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公开(公告)号：EP4156348A1
公开(公告)日：2023-03-29
申请号：EP21382857.7
申请日：2021-09-24
IPC分类号： H01M8/0234 , H01M8/0239 , H01M8/0243 , H01M8/0245 , H01M8/026 , H01M8/0265 , H01M8/10
摘要： A bipolar plate (10) for a proton exchange membrane fuel cell comprises a laminate (12) of carbon fibre reinforced plastic, CFRP, with a first outer ply (14). The CFRP comprises a resin (16) and a plurality of carbon fibres (18). The first outer ply (14) is arranged at a first lateral surface (18) of the laminate (12), wherein the laminate (12) comprises a first plurality of carbon nano tubes, CNTs (20). The first outer ply (14) comprises a first groove (22), wherein the first groove (22) is configured to define a first gas diffusion channel. At least some of the first plurality of CNTs (20) extend through the first outer ply (14) in a direction transversely to the first lateral surface (18) of the laminate (12).
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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
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
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3.发明公开
公开(公告)号：EP4438272A1
公开(公告)日：2024-10-02
申请号：EP23166078.8
申请日：2023-03-31
申请人： Airbus Operations GmbH , Airbus SAS
发明人： LINDE, Peter , LENCZOWSKI, Blanka
CPC分类号： B29C65/0681 , B29C66/72321 , B29C66/721 , B29C66/1142 , B29C66/43 , B29C66/836 , B29L2031/307620130101 , B29L2031/717220130101 , B29C66/863 , B29C66/865 , B23K20/122 , B29C66/54 , B29C66/81469 , B29C66/81422 , B29C66/81425 , B23K20/1255 , B23K20/2333 , B23K2101/00620180801 , B23K2101/1820180801 , B23K2103/1020180801 , B23K2103/17220180801 , B23K2103/4220180801
摘要： The invention relates to a method for friction stir welding along a butt joint weld line (40). A welding device (70) comprises a probe assembly (90) including at least a first and second probe device (100a, 100b). A first and second part (31a, 31b) to be joined along the weld line (40) are provided, wherein the parts are each formed as a laminate (1; 1') comprising at least a first layer (2a, 2b) formed with a first material and a second layer (5a, 5b) formed with a second material. The first and second materials have different material properties. The method comprises friction stir welding of the parts using the welding device, wherein simultaneously, the first probe device acts on the first layers and the second probe device acts on the second layers. Moreover, the invention relates to a friction stir welding device and to a workpiece comprising a butt weld seam.
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4.发明公开
公开(公告)号：EP4438287A1
公开(公告)日：2024-10-02
申请号：EP23166077.0
申请日：2023-03-31
申请人： Airbus Operations GmbH , Airbus SAS
发明人： LINDE, Peter , LENCZOWSKI, Blanka
CPC分类号： F17C1/14 , B32B1/08 , B32B5/02 , B32B15/08 , B32B15/14 , B32B15/20 , B32B27/20 , B32B27/281 , B32B27/285 , B32B27/286 , B32B2255/2020130101 , B32B2255/0220130101 , B32B2255/1020130101 , B32B2260/02120130101 , B32B2260/04620130101 , B32B2262/10120130101 , B32B2262/10620130101 , B32B2264/10820130101 , B32B2264/1220130101 , B32B2264/20320200801 , B32B2605/1820130101
摘要： The present invention proposes a storage tank (1) for liquified gas, in particular for liquid hydrogen (32), comprising a vessel (2) having a vessel wall (7) formed from a fibre metal laminate (8; 8'; 8"; 8‴) including metal layers (9) formed with an aluminum alloy and one or more synthetic layers (10; 10'; 10"; 10‴) with reinforcing fibres (14; 15) embedded in a thermoplastic matrix (13). Further, an aircraft or spacecraft (100) comprising such a storage tank (1) as well as a hydrogen-based propulsion system (105, 106) configured to be supplied with hydrogen at least from the storage tank (1) is proposed. Further, fibre metal laminates (8; 8'; 8"; 8‴) are proposed.
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公开(公告)号：EP4455019A1
公开(公告)日：2024-10-30
申请号：EP23170281.2
申请日：2023-04-27
发明人： LINDE, Peter , HEGENBART, Matthias
摘要： Disclosed is a tank 1000, 1000' comprising one or several anti-sloshing wall arrangement/s 100, 100', with a frame portion 10 and a door portion 20, wherein the frame portion 10 is fixed to a tank wall 200 of the tank, and it edges an opening O, and wherein the door portion 20 is configured to selectively close or unclose the opening O.
Further disclosed is an aircraft 1 comprising such tank and at least one engine 3000, the engine 3000 being configured to be fed with fuel, in particular with liquid hydrogen, contained in the tank.-
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
发明人： LINDE, Peter , MACHUNZE, Wolfgang
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8.发明公开LINING PANEL WITH INTEGRATED ELECTRIC LINES FOR AN AIRCRAFT AND METHOD FOR MANUFACTURING A LINING PANEL 审中-公开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
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）。
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9.发明公开FIBRE-REINFORCED METAL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT AND PRODUCTION METHODS FOR FIBRE-REINFORCED METAL COMPONENTS 审中-公开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
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。
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10.发明公开
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
发明人： TELKAMP, Michael , LINDE, Peter
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.
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