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81. 发明申请

US20110159248A1 AIRCRAFT FUSELAGE FRAME OF COMPOSITE MATERIAL WITH STABILISING RIBS 有权
标题翻译：具有稳定RIBS的复合材料的飞机熔融框架
公开(公告)号：US20110159248A1
公开(公告)日：2011-06-30
申请号：US12883269
申请日：2010-09-16
申请人： Elena ARÉVALO RODRÍGUEZ , Francisco José CRUZ DOMINGUEZ
发明人： Elena ARÉVALO RODRÍGUEZ , Francisco José CRUZ DOMINGUEZ
IPC分类号： B64C1/06 , B32B37/16 , B23P11/00
CPC分类号： B64C1/061 , B29C70/44 , B29C70/46 , B29C70/48 , B29D99/0014 , B29L2031/3082 , B64C2001/0072 , Y02T50/43 , Y10T29/49947 , Y10T428/24174 , Y10T428/24182 , Y10T428/24628
摘要： Aircraft fuselage frame in composite material with stabilising ribs which, in at least a first sector (31), comprises a frame (9) with an omega-shaped cross-section (11) formed by a top element (23), two webs (25, 25′), two feet (27, 27′) which includes at least one internal rib (41) formed by a top element (43) joined to the top element (23) of the frame (9), a web (45), two flanges (49, 49′) joined to the webs (25, 25′) of the frame (9) and a foot (47) aligned with the feet (27, 27′) of the frame (9). The invention also relates to a manufacturing procedure for the first sector (31) of the frame with stabilised web (10) comprising steps for: a) providing a frame (9) and at least one internal rib (41) with the configurations indicated; b) joining at least said internal rib (41) to the frame (9).
摘要翻译：在具有稳定肋的复合材料中的飞行器机身框架，其在至少第一扇区（31）中包括具有由顶部元件（23）形成的Ω形横截面（11）的框架（9），两个腹板 25,25'），两个脚部（27,27'），其包括由连接到所述框架（9）的顶部元件（23）的顶部元件（43）形成的至少一个内部肋（41），腹板 45），与框架（9）的腹板（25,25'）连接的两个凸缘（49,49'）和与框架（9）的脚部（27,27'）对准的脚部（47）。本发明还涉及具有稳定卷筒纸（10）的框架的第一扇区（31）的制造程序，包括以下步骤：a）提供具有所示配置的框架（9）和至少一个内部肋（41） b）至少将所述内部肋（41）连接到框架（9）。

82. 发明申请

US20100219287A1 PROTECTION AGAINST DIRECT LIGHTNING STRIKES IN RIVETED AREAS OF CFRP PANELS 有权
标题翻译：对CFRP面板区域直射雷击的防护措施
公开(公告)号：US20100219287A1
公开(公告)日：2010-09-02
申请号：US12552639
申请日：2009-09-02
申请人： Desiderio SÁNCHEZ-BRUNETE ÁLVAREZ , Luis Manuel DESCALZO FERNÁNDEZ
发明人： Desiderio SÁNCHEZ-BRUNETE ÁLVAREZ , Luis Manuel DESCALZO FERNÁNDEZ
IPC分类号： B64D45/02 , B23P13/00
CPC分类号： B64D45/02 , H02G13/00 , Y10T29/49622
摘要： The invention relates to a metalization structure of aircraft panels and process for obtaining such structure, such that it comprise a structure of a panel (1) made in composite material, the mentioned panel (1) comprising a metal mesh or foil (2) in its outer part, said panel (1) further comprising a bore which in turn comprises a shank and an upper countersinking (8), such that the mentioned panel (1) is fixed to another structural aircraft element (3) by means of metal fixing elements (4), characterized in that said structure comprise a metallization layer (7) arranged on the upper countersinking (8), extending in the adjacent area of the metal mesh or foil (2), such that it is ensured that electrical continuity exists between the upper countersinking (8) and the metal mesh or foil (2) during the time that the lightning bolt strikes the structure of the panel (1), further ensuring that most of the current discharged by the lightning bolt is conducted over the surface of the structure of the mentioned panel (1). The invention further relates to a process for making such structure of a panel (1).
摘要翻译：本发明涉及飞行器面板的金属化结构和用于获得这种结构的方法，使得其包括由复合材料制成的面板（1）的结构，所述面板（1）包括金属网或箔（2），其中其外部部分，所述面板（1）还包括孔，所述孔又包括柄和上锪孔（8），使得所述面板（1）通过金属固定固定到另一结构飞行器元件（3）元件（4），其特征在于，所述结构包括布置在上锪孔（8）上的金属化层（7），其在金属网或箔（2）的相邻区域中延伸，使得确保存在电连续性在闪电击中面板（1）的结构期间，在上沉头（8）和金属网或箔（2）之间，进一步确保由闪电放电的大部分电流在表面的结构（1）。本发明还涉及一种用于制造面板（1）的这种结构的方法。

