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51.发明授权公开(公告)号：US09919785B2
公开(公告)日：2018-03-20
申请号：US14067655
申请日：2013-10-30
Applicant: Airbus Operations, S.L.
Inventor： Alberto Arana Hidalgo , Tomas Rodriguez Hernandez
CPC classification number: B64C1/064 , B64C3/182 , Y10T156/10 , Y10T428/24124
Abstract: A stringer made of composite material for reinforcing aircraft skin panels. Plies are introduced at 90° in a segment close to the stringer run-out, and progressively reducing the number of plies at 0°, such that the majority of the number of plies is at 90° in an segment adjacent to the run-out, so the stiffness of the run-out is reduced, and the load it supports is also therefore reduced. This is an alternative solution to the solutions already existing for getting the stringer run-outs to support a smaller load, thereby reducing both the risk of the plies of the stringer peeling off and the risk of separation between stringer and skin panel. A method of manufacturing said stringer is also provided.
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公开(公告)号：US20180072423A1
公开(公告)日：2018-03-15
申请号：US15704114
申请日：2017-09-14
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Iker VÉLEZ DE MENDIZÁBAL ALONSO , Esteban MARTINO GONZÁLEZ , Carlos GARCÍA NIETO , Edouard MENARD , Enrique GUINALDO FERNÁNDEZ , Soledad CRESPO PEÑA , Jesús Javier VÁZQUEZ CASTRO
CPC classification number: B64D7/00 , B32B5/02 , B32B15/14 , B32B2307/558 , B32B2571/02 , B32B2605/18 , B64C1/062 , B64C1/066 , B64C1/12 , F01D21/045 , F41H5/0457 , F41H5/0471
Abstract: A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.
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公开(公告)号：US20170259902A1
公开(公告)日：2017-09-14
申请号：US15452899
申请日：2017-03-08
Applicant: Airbus Operations, S.L.
Inventor： Pablo Cebolla Garrofe , Iker Vélez De Mendizabal Alonso , Soledad Crespo Peña , Álvaro Calero Casanova , Carlos García Nieto , Enrique Guinaldo , Francisco Javier Honorato Ruiz , Álvaro Torres Salas
CPC classification number: B64C3/26 , B64C3/185 , B64C3/28 , B64C5/02 , B64C21/06 , B64D2045/0095 , Y02T50/166
Abstract: An aircraft aerodynamic surface includes a torsion box having an upper skin, a lower skin, and a front spar, and a leading edge having an external shell and an impact resisting structure. The external shell may be shaped with an aerodynamic leading edge profile, being configured to provide Laminar Flow Control (LFC) to the leading edge. The impact resisting structure is spanwise arranged between the external shell and the front spar, and is configured for absorbing a bird strike to prevent damage in the front spar. Also, at least one of the external shell and the impact resisting structure is fitted with the upper and lower skins of the torsion box to thereby facilitate leading edge exchange.
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公开(公告)号：US20170183076A1
公开(公告)日：2017-06-29
申请号：US15385405
申请日：2016-12-20
Applicant: Airbus Operations, S.L.
Inventor： Pío FERNÁNDEZ LÓPEZ , Pedro Felipe RAMOS-PAUL LASTRA , Cristina SADUÑO OBREGON , Víctor BARREIRO RODRÍGUEZ , David PULPON BEJAS
CPC classification number: B64C1/14 , B64D41/00 , B64D2041/002
Abstract: A door system configured to be attached to the fuselage of a tail cone of an aircraft wherein the tail cone comprises an exhaust gas duct of an auxiliary power unit of the aircraft and an opening of the exhaust gas duct located at the rear part of the tail cone. The door system comprises a door which is movable between an open and a closed position, the door being configured such that, in the closed position, it covers the opening of the exhaust gas duct and that the door being shaped such that it follows the aerodynamic shape of the fuselage of the tail cone in its closed position.
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公开(公告)号：US20170174357A1
公开(公告)日：2017-06-22
申请号：US15379782
申请日：2016-12-15
Applicant: Airbus Operations, S.L.
IPC: B64D41/00
CPC classification number: B64D41/00 , B64D13/06 , B64D2013/0611 , B64D2013/0618 , B64D2013/0644 , B64D2041/002 , B64D2221/00 , Y02T50/44 , Y02T50/54 , Y02T50/56
Abstract: An aircraft includes a bleed supply architecture, a nose section, a central section, and a rear section, a pneumatic system for supplying compressed bleed air to the different aircraft systems, a bleed supply for providing bleed air to the pneumatic system, and an auxiliary power unit. The aircraft additionally includes an electric powered load compressor coupled to the pneumatic system for providing bleed air to said pneumatic system. The auxiliary power unit is adapted for feeding electric power to the load compressor. The load compressor and the pneumatic system are installed at the same central section of the aircraft to reduce pressure losses.
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Patent Agency Ranking
公开(公告)号：US20170167391A1
公开(公告)日：2017-06-15
申请号：US15372645
申请日：2016-12-08
Applicant: Airbus Operations, S.L.
