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1. 发明公开

EP4279396A1 COMPONENT AND ELECTRICAL SYSTEM FOR AN AIRCRAFT, AND METHOD FOR CONNECTING COMPONENTS 审中-实审
公开(公告)号：EP4279396A1
公开(公告)日：2023-11-22
申请号：EP22174685.2
申请日：2022-05-20
申请人： Airbus Operations GmbH , Airbus SAS
发明人： FRIEDBERGER, Alois , HELWIG, Andreas , LINDE, Peter
IPC分类号： B64D47/00 , H01R13/03 , H01R12/00
摘要： The present invention provides a component (110;120) for an aircraft, the component (110;120) comprising at least one connection interface (111;121), wherein the connection interface (111;121) is configured to simultaneously establish an electrical connection and a mechanical connection. The present invention further provides an electrical system for an aircraft and a method for connecting components for an aircraft

2. 发明公开

EP4054933A1 FLOW BODY FOR AN AIRCRAFT WITH A SELECTIVELY ACTIVATABLE SHOCK BUMP 有权转让
公开(公告)号：EP4054933A1
公开(公告)日：2022-09-14
申请号：EP20801248.4
申请日：2020-11-04
申请人： Airbus Operations GmbH , Airbus Defence and Space GmbH
发明人： LINDE, Peter , MACHUNZE, Wolfgang
IPC分类号： B64C23/04 , B64C3/20 , F03G7/00

3. 发明授权

EP3251821B1 MAGNET PRESS FOR PRESSING A COMPONENT, IN PARTICULAR THERMOPLASTIC CONSOLIDATION AND/OR FORMING PRESS, AND METHOD FOR PRESSING SUCH A COMPONENT 有权
公开(公告)号：EP3251821B1
公开(公告)日：2019-03-13
申请号：EP16172910.8
申请日：2016-06-03
申请人： Airbus Operations GmbH
发明人： LINDE, Peter
IPC分类号： B30B1/42 , B29C43/36 , B29C70/46 , H01L39/00

4. 发明公开

EP3216690A1 LINING PANEL WITH INTEGRATED ELECTRIC LINES FOR AN AIRCRAFT AND METHOD FOR MANUFACTURING A LINING PANEL 有权
标题翻译：用于飞机的具有一体化电线的衬里面板及用于制造衬里面板的方法
公开(公告)号：EP3216690A1
公开(公告)日：2017-09-13
申请号：EP16158897.5
申请日：2016-03-07
申请人： Airbus Operations GmbH
发明人： BRODALE, Camilla , STEINLICHT, Thorsten , HEGENBART, Matthias , LINDE, Peter , HERZOG, Dirk
IPC分类号： B64C1/06 , B64C1/12 , B64C1/40 , B29C67/00
CPC分类号： E04B1/343 , B29C64/106 , B29C70/74 , B29C70/882 , B32B37/18 , B33Y10/00 , B33Y80/00 , B64C1/066 , B64C1/12 , B64C1/40 , B64D2221/00 , Y02T50/43 , Y02T50/46
摘要： The present invention pertains to a method for manufacturing a lining panel (1) with integrated electric lines (2) for a lining of a passenger cabin of an aircraft or spacecraft. The method comprise using (M3) an additive manufacturing, AM, or 3D printing technique to form the electric lines (2) on or into a panel body (3) of the lining panel (1). The present invention further pertains to a lining panel (1) with integrated electric lines (2) for a lining of a passenger cabin of an aircraft or spacecraft. The lining panel (1) comprises a panel body (3) and electric lines (2) being formed on or into the panel body (3) using an AM or 3D printing technique.
摘要翻译：本发明涉及一种用于制造具有用于飞机或航天器的客舱的内衬的集成电线（2）的衬板（1）的方法。该方法包括使用（M3）增材制造，AM或3D印刷技术在衬片面板（1）的面板主体（3）上或面板内形成电线（2）。本发明还涉及一种具有用于飞机或航天器的客舱的内衬的集成电线（2）的衬里面板（1）。衬里面板（1）包括使用AM或3D印刷技术在面板体（3）上或面板内形成的面板体（3）和电线（2）。

