Patents Assigned to Airbus Operations
  • Patent number: 8567721
    Abstract: The invention relates to a cover panel for an aircraft, comprising a decompression opening that can be closed by a decompression flap that comprises a membrane, and a ventilation opening that is provided separately in the cover panel and that is permanently open. Furthermore, the invention relates to an aircraft fuselage comprising such a cover panel.
    Type: Grant
    Filed: January 26, 2010
    Date of Patent: October 29, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Jens Voss, Markus Horst, Ingo Roth
  • Patent number: 8567150
    Abstract: The invention concerns a pressurized flooring for aircraft, provided with beams (1) including an upper sole (2), a vertical web plate (3), and a lower sole (4), the lower sole being provided with two oblique feet (7, 8) arranged on both sides of the vertical web plate and presenting a support surface (14, 15) provided for supporting pressurized curved membranes (9), characterized in that the lower sole includes a linking element (10) connecting the two oblique feet, so that said lower sole presents an enclosed section. Such a structure can be advantageously realized in composite material.
    Type: Grant
    Filed: May 16, 2007
    Date of Patent: October 29, 2013
    Assignee: Airbus Operations SAS
    Inventors: Laurent Gauthie, Phillippe Bernadet
  • Patent number: 8567066
    Abstract: A method of forming a rib-spar joint during assembly of an aircraft wing, the method comprising: providing a spar with a fixedly attached rib post, the rib post having a first coordination feature; providing a rib having a web with a first tooling feature; providing a tooling component having a second tooling feature for cooperating with the first tooling feature, a second coordination feature for cooperating with the first coordination feature, and a plurality of drill bushings; fixedly attaching the tooling component to the rib web by aligning the first and second tooling features; aligning the rib with the spar by aligning the first and second coordination features; drilling fastener holes in the rib and the rib post off the drill bushings of the tooling component; removing the tooling component from the rib web; and fastening the rib to the rib post using the fastener holes to form a rib-spar joint. The method may be applied to form front and/or rear rib-spar joints.
    Type: Grant
    Filed: September 21, 2011
    Date of Patent: October 29, 2013
    Assignee: Airbus Operations Limited
    Inventors: Richard Bestwick, Scott Grant
  • Patent number: 8567727
    Abstract: A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position by a respective actuator, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair of the flap elements only when the aerodynamic leading element of the pair has reached its extended position. Also, a method of operating the trailing edge flap arrangement.
    Type: Grant
    Filed: November 4, 2010
    Date of Patent: October 29, 2013
    Assignee: Airbus Operations Limited
    Inventor: Stuart Morris
  • Patent number: 8568069
    Abstract: A machining method for machining a superficial portion of a laminate using machine tool having a depth limiter which restricts a maximum depth of the machine tool. A guide frame having an inner guide contour restricts a maximum dimension of the superficial portion, and is secured over the superficial portion. The superficial portion is machined while the machine tool is guided by the guide contour. From another point of view, a machining apparatus for machining a superficial portion of a material is provided. The machining apparatus comprises a guide frame, an inner guide contour for guiding a machine tool, an attachment member for securing the guide frame to an attachment member, adjacent to the superficial portion, of the material.
    Type: Grant
    Filed: October 24, 2012
    Date of Patent: October 29, 2013
    Assignee: Airbus Operations GmbH
    Inventor: Willem Brugman
  • Patent number: 8572390
    Abstract: A method for transmitting data, a receiving method, related devices, and an aircraft equipped with the devices. The method includes determining an authentication word of the data; processing the data to obtain processed data; and transmitting the processed data on a transmission channel.
    Type: Grant
    Filed: March 27, 2007
    Date of Patent: October 29, 2013
    Assignee: Airbus Operations S.A.S.
    Inventors: Agnes Leclercq, Cecile Colle-Morlec
  • Patent number: 8567720
    Abstract: The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.
