Patents Assigned to Airbus Operations Limited
  • Aircraft fuel tank aperture sealing
    Patent number: 11420722
    Abstract: A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.
    Type: Grant
    Filed: November 25, 2019
    Date of Patent: August 23, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Paul Edwards, Antony Peacock, Timothy Sanderson
  • Aircraft wing and wing tip device
    Patent number: 11420723
    Abstract: An aircraft wing (1) including a fixed wing (3) and a wing tip device (4) at the tip of the fixed wing (3), the wing tip device (4) being rotatable relative to the fixed wing (3) between a flight configuration (4a) for use during flight, and a ground configuration (4b) for use during ground-based operations, in which ground configuration the wing tip device (4) is rotated relative to the fixed wing (3) such that the span of the wing (1) is reduced. The aircraft wing (1) has a gear assembly (31) that couples the wing tip device (4) to an actuator (30) such that the actuator (30) drives the rotation of the wing tip device (4) between the flight and ground configurations, the gear assembly (31) comprising a worm drive (32).
    Type: Grant
    Filed: May 24, 2019
    Date of Patent: August 23, 2022
    Assignee: Airbus Operations Limited
    Inventor: Benjamin Bishop
  • Aircraft assembly with a hot-air exhaust outlet and cooperating vortex generator, and method controlling same
    Patent number: 11414180
    Abstract: An aircraft assembly with a hot air exhaust outlet. The aircraft assembly has an assembly surface over which a hot-air exhaust flow from the hot-air exhaust outlet is exhausted. The aircraft assembly also has a vortex generator with a flow surface. The flow surface lies in an air flow over the vortex generator. The flow surface is arranged to interrupt the hot-air exhaust flow and generates a flow vortex to cool the air flow over the assembly surface.
    Type: Grant
    Filed: October 24, 2019
    Date of Patent: August 16, 2022
    Assignee: Airbus Operations Limited
    Inventors: Denys Custance, Daren Healy
  • Duct stringer
    Patent number: 11407489
    Abstract: A duct stringer is disclosed and forms at least part of a duct with a closed cross-section along which a fluid flows. An aperture is formed through a duct wall of the duct stringer and communicates with the duct. An insert is adhered in the duct stringer and is configured to engage with a fastening member to mount a fluid transporting conduit, such as a pipe, over the aperture.
    Type: Grant
    Filed: June 25, 2019
    Date of Patent: August 9, 2022
    Assignee: Airbus Operations Limited
    Inventor: Paul Douglas
  • Roller gear for a drive system
    Patent number: 11407501
    Abstract: A roller gear for use in a roller gear and sprocket configuration of a drive system is disclosed, particularly for use in a landing gear drive system of an aircraft. Alternative embodiments and, in particular, means for permitting removal and replacement of rollers and roller mounting pins in the roller gear are disclosed.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: August 9, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Arnaud Didey, Richard Billyeald, James Setter, Ian Dickason
  • Method of monitoring the pressure of an aircraft tire
    Patent number: 11407259
    Abstract: A method of monitoring the pressure of a tire of an aircraft, the method including: taking two or more pressure readings from the tire at different times; calculating an estimated deflation rate based on the pressure readings; and calculating a time for the tire to deflate to a reference pressure level based on the estimated deflation rate. Two or more temperature readings are each associated with one of the pressure readings, and the estimated deflation rate is calculated by normalising each pressure reading based on its associated temperature reading and a common reference temperature to obtain a temperature-normalised pressure reading, and calculating the estimated deflation rate based on the temperature-normalised pressure readings. The estimated deflation rate is compared with a threshold, and a warning provided if the estimated deflation rate exceeds the threshold.
    Type: Grant
    Filed: December 3, 2020
    Date of Patent: August 9, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: Andrew Bill
  • Aircraft cable routing system and method of installation thereof
    Patent number: 11402036
    Abstract: A cable routing system is disclosed including a routing fixture and an exit fitting. The routing fixture defines a channel for a cable. The channel is engaged by the exit fitting and a cable in the channels exits through an exit channel defined by the exit fitting. The exit channel is directed away from the channel in the routing fixture. The resulting assembly allows low profile cable runs that can conform to a structural surface and in which cables can be broken out easily, without a requirement to cut the cable. A clamp may be provided to further secure the exit fitting to the routing fixture. A method of installation involves installing a cable into a routing channel before installing the exit fitting. The cable routing system can be used in an aircraft, including space constrained areas such as within an aircraft wing.
