Patents Assigned to Airbus Operations
  • System for attaching two components together, such as an aircraft engine and the mounting pylon thereof
    Patent number: 8646724
    Abstract: An attaching system for attaching two components together, such as an aircraft engine and a mounting pylon, includes front trunnions and rear trunnions for supporting the aircraft engine. In this attaching system, at least two of the front or rear trunnions are vibration damping type trunnions that include a suspension assembly with an elastic element and resonant mass. The suspension assembly is shaped as a bent arm carrying the resonant mass on a free end and associated with the elastic element on another end. The vibration damping type trunnions also include a shackle attached between the engine and the suspension assembly so that the vibration damping type trunnions minimize any vibrations and efforts that would otherwise be applied to aircraft structure via the pylon.
    Type: Grant
    Filed: December 2, 2009
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Mathieu Bonnet, Eric Renaud
  • Aircraft hold and aircraft equipped with such a hold
    Patent number: 8646727
    Abstract: A device for keeping objects, especially luggage, in an aircraft hold, the device including a flexible partition and at least one winding mechanism. The flexible partition is mounted on the winding mechanism such that it can be both wound onto the winding mechanism or unwound from the winding mechanism. The flexible partition includes an attaching mechanism that operates with a complementary mechanism to maintain the flexible partition in an unwound position.
    Type: Grant
    Filed: June 13, 2008
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations SAS
    Inventor: Bernard Guering
  • Sliding door system
    Patent number: 8646211
    Abstract: A sliding door system includes at least one sliding door having an upper and lower sliding-door mount, as well as an upper and lower guide rail for displaceably receiving the upper and lower sliding-door mount, respectively. The guide rails extend parallel to each other and each have a clear inner width that is at least twice as large as the thickness of the sliding door. The upper and lower sliding-door mounts are each at most half as wide as the clear inner width of each guide rail, allowing moving the sliding door into recessed and lifted-out positions, each constituting a stable state. By overcoming a resistance force, the sliding door can be moved between stable states. The sliding door system is lightweight and robust, and enables sliding doors to be displaced freely without a particular sliding door being assigned in a fixed manner to a particular opening to be covered.
    Type: Grant
    Filed: April 6, 2012
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Peter Rosenbeck-Mortensen, Thomas Lund, Joyce Tan, Hans Henrik Jochumsen
  • 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
  • Clamping device and method for assembly of stringer couplings
    Patent number: 8646161
    Abstract: A clamping device is provided for an assembly of a stringer coupling in a region of a lateral butt joint between a first and a second fuselage section of an aircraft for coaxially connecting a respective first and second stringer of the first and the second fuselage sections, the stringer coupling intersecting a frame element profile in the region of the lateral butt joint. A supporting yoke is configured to bridge the frame element profile in an arc-shaped manner and includes a first end foot supported by the stringer coupling on the first side of the frame element profile and a second end foot supported by the stringer coupling on the second side of the frame element profile. The supporting yoke includes a middle tensioning hook configured to interact with the frame element profile. The first and the second end feet are tensionable against the stringer coupling.
    Type: Grant
    Filed: October 7, 2011
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Rolf Bense, Axel Sauermann, Eugen Gorr
  • Seat with a seat element, seat arrangement and method for monitoring a seat
    Patent number: 8646837
    Abstract: An aircraft passenger seat has at least one seat element characterized by at least one monitoring apparatus for monitoring the seat element. The seat arrangement has a plurality of seats, wherein at least one seat includes at least one sensor module for monitoring a seat element and a control unit for checking and controlling the monitoring, wherein the at least one sensor module is in a data exchange relationship with the control unit.
    Type: Grant
    Filed: November 12, 2008
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Sergio Bovelli, Martin Kluge, Winfried Kupke, Josef Schalk, Hans-Achim Bauer, André Zybala
  • Method for debugging operational software of a system onboard an aircraft and device for implementing the same
    Patent number: 8650547
    Abstract: A method for debugging the program of operational software of an onboard system, including flagging the program by positioning flags along an execution path for dividing the aforementioned execution path into adjacent functional intervals; normal execution of the program; acquiring an execution condition of the program by flag condition vectors; when an error is detected, searching a faulty functional interval based on the flag condition vectors, reverse execution of the program in the aforementioned faulty functional interval, and determination and correction of the error.
    Type: Grant
    Filed: September 12, 2008
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations SAS
    Inventors: Famantanantsoa Randimbivololona, Philippe Le Meur, Florent Fournier, Vincent Bregeon
  • 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
  • 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
  • Device for adjusting the height of an assembly without the use of tools
    Patent number: 8646738
    Abstract: The invention relates to a device comprising a base plate and a support for adjusting the height of an assembly, in particular of a galley module in an aircraft, without using tools. According to the invention, two opposing wedge bodies are arranged such that they can be displaced horizontally between the base plate and the support, the oppositely directed manual displacement of the two wedge bodies, when the lock levers have been raised, causes in the “adjusting position” a raising or lowering of the support for the height adjustment. The assembly is connected to the support, for example by a conventional screw connection through the attachment hole in the support. The device according to the invention allows a user to perform a simple and rapid height adjustment of an assembly arranged thereon, thereby greatly reducing the assembly effort required for prefabricated assemblies or modules in aircraft.
    Type: Grant
    Filed: May 12, 2010
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Melanie Stoob, Benedikt Schmidt-Kortenbusch, Nils Ischdonat, Rolf Bense
  • Method and device for attenuating the effects of turbulence on an aircraft
    Patent number: 8649919
    Abstract: A method for attenuating effects of turbulence on an aircraft, and a device to implement the method, the method including: using at least one signal on a wind profile signal, along an excitation direction, representing, at a given moment in an aircraft referential, a component along the excitation direction of the wind speed at a front of the aircraft according to a distance along a longitudinal direction of the aircraft; carrying out a frequency determination, in which the wind profile signal is processed to determine a frequential content; and selecting a control strategy to be adopted according to the previously determined frequential content, the strategy enabling at least one applicable control law to be identified.
    Type: Grant
    Filed: October 30, 2009
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Guillermo Jenaro Rabadan, Stephane Puig
  • Device and method for communication between a portable computer system and items of avionics equipment
    Patent number: 8649785
    Abstract: A device for communication between a portable computer system including a display screen and avionic equipment items comprises shielded walls forming at least a partial Faraday cage. The device also includes at least one wide band high output wireless transmitter-receiver arranged inside the shielded walls and adapted for carrying out a very short range point-to-point radio communication with the portable computer system when the portable computer system is placed inside the shielded walls. The device also includes at least one interface connected to the avionic equipment items and adapted for transmitting data originating from the portable computer system to the avionic equipment items and data originating from the avionic equipment items to the portable computer system, through the at least one said transmitter-receiver.
    Type: Grant
    Filed: October 22, 2009
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations SAS
    Inventors: Frederic Durand, Frederique Delannoy, Philippe Moreau, Pierre Depape, Sebastien Delautier, Sebastien Saletzki
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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