Patents Assigned to Airbus Operations
  • Assembly for separating a space into multiple areas
    Patent number: 8613407
    Abstract: The invention relates to an arrangement for dividing a space into a plurality of areas, said arrangement comprising at least one frame with at least one fixing means for holding the frame in corresponding frame receiving elements, and at least one foldable defining means. The frame is formed in such a way that the arrangement essentially fits onto at least one wall of the space when it is fixed, the foldable defining means being able to be held on the frame and preventing an air flow between adjacent areas of the space separated by the arrangement. The arrangement according to the invention enables a thermal separation of two adjacent areas of a space, that can each be air-conditioned differently, without forming an area containing air which is a mixture from two regions at different temperatures.
    Type: Grant
    Filed: May 14, 2009
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Sven Hartel, Volkhard Wendt
  • Aircraft with a reinforced floor structure
    Patent number: 8613408
    Abstract: The aircraft includes: a floor; a top panel of a central wing box; at least two rails and at least two beams, the rails and the beams extending between the floor and the panel; and at least one reinforcement suitable, independently of the rails, for taking up a force acting at the level of the floor and for transmitting said force to the beams and/or to the top panel.
    Type: Grant
    Filed: February 12, 2010
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations
    Inventor: Michel Marpinard
  • Assembly for an aircraft comprising a turbomachine attachment strut of which the means for attachment to the wing are arranged in a T shape
    Patent number: 8613405
    Abstract: An assembly for an aircraft including: a mechanism attaching a primary structure of an attachment strut to a wing, forming an isostatic system; an attachment housed in a leading edge of the wing and configured to only take up forces exerted along the transverse and longitudinal directions; and an attachment including a connecting rod extending rearwardly, of which one end is connected to the primary structure and the other end is connected to the wing element, the connecting rod being offset along the vertical direction of the attachment.
    Type: Grant
    Filed: July 29, 2010
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations S.A.S.
    Inventor: Laurent Lafont
  • Fault-tolerant system for data transmission in a passenger aircraft
    Patent number: 8614944
    Abstract: A transmission system for transmitting communications data from at least one data source to a plurality of terminals via a distributor, includes terminals connected in series in a terminal chain, via an input port and an output port. The first and last terminals in the chain are directly interconnected with a shunt connection in such a way that the communications data in the chain of terminals is transmitted from terminal to terminal, between the first and the last terminals of the chain if all the terminals are interconnected, and, if the connection between the terminals in the terminal chain is interrupted, the communications data from the first terminal of the chain of terminals is transmitted in the terminal chain up to the inactive terminal and the communications data from the last terminal is transmitted in the terminal chain up to the inactive terminal.
    Type: Grant
    Filed: June 26, 2006
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations GmbH
    Inventor: Roman Westeroth
  • Method and devices for projecting two-dimensional patterns onto complex surfaces of three-dimensional objects
    Patent number: 8614711
    Abstract: A method and device optimizing projection of a two-dimensional pattern onto a three-dimensional object surface. After defining an original curve on the two-dimensional pattern and a projection curve on the three-dimensional object surface, a point of the pattern is selected. The abscissa and ordinate of the projection of the selected point are determined according to the abscissa and ordinate of the selected point and first and second projection ratios, respectively. A projection plane, including the point of the projection curve determined by the abscissa of the projection of the selected point, is then determined. The projection of the selected point onto the three-dimensional object surface is determined according to the ordinate of the projection of the selected point, the intersection of the surface of the three-dimensional object with the plane of projection, and the projection curve.
    Type: Grant
    Filed: October 12, 2007
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations SAS
    Inventors: Francis Saraille, Henri Jeannin
  • Aerodynamic flight control surface said of crocodile style for aircraft
    Patent number: 8613409
    Abstract: A trailing edge aerodynamic airfoil of a load-bearing aerodynamic surface of an aircraft of the crocodile type has two airfoil flaps, with each flap being integral in a forward section with a rotational shaft that determines the axis of rotation of the airfoil flap. In a position called the zero setting, the airfoil flaps are essentially joined and form a rear section of the load-bearing surface, and each airfoil flap is movable in translation independently of the other airfoil flap, relative to the load-bearing surface, with each flap being entrained in rotation relative to the load-bearing surface around its axis of rotation by the motion in translation. The ends of the rotational shaft have extensions guided by runners fastened to these ends and acting conjointly with racks fastened to the load-bearing surface.
