Patents Assigned to Airbus Operation GmbH
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Patent number: 12371147Abstract: A fairing attachment system for a wing of an aircraft includes a high lift support structure configured to movably support a high-lift airfoil element of a wing of an aircraft relative to the wing. The system includes a fairing device extending in a lengthwise direction, configured to provide an aerodynamic housing of the high lift support structure when attached to a surface of the wing, and an adjustable attachment element configured to attach the fairing device to the high lift support structure. The adjustable attachment element is longitudinally extending and adjustable in length to compensate for tolerances of the high lift support structure relative to the wing during assembly. An aircraft wing includes the fairing attachment system. The fairing attachment system is used in a method for mounting a fairing device to a wing of an aircraft.Type: GrantFiled: April 26, 2023Date of Patent: July 29, 2025Assignee: Airbus Operations GmbHInventor: Markus Gibbert
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Patent number: 12371146Abstract: A wing for an aircraft includes a leading edge, a trailing edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create a wing box with the upper skin and the lower skin, and at least one droop nose at the leading edge, wherein the at least one droop nose is coupled with a forward end of a hinge arm that extends in a chordwise direction, and wherein a rearward end of the hinge arm is swivably supported directly at or in the wing box.Type: GrantFiled: July 5, 2023Date of Patent: July 29, 2025Assignee: Airbus Operations GmbHInventor: Stefan Bensmann
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Patent number: 12371150Abstract: A slat arrangement for a wing of an aircraft. The arrangement has a movable leading-edge slat and a connection section. The leading-edge slat includes a slat leading edge and a slat trailing edge. The connection section includes a receiving opening for receiving the slat trailing edge. The connection section includes an overhang having a free end. The slat trailing edge is configured to be translated under the overhang. A trailing region of the slat is configured to be elastically deformed by the overhang when the slat trailing edge is moved into the receiving opening.Type: GrantFiled: November 3, 2020Date of Patent: July 29, 2025Assignee: Airbus Operations GmbHInventor: Christian Heck
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Patent number: 12371164Abstract: A system for installing a self-supporting truss structure having interconnected truss elements on an aircraft fuselage. The truss structure has radially outer closed truss nodes and radially inner releasable connecting nodes. The installation system has a carrying device, movable on a fuselage floor and with an upper receptacle, a stand for temporarily holding truss elements in predetermined relative positions, and a movement device, on the upper receptacle, and holding the stand in a settable position relative to the support surface. The stand is further away from the support in installation positions than in a transport position. The installation system is configured, with the stand in the transport position, to move the carrying device into a predetermined internal fuselage position and to lock it there, to move the stand into a suitable installation position via the movement device, and to lock the at least one lockable connecting node via a drive.Type: GrantFiled: November 3, 2023Date of Patent: July 29, 2025Assignee: Airbus Operations GmbHInventors: Hermann Benthien, Andreas Poppe
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Patent number: 12366317Abstract: A fluid transport device including a first line connector, second line connector and inner line component that fluidly connects the first line connector to the second line connector via respective first and second coupling ends. In a mounted state, an outer line component of the device is attached to the first line connector and to the second line connector, so the outer line component covers the first and second coupling ends. In a demounted state, the outer line component is detached from the first and second line connector, wherein the outer line component is movable relative to the inner line component to uncover the first coupling end or the second coupling end. A method for assembling and disassembling a fluid transport device is also disclosed.Type: GrantFiled: August 17, 2023Date of Patent: July 22, 2025Assignee: Airbus Operations GmbHInventors: Ralf Becks, Tran Quang Tue Nguyen
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Patent number: 12351343Abstract: The present disclosure relates to a method for servicing an aircraft by a ground service unit. The method comprises reading a wireless parameter signal from a transponder at the aircraft, decoding the wireless parameter signal to derive at least one aircraft parameter of a water supply system and/or a waste system of the aircraft, moving a servicing equipment interface to a service panel of the aircraft, connecting the servicing equipment interface to a coupling at the service panel, servicing the aircraft via the servicing equipment interface corresponding to the at least one aircraft parameter, and writing a service parameter into the transponder at the aircraft.Type: GrantFiled: October 25, 2023Date of Patent: July 8, 2025Assignee: Airbus Operations GmbHInventors: Frank Schneider, Hannes Müller, Michael Rempe, Tim Lübbert, Frederik Albers
