Patents Assigned to Airbus Operation
  • Connection assembly for at least one item of electronic equipment in an aircraft
    Patent number: 8717776
    Abstract: An assembly for connection of an electronic equipment item to wiring of an aircraft, in which the item of electronic equipment is disposed in a support means and includes connection means configured to be connected to the wiring, a connection interface disposed between the wiring and the connection means to provide connection of the item of electronic equipment to the wiring, the connection assembly configured to change over from a connected state in which the connection means are connected to the connection interface to a disconnected state in which the connection means are free. The connection interface is fastened to the structure of the aircraft; whether the connection assembly is in the connected or disconnected state. The support means is movable and includes an at least partially open face turned toward the connection interface and onto which the connection means emerge.
    Type: Grant
    Filed: February 4, 2011
    Date of Patent: May 6, 2014
    Assignee: AIRBUS Operations S.A.S.
    Inventors: Emile Colongo, Pierre Salles
  • Method and device for treating a surface of a fibre composite material
    Patent number: 8715553
    Abstract: The present invention provides a method and a device for treating a surface of a fiber composite material which contains fibers of a specific hardness, the surface of the fiber composite material being removed abrasively by an abrasion means, the hardness of which is less than the hardness of the fibers contained in the fiber composite material and is greater than the hardness of a plastics material in which the fibers of the fiber composite material are embedded.
    Type: Grant
    Filed: November 5, 2010
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Carsten Barlag, Timo Stoeven
  • Assembling and shaping laminate panel
    Patent number: 8715561
    Abstract: A method of assembling and shaping a laminate panel. An intermediate member is mounted on a lay-up table and a lay-up is assembling by laying a series of plies onto the intermediate member on the lay-up table. The intermediate member and the lay-up are then removed from the lay-up table and placed them on a shaped surface. The lay-up is then forced against the shaped surface, via the intermediate member, in a manner that modifies the shape of the lay-up to form a shaped laminate panel. Finally the shaped laminate panel is removed from the intermediate member. The lay-up table can thus support the flexible intermediate member during assembly, and can be relatively flat to enable the lay-up to assembled by an automated process.
    Type: Grant
    Filed: August 28, 2009
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations Limited
    Inventors: Andrew Levers, Gary Wiles
  • Trailing edge flap
    Patent number: 8714493
    Abstract: A single slotted trailing edge flap arrangement for an aircraft wing, comprising a main flap element and an auxiliary flap element sealed to and supported by the main flap element for movement between a retracted and an extended position relative to the main flap element so as to vary the planform area of the flap. The auxiliary flap element remains sealed to the main flap element when in its extended position, and movement of the auxiliary flap element relative to the main flap element is solely translational. The auxiliary flap element may be translationally deployed from the main flap element by sliding the auxiliary flap element out from the underside of the main flap element. Also, a method of operating the flap arrangement.
    Type: Grant
    Filed: November 4, 2010
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations Limited
    Inventor: Stuart Morris
  • Method for instantaneously determining rates of distortion of signals on an AC electrical network, and associated device
    Patent number: 8717040
    Abstract: A method for instantaneously determining rates of distortion on variable frequency signals, and an associated device, in which a harmonic distortion rate is calculated across the shortest possible temporal window, corresponding to the duration of a period of a given signal's fundamental. Hence, the aim being to precisely determine the signal frequency value, whose HDR is to be calculated, an iteration of certain measurements, achieved at the time of a given calculation, is embodied in order to calculate the HDR on subsequent signals.