5. 发明公开

EP3170587A3 FIBRE-REINFORCED METAL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT AND PRODUCTION METHODS FOR FIBRE-REINFORCED METAL COMPONENTS 失效
标题翻译：用于航空器或航天器的纤维增强金属部件及纤维增强金属部件的生产方法
公开(公告)号：EP3170587A3
公开(公告)日：2017-08-09
申请号：EP16193619.0
申请日：2016-10-13
申请人： Airbus Operations GmbH
发明人： ZAHLEN, Pierre , HEGENBART, Matthias , LINDE, Peter
IPC分类号： B22F3/105 , C22C47/04 , C22C47/06 , C22C47/08 , C22C47/14 , C22C49/06 , C22C49/11 , C22C49/14 , B33Y10/00 , B22F3/18
CPC分类号： B64C1/06 , B22D19/02 , B22F3/1055 , B22F2999/00 , B23K11/0013 , B23K11/002 , B23K11/16 , B23K26/0006 , B23K26/342 , B23K2201/006 , B23K2203/10 , B23K2203/14 , B23K2203/172 , B33Y10/00 , B33Y80/00 , B64C2001/0072 , C22C47/04 , C22C47/068 , C22C47/08 , C22C47/14 , C22C49/06 , C22C49/11 , C22C49/14 , Y02P10/295 , B22F3/18
摘要： The present invention provides production methods for producing a fibre-reinforced metal component (1) having a metal matrix (2) which is penetrated by a plurality of reinforcing fibres (3). One production method comprises depositing in layers reinforcing fibres (3) in fibre layers,
depositing in layers and liquefying a metal modelling material (4) in matrix material layers (5), and consolidating in layers the metal modelling material (4) in adjacently deposited matrix material layers (5) to form the metal matrix (2) of the fibre-reinforced metal component (1). Here, the metal component (1) is formed integrally from alternately deposited matrix material layers (5) and fibre layers (6). An alternative production method comprises introducing an open three-dimensional fibrewoven fabric consisting of reinforcing fibres (3) into a casting mould, pouring a liquid metal modelling material (4) into the casting mould and consolidating the metal modelling material (4) to form the metal matrix (2) of the fibre-reinforced metal component (1). Here, the metal component (1) is formed integrally from the consolidated metal modelling material (4) and the reinforcing fibres (3).
摘要翻译：本发明提供用于制造具有被多根增强纤维（3）贯穿的金属基体（2）的纤维增强金属部件（1）的制造方法。一种生产方法包括在层中沉积纤维层中的增强纤维（3），分层沉积并且在基质材料层（5）中液化金属造型材料（4），并且将金属造型材料（4）层合并成相邻沉积基体材料层（5）以形成纤维增强金属部件（1）的金属基体（2）。这里，金属部件（1）由交替沉积的基体材料层（5）和纤维层（6）整体形成。一种替代的生产方法包括：将由增强纤维（3）组成的开放的三维纤维织物引入铸模中，将液态金属造型材料（4）倒入铸模并固化金属造型材料（4）以形成所述纤维增强金属部件（1）的金属基体（2）。这里，金属部件（1）由固结金属造型材料（4）和增强纤维（3）整体形成。

6. 发明公开

EP4368496A1 WINDOW FOR AN AIRCRAFT, AIRCRAFT, AND METHOD FOR DETERMINING THE POSITION AT WHICH A LASER BEAM IMPACTS A WINDOW 审中-公开
公开(公告)号：EP4368496A1
公开(公告)日：2024-05-15
申请号：EP22206123.6
申请日：2022-11-08
申请人： Airbus Operations GmbH
发明人： TELKAMP, Michael , LINDE, Peter
IPC分类号： B64C1/14 , B60J3/04
CPC分类号： B64C1/1476 , B64C1/1484 , B60J3/04
摘要： The present invention is directed to a window (100) for an aircraft (10), the window (100) comprising a first transparent layer (110), and a first plurality of light detectors (111) arranged around a circumference of the first transparent layer (110) and configured to measure the intensity of light refracted upon entering and exiting the first transparent layer (110). Furthermore, the present invention is directed to an aircraft and a method for determining the point at which a laser beam (20) impacts a window (100) of the aircraft.

