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    AIRCRAFT FLOOR ARRANGEMENT WITH CUSTOMIZABLE LOAD-BEARING CAPABILITIES
    2.
    发明申请
    AIRCRAFT FLOOR ARRANGEMENT WITH CUSTOMIZABLE LOAD-BEARING CAPABILITIES 有权

    公开(公告)号：US20250042533A1

    公开(公告)日：2025-02-06

    申请号：US18787441

    申请日：2024-07-29

    Applicant: Airbus Operations GmbH

    Inventor： Hermann BENTHIEN ,  Bernd SCHWING

    IPC: B64C1/18

    Abstract: An aircraft floor arrangement with customizable load-bearing capabilities is provided that comprises a plurality of floor panels and at least one support profile. The at least one support profile is configured to reinforce at least one of the floor panels such that the load-bearing capabilities are increased. The floor panels are provided with a plurality of interface points arranged at least along one direction. The interface points are configured for mounting of one of the support profiles to one of the floor panels via the interface points to reinforce the floor panels.

    METHOD AND TOOL SYSTEM FOR MANUFACTURING A COMPONENT FROM A FIBER-REINFORCED PLASTIC
    3.
    发明申请
    METHOD AND TOOL SYSTEM FOR MANUFACTURING A COMPONENT FROM A FIBER-REINFORCED PLASTIC 有权

    公开(公告)号：US20250033300A1

    公开(公告)日：2025-01-30

    申请号：US18913403

    申请日：2024-10-11

    Applicant: Airbus Operations GmbH

    Inventor： Hauke Seegel

    IPC: B29C70/48 ,  B29C33/38 ,  B29C33/40 ,  B29C70/44

    Abstract: A tool system for producing a component from a fiber-reinforced plastic includes a molding tool with a tool surface having a peripheral edge, a compensating body having a coefficient of thermal expansion greater than that of the molding tool, a closure device, and a heating device for heating the molding tool. The tool surface is configured to receive, at a first temperature, at least one ply of a semifinished fiber product having a peripheral contour within the peripheral edge, and of the compensating body, along the peripheral edge, so the compensating body extends from the peripheral edge in a direction of the peripheral contour. The closure device is configured to close the molding tool to form a closed mold and, at a same time, to enclose the at least one ply of the semifinished fiber product and the compensating body. The closed mold includes a resin conduit for receiving resin.

    Buffer for storing liquid at a consumer pressure
    4.
    发明授权
    Buffer for storing liquid at a consumer pressure 有权

    公开(公告)号：US12203249B2

    公开(公告)日：2025-01-21

    申请号：US18182045

    申请日：2023-03-10

    Applicant: Airbus Operations GmbH

    Inventor： Hannes Muller

    IPC: E03B7/07 ,  B64D11/02 ,  G05D16/20

    Abstract: A buffer for storing liquid at a consumer pressure includes a storage volume for holding a liquid and a gas. The storage volume may be separated by a partition element into a liquid compartment for holding the liquid and a gas compartment for holding the gas. A pressurizer is configured for increasing the pressure of gas in the storage volume to an operating pressure when liquid is or has been drained from the storage volume. A ventilator reduces the pressure of gas in the storage volume back to the operating pressure when the storage volume is filled with liquid. A water supply system for an aircraft including the buffer and an aircraft including such a water supply system are disclosed.

    Method for removing a two-part connector in a workpiece arrangement
    5.
    发明授权
    Method for removing a two-part connector in a workpiece arrangement 有权

    公开(公告)号：US12202031B2

    公开(公告)日：2025-01-21

    申请号：US17555982

    申请日：2021-12-20

    Applicant: Airbus Operations GmbH

    Inventor： Jörn Skirke ,  Alexander Schäfer

    IPC: B21J15/50

    Abstract: A method for removing a two-part connector in a workpiece arrangement includes providing a workpiece arrangement having first and second surfaces and having a hole connecting the first surface to the second surface. A connector is fastened in the hole, which connector has a bolt extending along a central axis and a sleeve fastened on the bolt. The bolt has a head portion and a shank portion with retaining grooves. The sleeve is fastened to the bolt on the side of the second surface such that the inner surface thereof engages with the retaining grooves and prevents a relative movement of bolt and sleeve parallel to the central axis. The sleeve has an outside diameter which is greater than the diameter of the hole in the workpiece arrangement. The sleeve is cut and or the bolt, and the connector is removed from the hole.