    Type: Grant
    Filed: June 12, 2007
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations SAS
    Inventors: Marc Weber, Aymeric Plo, Denis Blache
  • Method for coupling stiffening profile elements and structural component
    Patent number: 8715808
    Abstract: This invention provides a coupling method for coupling a first and a second stiffening profile element for an outer skin of an aircraft or space craft. In a first step the stiffening profile elements are arranged on the outer skin in such a manner that the stiffening profile elements oppose each other with their respective front sides and enclose within themselves a cavity. Furthermore, a fixing hole is formed through a wall of at least one of the stiffening profile elements in the cavity inside a coupling zone of the stiffening profile element. An access opening is formed through the wall in the cavity along the coupling zone. A coupling strap, which couples the stiffening profile elements together, is fastened to the coupling zone by means of a fastening element guided through the fixing hole.
    Type: Grant
    Filed: June 19, 2008
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Thorsten Roming, Thorsten Schroeer, Hauke Kirstein, Hinnik Gensch, Stefan Tacke
  • Method and device for checking that an aircraft fulfils successive time constraints
    Patent number: 8718912
    Abstract: A time constraint checking device performs a method for checking whether an aircraft is able to fulfill a plurality of successive time constraints corresponding to required times of arrival at a plurality of corresponding waypoints. The method includes comparing, for each of the waypoints, a comparison value depending on the time constraint with either an estimated time of arrival or minimum and maximum possible times of arrival based on speeds of the aircraft. The method performs different comparisons depending on whether the time constraints for a particular waypoint are a single time value or a time window, and an optimized time of arrival for meeting all future time constraints is also possible.
    Type: Grant
    Filed: March 15, 2012
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Maxime Wachenheim, Stéphane Bostetter, Alexandre Lanoix
  • Conduit harness
    Patent number: 8714496
    Abstract: A conduit harness has an inner part and an outer part which are snap-fitted together to provide redundancy in the event of failure of either part.
    Type: Grant
    Filed: June 14, 2011
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations Limited
    Inventors: Jack Blanchard, David Routledge
  • Aircraft with reduced environmental impact
    Patent number: 8714475
    Abstract: An aircraft with reduced environmental impact includes two turboprop engines mounted on the back of the aircraft at the rear thereof, and one acoustic masking device per turboprop engine. The acoustic masking device includes a masking element, such as a flap, which can move between a position in which it is retracted into the wing, and a position in which it is extended toward the rear of the wing. In the extended position, the flap intercepts the noise area generated toward the front by the turboprop engine, so as to reduce the perception of noise on the ground.
    Type: Grant
    Filed: August 22, 2013
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations SAS
    Inventors: Pierre-Emmanuel Gall, Guillaume Gallant
  • Sol for sol-gel process coating of a surface and coating method by sol-gel process using same
    Patent number: 8715405
    Abstract: Sol for the sol-gel coating of a surface, said sol comprising, in percent by weight: a)—3% to 30%, preferably 5% to 20%, more preferably 7% to 15%, especially 8% to 14%, more especially 10% to 13%, for example 10.8% or 12%, of at least one organometallic compound of zirconium, aluminium or titanium; b)—5% to 50%, preferably 5% to 40%, more preferably 10% to 40%, especially 15% or 20% to 30%, for example 22% or 23%, of at least one organosilane compound; c)—1% to 15%, preferably 2% to 10%, more preferably 3% to 8%, for example 5%, of at least one compound selected from acids, bases, glycols and ethoxyethanol; d)—the remainder to 100% of demineralized or distilled water; the total amount of a) and b) being greater than 30%, preferably greater than 31.2%; 31.5%; 32%; or 33%, more preferably greater than 35%, especially greater than 40%, more especially greater than 50%.
    Type: Grant
    Filed: May 30, 2006
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations SAS
    Inventors: Luc Le Blanc, Elisa Campazzi, Patrick Savigne
  • Device, system and method of estimating the angle of attack of an aircraft
    Patent number: 8718840
    Abstract: A device for estimating the angle of attack of an aircraft moving through the air comprises means for receiving a measured incidence presented locally by the air relative to the aircraft and means for determining the angle of attack of the aircraft as a function of the measured incidence and information about the airspeed of the aircraft. The means for determining the angle of attack of the aircraft comprise means for reading the angle of attack of the aircraft from a look-up table having at least the measured incidence and the airspeed information as inputs. Corresponding system and a corresponding method are also proposed.
