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公开(公告)号：US20140183301A1
公开(公告)日：2014-07-03
申请号：US14140665
申请日：2013-12-26
Applicant: AIRBUS OPERATIONS SL
Inventor： Coral Aida MORA ORDÓÑEZ
IPC: B64C7/00
Abstract: The invention provides an aircraft with a ventral fairing able to store equipment and systems in lateral zones. The ventral fairing (20) comprises a first zone of length L1 along the X-axis, where the area of the cross-section perpendicular to the X-axis increases in the direction of the air flow and a second zone of length L2, where the area of the cross-section perpendicular to the X-axis decreases in the direction of the air flow, being L1>L2 and being placed the rear end of said first zone behind the intersection of the trailing edge of the wing (15) with the fuselage (13).
Abstract translation: 本发明提供一种具有腹侧整流罩的飞行器，其能够在侧向区域中存储设备和系统。 腹侧整流罩（20）包括沿着X轴的长度为L1的第一区域，垂直于X轴的横截面的面积在空气流动方向上增加，长度为L2的第二区域，其中 垂直于X轴的横截面的面积在空气流动方向上减小，为L1> L2，并且将所述第一区域的后端放置在机翼（15）的后缘与后缘的后面之后与 机身（13）。
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公开(公告)号：US11085312B2
公开(公告)日：2021-08-10
申请号：US16034548
申请日：2018-07-13
Applicant: AIRBUS OPERATIONS SL
Inventor： Javier Fraile Martin , Anton Mendez-Diaz
IPC: F01D9/06 , F02K3/06 , B64C21/04 , B64D13/02 , B64D33/00 , F01D9/02 , F01D25/08 , B64D13/06 , B64D33/02 , F02C6/08
Abstract: An aircraft incorporating a cabin air recovery system in which the aircraft comprises a pressurizable cabin, main turbofan engines, each turbofan engine having fan blades, a gas turbine coupled with the fan blades and a by-pass duct bypassing the gas turbine. The cabin fluidly communicates with the by-pass duct downstream of the fan blades so that, during operation, cabin outflow air is discharged into the by-pass duct downstream of the fan blades. By re-utilizing excess cabin air, engine thrust and efficiency is improved, and fuel consumption is reduced.
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公开(公告)号：US20190168886A1
公开(公告)日：2019-06-06
申请号：US16205918
申请日：2018-11-30
Applicant: Airbus Operations SL
Inventor： Fernando ANGULO IBAÑEZ
Abstract: A fuel tank with a suction system, comprising a flexible hose comprising first and second extremities, the second extremity comprising an orifice configured to be connected to a first orifice of a first pipeline via a connection point. The first extremity of the flexible hose is fastened to a floating system and comprises at least one orifice, such that the orifice is a suction point always able to supply the engine from an upper layer of fuel available inside the tank, to avoid water and dirt from the lower layer.
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14.发明申请公开(公告)号：US20190099848A1
公开(公告)日：2019-04-04
申请号：US16117995
申请日：2018-08-30
Applicant: AIRBUS OPERATIONS SL
Inventor： Carlos RAMIREZ-ALCALA , Juan GUTIERREZ-SANTIAGO , Maria Angeles MARTIN-ARRAZOLA , Antonio ORTIZ-IGLESIAS , Juan Francisco GARCIA AMADO
CPC classification number: B23Q15/12 , B23B39/161 , B23B45/04 , B23B2215/04 , B23B2270/027 , B23Q17/2233 , B25H1/0028 , B25H1/0078
Abstract: An automatic drilling machine for simultaneously drilling at least two holes through a surface of a crosspiece. The machine comprises an automatic drilling unit having at least two tool holders, each one adapted for receiving a drilling tool. The automatic drilling unit has a cross-shaped channel configured to receive, at least partially, the crosspiece to be drilled inside the automatic drilling unit with. The tool holders are arranged, such as, when the drilling machine is mounted with the crosspiece to be drilled, the tool holders are positioned in accordance with the locations of the crosspiece where a hole is to be drilled.
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公开(公告)号：US20180134371A1
公开(公告)日：2018-05-17
申请号：US15815022
申请日：2017-11-16
Applicant: AIRBUS OPERATIONS SL
Inventor： Ladislao LÓPEZ LÓPEZ
CPC classification number: B64C9/12 , B64C9/00 , B64C9/16 , B64C9/32 , B64C9/323 , B64C13/16 , Y02T50/32
Abstract: An air brake system for aircraft comprising control surfaces, such as slats, flaps and spoilers mounted to the wings of an aircraft, wherein each control surface is split, along a spanwise direction, into parts of the control surface, and the parts of each control surface are deployed desynchronously when the aircraft touches down.
