ,  B29C70/885 ,  B32B3/06 ,  B32B3/14 ,  B32B3/18 ,  B32B7/12 ,  B32B15/01 ,  B32B15/14 ,  B64C1/069 ,  B64C1/12 ,  B64C1/1461 ,  B64C1/26 ,  B64C3/20 ,  B64C27/48 ,  B64C2001/0072 ,  B64C2027/4736 ,  Y02T50/43

摘要： A composite structure comprises stacked sets of laminated fiber reinforced resin plies and metal sheets. Edges of the resin plies and metal sheets are interleaved to form a composite-to-metal joint connecting the resin plies with the metal sheets.

摘要翻译： 复合结构包括层叠纤维增强树脂层和金属板的堆叠组。 树脂层和金属片的边缘交织以形成将树脂层与金属片连接的复合金属接头。

公开(公告)号：EP2334546B1

公开(公告)日：2013-05-22

申请号：EP09753155.2

申请日：2009-09-29

申请人： Airbus Operations

发明人： CASTANET, Marc-Antoine

IPC分类号： B64C1/12 ,  B64C3/26 ,  F16B5/00 ,  B64C1/06 ,  B64F5/00 ,  B29C70/28

CPC分类号： B64C1/12 ,  B29C35/02 ,  B29C53/40 ,  B29C66/1122 ,  B29C66/1222 ,  B29C66/1224 ,  B29C66/14 ,  B29C66/4322 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/7394 ,  B29C66/73941 ,  B29K2063/00 ,  B29K2101/10 ,  B29K2105/06 ,  B29K2277/10 ,  B29K2307/00 ,  B29K2309/08 ,  B29L2031/3082 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  B29K2307/04

摘要： The invention relates to a panel assembly for an aircraft fuselage, in which a first panel (10) and a second panel (20) respectively have a first end portion (11) and a second end portion (21) overlapping one another and connected to one another. The aim of the invention is particularly to limit the impact of the aerodynamic flow on the edge (25) of said second end portion (21) without impairing the mechanical aspect of the first panel (10). The aim is achieved by using a level difference (30) extending from said first end portion (11) opposite which the edge (25) of the second end portion (21) is located, the inner surface (14) of the first panel (10) having no level difference.

公开(公告)号：EP2170696B1

公开(公告)日：2012-08-29

申请号：EP08774921.4

申请日：2008-07-09

申请人： Airbus Operations GmbH

发明人： NOEBEL, Torsten ,  PAULUKUHN, Arne

IPC分类号： B64C1/06

CPC分类号： B64C1/064 ,  B64C1/065 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43

公开(公告)号：EP2242682B1

公开(公告)日：2012-05-23

申请号：EP09712562.9

申请日：2009-02-11

申请人： Airbus Operations GmbH

发明人： SAUERMANN, Axel

IPC分类号： B64C1/06 ,  B29C65/00

CPC分类号： B64C1/069 ,  B29B13/025 ,  B29C65/02 ,  B29C65/20 ,  B29C65/4815 ,  B29C65/483 ,  B29C65/5042 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/43 ,  B29C66/43441 ,  B29C66/5221 ,  B29C66/54 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/73715 ,  B29C66/73921 ,  B29C66/73941 ,  B29K2071/00 ,  B29K2101/12 ,  B29K2105/06 ,  B29K2307/00 ,  B29L2031/3082 ,  B64C2001/0072 ,  Y02T50/43 ,  B29C65/00 ,  B29K2063/00 ,  B29K2307/04

摘要： The invention relates to a method of connecting two fuselage sections (1, 2, 21, 22) formed by a fibre-reinforced plastics material, in particular wound fuselage sections (1, 2, 21, 22) for aircraft fuselage cells, having a multiplicity of stringers (10, 11, 35, 36) arranged with a uniform distribution at a distance from and parallel to one another on the inner side of an outer skin (3, 4, 25, 26), with the formation of a transverse joint (5, 30). In order to be able in particular to join together wound CFRP fuselage sections so that simple tolerance compensation is made possible in a continuous, industrial production process, the method according to the invention comprises the following steps: aligning a first and a second fuselage section (1, 2, 21, 22) with respect to one another, heating and adapting at least one transverse butt strap (9, 23), formed by a fibre-reinforced thermoplastic material, in such a way that tolerance compensation between differing cross-sectional geometries of the first and second fuselage sections (1, 2, 21, 22) is made possible, or heating at least one end region (27) of a second fuselage section (2, 22) formed by a fibre-reinforced thermoplastic material, and joining together the two fuselage sections (1, 2, 21, 22).

公开(公告)号：EP2444238A2

公开(公告)日：2012-04-25

申请号：EP11184885.9

申请日：2011-10-12

申请人： The Boeing Company

发明人： McCarville, Douglas A ,  Guzman, Juan C. ,  Hand, Michael Leslie

IPC分类号： B29C65/48 ,  B29L24/00

CPC分类号： B32B3/20 ,  B29C65/4835 ,  B29C65/505 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/1162 ,  B29C66/301 ,  B29C66/43 ,  B29C66/432 ,  B29C66/435 ,  B29C66/438 ,  B29C66/496 ,  B29C66/543 ,  B29C66/547 ,  B29C66/636 ,  B29C66/721 ,  B29C66/72523 ,  B29C66/81455 ,  B29C66/91411 ,  B29C66/919 ,  B29C66/929 ,  B29L2024/006 ,  B29L2031/3082 ,  B29L2031/3097 ,  B29L2031/7172 ,  B32B3/06 ,  B32B2605/00 ,  B32B2605/18 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T428/13 ,  Y10T428/19

摘要： Fluted core sandwich panels are joined together to form a composite structure. Variations in panel ends are accommodated by a core stiffener insert installed in a joint between ends of the panels.