83. 发明授权

US11691749B2 Aircraft with an engine control device in the engine compartment and method to obtain such aircraft 有权
公开(公告)号：US11691749B2
公开(公告)日：2023-07-04
申请号：US17175003
申请日：2021-02-12
申请人： Airbus Operations S.L.
发明人： Alberto Martinez Sancho
IPC分类号： B64D31/14 , B64F5/40 , F02D1/00 , B64D41/00
CPC分类号： B64D31/14 , B64F5/40 , B64D2041/002 , F02D2001/0095
摘要： A method to modify an aircraft including: disconnecting a first engine control device from command cables and transmission cables, wherein the first engine control device is in a fuselage section forward of a pressure bulkhead; replacing the engine control device with a jumper connector positioned in the fuselage section, wherein the jumper connector electrically connects the command cables to the transmission cables; installing a second engine control device in the fuselage aft of the pressure bulkhead, wherein the second engine control device is in an engine compartment of the fuselage; connecting the second engine control device to transmission cables at a location at or near the pressure bulkhead; connecting sensor cabling directly to the second engine control device, and connecting the engine control device directly to the engine.

84. 发明授权

US11649034B2 Flight control surface for an aircraft and method for manufacturing said flight control surface 有权
公开(公告)号：US11649034B2
公开(公告)日：2023-05-16
申请号：US16744342
申请日：2020-01-16
申请人： Airbus Operations, S.L.
发明人： Robert Kobierecki , Miguel Ángel Mendez Rodríguez , Juan Antonio Sánchez Ruiz , Alberto Balsa-Gonzalez
IPC分类号： B64C3/26 , B29C65/60 , B64C9/00 , B29L31/30
CPC分类号： B64C3/26 , B29C65/60 , B64C9/00 , B29L2031/3076
摘要： A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.

85. 发明申请

US20230017954A1 PROPELLER-TYPE PROPULSION SYSTEM FOR AN AIRCRAFT 有权
公开(公告)号：US20230017954A1
公开(公告)日：2023-01-19
申请号：US17866050
申请日：2022-07-15
申请人： Airbus Operations SAS , Airbus SAS , Airbus Operations S.L.
发明人： Jean-François ALLIAS , Franck ALVAREZ , Pascal POME , Nicolas JOLIVET , Rémi AMARGIER , Salvatore DEMELAS , Norberto SIMIONATO NETO , Benedikt BAMMER , Damien MARIOTTO
IPC分类号： B64D35/02 , B64D27/24 , B64D35/08
摘要： A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

86. 发明授权

US11542033B2 Dynamic illumination system for runway illumination 有权
公开(公告)号：US11542033B2
公开(公告)日：2023-01-03
申请号：US16842173
申请日：2020-04-07
申请人： Airbus Operations S.L.
发明人： Gabrielle Josephine Christiane De Brouwer
IPC分类号： B64D47/04 , H05B45/44 , H05B47/10 , F21V14/02 , F21V21/15 , H05B47/00 , H05B45/10 , H05B47/105
摘要： A dynamic runway illumination system, including a light source having an addressable light beam direction, and a control unit configured to receive aircraft attitude information and the orientation of the runway selected for takeoff or landing, obtain horizontal and vertical axes, the horizontal axis being collinear with the takeoff or landing longitudinal direction, determine the actual and the reference aircraft trajectories, obtain the actual and the reference vertical approach angles, and the actual horizontal approach angle, and actuate onto the light source to perform an angular movement in the light beam direction of an absolute value of the actual vertical approach angle minus the absolute value of the reference vertical approach angle about the vertical axis, and an angular movement of an absolute value of the actual horizontal approach angle about the horizontal axis, to vertically and horizontally align the beam of the light source towards the runway direction.