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Patent number: 12355184Abstract: An electrical connector for connecting electrical conductors in an aircraft includes a pin having a first contact surface and a socket to receive the pin. The socket has a second contact surface contacting a first contact surface of the pin when the pin is in the socket. A securing part is positioned to apply a contact or clamping force pressing the contact surfaces against each other. The securing part includes a shape memory alloy to exist in a martensite an austenite phase depending on temperature of the securing part, wherein the securing part assumes a first pre-set shape when the temperature is below a first temperature threshold, and a second pre-set shape when the temperature is above a second temperature threshold higher than the first temperature threshold, wherein the contact or clamping force applied by the securing part in the second pre-set shape is greater than in the first pre-set shape.Type: GrantFiled: November 10, 2022Date of Patent: July 8, 2025Assignees: Airbus (S.A.S.), Airbus Operations GmbHInventors: Frédéric Forget, Mihai Ioan Zecheru
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Patent number: 12351319Abstract: A heated leading-edge structure for an aircraft includes a leading-edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, a rear panel arranged at least partially arranged at a distance to the inner surface, a closed chamber inside the leading-edge structure, a heating device attached inside the chamber, and an air conveying device in fluid communication with the heating device. The air conveying device is configured to convey air from inside the chamber through the heating device to be heated and returned to the chamber, such that a circulating flow of heated air is created inside the chamber.Type: GrantFiled: November 17, 2023Date of Patent: July 8, 2025Assignee: Airbus Operations GmbHInventors: Bernhard Schlipf, Florian Lorenz
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Patent number: 12344790Abstract: A protective lining which includes a self-curing potting sealant compound. The lining can be used for an aircraft part, such as a tank wall liner which can be manufactured in-situ by casting the sealant into a prepared mold that is formed at least at the bottom side by the part to be protected by the tank wall liner. Specifically, for fuel tanks, the bottom portion forms the bottom side of the mold, whereas the ribs and stringers form a circumferential wall of the mold that prevents flowing of the potting sealant compound into neighboring molds.Type: GrantFiled: March 17, 2023Date of Patent: July 1, 2025Assignee: Airbus Operations GmbHInventors: Jose Martins, Heinz Burock, Ralph-Josef Hecktor
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Patent number: 12344377Abstract: A flap system for an aircraft comprises a wing structure, a trailing-edge and an attachment unit for movably coupling the trailing-edge movable to the wing structure. The attachment unit comprises an attachment mechanism and a cover element which at least partly encloses the attachment mechanism. The attachment unit comprises a drive element which is configured to move the cover element along an aerodynamic outer surface of a skin section of the wing structure between a first position and a second position, wherein the movement of the cover element along the aerodynamic outer surface is defined by a translational movement of the cover element relative to the skin section.Type: GrantFiled: January 29, 2024Date of Patent: July 1, 2025Assignee: Airbus Operations GmbHInventors: Florian Lorenz, Bernhard Schlipf
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Patent number: 12337981Abstract: A variable fairing for covering a hydrogen duct system installation on the outside of an aircraft part, wherein the fairing comprises at least one fairing body to be mounted on the aircraft part, an air inlet and an air outlet and at least one movable closure mechanism configured to open and close a top portion of the fairing.Type: GrantFiled: June 21, 2023Date of Patent: June 24, 2025Assignee: Airbus Operations GmbHInventor: Carsten Puschmann
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Publication number: 20250198329Abstract: An engine protection cover device for airtight sealing an engine of an aircraft or spacecraft includes an air intake cover being inflatable to correspond to the internal dimension of the air intake for airtight sealing the same, wherein the air intake cover includes an airtight sealable access opening for attaching or passing through an air dryer for drying the air inside the engine. An aircraft or spacecraft is disclosed with such an engine protection cover device.Type: ApplicationFiled: December 18, 2024Publication date: June 19, 2025Applicant: Airbus Operations GmbHInventors: Burkhard Brand, Andreas Noeske, Stefan Binz, Sonntag Nico
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Publication number: 20250201879Abstract: A method for a soft-start strategy of a fuel cell includes: providing a fuel cell, wherein the fuel cell is connected to load, providing a capacitor, wherein the capacitor is connected in between the fuel cell and the load, wherein the fuel cell includes an anode and a cathode and the anode and the cathode are in a preconditioned state, the method further including filling the cathode with a mass rate derived from a proportion of an input gas and a used gas, and a predefined current, such that the predefined current does not exceed a maximum current during a precharge of the capacitor.Type: ApplicationFiled: December 9, 2024Publication date: June 19, 2025Applicants: Airbus Operations GmbH, Airbus Operations SASInventors: Leonard Liphardt, Jean-François Allias, Lucas Filliatre
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Patent number: 12330785Abstract: An aircraft wing including a flap system mounted at a leading or trailing edge of the wing and includes at least two movable flap devices spaced apart in a spanwise direction Y from each other, each movable flap device supported by at least one support station and driven about a hinge axis by at least one drive system. The flap system includes a synchronizing torque element connected to the movable flap devices, wherein the synchronizing torque element is configured to transmit a torque between the movable flap devices to actuate a rotational movement of the movable flap devices, and wherein the synchronizing torque element is positioned between the movable flap devices and around an adjacent system or structural component that is also positioned between the movable flap devices.Type: GrantFiled: December 27, 2023Date of Patent: June 17, 2025Assignee: Airbus Operations GmbHInventors: Bernhard Schlipf, Christoph Winkelmann