    Type: Grant
    Filed: January 3, 2008
    Date of Patent: October 29, 2013
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Guillaume Gallant, Damien Aguera, Philippe Bernadet
  • Patent number: 8561389
    Abstract: A system is provided for inerting a volume in a vehicle has at least one exhaust gas extraction point on at least one internal combustion engine of the vehicle, and exhaust gas line for routing exhaust gas from the exhaust gas extraction point to the volume, and at least one exhaust gas inlet on the volume for introducing exhaust gas to generate a low-activity environment in the volume. Precisely in vehicles with internal combustion engines, using exhaust gas for inerting a volume makes it possible to suggest an especially simple, cost-effective and robust solution to guard against the formation of an ignitable mixture in the volume or the like.
    Type: Grant
    Filed: October 27, 2010
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations GmbH
    Inventor: Bernd Rehling
  • Patent number: 8562027
    Abstract: A fuel piping connection device for aircraft includes a male end fitting and a female end fitting that are configured to engage one another. The male and female end fittings are made of a resistive material that is an insulating material loaded with conducting fibers. Each of the male and female end fittings is configured to be bonded to a radial outer wall at an extremity of a respective tube in the fuel piping or to a radial outer wall at an extremity of a respective piping connector. Each of the male and female end fittings includes an inwardly projecting shoulder configured to engage with an axial end surface of the respective tube in the fuel piping or with an axial end surface of the respective piping connector.
    Type: Grant
    Filed: April 27, 2012
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations S.A.S.
    Inventors: Thomas Barre, Matthieu Biteau, Olivier Bourbon, Alexis Courpet, Jean-Marc Roques, Cedric Sable
  • Patent number: 8562031
    Abstract: A locking device for an aircraft door in a fuselage section of an aircraft includes at least one fuselage fitting disposed in a region of a sill of the fuselage section and at least one door fitting disposed in a region of a lower edge of the aircraft door and corresponding in number to the at least one fuselage fitting. The at least one fuselage fitting and the at least one door fitting are each configured to transfer at least one of a circumferential load and a radial load.
    Type: Grant
    Filed: May 7, 2010
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations GmbH
    Inventor: Ronald Risch
  • Patent number: 8562237
    Abstract: A ball-joint support for thin parts, through which a ball-joint is operably coupled to a thin part, and where the ball-joint includes an inner part with a central coaxial orifice through which a longitudinal axis is introduced, and an outer part that engages complementarily to the inner part is provided. The ball joint support includes a cap including a central through hole in which the ball joint is embedded inside via the outer part, and externally, the cap is embedded in a cylindrical opening included in the thin part, and mechanical means for axial retention of the thin part to the cap, wherein the thickness of the cap is greater than the thickness of the thin part where the cap engages.
    Type: Grant
    Filed: December 29, 2011
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations, S.L.
    Inventors: Jose Maria Pina Lopez, Enrique Vera Villares
  • Patent number: 8561284
    Abstract: A machining device has a machine head capable of displacement along at least three translation axes X, Y, Z for machining an immobile part fixed above the machining head. The machining head is maintained in a constant orientation by at least three articulated connecting rods. Two connecting rods define together with the machining head and with a first Y carriage, on which they are articulated, an deformable articulated parallelogram in the XZ plane. Another connecting rod is articulated on the machining head and on a second Y carriage and the second Y carriage is capable of displacement along Y on a second X carriage capable of displacement along X. The relative movement along X of the Y carriages results in a displacement in the Z direction. Several devices can be positioned in a plurality of tunnels, these tunnels being arranged so as to share several things.
    Type: Grant
    Filed: September 21, 2007
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations SAS
    Inventors: Andre Greffioz, Michel Vives
  • Patent number: 8561948
    Abstract: A method for ensuring the safety of an aircraft flying horizontally at low speed includes an operation in which, when the flaps of the aircraft are disposed in a maximum extended position and are blown on by airscrews, the flaps are at least partially retracted, automatically, based on whether the thrust of the engines is at least equal to a predetermined lift value.
