Patents Assigned to AIRBUS OPERATIONS (Societe Per Actions Simplifiee)
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Patent number: 12097966Abstract: A fuel pipe assembly is disclosed including a connector having a socket and a lug arrangement extending from the socket, a pipe having a first end portion adapted to fit within the socket, and a retainer having first and second parts which together form a collar configured to retain a pipe. The retainer has an open condition in which a pipe is insertable, and a closed condition. The retainer also has a channel arranged, in the closed condition, to capture the lug arrangement.Type: GrantFiled: July 28, 2021Date of Patent: September 24, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: Eric Bonte, David Petit, Anthony Bryant, Daniel Peachey, Javier Ruiz-De-Pablo
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Patent number: 12091197Abstract: An aircraft fuel system monitoring apparatus is disclosed having a processor configured to receive first information indicative of one or more parameters relating to fuel present in an aircraft; receive second information relating to the configuration of a fuel system of the aircraft; receive third information indicative of an orientation of the aircraft; receive fourth information indicative of a state of one or more non-fuel-related systems of the aircraft; and generate a prediction of a quantity of fuel present in the aircraft based on the received first information, the received second information, and one or both of the received third information and the received fourth information.Type: GrantFiled: March 19, 2021Date of Patent: September 17, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: Vikram Singh Mangat, Paul James Pilkington
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Patent number: 12093390Abstract: A method of operating a media scanner to protect a target machine from malware on a removable storage device is disclosed. The target machine and the removable storage device each include a respective data line, and the media scanner comprises a data switch. Data is scanned on the removable storage device with malware detection software of the media scanner via a first data path, the first data path comprising the data line of the removable storage device connected to the data line of the media scanner by the data switch in a first switching state. After the data has been scanned with the malware detection software, the data switch is operated to switch from the first switching state to a second switching state, thereby disconnecting the data line of the removable storage device from the data line of the media scanner and connecting the data line of the removable storage device to the data line of the target machine.Type: GrantFiled: October 5, 2020Date of Patent: September 17, 2024Assignees: AIRBUS OPERATIONS LIMITED, AIRBUS DEFENCE AND SPACE GmbHInventors: Hugh Soulsby, Adam Wedgbury, Kevin Ian Jones, Khan-Ferdous Wahid
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Patent number: 12091154Abstract: A pin joint assembly is disclosed having a first lug and a second lug, a pin extending through the first and second lugs, a U-shaped bushing between the first lug and the pin, wherein the U-shaped bushing includes a first end flange and a second end flange that extend radially outwards and retain the U-shaped bushing to the first lug, and wherein the U-shaped bushing includes a bearing surface between the first and second end flanges on which the first lug is slidable.Type: GrantFiled: January 13, 2022Date of Patent: September 17, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventor: Paul Morrell
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Patent number: 12084170Abstract: An aircraft landing gear is disclosed including a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.Type: GrantFiled: March 6, 2023Date of Patent: September 10, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: Fraser Wilson, Jeremy Bedarrides, Vladimir Platagea
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Patent number: 12077287Abstract: An aircraft wing structure (100) including a spar (101) and a systems module (200) that is releasably secured to brackets (300) on a first side of the spar (101) and the second, opposite side of the spar is configured to define a wall of a fuel tank of an aircraft wing.Type: GrantFiled: January 31, 2023Date of Patent: September 3, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: William Tulloch, Javier Ruiz De Pablo, Paul Dean, James Bird
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Patent number: 12077290Abstract: An assembly with an aircraft fuel tank is disclosed having a captive nut with an internal thread, a secondary structure, and a fastener which secures the secondary structure to the fuel tank. The fastener has a shaft which passes through the secondary structure and has an external thread coupled to the internal thread of the captive nut. The fuel tank has a fuel tank element with a hole, and the captive nut has a sleeve which is located in the hole with an interference fit between an outer surface of the sleeve and an inner surface of the wall of the hole.Type: GrantFiled: February 18, 2022Date of Patent: September 3, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: William Tulloch, Pat Broomfield
