公开(公告)号：US20240391581A1

公开(公告)日：2024-11-28

申请号：US18670164

申请日：2024-05-21

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Pierre-Antoine COMBES ,  Marc DE NICOLA

IPC: B64C3/32 ,  B64D27/40

Abstract: An assembly comprising a wing with a lower surface panel and an upper surface panel and an engine pylon comprising a primary structure fixed to the wing with a fixing base. The fixing base comprises fourth fixing yokes while the primary structure bears fourth fittings, the fourth fixing yokes being secured to the fourth fittings with fourth rods.

公开(公告)号：US12140569B2

公开(公告)日：2024-11-12

申请号：US17824097

申请日：2022-05-25

Applicant: Airbus Operations SAS

Inventor： Philippe Emile ,  Marc Grimal

IPC: G01N29/34 ,  B64F5/60

Abstract: The system includes an ultrasonic measuring device including ultrasonic transmitters and ultrasonic receivers, the ultrasonic measuring device carrying out ultrasonic measurements on a zone of interest of the component divided according to a gridding including cells, and carrying out the measurements cell after cell with the generation, by all the ultrasonic transmitters, of an ultrasonic signal that is sent into the component, and the measurement, by all the ultrasonic receivers, of the amplitude of the ultrasonic signal reflected by the cell in question of the component, a unit for computing, for all of the cells of the gridding, the sum of the amplitudes of all the measurements carried out for that cell, and a processing part for deducing the presence or absence of one or more defects. The system detects all the defects existing in the zone of interest of the component, whatever their orientation may be.

公开(公告)号：US12134463B2

公开(公告)日：2024-11-05

申请号：US17941075

申请日：2022-09-09

Applicant: Airbus Operations SAS ,  Airbus Atlantic SAS

Inventor： Matthieu Plet ,  Laurent Dubreuil ,  Alain Prudent ,  Xavier Matheis ,  Gilles Andrieu ,  Damien Desgaches

IPC: B64C25/14 ,  B64C25/04

Abstract: An aircraft including a main landing gear compartment which comprises a rear transverse wall, and a base wall forming a sealed barrier between a first, pressurized area and a second, non-pressurized area. The main landing gear compartment includes a body, produced in a single piece from composite material, separating the first, pressurized area and the second, non-pressurized area. The body includes a first part corresponding to the base wall, as well as a second part corresponding to the rear transverse wall. At least two longitudinal beams made of composite material, are connected to the body. This single body makes it possible to eliminate a large number of parts, to simplify the assembly process, and to reduce the duration thereof.

公开(公告)号：US20240360961A1

公开(公告)日：2024-10-31

申请号：US18644955

申请日：2024-04-24

Applicant: Airbus Operations SAS

Inventor： Nicolas TOUREILLE ,  Chloé MESIC ,  Laure MORETTI

IPC: F17C13/06

CPC classification number: F17C13/06 ,  F17C2205/0305 ,  F17C2205/0367 ,  F17C2270/0189

Abstract: A tank comprising an outer enclosure, an inner enclosure positioned in the outer enclosure, and at least one duct passing through first and second walls connected respectively to the outer and inner enclosures. The first and/or second walls comprises at least one deformable zone interposed between, on the one hand, an attachment zone which connects the wall and the outer or inner enclosure and, on the other hand, a connection zone which comprises a connection connecting the wall and the duct. Also an aircraft with such a tank.

公开(公告)号：US20240351704A1

公开(公告)日：2024-10-24

申请号：US18627739

申请日：2024-04-05

Applicant: Airbus Operations SAS

Inventor： Jérôme BADERSPACH ,  Jean GELIOT ,  Dimitri GARAY

IPC: B64D45/00 ,  A62C3/08

CPC classification number: B64D45/00 ,  A62C3/08 ,  B64D2045/009

Abstract: An assembly having a pylon with two side walls provided with apertures, a reservoir for extinguishing agent, a support which has two support elements, wherein each support element has an upwardly facing first bearing face to which the reservoir is fastened, a distal end, and a proximal end fastened by a first removable fastener, wherein the distal end is rotatable about a horizontal axis, and wherein each support element is movable between a use position, in which the first bearing face is horizontal, and a fitted position, in which the first bearing face is tilted downwards.

