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公开(公告)号：US11679568B2
公开(公告)日：2023-06-20
申请号：US17394074
申请日：2021-08-04
Applicant: AIRBUS OPERATIONS SL , Alestis Aerospace S.L.
Inventor： Alvaro Calero Casanova , Jesus Javier Vazquez Castro , Diego Garcia Martin , Asuncion Butragueno-Martinez , Maria del Carmen Aguilar Barroso , Jose Martin Bravo , Ana Frutos Muñoz
IPC: B29C70/36 , B32B3/12 , B32B7/12 , B32B27/12 , B32B37/12 , B29C70/54 , B29C70/44 , B29C65/00 , B29C65/48 , B29K101/12 , B29L9/00
CPC classification number: B29C70/36 , B29C65/48 , B29C66/7254 , B29C70/44 , B29C70/541 , B29C70/545 , B32B3/12 , B32B7/12 , B32B27/12 , B32B37/12 , B29K2101/12 , B29L2009/00
Abstract: A method for manufacturing an aeronautical sandwich panel with a honeycomb core and results in a core sealed to prevent infused resin from entering into the honeycomb core open cells while improving its mechanical properties, especially for curved or highly curved panels. In further embodiments, the invention proposes the automation of this process.
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公开(公告)号：US11577816B2
公开(公告)日：2023-02-14
申请号：US17364195
申请日：2021-06-30
Applicant: AIRBUS OPERATIONS SL
Inventor： Antonio Torres Esteban , Jose-Maria Blanco-Saiz , Manuel Recio Melero , Pedro Nogueroles Viñes
IPC: B64C3/26 , B64F5/10 , B29C70/30 , B64C1/06 , B64C5/02 , B64C7/00 , B64C9/00 , B29K105/08 , B29L31/30 , B64C1/00
Abstract: A composite laminate for an airframe lifting surface including: at least two sides and one ramp area defined by a decreasing staggered laminate extended along a ramp direction, wherein the composite laminate includes: first plies formed by tapes arranged parallel to the ramp direction, second plies formed by tapes arranged orthogonal to the ramp direction, third plies formed by tapes arranged in a first laying up direction, being the first laying up direction different from the ramp direction and the direction orthogonal to the ramp direction, and fourth plies formed by tapes arranged in a second laying up direction, being the second laying up direction different from the ramp direction, the direction orthogonal to the ramp direction and the first laying up direction; wherein in the ramp area, the tapes forming the third and/or fourth plies are extended from one laminate side to another laminate side.
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公开(公告)号：US20220341311A1
公开(公告)日：2022-10-27
申请号：US17702455
申请日：2022-03-23
Applicant: AIRBUS OPERATIONS SL
Inventor： Carlos RAMIREZ-ALCALA , Juan Manuel VAZQUEZ MARTINEZ , Juan Maria GONZALEZ LEAL , Jorge SALGUERO GOMEZ
Abstract: A drilling machine and a drilling method including drilling a first bore in a material with a drilling machine by applying a torque to a drilling tool for imparting a rotation at a first rotational speed to the drilling tool, and applying a thrust to the drilling tool for advancing the drilling tool at a first feed speed into the material, wherein a drilling parameter is measured while drilling the first bore, and a second rotational speed and a second feed speed are determined based on the drilling parameter, then drilling a second bore at the second rotational speed and at the second feed speed.
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公开(公告)号：US20210276258A1
公开(公告)日：2021-09-09
申请号：US17196280
申请日：2021-03-09
Applicant: AIRBUS OPERATIONS SL
Inventor： Alvaro JARA RODELGO , Alfonso PARRA RUBIO , Guillermo HERNAIZ LOPEZ , Pablo VAZQUEZ SANCHEZ , Enrique GUINALDO FERNANDEZ
IPC: B29C64/30 , B29C64/118 , B33Y10/00 , B33Y30/00 , B33Y40/20
Abstract: A method for manufacturing a part layer-upon-layer using Additive Manufacturing technology, the method including: printing the part together with an elastomeric enclosure shaped thereto leaving a gap free of material therebetween, the elastomeric enclosure including at least one opening; heating the ensemble of the printed part and elastomeric enclosure or keeping an operating printing temperature; applying vacuum by the at least one opening of the elastomeric enclosure so that the elastomeric enclosure deflates thus exerting pressure to the printed part; and maintaining the printed part under vacuum and heat during a predefined time.
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5.发明授权公开(公告)号：US10589393B2
公开(公告)日：2020-03-17
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
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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Patent Agency Ranking
公开(公告)号：US20190127077A1
公开(公告)日：2019-05-02
申请号：US16117746
申请日：2018-08-30
Applicant: AIRBUS OPERATIONS SL
Abstract: An aircraft tailcone comprising a tailcone fuselage, a turbomachine, for example an APU, housed inside the tailcone, a ram air intake on the tailcone fuselage for the ingestion of ram air towards the interior of the turbomachine compartment, an inlet flap operable reciprocately from an open position in which ingestion of ram air is allowed, and a closed position in which ram air ingestion is prevented. The ram air intake extends annularly along a perimeter of the tailcone fuselage, and the inlet flap is configured such in its closed position that a surface of the inlet flap is substantially flush with the tailcone fuselage.
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公开(公告)号：US20190127041A1
公开(公告)日：2019-05-02
申请号：US16119195
申请日：2018-08-31
Applicant: AIRBUS OPERATIONS SL
Inventor： Juan ZÚÑIGA SAGREDO
Abstract: An access cover for an aircraft hole that comprises a plurality of access cover holes, an inner surface, a plurality of first projections protruding from the inner surface, and a plurality of fixing elements configured to fix the access cover to a supporting structure of the aircraft hole. The fixing elements each comprise a male fixing element having an outer threaded surface, the male fixing element being configured to pass through a hole, and a locking element comprising a threaded hole and an extended portion, wherein the outer threaded surface of the male fixing element is configured to thread with the threaded hole of the locking element.
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公开(公告)号：US20190017399A1
公开(公告)日：2019-01-17
申请号：US16034548
申请日：2018-07-13
Applicant: AIRBUS OPERATIONS SL
Inventor： Javier FRAILE MARTIN , Anton Mendez-Diaz
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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9.发明申请公开(公告)号：US20180170563A1
公开(公告)日：2018-06-21
申请号：US15845330
申请日：2017-12-18
Applicant: Airbus Operations SAS , Airbus Operations SL
Inventor： Eric BOUCHET , Esteban MARTINO-GONZALEZ , Jerome COLMAGRO , Fernando INIESTA LOZANO , Julien MOULIS , Antoine ABELE
CPC classification number: B64D27/20 , B64C1/061 , B64C1/16 , B64D27/14 , B64D27/26 , B64D2027/268 , B64D2033/0286 , Y02T50/44
Abstract: In order to reduce the congestion of the attachment means for aircraft engines in a secondary vein, a first fuselage frame has two side portions for supporting the engine, each associated with one of the two partly buried side engines, these portions being curved inwards so as to surround and follow the profile of the outer shroud of an intermediate case. The side portion is attached on this shroud through first and second attachment arrangements spaced apart from each other circumferentially, these arrangements being configured in order to allow absorption of the forces related to the torque along a longitudinal direction of the engine.
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公开(公告)号：US09284038B2
公开(公告)日：2016-03-15
申请号：US14140665
申请日：2013-12-26
Applicant: AIRBUS OPERATIONS SL
Inventor： Coral Aida Mora Ordóñez
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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