Patents Assigned to Airbus Operation
  • Method and device for acquiring, recording and processing data captured in an aircraft
    Patent number: 8650015
    Abstract: A device for acquiring and recording data captured in an aircraft including a plurality of sources of data streams to be recorded, at least one source of dated values of recording parameters, and a recording mechanism recording data from the data streams and parameter values, on at least one non-volatile information medium. The recording mechanism is adapted to store, in separate files, the data of the various streams of data associated with the dated values of recording parameters.
    Type: Grant
    Filed: May 29, 2008
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations SAS
    Inventors: Jean-Luc Vialatte, Sophie Calvet
  • Sandwich component comprising a reinforced foam material
    Patent number: 8646182
    Abstract: Provided is a sandwich component with a core which comprises a foam material. A fibrous sheet-like material arranged in the foam material at least partially encloses a working region of the sandwich component in a sheet-like manner. At least one strut is incorporated in the foam material and extends from an entry surface of the foam material from outside the working region to at least the fibrous sheet-like material.
    Type: Grant
    Filed: March 31, 2010
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Hans-Jürgen Weber, Gregor Christian Endres
  • Laying-up method for non-planar composite components
    Patent number: 8649897
    Abstract: A method for laying-up the tapes of a prepeg composite material in the 0° direction of a non-planar composite component on a suitable mold using an ATL machine includes the steps of: a) determining the trajectories of the tapes as modified trajectories of geodesic trajectories complying with the following conditions in their projections in an horizontal plane: that the curvature radius R2 of their curved segments is bigger than a predetermined value Rmin; that the gap G2p between two contiguous tapes is comprised between 0 and a predetermined value Gmax; and b) providing modified trajectories to the ATL machine. The invention also refers to a non-planar composite component such as an skin of an aircraft wing having the tapes in the 0° direction following trajectories complying with conditions described.
    Type: Grant
    Filed: September 19, 2011
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations S.L.
    Inventors: Alberto Lozano Sevilla, José Orencio Granado Macarrilla, Vicente Martínez Valdegrama, Raúl Burgos Gallego
  • Engine assembly for an aircraft the engine attachment strut of which includes a structural case forming an internal radial delimitation of the secondary flow
    Patent number: 8646725
    Abstract: An engine assembly for an aircraft including a dual-flow turbomachine and an attachment strut. The turbomachine includes a structural case extending downstream of the hub of an intermediate casing, the case contributing to the internal radial delimitation of a passage for a secondary flow of the turbomachine. Also, the primary structure includes a structural case, assembled on the structural case and positioned directly downstream of the structural case such that it also contributes to the internal radial delimitation of the passage for the secondary flow. The primary structure also includes an offset structure positioned in the passage, and configured to connect the case to an element of the aircraft. The structural case also includes a thrust reversal system.
    Type: Grant
    Filed: July 29, 2010
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations S.A.S.
    Inventor: Laurent Lafont
  • Method and device for automatically monitoring lateral guidance orders of an aircraft
    Patent number: 8649920
    Abstract: A monitoring device automatically monitors lateral guidance orders of an aircraft. The device includes a failure monitoring device for implementing comparisons between roll control orders generated by a number of equipments in order to be able to detect a failure of one of the equipments concerning the generation of lateral guidance orders of the aircraft. Additionally, the device includes a failure anticipation comparator device for analyzing inlet parameters of the equipments to determine when a failure of one of the equipments should be anticipated.
    Type: Grant
    Filed: December 7, 2011
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Nicolas Potagnik, Jean Muller, Florent Lanterna
  • PRESSING A WELD USING THE FRICTION AGITATION WELDING PROCESS FOR BETTER SURFACE ADJUSTMENT
    Publication number: 20140034711
    Abstract: A friction agitation welding process for the joining of abutting plate-shaped workpieces consisting of an aluminium alloy, wherein a rotating Bobbin tool is moved along a weld between the two plate-shaped workpieces during feed, exerting a first and a second contact pressing force on first and second sides, respectively, and wherein said Bobbin tool is subjected to an additional axial force during its movement along the weld to plastically deform the area of the created welding seam such that the welding seam is pressed towards one side of the plate-shaped workpieces while forming a welding seam elevation protruding opposite from the workpiece surface.
    Type: Application
    Filed: October 11, 2013
    Publication date: February 6, 2014
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Hartmut Ostersehlte
  • METHOD AND DEVICE FOR AIDING THE MANAGEMENT OF THE FLIGHT OF AN AIRCRAFT
    Publication number: 20140039731
    Abstract: The device comprises servocontrol means which automatically control, in a combined manner, an automatic thrust system of the aircraft and airbrakes of the aircraft, as a supplement to usual means for steering the vertical trajectory, so that the aircraft attains a speed setpoint and/or altitude setpoint, at the location defined by a geographical constraint.
