Patents Assigned to Airbus Operations
  • Patent number: 10974817
    Abstract: A vertical tail unit (7) for flow control including: an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25), and surrounds an interior space (29), and wherein the outer skin (13) includes a porous section (31) in the area of the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13), wherein the air inlet (17) is fluidly connected to the pressure chamber (15), wherein the air outlet (19) is fluidly connected to the pressure chamber (15). The vertical tail unit (7) has reduced drag and an increased efficiency because the air inlet (17) is formed as an opening (35) in the outer skin (13) at the leading edge (23).
    Type: Grant
    Filed: October 8, 2018
    Date of Patent: April 13, 2021
    Assignee: Airbus Operations GmbH
    Inventor: Thomas Heuer
  • Patent number: 10975769
    Abstract: An oil heating system in a turbine engine such as an aircraft turbojet or turboprop main engines, or in an aircraft auxiliary power unit (APU). The turbine oil heating system includes a turbine engine oil circuit for conducting lubricating oil to the turbine engine, an electric starter generator oil circuit for conducting cooling oil from the electric starter generator, and an oil-to-oil heat exchanger connected with the engine oil circuit and connectable with the electric starter generator oil circuit, for transferring heat from the starter generator oil to the engine oil as to warm-up the engine oil during turbine engine motoring prior to actual starting sequence. A low cost and highly integrated system is therefore provided for reducing drag torque of a turbine engine prior to the starting phase.
    Type: Grant
    Filed: December 14, 2017
    Date of Patent: April 13, 2021
    Assignee: Airbus Operations, S.L.
    Inventors: Leire Segura Martinez De Ilarduya, Alberto Juarez Becerril, Salvatore Demelas
  • Patent number: 10968944
    Abstract: A cap configured for providing a sealed cavity around an end of a fastener and a method of bonding a cap to a structural member in which a contact adhesive is provided for fixing the cap to the structural member and a curable sealant is provided for bonding the cap to the substrate.
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: April 6, 2021
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: Richard Dobbin
  • Patent number: 10967955
    Abstract: A vertical tail unit (7) including an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25) with opposite lateral sides (27a, 27b), and surrounds an interior space (29), and wherein the outer skin (13) has a porous section at the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13) and fluidly connected to the pressure chamber (15), and an air outlet (19) provided in the outer skin (13) and fluidly connected to the pressure chamber (15).
    Type: Grant
    Filed: October 8, 2018
    Date of Patent: April 6, 2021
    Assignee: Airbus Operations GmbH
    Inventor: Thomas Heuer
  • Patent number: 10967979
    Abstract: An aircraft with rear mounted engines, comprising a vertical tail plane and a horizontal tail plane, in which the engines are mounted on top of the horizontal tail plane, such that the horizontal tail plane comprises an inner fixed part attached to the fuselage of the aircraft, the inner fixed part comprising an elevator, and two outer movable parts, each one of the outer movable parts being located at each side end of the horizontal tail plane which is furthest away from the fuselage of the aircraft, such that both the inner fixed part and the outer movable parts are at least partially subjected to a flow coming from the engines when the engines are in use.
    Type: Grant
    Filed: December 22, 2016
    Date of Patent: April 6, 2021
    Assignee: Airbus Operations S.L.
    Inventor: Jose Luis Martinez Munoz
  • Patent number: 10967958
    Abstract: A vortex generator arrangement comprising a section that defines an opening to a corresponding cavity, an aircraft airflow modification device disposed within the cavity, and at least one fluidic muscle actuator arrangement coupled to the airflow modification device.
    Type: Grant
    Filed: October 15, 2018
    Date of Patent: April 6, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Bruno Stefes
  • Patent number: 10967978
    Abstract: An aircraft air conditioning system including an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer. A first compressor is arranged in the ambient air supply line and is configured to compress the ambient air flowing through the ambient air supply line. A bleed air supply line allows a flow of bleed air bled off from an engine or an auxiliary power unit therethrough. A bleed air turbine is driven by the bleed air flowing through the bleed air supply line and is coupled to the first compressor so as to drive the first compressor.
    Type: Grant
    Filed: September 16, 2019
    Date of Patent: April 6, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Holger Bammann, Frank Klimpel, Hans Brunswig
  • Patent number: 10969028
    Abstract: A shrouded valve assembly includes a valve with a valve pipe and a valve channel. A valve member in the valve channel can regulate flow of fluid through the valve channel. A valve shroud provides a valve shroud chamber. First and second shrouded pipe assemblies are on opposite sides of the valve, each including a pipe in fluid communication with a respective end of the valve channel, and a pipe shroud providing a pipe shroud chamber. Each pipe shroud chamber is in fluid communication with a respective end of the valve shroud chamber. The pipe assemblies are connected to the valve shroud by first and second connections and to the valve by third and fourth connections, the fourth connection more flexible than both the first connection and the second connection. Load passes between the pipe assemblies via the valve shroud rather than via the valve, protecting the valve from damage.