    Type: Grant
    Filed: November 8, 2010
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Olivier Cazals, Thierry Druot
  • Monitoring device for a vacuum toilet
    Patent number: 8613115
    Abstract: A monitoring device and method are provided for monitoring a vacuum toilet, as well as a personal transport vehicle, in particular an aircraft, which uses a monitoring device for vacuum toilets. The monitoring device has a position detector for detecting the position of a toilet lid, a mechanical latching device and a flushing control unit. The latching device is designed to latch the toilet lid in an open position based on the weight of a person acting on a toilet seat. The flushing control unit is further designed to control the flushing operation based on the toilet lid position, and to block the flushing operation upon detection of the toilet lid in the open position. This makes it possible to improve both the comfort and hygienic conditions for the toilet user while using the vacuum toilet.
    Type: Grant
    Filed: November 5, 2010
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Christian Seibt, Matthias Mueller
  • Method and device for the detection of a thrust dissymmetry of an aircraft during a braking
    Patent number: 8613185
    Abstract: Disclosed is a ventilating air intake arrangement of an aircraft. The arrangement includes at least one air duct connected to an air intake orifice. At least one confined zone connects with the air duct and the air intake orifice, and the confined zone is configured in a manner in which outside air enters through the air intake orifice. A controllable mobile element modifies the flow of air entering the confined zone by varying a cross section of the air duct. A control unit is used to control the controllable mobile element, with the control unit being arranged so as to control the controllable mobile element to vary the cross section of the at least one air duct as a function of speed and altitude of the aircraft.
    Type: Grant
    Filed: June 26, 2009
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations SAS
    Inventor: Alain Dupre
  • METHOD OF COUPLING AEROFOIL SURFACE STRUCTURES AND AN AEROFOIL ASSEMBLY
    Publication number: 20130336795
    Abstract: A method of attaching first and second aerofoil sections to each other is disclosed. The method comprises the steps of: positioning one aerofoil section in an initial assembly orientation with respect to the other aerofoil section so that hinge elements on each aerofoil section are in alignment with each other, inserting a hinge shaft through said aligned hinge elements to initially couple the aerofoil sections together whilst the aerofoil sections are in their initial assembly orientation; and rotating one aerofoil section relative to the other aerofoil section about a compound angle defined by the hinge shaft into a second orientation in which the aerofoil sections are in their final, assembled orientation relative to each other. An aerofoil assembly is also disclosed.
    Type: Application
    Filed: May 31, 2013
    Publication date: December 19, 2013
    Applicant: Airbus Operations Limited
    Inventor: Simon John PARKER
  • HEAT EXCHANGER INCORPORATED INTO A WALL OF AN AIRCRAFT
    Publication number: 20130333857
    Abstract: An aircraft includes at least one wall delimiting a first zone (I) of the aircraft which is thermally insulated from the outside of the aircraft and a second zone (E) contained within the aircraft which is not thermally insulated with respect to the outside of the aircraft and a heat exchanger inside which a heat transfer fluid circulates, wherein the wall includes at least one duct inside which the heat transfer fluid circulates so as to act as a heat exchanger.
    Type: Application
    Filed: August 20, 2013
    Publication date: December 19, 2013
    Applicant: Airbus Operations SAS
    Inventors: Bernard Guering, Yves Durand
  • Method for reducing sound output at the back of a turbo engine and turbo engine improved by this method
    Patent number: 8607452
    Abstract: Disclosed is a method for producing a modified aircraft bypass turbojet engine having reduced sound output, in which the method is based on modifying an initial configuration of a rear portion of the turbojet engine to produce a modified rear portion of the turbojet engine. The modified rear portion includes a modified outer convex rear part shaped with a modified concave inner rear part that delimits an intermediate space beyond an initial cold stream outlet orifice. The intermediate space has a thickness at least equal to the thickness (E) of a sound deadening coating, which is placed in the intermediate space.
    Type: Grant
    Filed: March 17, 2008
    Date of Patent: December 17, 2013
    Assignee: Airbus Operations SAS
    Inventors: Franck Crosta, Damien Prat
  • Aircraft cooling system
    Patent number: 8608106
    Abstract: An aircraft cooling system (10) comprises a cooling element (12), which comprises a housing (14), a cooling air inlet (18) formed in the housing (14) and a plurality of heat exchangers (32, 34, 36, 38), which are disposed on lateral surfaces (24, 26, 28, 30) of the housing (14) and through which cooling air supplied through the cooling air inlet (18) may flow. A cooling air supply channel (40, 40?) connects a cooling air supply opening (44, 44?) formed in a tail section of an aircraft to the cooling air inlet (18) of the cooling element (12). A cooling air outlet channel (46) connects the heat exchangers (32, 34, 36, 38) of the cooling element (12) to a cooling air discharge opening (50).