    Type: Grant
    Filed: May 7, 2008
    Date of Patent: May 6, 2014
    Assignees: Airbus Operations S.A.S., Airbus
    Inventors: Thomas Spoerry, Bruno Chauveau
  • Wind tunnel with a closed section for aeroacoustic measurements with an anechoic coating
    Patent number: 8714003
    Abstract: A wind tunnel with a closed section for aeroacoustic measurements with an anechoic coating including: a) a first cavity having a thickness D1 in a range of 20?D1?50 mm filled with a fibrous material with a flow resistance R in a range of 10?R?50 kRayl/m; b) a first microperforated panel having a thickness t1 in a range of 0.25?t1?0.75 mm and with a perforation percentage p1 in a range of 15%?p1?30%; c) a second air cavity having a thickness D2 in a range of 10?D2?30 mm; d) a second microperforated panel having a thickness t2 in a range of 0.25?t2?0.75 mm and with a perforation percentage p2 in a range of 15%?p2?30%. The perforations of the panels can be circular or longitudinal slot-shaped having a diameter d or width w in a range of 0.2?d, w?0.5 mm.
    Type: Grant
    Filed: April 28, 2010
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations, S.L.
    Inventors: Heidi Leni Ruiz Villamil, Jose Julian Alvarez Gonzalez, Pedro Cobo Parra
  • Aircraft with at least one net for reducing aerodynamic noise from a structural element of the aircraft
    Patent number: 8714474
    Abstract: An aircraft includes at least one net for reducing aerodynamic noise from a structural element of the aircraft. The flexible net associated with the structural element is retractable and capable of occupying at least one position located between the following two end positions: a deployed position, in which the net is placed in a turbulence area, and a retracted position, in which the net is at least partially outside the turbulence area. The net may be automatically moved between positions based on an aircraft parameter such as speed or altitude.
    Type: Grant
    Filed: January 5, 2011
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Jean-François Piet, Stephane Perrin Decroux, Nicolas Molin, Bastien Caruelle
  • Decompression device and decompression system
    Patent number: 8714483
    Abstract: A decompression device is provided having a frame element, in which at least one decompression opening is formed, and a cover is fastenable by means of a fastening device to the frame element in order in a first position to close the decompression opening formed in the frame element. The fastening device includes at least one holding clip and at least one receiving device that is complementary to the holding clip. The holding clip and the receiving device complementary to the holding clip are situated in engagement with one another when the cover is situated in its first position and are adapted to move out of engagement when a predetermined differential pressure acts upon the cover in order to enable the cover to move relative to the frame element into a second position, in which the cover releases the decompression opening formed in the frame element.
    Type: Grant
    Filed: September 13, 2011
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Stephan Hoetzeldt, Oliver Schindler, Gerhard Penski
  • Aircraft seat assembly structure, and fitted fuselage
    Patent number: 8714484
    Abstract: An aircraft seat assembly structure (4) comprises at least one seat structure (5) that supports at least one seat, with which seat assembly structure is associated a reference frame that is defined by a longitudinal X-axis according to which the seat structure (5) comprises a front part and a rear part, by a Y-axis that is perpendicular to the X-axis, and that forms with said X-axis a horizontal XY plane when at least one seat is horizontal, and by a Z-axis that is perpendicular to the XY plane. In the front part, the seat structure (5) comprises a torsion bar (50) that is essentially parallel to the Y-axis that is equipped at a first lateral end (502) with a front lateral fastening device (500) that is designed to be made integral with lateral attachment means (26) of a shell structure (2) of an aircraft.