    Single Flap Drive System For Decentralized Flap Architectures
    6.
    发明申请
    Single Flap Drive System For Decentralized Flap Architectures 有权

    公开(公告)号：US20250019067A1

    公开(公告)日：2025-01-16

    申请号：US18768690

    申请日：2024-07-10

    Applicant: Airbus Operations GmbH

    Inventor： Jörg Wyrembek ,  Christoph Naue

    IPC: B64C13/50 ,  B64D45/00

    Abstract: A drive assembly for driving a movable flow body of an aircraft, includes: a power drive unit, a flight control computer, a first flex shaft connecting the power drive unit to an inboard drive station, a second flex shaft connecting the inboard drive station to an outboard drive station, a first actuator connected to the inboard drive station and being couplable with the movable flow body, a second actuator connected to the outboard drive station and being couplable with the movable flow body. The second actuator includes a redundant position feedback sensor. The power drive unit includes a power-off brake, wherein the position feedback sensor is configured to send a position feedback signal to the flight control computer, and the flight control computer is configured to control the power drive unit.

    Modular line assembly for installation in an aircraft fuselage
    7.
    发明授权
    Modular line assembly for installation in an aircraft fuselage 有权

    公开(公告)号：US12195163B2

    公开(公告)日：2025-01-14

    申请号：US18526601

    申请日：2023-12-01

    Applicant: Airbus Operations GmbH

    Inventor： Frank Schneider ,  Frederik Albers ,  Sonja Pawellek

    IPC: F16L3/02 ,  B64C1/06 ,  B64F5/10 ,  F16L3/22

    Abstract: A line assembly for installation in an aircraft fuselage includes a first line section having a first diameter, a second line section having a second diameter, a set of first line brackets, and a set of second line brackets. The first line brackets include a first receiving space configured to hold the first line section and a first support portion for attaching the first line brackets to a fuselage structural part. The second line brackets include a second receiving space configured to hold the second line section and a second support portion for attaching the second line brackets to the first line section. The second line section includes a higher flexibility than the first line section. The second line section is attached to the first line section through a plurality of second line brackets arranged at a distance to and independent from the first line brackets.

    System and method for a manufacturing environment with robotic system mounts having one or more end effectors positioned sympathetic to the underlying manufactured item
    9.
    发明授权
    System and method for a manufacturing environment with robotic system mounts having one or more end effectors positioned sympathetic to the underlying manufactured item 有权

    公开(公告)号：US12187456B2

    公开(公告)日：2025-01-07

    申请号：US18194261

    申请日：2023-03-31

    Applicant: Airbus Operations GmbH

    Inventor： Chace Fadlovich ,  Michael Woogerd ,  Eric Pospisil ,  Eric Davis

    IPC: B23P19/04 ,  B64F5/10

    Abstract: A robotic manufacturing system includes a track extending along a length of a component of a partially manufactured item, wherein the component has a non-constant longitudinal shape, the track being supported independently of the partially manufactured item. The system includes a jointed member having an elongated arcuate shape, a mount longitudinally movable along the track and configured to receive the jointed member in an articulating manner, and an end effector movably mounted on the jointed member. The jointed member is movable along a portion of the component length in a radial position sympathetic to the non-constant component longitudinal shape. The jointed member is longitudinally movable relative to the mount along its elongated arcuate shape such that the jointed member will move in an arc spaced from and around an outer component surface. A portion of the end effector is movable along a length of the jointed member.

    GUIDING AN AIRCRAFT AT AN AIRPORT
    10.
    发明申请
    GUIDING AN AIRCRAFT AT AN AIRPORT 有权

    公开(公告)号：US20250006069A1

    公开(公告)日：2025-01-02

    申请号：US18740158

    申请日：2024-06-11

    Applicant: Airbus Operations GmbH

    Inventor： Andreas POPPE ,  Andreas FRIEDEL

    IPC: G08G5/06

    Abstract: A method and an aircraft which utilizes information from a control tower, position information of the aircraft, and a map of an airport for guiding the aircraft along taxiways. The method may comprise receiving data representing a road map of an airport, determining a position of the aircraft, receiving data representing an assigned taxiway for the aircraft, wherein the assigned taxiway is divided into at least two sections and comprises at least one holding point. Further, data representing a taxi clearance for at least one of the at least two sections are received, wherein the data representing the assigned taxiway for the aircraft and the data representing the taxi clearance for one of the at least two sections of the assigned taxiway are received from a control tower of the airport. Then, the assigned taxiway and the taxi clearance may be indicated.

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