公开(公告)号：US20240343409A1

公开(公告)日：2024-10-17

申请号：US18632361

申请日：2024-04-11

Applicant: Airbus Operations SAS

Inventor： Mathieu BELLEVILLE

IPC: B64D37/30 ,  B64C3/18 ,  B64D27/12

CPC classification number: B64D37/30 ,  B64D27/12 ,  B64C3/185

Abstract: An aircraft having a wing, a dihydrogen-powered engine, a supply pipe for the dihydrogen, in which each wing has a front spar, a first rear spar extending behind the front spar and a second rear spar extending behind the first rear spar, in which the two rear spars together define a corridor, and in which each supply pipe extends backwards from the related engine then into the corridor of the wing carrying the related engine.

公开(公告)号：US20240327023A1

公开(公告)日：2024-10-03

申请号：US18602498

申请日：2024-03-12

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Christophe LABARTHE ,  Kotaro FUKASAKU

IPC: B64D37/30 ,  B64D27/18 ,  B64D29/02 ,  F02K1/36

CPC classification number: B64D37/30 ,  B64D27/18 ,  B64D29/02 ,  F02K1/36

Abstract: A propulsive assembly comprising a nacelle delimiting an internal volume, a T-shaped frame comprising a first wall fixed to the wing and a second wall that is vertical and that divides the internal volume into two sub-volumes, a dihydrogen consumer device, for each sub-volume, a dihydrogen processing system, a supply line connected between the processing system and the consumer device, and an input line connected between the processing system and a dihydrogen tank. Also an aircraft with a wing and such a propulsive assembly.

公开(公告)号：US12104554B2

公开(公告)日：2024-10-01

申请号：US18484548

申请日：2023-10-11

Applicant: Airbus Operations SAS

Inventor： Lionel Czapla ,  Benjamin Thubert

IPC: F02K1/64 ,  F02K1/32

CPC classification number: F02K1/32 ,  F02K1/645

Abstract: An aircraft propulsion assembly equipped with a thrust-reversing device which includes at least one lateral aperture, passing through the nacelle of the propulsion assembly, configured to be in an open state or a closed state, at least one inflatable barrier configured to be in a deflated state in which the barrier does not protrude into an annular duct channeling a flow of air and an inflated state in which the barrier, substantially rigid or semi-rigid, is deployed and extends across the annular duct to deflect at least a part of the flow of air toward the lateral aperture, and at least one supply system configured to supply the inflatable barrier with fluid. An aircraft is provided which includes at least one such propulsion assembly.

公开(公告)号：US12078428B2

公开(公告)日：2024-09-03

申请号：US17879869

申请日：2022-08-03

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Lionel Czapla ,  Jorge A. Carretero Benignos

IPC: F28D9/00 ,  B64D37/32 ,  B64D37/34 ,  F02C7/224 ,  F28F3/00 ,  F28F9/00

CPC classification number: F28D9/0006 ,  B64D37/32 ,  B64D37/34 ,  F02C7/224 ,  F28D9/0037 ,  F28F3/005 ,  F28F9/005 ,  F28F2265/16

Abstract: A heat exchanger including a sealed housing and a body positioned inside the housing, the body including a stack of least one first assembly of first and second plates pressed against each other, between which flows a first fluid, and at least one second assembly of third and fourth plates pressed against each other, between which flows a second fluid, the first and second assemblies being arranged so that they transfer heat between the first and second fluids. This configuration limits the risk of leaks and mixing of the two fluids.

公开(公告)号：US20240286374A1

公开(公告)日：2024-08-29

申请号：US18585348

申请日：2024-02-23

Applicant: Airbus Operations SAS

Inventor： Gérard MILLET ,  Vincent DELPY ,  Simon FOUCART-GAUDY ,  Marc-Antoine BROCARD

IPC: B32B3/08 ,  B32B3/12 ,  B32B3/26

CPC classification number: B32B3/08 ,  B32B3/12 ,  B32B3/266

Abstract: A tubular insert designed to be positioned in a through-orifice of a sandwich panel. This tubular insert comprises a tubular body and at least one tab that has a first end connected to the tubular body and a second end at a distance from the first end, the tab being able to move between a deployed position in which the second end is moved away from the tubular body and a retracted position in which the second end is positioned at the tubular body, the latter having, for each tab, a cutout delimiting the tab and an opening when the tab is in the deployed position. Also a sandwich panel having at least one such insert and a method for placing such an insert.