    Type: Application
    Filed: August 1, 2013
    Publication date: February 6, 2014
    Applicant: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Charles Renault Leberquer, Florian Constans, Josep Boada-Bauxell, Pascale Louise
  • Assembly Comprising A Device For Locking A Fastening
    Publication number: 20140037400
    Abstract: An assembly includes a support fastened to a structure by a fastening element extending along a fastening axis. and includes a bore for the passage of the fastening element. The fastening element includes a surface for driving in rotation. The assembly includes a device for locking the fastening element in rotation including a moveable end resting against the surface for driving in rotation the fastening element. The locking device is configured so that, at rest, the moveable end enters into the volume normally occupied by the surface of the fastening element. The locking device is placed between the support and the fastening element so as to be deformed elastically by the surface when the fastening element is put in place in the bore of the support. The moveable end includes locking shapes capable of interacting with the external shapes of the driving surface to stop the fastening element from rotating.
    Type: Application
    Filed: August 6, 2013
    Publication date: February 6, 2014
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Jacques Fournie, Thony Dupas
  • Circumferential stiffener for an aircraft fuselage
    Patent number: 8640990
    Abstract: A circumferential stiffener configured for a fuselage of an aircraft includes a web disposed at an angle to a normal axis of the circumferential stiffener, at least one inner flange, at least one outer flange and an integral angle profile configured for connection to a skin section of the fuselage.
    Type: Grant
    Filed: April 29, 2011
    Date of Patent: February 4, 2014
    Assignee: Airbus Operations GmbH
    Inventor: Torsten Noebel
  • Window for aircraft with microstructure as a sunscreen
    Patent number: 8640991
    Abstract: An aircraft window includes a microstructure so that light rays with a correspondingly large angle of incidence are reflected back to the exterior region. By contrast, light rays with another, i.e. smaller, angle of incidence are allowed to pass almost without hindrance. The microstructures are designed as optical prisms, wherein the order of magnitude of the prisms is in the region of light wave lengths.
    Type: Grant
    Filed: June 13, 2008
    Date of Patent: February 4, 2014
    Assignee: Airbus Operations GmbH
    Inventor: Michael Saalmann
  • Turbojet nacelle and method for controlling separation in a turbojet nacelle
    Patent number: 8640986
    Abstract: An aircraft turbojet nacelle comprising blowing means intended to inject a tangential airflow (Ft) into the internal volume (V) of the nacelle, said blowing means being provided in a wall of the air intake of the nacelle in the supersonic area of said air intake. The invention also concerns a method for controlling separation in an aircraft nacelle, wherein a tangential airflow is injected (Ft) into the internal volume (V) of the nacelle in the locally supersonic area of the air intake so as to pull the main airflow (F) into the extension of the inner wall of the nacelle.
    Type: Grant
    Filed: December 2, 2008
    Date of Patent: February 4, 2014
    Assignee: Airbus Operations SAS
    Inventors: Thierry Surply, Christophe Bourdeau
  • Aircraft with an arrangement of flow-influencing devices
    Patent number: 8645007
    Abstract: An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.
    Type: Grant
    Filed: June 8, 2012
    Date of Patent: February 4, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Burkhard Gölling, Rudibert King, Ulrich Notger Heinz, Wolfgang Nitsche
  • Fuel transfer monitoring system and method
    Patent number: 8645045
    Abstract: A fuel monitoring system for automatically monitoring a fuel transfer in an aircraft fuel system, the fuel system including a plurality of fuel tanks, the fuel monitoring system comprises a fuel quantity sensor arranged to measure the quantity of fuel in a first fuel tank and a data processor arranged to receive a fuel quantity measurement from the sensor, wherein in response to receiving a command to transfer fuel from the first fuel tank to one or more further fuel tanks the data processor is arranged to determine the rate of change of fuel quantity in the first tank from the received fuel quantity measurement and if the rate of change of fuel quantity is less than a threshold value and the received fuel quantity measurement is greater than an expected value then the data processor is further arranged to provide an output indicating that the commanded fuel transfer has failed.
    Type: Grant
    Filed: November 19, 2008
    Date of Patent: February 4, 2014
    Assignee: Airbus Operations Limited
    Inventor: Petter Sjungargard
  • Aircraft engine mounting structure, assembly comprising this structure and associated aircraft
    Patent number: 8640987
    Abstract: An engine is suspended from a main linear portion of a structure mounted on a fuselage or a wing surface of an aircraft. A connection includes flat symmetrical wings at an angle to one another, to support an attaching flange on which the engine is mounted, directly or through a mounting element. The flat shape of the wings makes them easy to manufacture, and enables them to resist the forces satisfactorily. The intermediate element resists overhang forces of the mounting satisfactorily. Flexible connections filter the engine's vibrations and prevent irregular forces being transmitted.
    Type: Grant
    Filed: September 20, 2010
    Date of Patent: February 4, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Frederic Journade, Laurent Lafont, Laurent Agostini, Eric Renaud, Delphine Jalbert
  • Multiport passive device for sharing optical signals
    Patent number: 8644709
    Abstract: A multiport passive optical signal sharing device enabling optical signals received by each of a first plurality of ports of the device to be transmitted to all of the ports of a second plurality of ports of the device. The device includes a first coupling mechanism adapted to combine signals received by each port of the first plurality of ports of said device into a first optical signal, the first optical signal being transmitted over a bi-directional optical link. The device further includes a second coupling mechanism and guide for redirecting the first optical signal in a form of a second optical signal into the bi-directional optical link, in the opposite direction from that of the first optical signal, the first coupling mechanism being adapted to duplicate the second optical signal on each port of the second plurality of ports of the device.
