公开(公告)号：US10549492B2

公开(公告)日：2020-02-04

申请号：US14725626

申请日：2015-05-29

Applicant: Airbus Operations, S.L.

Inventor： Gabriel Cruzado Parla ,  Fernando Munoz Ajenjo ,  Jose Cuenca Rincon ,  Maria Mora Medias

IPC: B29C33/68 ,  B29C70/44 ,  B29K105/08 ,  B29K307/04 ,  B29L31/30

Abstract: The present disclosure refers to a method for manufacturing carbon fiber panels stiffened with omega stringers for the construction of aircraft structures, such as fuselage sections, wing panels, etc. One tubular pressure member is provided for each omega stringer of the structure to be manufactured, wherein the tubular pressure member is configured with the shape of the omega stringer. Each tubular pressure member is enclosed between the omega stringer and part of the laminate, and autoclave pressure is applied to the interior of the tubular pressure member, so that the tubular pressure member is used to consolidate the omega stringers and/or part of the laminate from the interior of these two elements, while these two elements are being co-cured or co-bonded in an autoclave. Imperfections on those internal surfaces such as resin wrinkles of the structure are reduced.

公开(公告)号：US10543928B2

公开(公告)日：2020-01-28

申请号：US15349180

申请日：2016-11-11

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Salvatore Demelas

IPC: B64D33/00 ,  B64D31/00

Abstract: An electric power distribution system for an aircraft is provided, which includes an engine gearbox, a power distribution center, two or more three-phase synchronous electric power generators, a neutral current transformer per generator, a single set of power feeder wires, and a single generator control unit (GCU). The generators are connected in parallel with each other, and connected with the power distribution center by the same set of power feeder wires. The GCU is electrically coupled with each generator to feed the generator with an excitation field current, and with each neutral current transformer to sense an instantaneous neutral-current value. The GCU is adapted to perform a generator voltage regulation loop based on a desired voltage value and the at least two sensed instantaneous neutral-current values by individually modifying the excitation field current of each generator.

公开(公告)号：US10507622B2

公开(公告)日：2019-12-17

申请号：US15726816

申请日：2017-10-06

Applicant: AIRBUS OPERATIONS SL

Inventor： Jose Cuenca Rincon ,  Juan Salamero Laorden ,  Ana Teresa Rodriguez-Bellido

IPC: B29C70/44 ,  B29C35/02 ,  B29C73/10 ,  B29C73/32 ,  B29C73/34 ,  B32B37/00 ,  B32B37/10 ,  B29C73/30 ,  B29C43/36 ,  B29K63/00 ,  B29C73/12 ,  B29K105/06

Abstract: A system for curing polymer matrix composite parts out of autoclave in manufacturing and repairing processes including: (i) an inner vacuum bag (3) placed over the lay-up to be cured located over a working area (15, 18) with the edges of the inner vacuum bag (3) joined to the working area by first sealing elements (8); (ii) a Perforated bulkhead (4) located over the inner vacuum bag (3), (iii) an Outer vacuum bag (2) over a perforated bulkhead (4) and over the edges of the inner vacuum bag with the edges of the outer vacuum bag (2) joined to the working area (15, 18) by second sealing elements (1), (iv) a vacuum device (5, 7, 6) and (v) a heating source (9, 20).

公开(公告)号：US10472073B2

公开(公告)日：2019-11-12

申请号：US15395425

申请日：2016-12-30

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Carlos Casado Montero

IPC: B64D13/08 ,  B64D13/06

Abstract: An air conditioning system 1 for a cabin 10 including a pressurized air source 2, a cooling air source 3, a main heat exchanger 4, a compressor 5, a manifold 6 and a mixing chamber 7. An inlet 43 to a cold side of the main heat exchanger 4 is in fluid communication with the cooling air source 3. An inlet 41 of a hot side of the main heat exchanger 4 is in fluid communication with the pressurized air source 2. An inlet 51 of the compressor is in fluid communication with the outlet 44 of the cold side of the main heat exchanger 4.