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Patent number: 12078428Abstract: A heat exchanger including a sealed housing and a body positioned inside the housing, the body including a stack of least one first assembly of first and second plates pressed against each other, between which flows a first fluid, and at least one second assembly of third and fourth plates pressed against each other, between which flows a second fluid, the first and second assemblies being arranged so that they transfer heat between the first and second fluids. This configuration limits the risk of leaks and mixing of the two fluids.Type: GrantFiled: August 3, 2022Date of Patent: September 3, 2024Assignees: AIRBUS SAS, AIRBUS OPERATIONS SASInventors: Lionel Czapla, Jorge A. Carretero Benignos
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Patent number: 12077289Abstract: An aircraft assembly is disclosed including a longitudinal spar and an aerofoil cover integrally formed from a composite laminate material to form a spar-cover such that the composite material of the spar extends continuously into the cover through a fold region created between the spar and the cover. The spar and cover are separated by a recess at a longitudinal end of the fold region to define a spar end region and a cover end region, and a reinforcement element extends between the spar end region and the cover end region to couple the spar end region with the cover end region.Type: GrantFiled: May 28, 2020Date of Patent: September 3, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: Robert Charles Spreadbury, Richard Hipkiss, Janusz Walega
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Patent number: 12066046Abstract: A blind fastener is disclosed having a bolt part, a sleeve part, and a tubular insulating sheath. The bolt part is at least partially received within the sleeve part. A first end of the sheath is retained on the bolt part such that relative axial movement between the first end of the sheath and the bolt part is substantially prevented. The blind fastener is movable between: a pre-installation configuration in which the sleeve part has a first axial position relative to the bolt part and a predetermined section of the sheath is adjacent an outer surface of the sleeve part; and a post-installation configuration in which the sleeve part has a second, different axial position relative to the bolt part and the predetermined section of the sheath is adjacent an inner surface of the sleeve part.Type: GrantFiled: August 26, 2021Date of Patent: August 20, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: Matthew Cross, Andrew John Fay, Matthew Webster
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Patent number: 12065001Abstract: A tire inflation optimization apparatus configured to determine an optimum inflation pressure for a tire installed on an aircraft is disclosed. The apparatus includes a memory and a controller. The memory stores information relating tire gas properties to aircraft schedule parameters and a reference pressure for the tire. The controller is configured to receive future schedule information indicative of a future flight schedule for the aircraft and to determine an optimum inflation pressure for the tire based on the received future schedule information, the stored information relating tire gas properties to aircraft schedule parameters, and the stored reference pressure.Type: GrantFiled: December 15, 2021Date of Patent: August 20, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventor: Andrew Bill
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Patent number: 12065244Abstract: A wing (5) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement arranged (27) between two supports (23, 25) of the high lift device (15) having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position in which it prevents a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7) when the fixed wing (7) deforms in the spanwise direction. One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which transition from a first stable state to a second state when the load acting on the hold-down arrangement (27) exceeds an operational threshold.Type: GrantFiled: November 3, 2020Date of Patent: August 20, 2024Assignee: AIRBUS OPERATIONS GMBHInventor: Stefan Bensmann
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Patent number: 12066352Abstract: The present invention comprises a method for detecting a leak in a vacuum assembly comprising the steps: implementation of a first detection process to identify a leak area, involving the supply of a vacuum assembly which has a plurality of sensors for detecting a parameter, the determination of values of the parameter over time during the evacuation of a cavity of the vacuum assembly, the creation of a value-time curve for each sensor of the vacuum assembly from the values detected for the respective sensors by means of an evaluation unit, the comparison of the value-time curves created with one another and identification of differences depending on the comparison by means of the evaluation unit, and the identification of a leak area in the vacuum assembly depending on the differences determined in the value-time curves and the respective position of the sensor in relation to the vacuum assembly; and implementation of a second detection process following the first detection process to detect the leak wType: GrantFiled: September 3, 2018Date of Patent: August 20, 2024Assignees: DEUTSCHES ZENTRUM FUER LUFT—UND RAUMFAHRT, AIRBUS OPERATIONS GMBHInventors: Hakan Ucan, Anja Haschenburger, Clemens Heim, Jan Timo Hesse
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Patent number: 12065235Abstract: An aircraft wing including a leading edge slat and a fixed aerofoil portion. The leading edge slat is moveable between a stowed position and deployed position. In the deployed position a trailing edge of the leading edge slat includes a sealed portion and an unsealed portion. The sealed portion forms a seal with the fixed aerofoil portion and the unsealed portion provides an airflow gap between the leading edge flap and the fixed aerofoil portion. The invention provides substantially the same benefits as a sealed leading edge slat whilst improving stall control behavior in local zones around the unsealed portion.Type: GrantFiled: October 26, 2020Date of Patent: August 20, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: Ben Commis, Neil Lyons, Edmund Kay
