公开(公告)号：US20250026465A1

公开(公告)日：2025-01-23

申请号：US18769034

申请日：2024-07-10

Applicant: Airbus Operations SAS

Inventor： Patrick LIEVEN ,  Edmond FROGER

IPC: B64C1/06 ,  B64C1/26

Abstract: An assembly comprising at least first and second components, at least one connection element comprising a rod configured to ensure uptake of the traction/compression forces between the first and second components, and at least one pair of first and second contact surfaces provided respectively with first and second bumps and rigidly secured respectively to the first and second components, the first and second bumps having complementary shapes configured to nest in one another and ensure transmission of the shear forces between the first and second components. Also, an aircraft comprising at least one such assembly.

公开(公告)号：US20250025724A1

公开(公告)日：2025-01-23

申请号：US18775921

申请日：2024-07-17

Applicant: AIRBUS OPERATIONS SAS

Inventor： Antoine PILON

IPC: A62C3/06 ,  A62C2/04 ,  A62C3/08

Abstract: A method for monitoring an engine of an aircraft supplied with dihydrogen, comprising a safety device including a safety valve that is movable between an open position in which the engine is supplied with dihydrogen and a closed position in which the engine is no longer supplied with dihydrogen, an engine fire detection system, a dihydrogen leak detection system and an engine damage detection system, and comprising electronic circuitry adapted to implement the monitoring method. If a locking authorization is given and if one out of three conditions A, B and C is true, then the safety device closes the safety valve, with: the condition A is true if an engine fire detection system detects a fire, the condition B is true if a dihydrogen leak detection system detects a dihydrogen leak, and the condition C is true if an engine damage detection system detects engine damage.

公开(公告)号：US20250010998A1

公开(公告)日：2025-01-09

申请号：US18761974

申请日：2024-07-02

Applicant: Airbus Operations SAS

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

IPC: B64D27/40 ,  B64D27/18

Abstract: An aircraft propulsion system comprising a turbojet having a fan casing with a rear face, a pylon with a front part and a lower spar with a rear fitting fixed to it, and a front engine attachment fixed between an upper part of the fan casing and the front part, a front arch having two arms, each having a first end fixed to the lower spar and a second end fastened in an articulated manner to the rear face, and two lateral rods, each having a first end fastened in an articulated manner to the rear fitting and a second end fastened in an articulated manner to the rear face.

公开(公告)号：US12188362B2

公开(公告)日：2025-01-07

申请号：US18457134

申请日：2023-08-28

Applicant: Airbus Operations SAS

Inventor： Christian Flemin

IPC: B64D29/00 ,  F01D25/12 ,  B64D33/02 ,  B64D33/08

Abstract: An aircraft engine nacelle in which the inner fixed structure has a heat exchanger which is filled with a two-phase heat transfer fluid and which comprises a tube forming a loop with front, rear, lower and upper strands, and also a first complementary strand between the central zones of the front strand and of the upper strand, a second complementary strand between the central zones of the front strand and of the lower strand, a third complementary strand between the central zones of the rear strand and of the upper strand, and a fourth complementary strand between the central zones of the rear strand and of the lower strand.

公开(公告)号：US20240418137A1

公开(公告)日：2024-12-19

申请号：US18742458

申请日：2024-06-13

Applicant: Airbus Operations SAS

Inventor： Frédéric CHELIN ,  Christophe BOURDEAU ,  Olivier SCHOLZ

IPC: F02K1/72

Abstract: An aircraft nacelle equipped with a thrust reversal device, which comprises: at least one longitudinal actuator for activating or deactivating the thrust reversal device, at least one deflection system configured to deflect an air stream channeled in the nacelle towards a lateral opening in the nacelle, in the activated state, at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system towards the upstream end of the nacelle, for each longitudinal actuator, a hollow longitudinal deflector, which is configured to house the longitudinal actuator and has an aerodynamic profile that has a leading edge oriented towards the deflection system.

公开(公告)号：US20240417091A1

公开(公告)日：2024-12-19

申请号：US18742394

申请日：2024-06-13

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Kotaro FUKASAKU ,  Rémi AMARGIER

IPC: B64D27/40

Abstract: A device for coupling a propulsion system to an engine pylon of an aircraft, the device comprising a baseplate comprising a base suitable for being fastened to the propulsion system, and a first wall extending substantially perpendicularly to the base. The first wall of the baseplate interacts with first and second sleeves, a pair of flanges and a fasteners to the engine pylon. The fasteners comprise two adjacent fastening screws extending parallel to each other.

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.