    Type: Grant
    Filed: November 27, 2006
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations SAS
    Inventor: Stephane Chardon
  • Patent number: 8562780
    Abstract: A process for the production of a stiffened panel made of composite material includes the stages of depositing the fibers that constitute the panel on a rigid device, depositing at least one stiffener, covering the unit with a sealed wall, and then polymerizing, and providing—for each stiffener—a rigid counter-mold in contact with the convex surface of the stiffener, covering the zone(s) of the panel that is/are not covered by the stiffener with at least one band sufficiently rigid to transmit compression forces by allowing play between the band and the stiffener, and then depositing a seal such that the seal, the band, and the rigid counter-mold form the sealed wall, whereby the seal is able to have two states, a first malleable state during application so that it adapts to the profile of the lateral edges of the stiffeners, and a hardened state to ensure transmission of compression forces in a manner essentially identical to the rigid counter-molds or to the bands arranged on either side of the seal so as n
    Type: Grant
    Filed: July 20, 2011
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations SAS
    Inventors: Denis De Mattia, Mathieu Lannuzel
  • Patent number: 8565942
    Abstract: According to the invention, during take-off, the aircraft (AC) is given the tail strike attitude (?ts) and the ailerons (6G, 6D) are deflected fully downwards.
    Type: Grant
    Filed: March 30, 2009
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations (SAS)
    Inventor: Frédéric Sauvinet
  • Patent number: 8561489
    Abstract: An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; a hole in the skin layer; an ultrasonic gauge which is mounted to an inner surface of the skin layer adjacent to the hole in the skin layer; and an access panel which covers the hole and can be removed to gain access to the gauge.
    Type: Grant
    Filed: September 22, 2009
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations Limited
    Inventors: Bryn Pettitt, James Beale
  • Patent number: 8564300
    Abstract: A method, and corresponding apparatus, for testing an aircraft control system is disclosed. The method includes simultaneously coupling a test device to a plurality of separate test points in an aircraft control system, selecting each test point individually such that the test device is enabled for electrical connection with the selected test point, conducting a test on the control system at each selected test point using the test device, detecting a signal or voltage at the selected test point, and indicating a result of the test at the selected test point to an operator.
    Type: Grant
    Filed: November 29, 2007
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Sven Knoop, Mike Galinski
  • Patent number: 8564536
    Abstract: A control device is provided for display means including several screens adapted for displaying several formats. The control device includes several command keys and means for automatic configuration of a command function for display of a format and visualization means associated with the command keys, adapted for respectively assigning to the command keys formats that can be displayed on a screen. The control device is usable in a cockpit of an aircraft.
    Type: Grant
    Filed: August 25, 2009
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations S.A.S.
    Inventor: Gregory Detouillon
  • Patent number: 8561266
    Abstract: In a holder arrangement of an aircraft or spacecraft comprising a structural member, a holder comprising at least one lower part and at least one upper part is provided, and these are formed so as to be able to be clamped together to be attached with a non-positive fit to a fastening portion of the structural member. The fastening portion can be clamped between the lower part and the upper part. The holder arrangement is characterised by at least one fixing strip which can be connected to the fastening portion of the structural member in the longitudinal direction thereof and which comprises a fixing profile for fixing the holder to the structural member in the longitudinal direction of the structural member with a positive fit. An aircraft or spacecraft has at least one holder arrangement of this type.
    Type: Grant
    Filed: October 26, 2009
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations GmbH
    Inventor: Cihangir Sayilgan
  • Patent number: 8561649
    Abstract: A weaving process for direct manufacture of three-dimensional structures with bidimensional walls with corners, without the need for sewing or other assembly between two ridges. The weaving is made by transforming weft threads into warp threads for making at least one face. The process is particularly adapted for the weaving of reinforcing elements for composite structures of corner fitting type.
    Type: Grant
    Filed: December 19, 2012
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations S.A.S.
    Inventors: Xavier Legrand, Mathieu Piana, Georgi Tsarvarishki, Julien Charles, Philippe Blot, Dominique Guittard