摘要翻译： 槽纹夹芯板接合在一起以形成复合结构。 在面板端部的变化由安装在面板的端部之间的接头的芯加强件插入容纳。

公开(公告)号：EP2209710B1

公开(公告)日：2012-02-08

申请号：EP08843828.8

申请日：2008-10-30

申请人： Airbus Operations GmbH

发明人： STEPHAN, Andreas

IPC分类号： B64C1/00

CPC分类号： B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49346 ,  Y10T29/49622

摘要： The invention relates to a transversal butt strap (1, 19, 37) for producing a fuselage cell of an aircraft, by connecting a plurality of CFK fuselage sections (5, 26, 27, 43) produced especially by a winding method and respectively forming a transversal seam. The flexible transversal butt strap (1, 19, 37) is multi-layered, i.e. it comprises a plurality of strap segments (7-9, 20-23, 38-40) arranged one over the other, each strap segment (7-9, 20-23, 38-40) comprising a plurality of longitudinal slits (10, 11, 44, 45) that can respectively perform slight radial bending movements in order to generate a tolerance compensation in the radial direction between the fuselage sections (5, 26, 27, 43) to be joined together. A sliding movement is performed between the partial straps (17,18, 50, 51) of the strap segments (7-9, 20-23, 38-40) arranged one above the other, in the axial direction of the barrel-shaped fuselage sections (5, 26, 27, 43), and the ends (5, 26, 27, 43) of the fuselage sections (5, 26, 27,43) are bezelled (35, 36) on the inside thereof. The invention also relates to methods for creating a connection between two CFK fuselage sections (5, 26, 27, 43) preferably produced by a winding method, using a transversal butt strap (1, 19, 37) according to the invention.

公开(公告)号：EP2257467A1

公开(公告)日：2010-12-08

申请号：EP09720770.8

申请日：2009-02-16

申请人： Airbus Operations GmbH

发明人： TACKE, Stefan ,  MISCHEREIT, Stephan ,  REYE, Volker

IPC分类号： B64C1/12 ,  B64C1/06

CPC分类号： B64C1/069 ,  B64C1/06 ,  B64C2001/0072 ,  B64C2211/00 ,  Y02T50/43 ,  Y10T29/49826

摘要： A transverse butt connection between two fuselage sections, more particularly for creating a fuselage cell for an aircraft, can have a number of stringers arranged spaced out uniformly parallel to one another inside on an outer skin. In order to enable a universal tolerance compensation with standardised compensating means within a predetermined tolerance band between two fuselage sections which are to be joined together, both end areas of the fuselage sections can have on the inside oppositely inclined skin wedge surfaces and the connection of the two end areas is carried out by a circumferential transverse butt strap which is provided with two oppositely inclined transverse butt strap wedge surfaces in the underneath area wherein a wedge can be pushed in between each one transverse butt strap wedge surface and a skin wedge surface for tolerance compensation between the fuselage sections.

公开(公告)号：EP2164754A2

公开(公告)日：2010-03-24

申请号：EP08761201.6

申请日：2008-06-19

申请人： Airbus Operations GmbH

发明人： ROMING, Thorsten ,  SCHROEER, Thorsten ,  KIRSTEIN, Hauke ,  GENSCH, Hinnik ,  TACKE, Stefan

IPC分类号： B64C1/06 ,  B64F5/00

CPC分类号： B64C1/12 ,  B64C1/064 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49826 ,  Y10T428/19 ,  Y10T428/192 ,  Y10T428/197 ,  Y10T428/24124 ,  Y10T428/24132 ,  Y10T428/24298 ,  Y10T428/24314 ,  Y10T428/24322 ,  Y10T428/24331 ,  Y10T428/24661 ,  Y10T428/24744 ,  Y10T428/24752 ,  Y10T428/24777 ,  Y10T428/2495 ,  Y10T428/249923

摘要： This invention provides a coupling method for coupling a first and a second stiffening profile element for an outer skin of an aircraft or space craft. In a first step the stiffening profile elements are arranged on the outer skin in such a manner that the stiffening profile elements oppose each other with their respective front sides and enclose within themselves a cavity. Furthermore, a fixing hole is formed through a wall of at least one of the stiffening profile elements in the cavity inside a coupling zone of the stiffening profile element. An access opening is formed through the wall in the cavity along the coupling zone. A coupling strap, which couples the stiffening profile elements together, is fastened to the coupling zone by means of a fastening element guided through the fixing hole.

摘要翻译： 本发明提供一种用于联接飞行器或航天飞机的外皮的第一和第二加强型材元件的联接方法。 在第一步骤中，加强型材元件以这样的方式设置在外皮上，使得加强型材元件以它们各自的前侧彼此相对并且在其内包围空腔。 此外，在加强型材元件的连接区域内的空腔内的至少一个加强型材元件的壁上形成固定孔。 通过沿着联接区域的空腔中的壁形成进入口。 将加强型材元件连接在一起的联接带通过引导通过固定孔的紧固元件紧固到联接区域。