    Type: Grant
    Filed: April 28, 2017
    Date of Patent: April 6, 2021
    Assignee: Airbus Operations GmbH
    Inventors: Manfred Haug, Michael Rappitsch, Konrad Rauch
  • Patent number: 10971948
    Abstract: The modular element for a hybrid electrical power distribution and data communication network of an aircraft comprises a section of a bus and a set of data links extending substantially parallel along a length of the modular element. The bus section comprises connection points at different locations distributed along its length. The set of data links comprises connection points at different locations distributed along its length, each arranged in proximity to a connection point of the bus section. It also comprises a data link between each of the connection points and a cross-connect point. The bus section and the set of data links comprise interconnection points making it possible to link the modular element to first and second, other, modular elements arranged longitudinally in series with the modular element.
    Type: Grant
    Filed: July 31, 2018
    Date of Patent: April 6, 2021
    Assignees: AIRBUS OPERATIONS SAS, AIRBUS OPERAITONS GMBH
    Inventors: Jonathan Jacquemoud-Collet, Thomas Morin, Nicholas Brownjohn, Hartmut Hintze
  • Patent number: 10967518
    Abstract: A production system for automated assembly of vehicle components, in particular for automated assembly of structural components of an aircraft or spacecraft.
    Type: Grant
    Filed: January 11, 2019
    Date of Patent: April 6, 2021
    Assignee: Airbus Operations GmbH
    Inventors: Frank Neuhaus, Rainer Schildt, Wolfgang Juedes
  • Patent number: 10962448
    Abstract: A monitoring method, the purpose of which is, when a loss of power is detected in an aircraft engine, to generate an alarm in the form of a single message displayed on a display screen in the cockpit, in order to indicate if the level of damage suffered by the engine is critical or not. The steps implemented are based on alarm signals transmitted by a central processing unit of the engine and also on alarm signals transmitted by a diagnostic device for the onboard systems of the aircraft, in order to take account of both the situation of the engine and also the situation of the systems surrounding the engine which can be affected by damage to an engine.
    Type: Grant
    Filed: December 19, 2018
    Date of Patent: March 30, 2021
    Assignee: Airbus Operations SAS
    Inventors: Antoine Pilon, Natalino Agostino, Adrien Pierrel
  • Patent number: 10965816
    Abstract: In a method for testing an audio communication system of an aircraft, it is detected whether a jack plug of a headset is plugged into a jack of the audio communication system. Subject to the condition that no jack plug is detected, an electrical connection is made between an audio output of the jack and a microphone input of the jack by means of a test bridge circuit provided for at the jack. Furthermore, a test input signal is applied to an audio input connected to the audio output of the jack, and a test output signal is tapped off at a microphone output connected to the microphone input of the jack. The test output signal is used to ascertain a functional state of the audio communication system. Furthermore, an aircraft having an audio communication system is described.
    Type: Grant
    Filed: May 21, 2019
    Date of Patent: March 30, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Matthias Heinisch, Hans-Achim Bauer
  • Patent number: 10962029
    Abstract: A reservoir for a hydraulic system has a housing with an interior space and a fluid outlet, a hydraulic driving device coupled to a shaft extending in the housing to introduce a torque, and a separating device in the housing, for dividing the interior space into two separate sections. The fluid outlet is fluidically connected to a first section. The separating device extends along the shaft in the housing and sets the size ratio of the two separate sections by pivoting at least one first surface, coupled to the shaft, of the separating device about an axis defined by the shaft. The separating device is coupled to the hydraulic driving device such that the at least one first surface exerts a pressure on a fluid in the first section which is dependent on a surface area of the first surface and the torque.
    Type: Grant
    Filed: April 18, 2019
    Date of Patent: March 30, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Simon MacLennan, Robert Behr
  • Patent number: 10960981
    Abstract: An aircraft region comprising an aisle section extending in a longitudinal direction of the aircraft region, a bench seat oriented transversely with respect to the longitudinal direction and having a first seat adjacent to the aisle section and a second seat arranged remote from the aisle section, and an aircraft stowage bin system having a first stowage bin arranged at least in part above the first seat and a second stowage bin arranged at least in part above the second seat. The first stowage bin has a first rear side facing away from the aisle section, and the second stowage bin has a second rear side facing away from the aisle section. The second stowage bin is arranged above the second seat such that it is accessible for a person sitting on the second seat or standing in the longitudinal direction in front of the second seat.
