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公开(公告)号：US12054292B2
公开(公告)日：2024-08-06
申请号：US17861371
申请日：2022-07-11
Applicant: Airbus Operations S.L.
Inventor： Cesar Martin Blazquez , Carlos Flores Hernandez
Abstract: A method for the assembly of frames in an aircraft shell, wherein the aircraft shell comprises a skin and a plurality of stringers co-cured with the skin, wherein the skin has a plurality of reference marks. Identifying the reference marks on the skin using a first robot with artificial vision, establishing a local reference for the positioning of each frame based on a reference mark, grabbing a frame using the first robot, establishing a relative position between the first robot and the frame based on the reference mark, positioning the frame on an inner side of the aircraft shell using the first robot, and with a second robot, drilling holes through the frame and skin, and attaching the frame to the skin with fasteners.
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公开(公告)号：US20240199231A1
公开(公告)日：2024-06-20
申请号：US18530281
申请日：2023-12-06
Applicant: Airbus Operations SAS , Airbus Operations S.L.
Inventor： Günther DRESSLER , Asuncion BUTRAGUENO-MARTINEZ , Rodolphe TROUVE , Dirk FELTIN
CPC classification number: B64F5/10 , B64C1/1484 , B64C2001/0072
Abstract: A method of manufacturing an aircraft window frame, the frame having a first surface that has at least first and second faces extending all around the frame and connected by a curved junction zone, the frame being made of a composite material that includes fibers embedded in a resin matrix. The method includes steps of: assembling fiber layers and at least one reinforcement situated at the level of the junction zone and having first and second peripheral edges; consolidating or polymerizing of the assembly; and removing the frame from the mold. During the step of assembling, a barrier layer is positioned between the reinforcement and the first surface to cover the reinforcement and to form a barrier limiting propagation of resin in the direction of the first surface. A window frame obtained by using that method is provided as well as an aircraft including the frame.
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公开(公告)号：US11772800B2
公开(公告)日：2023-10-03
申请号：US17188115
申请日：2021-03-01
Applicant: Airbus Operations S.L.
Inventor： Alberto Martinez Sancho
CPC classification number: B64D13/06 , B64D2013/0611 , B64D2013/0651
Abstract: An operating method of a vehicle cabin air supply device comprising taking fresh air from outside the cabin, diverting the fresh air to an air exhaust during an exhaust duration period after starting the air supply device, before injecting the fresh air into the cabin, such that the fresh air injected in the cabin after the exhaust duration period minimizes unpleasant odors in the cabin. A vehicle cabin air supply device and an aircraft comprising such a device is also provided.
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174.发明授权公开(公告)号：US11691749B2
公开(公告)日：2023-07-04
申请号：US17175003
申请日：2021-02-12
Applicant: Airbus Operations S.L.
Inventor： Alberto Martinez Sancho
CPC classification number: B64D31/14 , B64F5/40 , B64D2041/002 , F02D2001/0095
Abstract: A method to modify an aircraft including: disconnecting a first engine control device from command cables and transmission cables, wherein the first engine control device is in a fuselage section forward of a pressure bulkhead; replacing the engine control device with a jumper connector positioned in the fuselage section, wherein the jumper connector electrically connects the command cables to the transmission cables; installing a second engine control device in the fuselage aft of the pressure bulkhead, wherein the second engine control device is in an engine compartment of the fuselage; connecting the second engine control device to transmission cables at a location at or near the pressure bulkhead; connecting sensor cabling directly to the second engine control device, and connecting the engine control device directly to the engine.
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175.发明授权公开(公告)号：US11649034B2
公开(公告)日：2023-05-16
申请号：US16744342
申请日：2020-01-16
Applicant: Airbus Operations, S.L.
Inventor： Robert Kobierecki , Miguel Ángel Mendez Rodríguez , Juan Antonio Sánchez Ruiz , Alberto Balsa-Gonzalez
CPC classification number: B64C3/26 , B29C65/60 , B64C9/00 , B29L2031/3076
Abstract: A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.
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Patent Agency Ranking
公开(公告)号：US20230017954A1
公开(公告)日：2023-01-19
申请号：US17866050
申请日：2022-07-15
Applicant: Airbus Operations SAS , Airbus SAS , Airbus Operations S.L.
Inventor： Jean-François ALLIAS , Franck ALVAREZ , Pascal POME , Nicolas JOLIVET , Rémi AMARGIER , Salvatore DEMELAS , Norberto SIMIONATO NETO , Benedikt BAMMER , Damien MARIOTTO
Abstract: A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.
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公开(公告)号：US11542033B2
公开(公告)日：2023-01-03
申请号：US16842173
申请日：2020-04-07
Applicant: Airbus Operations S.L.
Abstract: A dynamic runway illumination system, including a light source having an addressable light beam direction, and a control unit configured to receive aircraft attitude information and the orientation of the runway selected for takeoff or landing, obtain horizontal and vertical axes, the horizontal axis being collinear with the takeoff or landing longitudinal direction, determine the actual and the reference aircraft trajectories, obtain the actual and the reference vertical approach angles, and the actual horizontal approach angle, and actuate onto the light source to perform an angular movement in the light beam direction of an absolute value of the actual vertical approach angle minus the absolute value of the reference vertical approach angle about the vertical axis, and an angular movement of an absolute value of the actual horizontal approach angle about the horizontal axis, to vertically and horizontally align the beam of the light source towards the runway direction.
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公开(公告)号：US20220355943A1
公开(公告)日：2022-11-10
申请号：US17737134
申请日：2022-05-05
Applicant: Airbus SAS , Airbus Operations SAS , Airbus Operations GmbH , Airbus Operations S.L.
Inventor： Jorge CARRETERO BENIGNOS , Benedikt BAMMER , Olivier VERSEUX , Maria Del Sagrario JUANAS FERNANDEZ , Jorge MOLANO REMBIASZ , Thomas SCHERER , Alexander SOLNTSEV
Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.
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公开(公告)号：US11426953B2
公开(公告)日：2022-08-30
申请号：US16033300
申请日：2018-07-12
Applicant: AIRBUS DEFENCE AND SPACE GMBH , AIRBUS OPERATIONS, S.L.
Inventor： Katharina Schlegel , Alois Friedberger , David Lopez-Bravo
IPC: B29C70/38 , B29C70/34 , B29C70/50 , B29C37/00 , B29K105/08
Abstract: A fiber composite laying device for producing a fiber composite scrim for forming a fiber composite component has a laying head which is designed or configured to continuously supply a reinforcement fiber band, a compaction roller which is designed or configured to receive the supplied reinforcement fiber band, lay the band on a laying surface and press the band onto the laying surface at an average compaction pressure, and pressure sensors which are arranged on the compaction roller and are designed or configured to detect a local compaction pressure on the laid reinforcement fiber band.
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公开(公告)号：US11264553B2
公开(公告)日：2022-03-01
申请号：US16421844
申请日：2019-05-24
Applicant: Airbus Operations S.L.
Inventor： Brice Lenoir , Panagiotis Mourtis Ioannou
Abstract: An overheat detection system and insulation muff comprising an overheat detection system. The overheat detection system comprises a thermometer, a thermal harvesting module comprising at least one passive radiator, the thermal harvesting module being able to generate electrical energy from the thermal difference between two elements, and a digital module, comprising a power management system, a data treatment system and a wireless transmission system, wherein the electrical energy generated by the thermal harvesting module powers the thermometer and the digital module.
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