    Type: Grant
    Filed: September 4, 2009
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Bernard Guering, Cedric Meyer
  • Turbomachine support pylon for aircraft
    Patent number: 8714477
    Abstract: An aircraft support pylon designed to attach a turbomachine housed in a nacelle to an aircraft fuselage is disclosed. The pylon includes a cooler, located substantially in the vicinity of a leading edge of the pylon, and able to be heated by a hot fluid, the hot fluid intended to be cooled by heat exchange with cold air outside the cooler. The pylon also includes at least one air evacuation duct, at the exit from the cooler and extending longitudinally in an internal volume of the pylon to a trailing edge of the pylon.
    Type: Grant
    Filed: April 26, 2011
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Christelle Rinjonneau, Pierre Guillaume
  • Method of operating a cooling system and cooling system
    Patent number: 8713950
    Abstract: In a method of the application, cooling energy is produced by a refrigerating device. The cooling energy produced by the refrigerating device is supplied to at least one cooling station by a cooling circuit, circulating in which is a refrigerant, which upon release of its cooling energy to the at least one cooling station is converted from the liquid to the gaseous state and is then converted back to the liquid state by corresponding pressure- and temperature control in the cooling circuit. Upon transfer of the cooling system to its state of rest, a control value disposed in the cooling circuit is controlled in such a way that a desired operating pressure (??) arises in the cooling circuit downstream of the control valve. Refrigerant cooled by the refrigerating device is received in a reservoir disposed upstream of the control valve in the cooling circuit.
    Type: Grant
    Filed: March 5, 2010
    Date of Patent: May 6, 2014
    Assignee: Airbus Operations GmbH
    Inventor: Sebastian Roering
  • AIRCRAFT WING WITH WING TIP DEVICE
    Publication number: 20140117158
    Abstract: An aircraft wing assembly comprising a wing (2) having a wing box structure including an upper wing cover (7) and a lower wing cover (8), and a wing tip device (1) attached to the outboard end of the wing, the wing tip device including an upper cover (9) and a lower cover (10), wherein a gap (g) between opposing edges of the wing tip device lower cover (10) and the lower wing cover (8) is at least 5 mm, and further comprising a seal assembly (20) for aerodynamically sealing the gap (g), wherein the seal assembly (20) includes a bridging component (21) on an interior side of the gap (g), and a seal (22) which fills the gap (g) and is supported by the bridging component (21). Also, an aircraft having the wing assembly, and a method of attaching a wing tip device (1) to the outboard end of a wing (2).
    Type: Application
    Filed: April 23, 2012
    Publication date: May 1, 2014
    Applicant: AIRBUS OPERATIONS LIMITED
    Inventors: Huw Davies, Nigel McKenna
  • CONNECTOR FOR SECURING DOUBLE SKIN PIPEWORK AND ASSEMBLY OBTAINED
    Publication number: 20140117162
    Abstract: A connector for securing floating double skin pipework to a structure includes means for securing to the structure, and an external body forming an outer channel and an internal tube forming an inner channel around the longitudinal axis of the connector. The means for securing to the structure includes a fixed connection backed up by a sliding connection along the longitudinal axis of the connector. The connector includes at least one bore for producing the fixed connection and at least one holding rail for producing the sliding connection.
    Type: Application
    Filed: October 29, 2013
    Publication date: May 1, 2014
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Alexis Courpet, Thomas Barre, Olivier Bourbon, Matthieu Biteau, Jean-Marc Roques, Sébastien Escande, Brice Lenoir
  • Composition for the Local Application of Chemical Conversion Layers
    Publication number: 20140120357
    Abstract: An aqueous composition for forming a chemical conversion layer on a metal surface, wherein the composition contains at least one active component for the formation of the chemical conversion layer, as well as at least one thickener, and has a viscosity in the range between 10 mPa*s and 10000 mPa*s.
    Type: Application
    Filed: October 28, 2013
    Publication date: May 1, 2014
    Applicants: EADS Deutschland GmbH, Airbus Operations GmbH
    Inventors: Sonja Nixon, Martin Beneke, Dominik Raps