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Patent Agency Ranking
公开(公告)号：US20170354986A1
公开(公告)日：2017-12-14
申请号：US15619059
申请日：2017-06-09
Applicant: AIRBUS OPERATIONS SL
Inventor： Israel CASAS CAZALLA , David ESTEBAN MUÑOZ
Abstract: An auxiliary element (1) for the local deposition of fluid for a fluid dispenser header (10), includes a hollow main body (2), including a hollow conduit (3) inside the main body (2), configured such that the fluid flows through its interior, comprising an opening for the inlet of fluid (5) coming from the fluid dispenser header at one end, and a fluid outlet opening (6) at the opposite end, a cavity (4) located between the wall of the main body (2) and the hollow conduit (3), configured such that residual particles of the fluid flow through its interior, at least one connecting mean (8) to the interior of the hollow conduit (3) to the residual particles cavity (4) and an opening (7) located on the main body (2), configured for the outlet of residual particles from the cavity (4).
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17.发明申请公开(公告)号：US20170334378A1
公开(公告)日：2017-11-23
申请号：US15597604
申请日：2017-05-17
Inventor： Jens Schult , Leire Segura Martinez De Ilarduya , Joerg Wangemann
IPC: B60R16/03
Abstract: An electrical power supply system for an aircraft includes a plurality of generators, each being couplable to and rotatable by an aircraft engine. and a plurality of electrical conversion units, each having a plurality of inputs and at least one output. Each generator includes at least four AC phases. The inputs of each individual electrical conversion unit are connected to a plurality of phases of at least two of the plurality of generators. The electrical conversion units each includes a rectification and conversion device for providing an output voltage having a predeterminable frequency and voltage level at the output.
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公开(公告)号：US12103252B2
公开(公告)日：2024-10-01
申请号：US17742263
申请日：2022-05-11
Applicant: AIRBUS OPERATIONS SL
Inventor： Alberto Arana Hidalgo , Pedro Nogueroles Vines
CPC classification number: B29C70/541 , B29C70/462 , B29L2031/3082
Abstract: A device (40) and a method for manufacturing composite parts such as aircraft bulkheads (23), in which a component of the composite part is placed on a first mold (11) with a robotic device (21), a component of another composite part is placed on a second mold (12) with a robotic device (22), the second mold (12) having a surface identical to the surface the first mold (11), and the first mold and the second mold being mounted on a frame in a central symmetric arrangement around a symmetry central point (15), such that components are placed on the molds (11, 12) symmetrically so as to obtain two identical composite parts at the same time.
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公开(公告)号：US20230364867A1
公开(公告)日：2023-11-16
申请号：US17742263
申请日：2022-05-11
Applicant: AIRBUS OPERATIONS SL
Inventor： Alberto Arana Hidalgo , Pedro Nogueroles Vines
CPC classification number: B29C70/541 , B29C70/462 , B29L2031/3082
Abstract: A device (40) and a method for manufacturing composite parts such as aircraft bulkheads (23), in which a component of the composite part is placed on a first mold (11) with a robotic device (21), a component of another composite part is placed on a second mold (12) with a robotic device (22), the second mold (12) having a surface identical to the surface the first mold (11), and the first mold and the second mold being mounted on a frame in a central symmetric arrangement around a symmetry central point (15), such that components are placed on the molds (11, 12) symmetrically so as to obtain two identical composite parts at the same time.
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公开(公告)号：US20230339593A1
公开(公告)日：2023-10-26
申请号：US18127052
申请日：2023-03-28
Applicant: AIRBUS SAS , Airbus Operations SAS , AIRBUS OPERATIONS LTD , Airbus Operations SL , Airbus Operations GmbH
Inventor： Elisa Alvarez López-Herrero , Matthias Wolff , Alexander Broer , Rainer Tegtmeyer , Michael Wießmeier , Till Marquardt , André Anger , Anna-Katrin Wengorra , Marco Dias Figueiredo , Jose Luis Martinez Munoz , Alberto Gallegos Elvira , Kaya Sahin , Guillaume Gallant , Kasidit Leoviriyakit , Philip Wright
Abstract: An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.
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