公开(公告)号：EP2164679B1

公开(公告)日：2012-03-28

申请号：EP08773264.0

申请日：2008-06-06

申请人： MTU Aero Engines GmbH ,  EADS Deutschland GmbH

发明人： BAYER, Erwin ,  REESE, Eggert ,  STEINWANDEL, Jürgen

IPC分类号： B24C1/10

CPC分类号： B24C1/10 ,  B24C1/083 ,  B24C5/005

摘要： The present invention relates to a method for surface peening, particularly for ultrasonic surface peening, of a component (22) in the region of a passage opening (24) in which a vibration device (10) that impinges the blasting material is disposed on one side (18) and a counter element (28) is disposed on an opposite side (26) relative to a component region (20) having said passage opening (24), wherein the counter element (28) is disposed at a distance relative to the corresponding side (26) of the component region (20). The invention further relates to a device for carrying out such a method.

公开(公告)号：EP2490854A1

公开(公告)日：2012-08-29

申请号：EP10775717.1

申请日：2010-10-22

申请人： Airbus SAS

发明人： HECKL, Matthias ,  HÖNLE, Christian ,  HESTERMANN, Fritz ,  STALLA, Reinhold

IPC分类号： B23P13/00 ,  B23B41/00 ,  B23Q3/06 ,  B64F5/00

CPC分类号： B23P13/00 ,  B23B35/00 ,  B23B41/00 ,  B23B2215/04

摘要： The invention relates to a method for introducing bores (58) that are aligned in relation to each other into a body section (28) of a component (20) consisting of a plurality of individual bodies (28, 30), wherein the component (20) is joined, straightened, and mounted stress-free and the bores (58) are finish-drilled. The invention relates to a method for producing a freight door (20), which is straightened before the finish-drilling and transferred stress-free into the installation position thereof, and to such a freight door (20).

公开(公告)号：EP2113036A2

公开(公告)日：2009-11-04

申请号：EP08706752.6

申请日：2008-01-12

申请人： Airbus SAS

发明人： ENGLHART, Martin ,  KRUG, Hans ,  JONKE, Dietrich ,  PIRINGER, Helmut

IPC分类号： C22C47/00

CPC分类号： C22C47/04 ,  C22C47/062 ,  Y10T428/249927

摘要： The invention relates to a fiber composite comprising a metallic matrix as well as a method for producing the same. A fiber material composed of single fibers (1) is embedded in a metallic matrix formed by a metallizing layer (2) that surrounds the fiber (1) and a metallic final layer (4) which is applied to the metallizing layer (2). In addition, a metallic adhesive layer (3) can be provided between the metallizing layer (2) and the metallic final layer (4). The metallic final layer (4) can be formed by means of one or several applications and can be machined using any mechanical machining processes.

公开(公告)号：EP2456671A2

公开(公告)日：2012-05-30

申请号：EP10735005.0

申请日：2010-07-22

申请人： Airbus Operations GmbH

发明人： GOEHLICH, Robert, Alexander ,  SAYILGAN, Cihangir

IPC分类号： B64F5/00

CPC分类号： B64D9/00 ,  B64C1/20 ,  B64F5/50 ,  Y10T29/49826

摘要： The invention relates to a method for system installation in a fuselage (4), to a device (2) comprising a rail system (14) for carrying out said method, and to a freight loading system (50) that uses the rail system (14) as a guidance system for unit loads (52, 54).

公开(公告)号：EP2414227A2

公开(公告)日：2012-02-08

申请号：EP10714224.2

申请日：2010-03-30

申请人： Airbus Operations GmbH

发明人： GOEHLICH, Robert Alexander

IPC分类号： B64C1/06

CPC分类号： B64C1/12 ,  B32B1/00 ,  B32B3/12 ,  B32B3/266 ,  B32B5/02 ,  B32B5/18 ,  B32B5/22 ,  B32B5/245 ,  B32B5/32 ,  B32B7/02 ,  B32B15/046 ,  B32B27/02 ,  B32B27/04 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2266/02 ,  B32B2266/0214 ,  B32B2266/045 ,  B32B2307/536 ,  B32B2307/718 ,  B32B2605/18 ,  B64C1/40 ,  B64C2001/0072 ,  B64C2211/00 ,  B64D11/00 ,  B64D13/00 ,  Y02T50/43 ,  Y02T50/44 ,  Y02T50/46 ,  Y10T29/49

摘要： A fuselage segment of an aircraft fuselage is provided with an outer skin and an inner skin that are spaced apart from one another by a core, wherein conduits for system installations are integrated into the core, as well as a method for manufacturing such a fuselage segment.

