公开(公告)号：US20220185495A1

公开(公告)日：2022-06-16

申请号：US17550268

申请日：2021-12-14

Applicant: AIRBUS OPERATIONS SL

Inventor： Pablo Manuel CALDERON GOMEZ ,  Carlos CASADO-MONTERO

IPC: B64D37/32 ,  B64D33/02 ,  B64D31/00 ,  B64D37/30 ,  B64D41/00 ,  F02M67/06 ,  F02C3/00 ,  B01D53/22

Abstract: An aircraft including a combustion engine with a combustion chamber an injection device for injecting fuel in the combustion chamber and an air separation device adapted to separate air into an oxygen-enriched gas mix and an nitrogen-enriched gas mix, wherein the oxygen-enriched gas mix is injected into the combustion chamber with the fuel while the nitrogen-enriched gas mix is used to inert at least some portions of the aircraft in the environment of said combustion engine.

公开(公告)号：US20210299947A1

公开(公告)日：2021-09-30

申请号：US17212592

申请日：2021-03-25

Applicant: AIRBUS OPERATIONS SL

Inventor： Asuncion BUTRAGUENO-MARTINEZ ,  Guillermo HERNAIZ LOPEZ ,  Jose SANCHEZ-GOMEZ

IPC: B29C64/118 ,  B33Y10/00 ,  B33Y70/00

Abstract: A method for manufacturing a part layer-upon-layer using Additive Manufacturing technology suitable for structural applications. The method includes selectively depositing at least a first type filament and a second type filament, wherein the second type filament differs from the first type filament at least in the cross-sectional dimension.

公开(公告)号：US11014687B2

公开(公告)日：2021-05-25

申请号：US16117746

申请日：2018-08-30

Applicant: AIRBUS OPERATIONS SL

Inventor： Victor Barreiro Rodriguez ,  Pio Fernandez-Lopez ,  Marcos Javier Chiabrando

IPC: B64D41/00 ,  B64C1/16 ,  B64D33/02

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.

公开(公告)号：US10532710B2

公开(公告)日：2020-01-14

申请号：US15597604

申请日：2017-05-17

Applicant: Airbus Operations SL ,  Airbus Operations GmbH

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.

公开(公告)号：US20180354651A1

公开(公告)日：2018-12-13

申请号：US16003433

申请日：2018-06-08

Applicant: AIRBUS OPERATIONS SL

Inventor： Carlos GARCIA NIETO ,  Jaime CABRERA VALOR ,  Rosario MOLINA MORENO ,  Sergio HERNANDEZ SANMARTIN ,  María Pilar GUILLÉN MORENO ,  Fernando ALVAREZ ALVAREZ

IPC: B64F5/00

CPC classification number: B64F5/00 ,  B05B12/24 ,  B05B12/26 ,  B05B13/005 ,  B25J15/00

Abstract: A method for masking an aeronautical structure with a frisket before painting such aeronautical structure, including the steps of: providing the aeronautical structure comprising at least one hole; providing the frisket; providing at least one jamming element, wherein said jamming element is configured to be inserted into the at least one hole; providing at least one C-shaped jamming element configured to be placed on a lateral of the first section; arranging the frisket partially over the at least one hole; inserting the at least one jamming element into the at least one hole, partially holding the frisket; wrapping the first section of the aeronautical structure with the frisket, said first section being masked to avoid its painting; and placing the at least one C-shaped jamming element laterally embracing the first section with the frisket, the frisket being clamped against said first section.

公开(公告)号：US20180162706A1

公开(公告)日：2018-06-14

申请号：US15816203

申请日：2017-11-17

Applicant: AIRBUS OPERATIONS SL

Inventor： Angel PALOMARES MORA

IPC: B66F11/04 ,  B64F5/50 ,  B66F7/14 ,  B60P1/02

Abstract: An elevator system (400) to assist the installation of a heavy load (122), such as an auxiliary power unit (APU) in into a compartment of an aircraft (110) compartment (126). The elevator system includes bar assemblies which rotate to lift the load into the compartment. The bar assemblies rotate in synchrony.

公开(公告)号：US20170320561A1

公开(公告)日：2017-11-09

申请号：US15588332

申请日：2017-05-05

Applicant: AIRBUS OPERATIONS SL

Inventor： Carlos GARCIA NIETO ,  Fernando PEREIRA MOSQUEIRA ,  Iker VELEZ DE MENDIZABAL ALONSO ,  Enrique GUINALDO FERNANDEZ ,  Francisco Javier HONORATO RUIZ

IPC: B64C9/00 ,  B64C9/02 ,  B64C5/02

CPC classification number: B64C9/00 ,  B64C5/02 ,  B64C9/02 ,  Y02T50/44

Abstract: An aircraft aerodynamic surface (1) including a torsion box (2) having a front spar (21) and rear spar (22), a first control surface (3) including a front spar (31) and a trailing edge (32) and a second control surface (4) having a front spar (41), a trailing edge (42), and a pivot device (5, 6, 7, 8) for pivotally attaching the first control surface (3) and the second control surface (4) to the rear spar (22) of the torsion box (2), the first control surface is an inboard control surface (4) including two lateral ribs (9, 9′), six inner ribs (11, 12, 13, 14, 15, 10) and an inner spar (16), and the second control surface (3) is an outboard control surface which includes two lateral ribs (20, 20′), three internal ribs (17, 18, 19), two internal spars (24, 24′) and one internal spar (23).