公开(公告)号：US10443623B2

公开(公告)日：2019-10-15

申请号：US15458688

申请日：2017-03-14

Applicant: AIRBUS OPERATIONS S.L. ,  Airbus Operations GmbH

Inventor： Antón Méndez Díaz ,  Javier Fraile Martin ,  Neus Busquets More ,  Jan Barkowsky

IPC: F04D29/58 ,  B64D15/04 ,  F04D27/00 ,  F04D29/54 ,  F04D29/56 ,  B64D13/08 ,  F02C6/08 ,  F02C9/18 ,  B64D13/06

Abstract: An engine bleed air system of an aircraft, comprising a heat exchanger which comprises a rectangular core with a rectangular outlet section, a cylindrical outlet duct and a transition area between the rectangular outlet section of the rectangular core and the cylindrical outlet duct, and at least a downstream system, further comprising a flow deflector located at least in the cylindrical outlet duct, such that the outlet flow characteristics homogeneity are improved and a particular flow deflection and distribution of the outlet flow is achieved, avoiding the damage of the at least one downstream system. The invention also provides a method for homogenizing the temperature of the outlet flow of a heat exchanger outlet in an engine bleed air system of an aircraft.

公开(公告)号：US10377464B2

公开(公告)日：2019-08-13

申请号：US15457499

申请日：2017-03-13

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Pablo Cebolla Garrofe ,  Álvaro Calero Casanova ,  Soledad Crespo Peña ,  Carlos Garcïa Nieto ,  Iker Vélez De Mendizábal Alonso ,  Enrique Guinaldo Fernandez ,  Francisco Javier Honorato Ruiz ,  Alvaro Torres Salas

IPC: B64C3/26 ,  B29C45/00 ,  B29C45/14 ,  B29C45/40 ,  B29C69/00 ,  B29C33/48 ,  B29K105/06 ,  B29L31/30 ,  B29C33/30 ,  B64C3/28 ,  B64C21/06 ,  B29K105/12

Abstract: This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection molding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles to close the tool. Further, the injection molding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demolded.

公开(公告)号：US10369762B2

公开(公告)日：2019-08-06

申请号：US15448800

申请日：2017-03-03

Applicant: Airbus Operations, S.L.

Inventor： Fernando Pereira Mosqueira ,  Andrea Ivan Marasco ,  Esteban Martino Gonzalez

IPC: B32B5/18 ,  B32B3/12 ,  B32B15/01 ,  B32B27/20 ,  B32B5/26 ,  B32B5/28 ,  B32B7/02 ,  B32B15/20 ,  B29D99/00 ,  B32B3/02 ,  B64C1/06 ,  B33Y80/00

Abstract: A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.

公开(公告)号：US10286993B2

公开(公告)日：2019-05-14

申请号：US15366126

申请日：2016-12-01

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Jesús Javier Vázquez Castro ,  Fernando Pereira Mosqueira

IPC: B64C1/10 ,  B64C1/34 ,  B64C1/00

Abstract: A pressure bulkhead for an aircraft comprising a fuselage. The pressure bulkhead comprises an inflatable element, suitable for being filled with air, which in turn comprises a cover which delimits an inner zone. The pressure bulkhead further comprises a seal suitable for providing an airtight seal between the cover and the fuselage of the aircraft.

公开(公告)号：US10202201B2

公开(公告)日：2019-02-12

申请号：US14951576

申请日：2015-11-25

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Angel Palomares Mora

IPC: B64D45/00 ,  B64D41/00 ,  B64D33/02 ,  F01D5/02 ,  F01D25/30 ,  F02C7/04

Abstract: The invention refers to an APU compartment, and a method for extinguishing a fire in an APU compartment. The APU compartment (1) comprises an APU (2), an exhaust (5), an aperture (7) providing a passage between the APU compartment (1) and the inside of the exhaust (5), and a fire detection system, wherein the APU compartment (1) of the invention is constructed as an air tight compartment, and additionally comprises a conduit (9) for providing external air to the APU compartment (1), a door (8) for closing the conduit (9) inlet, and a control unit (6) configured to close the door (8) when a fire is detected, such that when the door (8) is closed and the APU (2) is in operation, the air contained in the APU compartment (1) is sucked through the aperture (7) to be expelled out of the APU compartment (1) to extinguish the fire.

公开(公告)号：US10124876B2

公开(公告)日：2018-11-13

申请号：US14952376

申请日：2015-11-25

Applicant: Airbus Operations S.L. ,  Airbus Operations SAS

Inventor： Esteban Martino Gonzalez ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Angel Pascual Fuertes ,  Sandra Linares Mendoza ,  Julien Guillemaut ,  Eric Bouchet ,  Jerome Colmagro ,  Jonathan Blanc

IPC: B64C1/06 ,  B64C1/12 ,  B64C1/16 ,  B64C1/26 ,  B64C3/32

Abstract: An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.