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Patent number: 12065266Abstract: A method of testing an aircraft landing gear is disclosed including: a) generating a test signal with the first tachometer, wherein the first wheel is not rotating during the generation of the test signal; b) receiving the test signal via one of the tachometer output lines; c) issuing a braking command in response to the receipt of the test signal, wherein the braking command is issued via the braking command line which is associated with the one of the tachometer output lines; and d) monitoring a response of the first or second braking system to the braking command to test for a cross-connection between the first and second braking systems. The landing gear includes first and second wheels; a first braking system having a first tachometer mounted to the first wheel and configured to generate a first tachometer signal indicating rotation of the first wheel, and a first brake configured to brake the first wheel.Type: GrantFiled: July 14, 2021Date of Patent: August 20, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventor: Alexander Hayes
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Patent number: 12065239Abstract: An aircraft comprising a fuselage, first and second wings positioned on either side of the fuselage, wherein each wing includes an inner part connected to the fuselage and an outer part continuing the inner part, the end of each inner part connected to the fuselage having a height greater than half the height of the fuselage and extending over a length greater than or equal to half of a distance separating the nose and the tail of the fuselage.Type: GrantFiled: September 8, 2022Date of Patent: August 20, 2024Assignees: AIRBUS SAS, AIRBUS OPERATIONS SASInventors: Andrew Booth, Julien Laverne, Alistair Forbes
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Patent number: 12060959Abstract: A pipe support block for an aircraft fluid system is disclosed in which the pipe support block is arranged to support a pipe on a structural member, such as a bracket. The pipe support has a first part and a second part which together form a collar. The collar has a pipe receiving bore and is configured to support a fluid pipe on the structural member. First and second fastener holes extend through both the first part and the second part. The first and second fastener holes are each arranged to receive a fastener to fasten the first and second parts to each other and to the structural member.Type: GrantFiled: June 17, 2020Date of Patent: August 13, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventor: Mouayiad Shebli
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Patent number: 12060162Abstract: A spark containment cap for forming a sealed cavity around an end of a fastener protruding from a structure is disclosed having a cap body with an annular base terminating at a rim which surrounds an opening into an air cavity arranged to enclose the end of the fastener. An annular sealing volume extends around the rim arranged to receive an annular bead of a curable sealing material around the opening into the cavity to provide a seal between the cap body and the structure to seal a volume of gas within the cavity. An engaging feature is configured to engage with the end of the fastener to prevent rotation of the fastener relative to the cap when the end of the fastener is received by the cap. A fastening system, a joint, an aircraft and a method of securing a fastener and a spark containment cap to a structure are also disclosed.Type: GrantFiled: January 14, 2022Date of Patent: August 13, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventor: Richard Dobbin
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Patent number: 12060161Abstract: A spark containment cap forms a sealed cavity around an end of a fastener protruding from a structure. The cap has a cap body defining an air cavity enclosing the end of the fastener. The cap body includes an annular base (210) terminating at a base rim (211) surrounding an opening into the air cavity. An annular skirt of the cap provides an annular sealing volume extending around the base rim to receive an annular bead of a curable sealing material around the opening into the cavity to provide a seal between the cap body and the structure to seal a volume of gas within the cavity. The cap body includes a cap upper to receive the end of the fastener. The cap upper (220) is positionable so that an axis of the cap upper is offset from an axis of the annular skirt (230).Type: GrantFiled: May 28, 2020Date of Patent: August 13, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventor: Richard Dobbin
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Patent number: 12060147Abstract: An aircraft system for an aircraft, the aircraft system including a controller configured, during a take-off procedure, to receive a first signal indicative of a climb rate of the aircraft and, when the controller determines, on the basis of the first signal, that the climb rate of the aircraft is positive, cause a retraction alert to be issued to a flight crew of the aircraft, the retraction alert indicative that a landing gear of the aircraft is retractable.Type: GrantFiled: April 22, 2022Date of Patent: August 13, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventor: Fernando Izquierdo Civera