Inventor： Salvatore Demelas
CPC classification number: F02C9/28 , F02C7/22 , F02C7/232 , F02C7/36 , F02C9/30 , F05D2220/323 , F05D2220/50 , F05D2260/40311 , F05D2270/301 , F05D2270/3013 , F05D2270/303 , F05D2270/306 , Y02T50/671
Abstract: A fuel control system for a gas turbine engine of an aircraft having an engine gearbox, a fuel tank, and an engine combustion chamber, wherein the system includes a high pressure fuel pump, at least one electrically controlled fuel injector, a fuel pressure and temperature sensors, and a fuel controller coupled with the sensors to calculate the fuel density, the controller being also coupled with the fuel injector to determine the fuel flow injection rate, the controller being further coupled with the fuel pump to establish a pump output pressure value, according to the fuel density and the flow injection rate of the pumped fuel, such that a constant fuel pressure value is supplied to the fuel injector, to finally inject a constant high fuel injection pressure in the combustion chamber.
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公开(公告)号：US20170144385A1
公开(公告)日：2017-05-25
申请号：US14982039
申请日：2015-12-29
Applicant: AIRBUS OPERATIONS, S.L
Inventor： Gabriel Cruzado Parla , Pablo Lopez Fernandez , Aitor Echevarria Hernandez , Alberto Martinez Cerezo , Alberto Mulas De Lamo , Maria Mora Medias
IPC: B29C70/38
CPC classification number: B29C70/382 , B29C70/345 , B29C70/386 , B29C70/545 , B29D99/0003 , B29L2031/06
Abstract: The disclosure refers to a method for manufacturing rod-shaped components of composite material, for example rowings or fillers, wherein a laminate is layered by automatically laying up a plurality of plies of composite material, which is then cut in an automated machine to obtain a plurality of rods having substantially the same cross-sectional shape. The obtained rods are then simultaneously conformed by applying heat and pressure to obtain rods with the desired cross-sectional shape. With the method of the disclosure, a large number of these types of components are produced with improved quality and in a very simple manner, using the machinery and equipment already commonly existing in a factory of aeronautic components.
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58.发明申请公开(公告)号：US20170129191A1
公开(公告)日：2017-05-11
申请号：US15343788
申请日：2016-11-04
Applicant: Airbus Operations, S.L.
CPC classification number: B29C70/342 , B29C33/42 , B29C45/26 , B29C70/222 , B29C70/446 , B29C70/462 , B29C70/48 , B29K2105/08 , B29K2307/04 , B29L2031/005 , B29L2031/3082 , B29L2031/7096 , B64C1/1461 , B64C1/1492 , Y02T50/43
Abstract: The present disclosure refers to the manufacturing process of an aperture surrounding frame for an aircraft fuselage. The method includes providing a tubular braiding material (2) with a perimeter equal to the perimeter of the frame to be manufactured, cutting the tubular braiding material (2) to obtain annular-shaped braiding slices (3), providing an annular-shaped inner mold (4) where the annular-shaped inner mold has a surface with a desired shape for the aperture surrounding frame, layering up at least one braiding slice (3) around the inner mold (4), forming the at least one braiding slice (3) around the inner mold (4), and curing the aperture surrounding frame pre-form. The present disclosure also refers to an aperture surrounding frame (1) for an aircraft fuselage formed as a continuous body by at least one annular-shaped braiding slice (3) with a perimeter equal to the perimeter of the desired aperture surrounding frame.
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公开(公告)号：US09637214B2
公开(公告)日：2017-05-02
申请号：US14584857
申请日：2014-12-29
Applicant: Airbus Operations, S.L.
CPC classification number: B64C1/064 , B29C70/34 , B29C70/44 , B29C70/446 , B29D99/0014 , B29L2031/3076 , B64C3/182 , B64C2001/0072 , Y02T50/43 , Y10T156/1002
Abstract: A manufacturing method is disclosed for manufacturing of a composite stiffening element, including: arranging composite laminates partially between caul plates and mold halves, and partially between a movable upper sandwich plate and a movable lower sandwich plate, moving the upper and lower sandwich plates together and moving the assembly formed by the first caul plate and the first mold half and the assembly formed by the second caul plate and the second mold half, and joining and co-curing the composite laminates to make up the composite stiffening element. A composite stiffening element is also disclosed.
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60.发明申请AIRCRAFT REAR PORTION COMPRISING A VERTICAL STABILIZER HAVING A BOX-SECTION STRUCTURE INCLUDING A LOWER PORTION ACCOMMODATED IN THE FUSELAGE 审中-公开包括具有盒子结构的垂直稳定器的飞机后部分，包括在FUSELAGE中容纳的较低部分公开(公告)号：US20170066518A1
公开(公告)日：2017-03-09
申请号：US15259585
申请日：2016-09-08
Applicant: Airbus Operations SAS , Airbus Operations S.L.
Inventor： Guillaume Gallant , Jose Luis Martinez Munoz
CPC classification number: B64C1/068 , B64C1/069 , B64C1/26 , B64C5/02 , B64C5/06 , B64D29/06 , B64D41/00 , B64D2041/002
Abstract: To optimize the structure of an aircraft tail section, an aircraft rear section comprises a fuselage section, a tail section, and a vertical stabilizer comprising a box-section structure which comprises a box-section upper part extending on the outside of the tail section, and a box-section lower part housed inside the tail section, such that the tail section is wholly supported by the box-section structure.
Abstract translation: 为了优化飞机尾部的结构，飞机后部包括机身部分，尾部和垂直稳定器，其包括箱部结构，该箱部结构包括在尾部的外侧延伸的箱部上部， 以及容纳在尾部内的箱部下部，使得尾部完全由箱部结构支撑。
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