    Type: Grant
    Filed: June 25, 2019
    Date of Patent: August 2, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Anthony Bryant, Paul O'Shaughnessy, Christopher Bills
  • Aircraft assembly
    Patent number: 11401025
    Abstract: A wing leading edge assembly is disclosed including a leading edge panel and a cover panel located over the structural component. The cover panel has a thermoplastic layer with an inner surface. A thermoplastic fastening member extends through the structural component and is welded to the inner surface so that the structural component is fastened between the inner surface and the fastening member.
    Type: Grant
    Filed: October 8, 2019
    Date of Patent: August 2, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Rodney Evans, David Andrew Phipps
  • Fastener locking
    Patent number: 11396901
    Abstract: A locking apparatus for locking the rotational position of a fastener component which is rotatable about an axis relative to a structure. The locking apparatus includes a collar and a rigid arm. The collar is configured to engage with the fastener component such that relative rotation of the collar and the fastener component is substantially prevented. The arm has a first end configured to engage with the collar such that rotation of the collar relative to the first end is substantially prevented, and a second end configured to engage with the structure such that rotation of the arm relative to the structure is substantially prevented. The collar has an inner surface having a first finite order of rotational symmetry about the axis, and an outer surface having a second, larger, finite order of rotational symmetry about the axis.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: July 26, 2022
    Assignee: Airbus Operations Limited
    Inventors: William Tulloch, Danny Payne
  • Actuator for an aircraft component
    Patent number: 11377202
    Abstract: A starboard wing of an aircraft includes various movable aerodynamic surfaces, such as a spoiler, slat, aileron, flap or the like. An actuator is provided for moving each such surface. The location and mounting of the actuator of the starboard wing is symmetrical about the centreline of the aircraft to that of the actuator of the port wing. The location of the piston, arm or other mechanical output of the actuator is at a centre portion of the actuator (i.e. at or near the midline of the actuator. The input port(s) for power is/are also at the centre portion. The actuator for the starboard wing may thus be substantially identical to the actuator for the port wing.
    Type: Grant
    Filed: September 16, 2019
    Date of Patent: July 5, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: Daren Healy
  • Aircraft landing gear
    Patent number: 11377205
    Abstract: A landing gear is disclosed having a main strut being connected to a first attachment point located on the aircraft. The landing gear includes an inboard sidestay and outboard sidestays. The inboard sidestay has a first end connected to the main strut for movement along the main strut and is connected at a second end to a second attachment point located on the aircraft. The outboard sidestay has a first end connected to the main strut for movement along the main strut and is connected at a second end to a third attachment point located on the aircraft. When the landing gear is in a deployed configuration, the connection between the first end of each of the inboard and outboard sidestays and the main strut allows for movement of each first end along at least a portion of the length of the main strut.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: July 5, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: John Woolcock, Nicholas Hancock
  • Wing assembly tension joint and method of assembly
    Patent number: 11370525
    Abstract: A wing assembly is disclosed. The wing assembly includes a main structure having a first contact face and a first recess arranged to receive a portion of a tension bolt; and a modular edge having a second contact face and a second recess arranged to receive a portion of the tension bolt. The modular edge is pivotally mounted on the main structure for rotation between an installation position and an operational position in which the modular edge is aligned with the main structure to form at least part of an edge of the wing assembly. The wing assembly is arranged such that, when the modular edge is in the operational position, tension in a tension bolt received in the first and second recesses acts to press the first and second contact faces together, thereby forming a tension joint that resists pivoting of the modular edge relative to the main structure.
