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    Aircraft comprising a structure, a tank and means for fastening the tank to the structure
    1.
    发明授权
    Aircraft comprising a structure, a tank and means for fastening the tank to the structure 有权

    公开(公告)号：US12296973B2

    公开(公告)日：2025-05-13

    申请号：US18363426

    申请日：2023-08-01

    Applicant: Airbus Operations SAS

    Inventor： Anthony Mertes

    IPC: B64D37/04

    Abstract: An aircraft comprising a structure, a tank housed in the fuselage, and fastening means which comprise a front fastening system, a rear fastening system and a lateral fastening system. The front system comprises a front plate, two lateral connecting rods and a central connecting rod that are fastened between the front plate and the tank. The rear system comprises a rear plate and a rear connecting rod fastened between the rear plate and the tank. The lateral system comprises a lateral connecting rod fastened between the structure and the tank, wherein one of the connection points is behind the other connection point.

    Powerplant for an aircraft
    2.
    发明授权
    Powerplant for an aircraft 有权

    公开(公告)号：US12291350B2

    公开(公告)日：2025-05-06

    申请号：US18456586

    申请日：2023-08-28

    Applicant: Airbus Operations SAS

    Inventor： Lionel Czapla ,  Emmanuel Vardelle

    IPC: B64D37/32 ,  B64D27/12 ,  B64D37/04 ,  B64D37/30 ,  F02C3/22 ,  F02C7/20 ,  F02C7/22

    Abstract: A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective plate fastened to the frame and positioned between the casing and the supply pipe. With such an arrangement, if a blade of the turbine became detached it would meet the protective plate blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

    PROPULSION ASSEMBLY FOR AN AIRCRAFT
    3.
    发明申请
    PROPULSION ASSEMBLY FOR AN AIRCRAFT 有权

    公开(公告)号：US20250121927A1

    公开(公告)日：2025-04-17

    申请号：US18908982

    申请日：2024-10-08

    Applicant: Airbus SAS ,  Airbus Operations SAS

    Inventor： Nandakumar DEVASIGAMANI ,  Lionel CZAPLA ,  Jorge A. CARRETERO BENIGNOS

    IPC: B64C7/00 ,  B64D33/04 ,  B64D37/30

    Abstract: A propulsion assembly having a propulsion system comprising a fairing, a rotary assembly having a combustion chamber and housed in the fairing, an exhaust nozzle positioned downstream of the combustion chamber and delimited by a nozzle wall, and ensuring the discharge of the combustion gases originating from the combustion of the dihydrogen in the combustion chamber, a dihydrogen tank, a supply duct which connects the tank and the combustion chamber, and at least one vane positioned inside the exhaust nozzle, wherein the supply duct has a duct portion arranged in the vane.

    AIRCRAFT COMPRISING AT LEAST ONE ENGINE ATTACHMENT SYSTEM THAT HAS REDUCED VERTICAL BULK
    4.
    发明申请
    AIRCRAFT COMPRISING AT LEAST ONE ENGINE ATTACHMENT SYSTEM THAT HAS REDUCED VERTICAL BULK 有权

    公开(公告)号：US20250115365A1

    公开(公告)日：2025-04-10

    申请号：US18905523

    申请日：2024-10-03

    Applicant: Airbus Operations SAS

    Inventor： Michael BERJOT ,  Rémi LANSIAUX ,  Jean-Baptiste VIGNES

    IPC: B64D27/40

    Abstract: An aircraft comprising at least one engine attachment system connecting a primary structure of a pylon and a motor, having a right-hand interface connected to the right-hand lateral face of the primary structure, a left-hand interface connected to the left-hand lateral face of the primary structure, first and second shackles connecting the right-hand and left-hand interfaces to the motor by virtue of engine connection pins and interface connection pins, a right-hand emergency connection pin cooperating with the right-hand interface and the motor, and a left-hand emergency connection pin cooperating with the left-hand interface and the motor.

    METHOD FOR REPAIRING A STRUCTURAL PART OF AN AIRCRAFT HAVING A PROTECTION DEFECT, AND STRUCTURAL AIRCRAFT PART THUS REPAIRED
    6.
    发明申请
    METHOD FOR REPAIRING A STRUCTURAL PART OF AN AIRCRAFT HAVING A PROTECTION DEFECT, AND STRUCTURAL AIRCRAFT PART THUS REPAIRED 有权

    公开(公告)号：US20250074626A1

    公开(公告)日：2025-03-06

    申请号：US18794716

    申请日：2024-08-05

    Applicant: Airbus Operations SAS

    Inventor： Clement CHIROL ,  Marine CHESNEAU ,  Mélanie BEDU

    IPC: B64F5/40 ,  B05D5/00

    Abstract: A method for repairing a zone of a metal structural aircraft part having a protection defect in the vicinity of an orifice for receiving a fastener. There is a step of positioning an isolation element on the zone around the orifice, a step of applying a coat of paint to the zone, covering the isolation element, and a step of inserting a metal fastener into an orifice of the isolation element, prior to or following the step of applying the coat of paint. The isolation element makes it possible to avoid direct contact between the metal of the fastener and the metal forming the aircraft structure, and therefore to avoid any risk of galvanic coupling between the damaged zone and the fastening.

    PROPULSION UNIT COMPRISING AT LEAST ONE ELECTRIC MOTOR AND A COUPLING SYSTEM POSITIONED ON EITHER SIDE OF A TRANSMISSION SYSTEM
    8.
    发明申请
    PROPULSION UNIT COMPRISING AT LEAST ONE ELECTRIC MOTOR AND A COUPLING SYSTEM POSITIONED ON EITHER SIDE OF A TRANSMISSION SYSTEM 有权

    公开(公告)号：US20250033787A1

    公开(公告)日：2025-01-30

    申请号：US18779955

    申请日：2024-07-22

    Applicant: Airbus Operations SAS

    Inventor： Jean-François ALLIAS ,  Rémi AMARGIER

    IPC: B64D35/021 ,  B64D27/34

    Abstract: A propulsion unit comprising a propulsion system, at least one electric motor positioned in a first external zone, a transmission system, a coupling device which comprises: a first coupling shaft coupled to an output of the electric motor, passing through the transmission system and having a first end protruding into a second external zone; a second coupling shaft coupled to an input of the transmission system, passing through at least one wall of the transmission system and having a first end protruding into the second external zone; and a coupling system configured to couple the first ends of the first and second coupling shafts in terms of rotation and which is positioned in the second external zone. Also an aircraft having at least one such propulsion unit.

    Tank system with a valve in the form of a pendulum system
    9.
    发明授权
    Tank system with a valve in the form of a pendulum system 有权

    公开(公告)号：US12208914B2

    公开(公告)日：2025-01-28

    申请号：US18339328

    申请日：2023-06-22

    Applicant: Airbus Operations SAS ,  Airbus SAS

    Inventor： Thomas Andrieu ,  Jérôme Milliere ,  Julien Laverne ,  Jonathan Landolt

    IPC: B64D37/22 ,  B64D37/06

    Abstract: A tank system comprising a tank, a drainage line fixed in the bottom part of the tank and having a drainage port at each end and, for each drainage port, a funnel having a wall through which at least one window passes, a body that can move in translation, for each funnel, a plug that is secured to the body and arranged to be able to move inside said funnel between an open position and a closed position, and an arm, a first end of which is mounted in an articulated manner to the top part of the tank and a second end of which is mounted in an articulated manner on the body.

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