7. 发明公开

EP3718876A1 PANELS FOR A CABIN OF AN AIRCRAFT 有权
公开(公告)号：EP3718876A1
公开(公告)日：2020-10-07
申请号：EP19382241.8
申请日：2019-04-02
申请人： Airbus Operations GmbH , Airbus Operations, S.L.U.
发明人： BLANCO VARELA, Tamara , LINDE, Peter
IPC分类号： B64C1/06 , B64C1/18
摘要： A panel (1000) for a cabin of an aircraft, the panel (1000) comprising at least one laminate (150) comprising one or more of a first layer comprising lithiated carbon fibers (100), a second layer comprising carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and at least one pressure sensor (50a, 50b) established on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150), based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

9. 发明公开

EP3219474A1 METHOD AND DEVICE FOR 3D-PRINTING A FIBER REINFORCED COMPOSITE COMPONENT BY TAPE-LAYING 审中-公开
标题翻译：通过薄膜层叠法对纤维增强复合材料组分进行三维印刷的方法和装置
公开(公告)号：EP3219474A1
公开(公告)日：2017-09-20
申请号：EP16160730.4
申请日：2016-03-16
申请人： Airbus Operations GmbH
发明人： HIRANO, Yoshiyasu , LINDE, Peter , HEGENBART, Matthias , SCHÖNKE, Jan
IPC分类号： B29C70/38 , B29C67/00 , B29C35/08
CPC分类号： B29C70/38 , B29C64/165 , B29C2035/0838 , B33Y10/00 , B33Y30/00
摘要： A 3D-printing or tape laying method for manufacturing a fiber reinforced composite component (10). The method comprises supplying a spread tow tape (1) containing a plurality of reinforcing fibers (2) from a tape supply (3) to a merging station (4), supplying a plurality of matrix material filaments (5) from a multi-filament supply (6) to the merging station (4), pressing together the plurality of matrix material filaments (5) with the spread tow tape (1) at the merging station (4), heating the spread tow tape (1) together with the plurality of matrix material filaments (5) at the merging station (4) to a melting temperature (T) of the matrix material filaments (5) to form an impregnated fiber ply (7), and depositing the impregnated fiber ply (7) in composite layers (8) onto a print bed (9) to form the fiber reinforced composite component (10). A 3D-printer (100) or tape-laying machine implementing such a method.
摘要翻译：一种用于制造纤维增强复合部件（10）的3D打印或铺带方法。该方法包括：将包含多个增强纤维（2）的铺展的拖曳带（1）从带供应装置（3）供应到合并站（4），将多个基体材料细丝（5）从复丝向汇合站（4）供应（6），在汇合站（4）处将多根基质材料细丝（5）与展开的拖曳带（1）一起压在一起，将展开的拖曳带（1）与（4）处的多个基质材料细丝（5）至基质材料细丝（5）的熔融温度（T）以形成浸渍的纤维层（7），并且将浸渍的纤维层（7）沉积在复合层（8）到印刷底座（9）上以形成纤维增强复合部件（10）。 3D打印机（100）或铺带机实现这种方法。

10. 发明公开

EP4220787A1 INTERCONNECTING DEVICE FOR SOLID OXIDE FUEL CELLS AND A FUEL CELL STACK COMPRISING THE SAME 有权
公开(公告)号：EP4220787A1
公开(公告)日：2023-08-02
申请号：EP22154251.7
申请日：2022-01-31
申请人： Airbus Operations GmbH
发明人： NEHTER, Pedro , LINDE, Peter
IPC分类号： H01M8/2435 , H01M8/2483 , H01M8/12
摘要： An interconnecting device for compact solid oxide fuel cells is proposed, the interconnecting device comprising a body having a first interface surface, and a second interface surface on distinct sides of the body, wherein the first interface surface comprises at least one anode exhaust input and at least one cathode exhaust input in a distance to the at least one anode exhaust input, wherein the second interface surface comprises at least one fuel supply port and at least one air supply port in a distance to the at least one fuel supply port, wherein the at least one anode exhaust input is in fluid communication with the at least one fuel supply port and/or at least one anode exhaust outlet arranged at a distance to the first interface surface and the second interface surface, wherein the at least one cathode exhaust input is in fluid communication with the at least one air supply port and/or at least one cathode exhaust outlet arranged at a distance to the first interface surface and the second interface surface, wherein at least one first electrical port is arranged at or in the at least one cathode exhaust input and is connectable from the first interface surface, wherein at least one second electrical port is arranged at or in the at least one fuel supply port and is connectable from the second interface surface, and wherein the at least one first electrical port is electrically connected to the at least one second electrical port.

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