公开(公告)号：EP2323837A2

公开(公告)日：2011-05-25

申请号：EP09776105.0

申请日：2009-08-18

申请人： Airbus SAS

发明人： LUINGE, Hans ,  WACHINGER, Georg

IPC分类号： B29C70/48 ,  B32B27/38 ,  B32B27/04 ,  B32B27/08 ,  B32B27/20 ,  B32B27/12 ,  B29C70/02 ,  B29C70/44 ,  B29B11/16

CPC分类号： B32B5/26 ,  B29B11/16 ,  B29C70/025 ,  B29C70/443 ,  B29K2105/18 ,  B32B9/00 ,  B32B27/12 ,  B32B27/20 ,  B32B27/281 ,  B32B27/285 ,  B32B27/286 ,  B32B27/302 ,  B32B27/304 ,  B32B27/308 ,  B32B27/32 ,  B32B27/34 ,  B32B27/36 ,  B32B27/38 ,  B32B38/08 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2264/102 ,  B32B2307/3065 ,  B32B2307/514 ,  B32B2307/558 ,  B32B2605/08 ,  B32B2605/18 ,  C08J5/24 ,  Y10T442/20

摘要： It is desirable in many uses of fiber composite components to have improved properties (e.g. fire resistance) which are often impossible or difficult to obtain by means of conventional matrix materials (e.g. epoxy resin systems). The invention relates to a method for producing a fiber composite component, comprising the steps of injecting matrix material into a semifinished textile product (1') and then curing the infiltrated semifinished product (1'). The semifinished textile product (1') that is to be cured contains at least one semifinished product layer which is formed by a film (14') of a thermoplastic (12) with particles (10) that are nano-dispersed therein. This allows oriented exfoliated phyllosilicates (10) to be incorporated into an epoxy resin matrix of a fiber composite component, for example, the thermoplastic (12) being used as a "vehicle" and being dissolved in the matrix material, for example.

公开(公告)号：EP1003054B1

公开(公告)日：2010-07-28

申请号：EP99122187.0

申请日：1999-11-06

申请人： Airbus Operations GmbH

发明人： Staudigel, Lothar ,  Trutzel, Michael

IPC分类号： G02B6/36

CPC分类号： G02B6/02209

公开(公告)号：EP2497984A1

公开(公告)日：2012-09-12

申请号：EP12157500.5

申请日：2012-02-29

申请人： Tyczka Totalgaz GmbH

发明人： Munkhart, Zoltan

IPC分类号： F16K17/32

CPC分类号： F16K31/56 ,  F16K17/32 ,  F16K31/025 ,  F16K37/0083

摘要： Sicherheitsabsperrventil (1) zum Absperren einer Gasleitung mit einem in Schließrichtung vorgespannten Ventilschieber (4), einem vorgespannten Sperrbolzen (36) zur Sicherung des Ventilschiebers (4) in einer Öffnungsstellung und mit einer Membran (38) zur Beaufschlagung des Sperrbolzens (36) aufgrund eines Gasdruckes mit einer Rückstellkraft (F), wobei eine fernbetätigbare Freigabeeinrichtung (62) zur Aufbringung der Rückstellkraft (F) und Rückführung des Sperrbolzens (36) vorgesehen ist, die im Ruhezustand kräfteübertragungsfrei geschaltet ist, sowie ein Verfahren zum Absperren einer Gasleitung.

摘要翻译： 安全关闭阀（1）具有用于将阀滑块（4）保护在打开位置的偏压锁定螺栓（36）。 提供远程操作的释放介质（62），用于独立于气体压力释放阀滑块。 提供用于施加恢复力（F）的致动器（64）。 锁定螺栓可操作地连接到致动元件（66），使得恢复力在锁定螺栓上传递。 还包括用于通过安全关闭阀关闭气体管线的方法的独立权利要求。

公开(公告)号：EP2490855A1

公开(公告)日：2012-08-29

申请号：EP10779227.7

申请日：2010-10-22

申请人： Airbus SAS

发明人： ANTAR, Nebil ,  ARENT, Jan-Christoph ,  HECKL, Matthias ,  HÖNLE, Christian

IPC分类号： B23P13/00 ,  B23B35/00 ,  B23B41/00 ,  B23Q3/06

CPC分类号： B23P13/00 ,  B23B39/161 ,  B23B41/00 ,  B23B2215/04 ,  B23B2260/1285 ,  Y10T408/21 ,  Y10T408/36 ,  Y10T408/55

摘要： The invention relates to a drilling device comprising a receiving unit for receiving a component (20), in particular a freight door, having at least one drill head (72) for introducing at least one bore (58) into the component (20), wherein the receiving unit provides stress-free mounting of the component (20) in the installed position.

公开(公告)号：EP2454150A2

公开(公告)日：2012-05-23

申请号：EP10732376.8

申请日：2010-07-15

申请人： Airbus Operations GmbH

发明人： ROMING, Thorsten ,  HORNEBER, Hansjörg ,  SCHRÖER, Thorsten ,  WIRTZ, Tobias ,  EDELMANN, Klaus ,  MENKEN, Tanja

IPC分类号： B64C1/06

CPC分类号： B64C1/061 ,  B64C1/068 ,  B64C1/12

摘要： The invention relates to a shell segment (19) for producing a fuselage cell section for a fuselage cell of an airplane, comprising at least one skin field (20) and a plurality of longerons disposed thereon, in particular stringers (21-24), and at least one transverse reinforcement element running substantially transversely to the longerons, in particular at least one frame (26). Because the connection of the at least one transverse reinforcement element to the at least one skin field (20) is established by way of at least one connection bracket (1, 27-29), wherein the at least one connection bracket (1, 27-29) comprises at least one bead (9), the angle brackets required for previously known embodiments of shell segments for absorbing tilting moments of the frames can be eliminated. In this way, it is possible to considerably lower the weight, and also reduce the manufacturing complexity.