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.

公开(公告)号：US20240280428A1

公开(公告)日：2024-08-22

申请号：US18442180

申请日：2024-02-15

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Nicolas DUPE ,  Nicolas JEAN ,  Cyrille DAJEAN ,  Christian MELONI

IPC: F01D25/24 ,  F01D17/02 ,  F02K1/62

CPC classification number: F01D25/24 ,  F01D9/00 ,  F01D17/02 ,  F01D17/08 ,  F02K1/625 ,  G01L19/147 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2260/80

Abstract: A measuring rake, configured to be arranged on a link rod, includes a sheath including a front face and two side walls delimiting between them a recess configured to receive the link rod, an electronic circuit arranged on the front face of the sheath and including at least one sensor, a patched leading edge fixed removably to the sheath, and a seal arranged between the patched leading edge and the electronic circuit, the patched leading edge including a plurality of air intakes, each forming a fluidic passage between an outer face and an inner face of the patched leading edge opening out facing at least one sensor of the electronic circuit, the measuring rake making it possible to obtain a measuring tool which can be assembled simply and quickly, with easy access to the electronic circuit, and making it possible to avoid problems of orifice blockages or air leaks.

公开(公告)号：US20240262486A1

公开(公告)日：2024-08-08

申请号：US18428366

申请日：2024-01-31

Applicant: Airbus Operations SAS

Inventor： Patrick LIEVEN ,  Anthony MERTES ,  Flavio Ferreira RAIMUNDO

IPC: B64C1/14

CPC classification number: B64C1/1461

Abstract: An access door assembly for a fuselage having a structure delimiting an access hatch, an upper part and a lower part of an access door, hinges fastened between the structure and the upper part in the vicinity of an upper edge, a guiding system between the lower part and the structure and guiding the lower part in translation, upper locks between the upper part and the lower part and/or the structure and lower locks between the lower part and the structure.

公开(公告)号：US12054272B2

公开(公告)日：2024-08-06

申请号：US17964083

申请日：2022-10-12

Applicant: Airbus Operations SAS

Inventor： Franck Rumiel ,  Thomas Robiglio ,  Paolo Messina

IPC: B64D27/40

CPC classification number: B64D27/40 ,  B64D27/402 ,  B64D27/404

Abstract: An assembly of a pylon and of an engine with a rear engine attachment having two fittings, wherein each one has a shoe fastened to a lower spar of the pylon, two transverse arms, one front and one rear, which are as one with the shoe and offset such that the front transverse arm, respectively rear transverse arm, of one fitting bears in planar fashion against the front transverse arm, respectively rear transverse arm, of the other fitting, wherein each transverse arm is pierced with a bore, wherein the two front transverse arms and the two rear transverse arms are spaced apart parallel to the longitudinal direction and thus form a female clevis, and wherein the assembly also has a lower rod mounted articulated in the female clevis and on the engine. With such an assembly, the number of components is reduced.

公开(公告)号：US20240253802A1

公开(公告)日：2024-08-01

申请号：US18425100

申请日：2024-01-29

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： François PONS ,  Laurent CAZEAUX ,  Arnulfo CARAZO MENDEZ ,  Florent MERCAT ,  Alexandre BELLANGER ,  Laurent PRESSEQ ,  Maxime GAUTHIER ,  Manuel TEIGNE ,  Philippe WESSEL ,  Joelle BONNEFONT

IPC: B64D33/02

CPC classification number: B64D33/02 ,  B64D2033/0206

Abstract: An alveolar structure of an acoustic damping panel which is configured for damping at least one sound wave at a sound frequency, wherein the alveolar structure comprises at least one partition provided with at least one cavity configured such that the partition vibrates at a vibrational frequency substantially equal to the sound frequency of the sound wave to be damped. Also a method for producing such an alveolar structure, an acoustic damping panel comprising at least one such alveolar structure, and an aircraft comprising at least one such acoustic damping panel.