    Type: Grant
    Filed: September 7, 2010
    Date of Patent: February 4, 2014
    Assignee: AIRBUS Operations S.A.S.
    Inventors: Juan Lopez, Sebastien Delorge, Alexandre Touya
  • Hybrid drive for an aircraft
    Patent number: 8640439
    Abstract: A drive device for an aircraft comprises a gas turbine apparatus for generating a first drive energy and electric motor for generating a second drive energy. The gas turbine apparatus and the electric motor are set up in such a way that the drive unit may be provided with at least one of the first drive energy and the second drive energy. The drive unit is set up to generate propulsion using at least one of the first drive energy and the second drive energy.
    Type: Grant
    Filed: November 29, 2007
    Date of Patent: February 4, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Claus Hoffjann, Hansgeorg Schuldzig, Andreas Westenberger
  • HEAT EXCHANGER, HEATER AND GALLEY
    Publication number: 20140027088
    Abstract: A heat exchanger for cooling air, with a coolant onward-flow connection for feeding liquid coolant for cooling air and a coolant return-flow connection for discharging liquid coolant. For removing ice by melting accumulated ice in the heat exchanger, a heater is provided that is associated with an electrical heating element. An operational safety device prevents overheating of the heater. The operational safety device comprises a fault-current detection device. Such a heater, with a heating element for heating air for subjecting accumulated ice to heated air, and with such an operational safety device is provided. Also, a galley for a commercial aircraft is provided with a receiving space for trolleys, and a cooling device for cooling the receiving space. The cooling device comprises such a heat exchanger for cooling air.
    Type: Application
    Filed: January 25, 2013
    Publication date: January 30, 2014
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • METHOD FOR MONITORING THE COORDINATED EXECUTION OF SEQUENCED TASKS BY AN ELECTRONIC CARD COMPRISING AT LEAST TWO PROCESSORS SYNCHRONIZED TO TWO DIFFERENT CLOCKS
    Publication number: 20140033225
    Abstract: A method for monitoring the coordinated execution of sequenced tasks by an electronic device including a main electronic card including at least one main processor synchronized to a main clock and at least one auxiliary electronic card including at least one auxiliary processor synchronized to an auxiliary clock, includes emitting by the main processor of a coordination marker to the auxiliary processor at the start of each main time period; emitting by the auxiliary processor of a response word formed on the basis of the last coordination marker received to the main processor at the end of each auxiliary time period; validating by the main processor of the response word received with respect to the first coordination marker emitted; and signaling by the main processor if the response word received is not valid so as to signal a defect of coordination of the auxiliary processor.
    Type: Application
    Filed: July 24, 2013
    Publication date: January 30, 2014
    Applicant: Airbus Operations SAS
    Inventors: Gilles Tost, David Roblero Martinez, Thierry Dejean, Sophie Deneuville, Laurent Marliere, Hélène Blouin
  • AIRCRAFT FUSELAGE STRUCTURAL ELEMENT WITH VARIABLE CROSS-SECTION
    Publication number: 20140027573
    Abstract: An aircraft fuselage structural element has the general form of an elongated profile and includes a web and at least one flange. The at least one flange has a curved cross-section tangent to the web. Use in a profile to increase the residual compressive strength after impact.
    Type: Application
    Filed: July 29, 2013
    Publication date: January 30, 2014
    Applicant: AIRBUS OPERATIONS (S.A.S)
    Inventors: Hélène CAZENEUVE, Fabrice MONTEILLET, Yann MARCHIPONT
  • METHOD FOR MONITORING THE COORDINATED EXECUTION OF SEQUENCED TASKS BY AN ELECTRONIC CARD COMPRISING AT LEAST TWO PROCESSORS SYNCHRONIZED TO ONE AND THE SAME CLOCK
    Publication number: 20140033224
    Abstract: A method for monitoring the coordinated execution of sequenced tasks by an electronic card including at least one first processor (PP1) and a second processor (PP2) synchronized to the same clock of determined time period, includes: recording in memory means by the first processor (PP1) of a first identifier (ID1) characterizing the time period (T1) in the course of which the first sequenced task has been executed; recording in the memory means by the second processor (PP2) of a second identifier (ID2) characterizing the time period (T1) in the course of which the first accessory task (N1) has been executed; comparing by the first processor (PP1) the first identifier (ID1) and the second identifier (ID2); and signaling by the first processor (PP1) in the case of failure of the comparison so as to signal a defect of coordination of the processors (PP1, PP2).
    Type: Application
    Filed: July 24, 2013
    Publication date: January 30, 2014
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Gilles Tost, David Roblero Martinez, Thierry Dejean, Sophie Deneuville, Laurent Marliere, Hélène Blouin