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：US20200164994A1

公开(公告)日：2020-05-28

申请号：US16689188

申请日：2019-11-20

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Christophe LABARTHE

IPC: B64D29/06 ,  B64D29/08 ,  B64D33/02 ,  B64D29/02

Abstract: An aircraft nacelle which comprises a structure, an upstream cowl, an upper cowl arranged to the rear of the upstream cowl and having a starboard-side door and a port-side door, each being articulated between a closed position and an open position, each having a front edge, a rear edge, an inner edge and an outer edge. The nacelle comprises, for each door, an articulation and a locking system. Each door is articulated at the level of its outer edge and, in the closed position, the inner edge of one door is contiguous with the inner edge of the other door. Such a nacelle makes the technicians' work easier because the two articulated doors can be opened wide and give easy access under the cowl.

公开(公告)号：US20200369396A1

公开(公告)日：2020-11-26

申请号：US16879121

申请日：2020-05-20

Applicant: Airbus Operations SAS

Inventor： Christophe LABARTHE ,  Michael BERJOT ,  Thomas DEFORET

IPC: B64D27/26

Abstract: A rear engine attachment system for an aircraft engine. The attachment system has an engine pylon with a lower spar having a lower surface, and a rear engine attachment having a beam fixed against the lower surface and to which a pair of rods is fixed. Each rod is fixed to the beam by at least one first connection point and to the engine by at least one second connection point. The beam includes front and rear fittings, and an intermediate fitting with a shoe and an intermediate clevis. The shoe presses against the lower surface. The front fitting presses against the intermediate fitting at the front and the rear fitting presses against the intermediate fitting at the rear. The fixing to the lower spar is ensured by bolts, each passing through the front base or the rear base, the shoe and the lower spar.

公开(公告)号：US20250026481A1

公开(公告)日：2025-01-23

申请号：US18774119

申请日：2024-07-16

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Christophe LABARTHE ,  Kotaro FUKASAKU

IPC: B64D29/06 ,  B64D37/34

Abstract: A nacelle comprising a cowl which has a window, a box structure around the window and containing a conditioning device for conditioning dihydrogen, a door mounted pivotably on the cowl between a closed position and an open position, a maneuvering system for moving the door from the closed position to the open position, a detector for detecting the presence of dihydrogen in the box structure, and a control unit designed to make the maneuvering system open on the basis of information supplied by the detector.

公开(公告)号：US20220306306A1

公开(公告)日：2022-09-29

申请号：US17701818

申请日：2022-03-23

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Christophe LABARTHE ,  Franck ALVAREZ ,  Fabien LATOURELLE ,  Olivier VERSEUX ,  Pascal POME ,  Jean Francois ALLIAS ,  Olivier CIET ,  Olivier RASPATI ,  Anthony ROUX ,  Benedikt BAMMER

IPC: B64D27/24 ,  B60L50/70 ,  B64D29/00 ,  B64D33/08 ,  B64C11/00 ,  B60L58/33 ,  F02K5/00

Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.

公开(公告)号：US20220289396A1

公开(公告)日：2022-09-15

申请号：US17685608

申请日：2022-03-03

Applicant: Airbus Operations SAS

Inventor： Theophile HORDE ,  Lionel CZAPLA ,  Christophe LABARTHE

IPC: B64D27/26 ,  B64D29/00

Abstract: An aircraft pylon comprising a primary structure and a pipe segment having an internal duct positioned inside at least one structural tube primary structure. This solution makes it possible to reduce the crowding outside the structural tubes of the primary structure, makes it easier to integrate other equipment inside the pylon, and may help to improve the aerodynamic performance of the pylon by reducing its cross section.

公开(公告)号：US20240025553A1

公开(公告)日：2024-01-25

申请号：US18355779

申请日：2023-07-20

Applicant: Airbus Operations SAS

Inventor： Mathieu MAHE ,  Christophe LABARTHE ,  Frederic JOURNADE ,  Frédéric VINCHES ,  Franck ALVAREZ ,  Lionel CZAPLA ,  Emmanuel VARDELLE ,  Rémi AMARGIER ,  Kotaro FUKASAKU

IPC: B64D27/24 ,  H01M8/2465

CPC classification number: B64D27/24 ,  H01M8/2465 ,  B64D2027/264

Abstract: A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

公开(公告)号：US20220246971A1

公开(公告)日：2022-08-04

申请号：US17584858

申请日：2022-01-26

Applicant: Airbus Operations SAS

Inventor： Janik FERNANDEZ GARCIA ,  Jordan COOK ,  Julien CAYSSIALS ,  Christophe LABARTHE

IPC: H01M8/2483 ,  H01M8/2404 ,  B64D27/24 ,  H01M8/2475

Abstract: A device for grouping together fuel cells, including at least two fuel cells, a support including a casing, at least one feeder configured to supply the fuel cells with fluid, at least one manifold configured to collect a fluid from the fuel cells, the feeder and the manifold being rigidly secured to the casing and positioned between the casing and the fuel cells.

公开(公告)号：US20200369397A1

公开(公告)日：2020-11-26

申请号：US16880171

申请日：2020-05-21

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Christophe LABARTHE

IPC: B64D29/02 ,  B64D27/02 ,  B64D27/26

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a pylon configured to be fastened beneath a wing of the aircraft, a turbomachine having a longitudinal direction, a median plane and a transverse plane, and a nacelle surrounding the turbomachine and having a load support disposed in the top part of the nacelle. The load support has a structural part fastened to the pylon and an aerodynamic part capping the structural part. The aerodynamic part has, at the front, a front part fastened to the structural part and, at the rear, a rear part fastened to the pylon. Separating the load support into two parts makes it possible to reduce the movements of the aerodynamic part capping the structural part of the load support.