87. 发明申请

US20220355943A1 ELECTRIC PROPULSION UNIT OF AN AIRCRAFT COMPRISING A COOLING SYSTEM INCORPORATING AT LEAST ONE FRONT AIR INLET AND AIRCRAFT COMPRISING AT LEAST ONE SUCH ELECTRIC PROPULSION UNIT 有权
公开(公告)号：US20220355943A1
公开(公告)日：2022-11-10
申请号：US17737134
申请日：2022-05-05
申请人： Airbus SAS , Airbus Operations SAS , Airbus Operations GmbH , Airbus Operations S.L.
发明人： Jorge CARRETERO BENIGNOS , Benedikt BAMMER , Olivier VERSEUX , Maria Del Sagrario JUANAS FERNANDEZ , Jorge MOLANO REMBIASZ , Thomas SCHERER , Alexander SOLNTSEV
IPC分类号： B64D27/24 , B64D33/08
摘要： An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

88. 发明授权

US11426953B2 Fiber composite laying device and fiber composite laying method for producing a fiber composite scrim for forming a fiber composite component 有权
公开(公告)号：US11426953B2
公开(公告)日：2022-08-30
申请号：US16033300
申请日：2018-07-12
申请人： AIRBUS DEFENCE AND SPACE GMBH , AIRBUS OPERATIONS, S.L.
发明人： Katharina Schlegel , Alois Friedberger , David Lopez-Bravo
IPC分类号： B29C70/38 , B29C70/34 , B29C70/50 , B29C37/00 , B29K105/08
摘要： A fiber composite laying device for producing a fiber composite scrim for forming a fiber composite component has a laying head which is designed or configured to continuously supply a reinforcement fiber band, a compaction roller which is designed or configured to receive the supplied reinforcement fiber band, lay the band on a laying surface and press the band onto the laying surface at an average compaction pressure, and pressure sensors which are arranged on the compaction roller and are designed or configured to detect a local compaction pressure on the laid reinforcement fiber band.

89. 发明授权

US11264553B2 Overheat detection system and insulation muff comprising an overheat detection system 有权
公开(公告)号：US11264553B2
公开(公告)日：2022-03-01
申请号：US16421844
申请日：2019-05-24
申请人： Airbus Operations S.L.
发明人： Brice Lenoir , Panagiotis Mourtis Ioannou
IPC分类号： H01L35/04 , G01K1/14 , G01K3/00 , H01L35/34
摘要： An overheat detection system and insulation muff comprising an overheat detection system. The overheat detection system comprises a thermometer, a thermal harvesting module comprising at least one passive radiator, the thermal harvesting module being able to generate electrical energy from the thermal difference between two elements, and a digital module, comprising a power management system, a data treatment system and a wireless transmission system, wherein the electrical energy generated by the thermal harvesting module powers the thermometer and the digital module.

90. 发明授权

US11220354B2 Composite fuselage assembly and methods to form the assembly 有权
公开(公告)号：US11220354B2
公开(公告)日：2022-01-11
申请号：US16515330
申请日：2019-07-18
申请人： AIRBUS OPERATIONS S.L.
发明人： Esteban Martino-Gonzalez , Alberto Arana Hidalgo , Melania Sanchez Perez , Carlos Garcia Nieto , Jesus Javier Vazquez Castro , Edouard Menard , Fernando Iniesta Lozano , Maria Almudena Canas Rios
IPC分类号： B64F5/10 , B64C1/26 , B64C3/26 , B64C5/02 , B64C1/00
摘要： A method for manufacturing a composite rear section assembly having a continuous skin solution including obtaining a vertical tail plane tooling that has intermediate tooling for tooling intermediate preforms of a vertical tail plane (800), obtaining a fuselage barrel tooling (420a), (420b), (420c) and (420d) the fuselage barrel tooling having a cut-out (503a), (503b), (503c) and longitudinal cavities (501a), (501b), (501c) and (501d), attaching the vertical tail plane tooling to the fuselage barrel tooling by the cut-out of the fuselage barrel tooling, performing a composite skin lay-up (801) over the fuselage barrel tooling and the vertical tail plane tooling to obtain a continuous skin, curing the composite skin lay-up, the vertical tail plane tooling and the fuselage barrel tooling and demolding the tools to obtain the composite assembly with a continuous skin (1300), (1600).

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