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Patent number: 12330786Abstract: A fastening system to attach a fixture to a monument installed in a passenger cabin including a wall portion of the monument having at least one first fastening element; and a frame having at least one second fastening element and which is configured to cover the fixture, at least in part, in a fastened state. The first and second fastening elements are configured to engage with one another and be movable relative to one another in a pre-assembled state, and to fix one another in the fastened state. The fastened state can be produced in that, in the pre-assembled state, the frame is moved relative to the wall portion in a fastening direction extending at least substantially parallel to a main extension plane of the wall portion. A method for attaching a fixture to a monument provided for installation in a passenger cabin via a fastening system is provided.Type: GrantFiled: March 31, 2021Date of Patent: June 17, 2025Assignee: Airbus Operations GmbHInventor: Henning Joest
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Patent number: 12325505Abstract: An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.Type: GrantFiled: March 28, 2023Date of Patent: June 10, 2025Assignees: AIRBUS SAS, Airbus Operations SAS, AIRBUS OPERATIONS LTD, Airbus Operations SL, Airbus Operations GmbHInventors: Elisa Alvarez López-Herrero, Matthias Wolff, Alexander Broer, Rainer Tegtmeyer, Michael Wießmeier, Till Marquardt, André Anger, Anna-Katrin Wengorra, Marco Dias Figueiredo, Jose Luis Martinez Munoz, Alberto Gallegos Elvira, Kaya Sahin, Guillaume Gallant, Kasidit Leoviriyakit, Philip Wright
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Patent number: 12319414Abstract: A seat rail system for an interior space of a vehicle includes a seat rail having a plurality of attachment sockets arranged in a row along a longitudinal extension of the seat rail. Each attachment socket has an at least partly spheroid concave bearing surface. Two coupling openings are embedded in each concave bearing surface; an attachment stud having an at least partly spheroid or cylindroid convex bearing surface with a curvature corresponding to a curvature of the concave bearing surface of the attachment sockets. A coupling pin is arranged on or in the convex bearing surface and configured to enter one of the attachment openings to couple the attachment stud to the seat rail. A locking pin is configured to enter the respective other attachment opening through a through hole in the attachment stud and thereby lock the attachment stud to the seat rail.Type: GrantFiled: July 21, 2022Date of Patent: June 3, 2025Assignee: Airbus Operations GmbHInventors: Andreas Poppe, Hermann Benthien
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Patent number: 12319415Abstract: A honeycomb structure including a first external side, a second external side, and an anti-friction agent buffer for receiving an anti-friction agent. An opening to an anti-friction agent inlet and an opening to an air outlet are present on the first external side. This honeycomb structure may be useful in an aircraft as part of a belly-landing system for the aircraft.Type: GrantFiled: June 29, 2023Date of Patent: June 3, 2025Assignee: Airbus Operations GmbHInventors: Markus Kerber, Marc Wesseloh
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Patent number: 12319438Abstract: A dynamically controlled cargo loading system for an aircraft includes electrical cargo conveying devices for conveying cargo items on a cargo loading deck; speed sensors, which are configured to capture current conveying speeds of the cargo conveying devices and/or the conveyed cargo items; electrical measuring devices, which are configured to capture current electrical parameters of the cargo conveying devices; and a control device which is configured to control the cargo conveying devices depending on the captured current conveying speeds and/or the recoded current electrical parameters such that at least one of the following variables is optimized: the electrical power consumption of the cargo conveying devices, the mechanical wear of the cargo conveying devices, the mechanical load action on the cargo items, the conveying time of the cargo items and the noise generation during the conveying of the cargo items.Type: GrantFiled: August 24, 2022Date of Patent: June 3, 2025Assignee: Airbus Operations GmbHInventors: Sven Scherenberger, Dennis Fischer, Oliver Nuessen
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Patent number: 12319408Abstract: A fairing arrangement for an aircraft high-lift mechanism, the high-lift mechanism including a flap arranged at an aircraft wing trailing edge and a mounting and guiding mechanism for the flap. The fairing arrangement includes a flap side fairing unit and a wing side fairing unit. The flap side fairing unit includes a flap side fairing covering an aft part of the mounting and guiding mechanism and a flap side fairing mount mounting the flap side fairing to the flap. The wing side fairing unit includes a wing side fairing covering a forward part of the mounting and guiding mechanism and a wing side fairing mount mounting the wing side fairing to the wing. The wing side fairing mount is configured to connect the wing side fairing movably to the wing such that the wing side fairing is rotatable around an axis directed at least partially in a vertical direction.Type: GrantFiled: December 18, 2023Date of Patent: June 3, 2025Assignee: Airbus Operations GmbHInventors: Wolfgang Ehrhard, Luc Andreani, Florian Lorenz