    Type: Grant
    Filed: September 17, 2019
    Date of Patent: June 28, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: Benjamin Bishop
  • Avionics networks
    Patent number: 11360446
    Abstract: An aircraft control system including transducers connected by interface units to an avionics network, such as an AFDX network. Each transducer is directly connected to an interface unit local to the transducer. Each interface unit is a configurable unit and has a signal processing module converting data to a format suitable for transmission over the network. Each interface unit may be configurable, via software commands, to operate in an application session mode, a data-loading mode, or a maintenance mode. Each interface unit may be directly associated with one of the software applications of the aircraft control system. The network may include a lower bandwidth part where data communication is conducted over sampling ports only. Interface units may be configured or installed using a plug and play method.
    Type: Grant
    Filed: June 4, 2019
    Date of Patent: June 14, 2022
    Assignees: Airbus Operations Limited, Airbus Operations SAS
    Inventors: Anand Pavaskar, Romain Desautard, Kayvon Barad, Sylvain Sauvant, Juan Lopez, Emilie Claudel
  • Apparatus, aircraft and method for moving a wing tip device away from a load-alleviating configuration
    Patent number: 11358708
    Abstract: An aircraft (1) including a fixed wing (7) and a wing tip device (9) moveably mounted thereon. The wing tip device (9) is movable from a load-alleviating configuration to a flight configuration. The wing tip device includes an airflow channel (88) extending between respective apertures (83, 84) on the upper surface and lower surface of the wing tip device. The channel (88) is configurable between an open state in which air can flow through the channel and a closed state in which the airflow through the channel (88), via the apertures (83, 84), is blocked. The channel (88) is configured such that when the wing tip device (9) is in the load-alleviating configuration and the channel (88) is in the open state, the aerodynamic loading on the wing tip device in flight urges the wing tip device towards the flight configuration.
    Type: Grant
    Filed: October 29, 2019
    Date of Patent: June 14, 2022
    Assignee: Airbus Operations Limited
    Inventor: Ciaran O'Rourke
  • Wing tip device attachment apparatus and method
    Patent number: 11352127
    Abstract: An aircraft wing subassembly including: a wing skin defining a first outer surface, and, a structural reinforcement member, the structural reinforcement member defining a second outer surface, wherein the structural reinforcement member is arranged within the wing such that the first outer surface and the second outer surface form part of an outer wing surface.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: June 7, 2022
    Assignee: Airbus Operations Limited
    Inventors: Julien Chaussee, Camille Paumes, Norman Wijker, Stuart Alexander
  • Wing tip device
    Patent number: 11345461
    Abstract: A wing tip device for attaching to an aircraft wing comprising a first wing tip device element having a root end and a tip end; a second wing tip device element coupled to the tip end of the first wing tip device element; wherein the second wing tip device element has an inboard portion extending inboard from the tip end of the first wing tip device element and/or an outboard portion extending outboard from the tip end of the first wing tip device element, when viewed in the wing planform direction.
    Type: Grant
    Filed: September 5, 2019
    Date of Patent: May 31, 2022
    Assignee: Airbus Operations Limited
    Inventor: Ben Commis
  • Controller for an aircraft braking system
    Patent number: 11345466
    Abstract: A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.
    Type: Grant
    Filed: February 14, 2019
    Date of Patent: May 31, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Nicholas Crane, Adrian Harrison
  • Seal
    Patent number: 11346446
    Abstract: A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.
    Type: Grant
    Filed: September 30, 2019
    Date of Patent: May 31, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: Paul Blades
  • Landing gear controller
    Patent number: 11345464
    Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.
    Type: Grant
    Filed: June 15, 2018
    Date of Patent: May 31, 2022
    Assignee: Airbus Operations Limited
    Inventor: David Marles
  • Hollow fastener for coupling aerospace structures
    Patent number: 11332231
    Abstract: A fastener for holding together two or more structures. The fastener includes a first bush and a second bush. The first bush includes a hollow shaft having a first end and a second end opposite to the first end. The first end of the first bush has a first radially-extending protrusion. The second bush includes a hollow shaft having a first end and a second end opposite to the first end. The first end of the second bush has a second radially-extending protrusion. The second end of the second bush is configured to connect to the second end of the first bush so as to resist separation of the first and second bushes and so as to define an axial hole through the fastener defined by the shaft of the first bush and the shaft of the second bush.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: May 17, 2022
    Assignee: Airbus Operations Limited
    Inventors: William Tulloch, Pat Broomfield