公开(公告)号：US20190263528A1

公开(公告)日：2019-08-29

申请号：US16336956

申请日：2016-09-29

Applicant: Airbus Operations S.L.

Inventor： Carlos CASADO-MONTERO ,  Victor BARREIRO RODRIGUEZ ,  Alexandra CARRASCO CARRASCAL

IPC: B64D13/08 ,  B64D13/06 ,  B64D27/10 ,  B64D41/00

Abstract: A secondary power unit for an aircraft comprises a gas turbine engine having at least one drive shaft, a twin-load compressor including first and second load compressors both coupled with the drive shaft, a first ram-air intake in fluid communication with the twin-load compressor, and a flow regulating arrangement coupled with the first and second compressors outputs to individually regulate the generated flow of compressed air. The flow regulating arrangement is also adapted to be fluidly communicated with an Air Cycle Machine of an aircraft, and a control system is adapted to feed the flow of compressed air as bleed air to the Air Cycle Machine of an aircraft, both when the aircraft is on ground and in flight. The secondary power unit is capable of avoiding bleed air extraction from the main engines with the aim of reducing fuel consumption.

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：US20190168480A1

公开(公告)日：2019-06-06

申请号：US16205973

申请日：2018-11-30

Applicant: Airbus Operations S.L.

Inventor： Esteban MARTINO-GONZALEZ ,  Iker VELEZ DE MENDIZABAL ALONSO ,  David APELLANIZ DE LA FUENTE

IPC: B32B3/12 ,  B64C3/26 ,  B64C1/12

Abstract: A deformable auxetic structure for absorbing energy of an impact that comprises a plurality of interconnected adjoining tridimensional auxetic cells where each tridimensional auxetic cell comprises at least one surface element and a plurality of legs extending from the surface, the plurality of legs and the surface element being configured such that the sectional cut of the structure in at least two planes perpendicular to the surface element follows an auxetic pattern.

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：US20190100326A1

公开(公告)日：2019-04-04

申请号：US16149497

申请日：2018-10-02

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Antonio DE JULIAN AGUADO ,  José Luis LOZANO GARCÍA

IPC: B64D37/04 ,  F16B5/02 ,  B64D37/06

Abstract: A fitting for transporting an industrial part, the fitting including: a first fitting member comprising a first surface, and a second fitting member including a second surface, wherein the first surface of the first fitting member includes a protuberance and the second surface of the second fitting member includes a recess, wherein the protuberance and the recess are configured such that the protuberance is insertable in the recess when the protuberance is inserted along the recess the first fitting member and the second fitting member are slidable one on another along at least a first direction.

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：US20180371781A1

公开(公告)日：2018-12-27

申请号：US16013194

申请日：2018-06-20

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Ladislao LÓPEZ LÓPEZ

IPC: E04H6/44 ,  E04H15/06 ,  E04H15/34

Abstract: A protective system to shield a vehicle from hailstones. The protective system includes: a protective sheet (1), a reel (2) on which is wound the protective sheet (1), a deployment element (3) configured to deploy the protective sheet (1) from the reel (2) to over the vehicle, wherein an end (12) of the deployment element (3) is fixed to a pivot point such that the deployment element swings from a retracted position and a deployed position, and a support structure (4) configured to support the protective sheet (1) above the aircraft, wherein the support structure (4) is between the fixed end (11) of the deployment element (3) and the reel (2).

公开(公告)号：US20180346132A1

公开(公告)日：2018-12-06

申请号：US15997005

申请日：2018-06-04

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Carlos CASADO-MONTERO ,  Alberto MOLINA PARGA

IPC: B64D13/08 ,  B64D33/02 ,  B64D41/00

CPC classification number: B64D41/00 ,  B64D13/06 ,  B64D2013/0611 ,  B64D2013/0648 ,  B64D2013/0696

Abstract: The invention relates to an aircraft incorporating an enhanced power unit for generating electric, pneumatic and/or hydraulic power for the aircraft during all stages of the aircraft operation. The power unit (1) comprises: a heat engine (14) with a drive shaft (2) and a combustion gases exhaust (7). The power unit (1) also includes a Rankine cycle system (12) for recovering thermal energy from a heat source of the power unit (1) for the assistance of the heat engine (14). The heat source for the Rankine cycle system can be taken from the exhaust gases of the heat engine, from the oil coolant circuit of the heat engine or from the output of a compressor driven by the heat engine. Preferably, the aircraft cabin air is reused as a source of oxygen for the combustion. The invention reduces bleed air extraction from the aircraft main engines thereby reducing fuel consumption.

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.