    Type: Grant
    Filed: June 12, 2018
    Date of Patent: March 30, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Martin Metten
  • Patent number: 10961907
    Abstract: An aircraft incorporating a bleed system for extracting compressed air from the aircraft main engines to be used as a source of pressurized air for the aircraft. The bleed air system includes a first pre-cooler installed at one of the main engines nacelle and coupled with the bleed duct, and adapted for cooling down the bleed air extracted from the main engine, and a second pre-cooler installed at the pylon and coupled with bleed duct and downstream the first pre-cooler. The working temperature of the aircraft bleed system is reduced, down to max 200° C., so that the dimensions of an Over Heat Detection System (OHDS) is reduced.
    Type: Grant
    Filed: June 26, 2018
    Date of Patent: March 30, 2021
    Assignee: Airbus Operations, S.L.
    Inventors: Marta Castillo De Alvear, Juan Tomas Prieto Padilla
  • Patent number: 10962075
    Abstract: To increase a compactness of damping systems intended to operate in the event of a dynamic landing of an aircraft, a damping system comprises a primary damper device and a secondary damper device. The primary damper device comprises at least one beam, each beam extending along a direction of a longitudinal axis. The damping system is configured so that at rest, the primary damper device has a stiffness greater than a stiffness of the secondary damper device in the direction of the longitudinal axis. When a force is applied to the damping system along the direction of the longitudinal axis, with a value less than a limit value, each beam remains in a compression state. When the force applied has a value greater than or equal to the limit value, each beam undergoes buckling and the secondary damper device undergoes elastic deformation.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: March 30, 2021
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Jérôme Dubost, Guilhem Colombies, Julien Guesdon
  • Patent number: 10953861
    Abstract: An apparatus for reducing brake wear having a brake de-selection function for selectively disabling at least one brake on a vehicle; and a controller. The controller is configured to receive torque information which relates to torque reacted by a brake on the vehicle during a braking event and wheel speed information which relates to a speed of a wheel associated with the brake during the braking event; calculate an energy input into the brake during the braking event, based on the received torque information and the received wheel speed information; determine whether the calculated energy input meets at least one predefined energy input criterion; and activate the brake de-selection function if the calculated energy input meets the at least one predefined energy input criterion.
    Type: Grant
    Filed: September 18, 2017
    Date of Patent: March 23, 2021
    Assignees: Airbus Operations Limited, Airbus Operations S.A.S.
    Inventors: Kurt Brüggemann, Brice Cheray, Louis Emmanuel Romana
  • Patent number: 10946951
    Abstract: An aircraft (5) including a wing (3) and a winglet (1) at the end of the wing, the winglet including: a root (7); a tip (9); a transition region (11) extending away from the root; and a wing-like region (13) extending from the distal end of the transition region to the tip. When the aircraft wing (3) is under the worst-case static loading, the tip of the winglet is located at the maximum spanwise extent of the winglet (1), but when the aircraft wing (3) is under the no-load condition, the wing-like region (13) is canted inboard such that the tip (9) of the winglet (1) is located inboard of the maximum spanwise extent of the winglet.
    Type: Grant
    Filed: February 20, 2018
    Date of Patent: March 16, 2021
    Assignees: AIRBUS OPERATIONS LIMITED, AIRBUS OPERATIONS GMBH
    Inventors: Ben Commis, Christopher Wright, Kasidit Leoviriyakit, Gerd Heller
  • Patent number: 10951019
    Abstract: An electrical link (290) configured to link a DC high-voltage power source (270) to a user apparatus (250), and includes an electrical conductor (240) surrounded by an insulating cover and an electrical protection device (200) including: a conductive sleeve (280) arranged around the insulating cover, a biasing module (245) configured to voltage-bias the conductive sleeve (280), a circuit breaker (210) arranged on the conductor (240) and configured to cut off a current transiting through the conductor (240), and a detection module (220) connected to the conductive sleeve (280) and configured to detect a current leak out of the conductor (240) and to command the circuit breaker (210) on the basis of the detection. The invention also relates to a method for the secure supply of electric power.
    Type: Grant
    Filed: May 2, 2018
    Date of Patent: March 16, 2021
    Assignee: AIRBUS OPERATIONS (SAS)
    Inventors: Franck Flourens, Christian Donadille, Patrick Oms
  • Patent number: 10946948
    Abstract: A door assembly for a vehicle. The door assembly includes a door frame, a door panel, a rotating strut, and a linear door guide. The door opens and closes through a combination of rotating and sliding motion, which minimizes the required operational footprint. The strut is mounted on the door panel such that the strut is hidden from view when the door is in an open position.
    Type: Grant
    Filed: June 28, 2018
    Date of Patent: March 16, 2021
    Assignees: Airbus Operations GmbH, Airbus Americas, Inc.
    Inventors: Andreas Heidtmann, David Will, Roland Lange, Sassa Nadine Boos