    Type: Grant
    Filed: November 21, 2008
    Date of Patent: December 17, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Torben Baumgardt, Ralf-Henning Stolte, Volker Piezunka, Uwe Wollrab
  • System for deicing and/or defogging an aircraft surface, method for controlling same, and aircraft equipped with same
    Patent number: 8612067
    Abstract: The invention concerns a system for deicing and/or defogging an aircraft surface (4) comprising: a temperature sensor (5) located proximate said surface (4) and adapted to generate a temperature information (TPT); a computer (20) adapted to generate a control information (CMD) based on the temperature information (TPT) and to transmit the control information (CMD) over a computer network (18) of the aircraft; an electric power supply system (8) located in the electrical center of the aircraft (18) and comprising a switch (12) adapted to be switched based on the control information (CMD); a heating element (6) located proximate said surface (4) and electrically powered via said switch (12). The invention also concerns a method for controlling such a system.
    Type: Grant
    Filed: September 20, 2006
    Date of Patent: December 17, 2013
    Assignee: Airbus Operations S.A.S.
    Inventors: Joseph Leon, Jean-Yves Vilain
  • Cable raceway
    Patent number: 8609986
    Abstract: A cable raceway assembly is provided having channel sections with protrusions and clamp insertable with recesses engageable with the protrusions provide a snap-fit ratchet-type engagement.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: December 17, 2013
    Assignee: Airbus Operations Limited
    Inventor: George Edmond
  • Ergonomic and space-saving arrangement of monuments underneath a rest compartment in an aircraft
    Patent number: 8602354
    Abstract: The invention relates to a rest compartment arrangement in an aircraft, comprising a rest compartment and at least one monument, wherein the rest compartment is arranged above a cabin floor and comprises a passage that extends from a rest compartment floor in the direction of the cabin floor. When compared to the state of the art, the invention is characterized in that the at least one monument comprises at least one wall which above a seat region situated therein forms a recess to accommodate the passage. As a result of this, monuments can be positioned in a space-saving manner underneath the passage in the cabin without this resulting in reduced comfort, because the recess above the seat region is not perceived to be distracting by the passenger.
    Type: Grant
    Filed: March 11, 2009
    Date of Patent: December 10, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Thomas Sütthoff, Matthias Breuer, Felix Helfrich
  • Interface element, aircraft interior equipment component and method for installing an aircraft interior equipment component
    Patent number: 8602358
    Abstract: An interface element connects a first section of an aircraft supply system, which is provided on an aircraft interior equipment component, to a second section of the aircraft supply system and includes a carrier structure which is fastenable to the aircraft interior equipment component. Further, the interface element includes a connector element which is connectable to the first section of the aircraft supply system provided on the aircraft interior equipment component and which is mounted on the carrier structure by way of a bearing device. The bearing device includes at least one resilient bearing element which enables the connector element to be mounted such that it is movable in all three spatial directions.
    Type: Grant
    Filed: June 15, 2009
    Date of Patent: December 10, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Gerrit Pladeck, Remigiusz Kowalski, Dietmar Ströbele, Joerg Stuetzer, Stefan Knoepfle
  • Installation system for the connection of systems to a structure of an aircraft, a measurement system and a method
    Patent number: 8602357
    Abstract: An installation system includes a structure for an aircraft, at least one carrier for an arrangement of at least one device of the aircraft, at least two attachment elements configured to attach the at least one carrier to the structure, and at least one mounting having an adjustable reception element receiving one of the at least two attachment elements.
    Type: Grant
    Filed: June 22, 2010
    Date of Patent: December 10, 2013
    Assignee: Airbus Operations GmbH
    Inventor: Cihangir Sayilgan
  • Process and device for welding a thermoplastic stiffener
    Patent number: 8603279
    Abstract: The invention relates to a device for welding a stiffener to a skin. The stiffener has a stiffener foot with a bearing surface parallel to the skin surface and a stiffener flange projecting away from the plane of the bearing surface. The device includes a metallic support includes a seating surface matching the shape of the receiving side; a groove which accommodates a flange of the stiffener inserted in the groove; an insulative supporting structure for positioning a bearing surface against the receiving side; and a conformal panel for applying pressure forcing said bearing surface against said receiving side. A heater temporarily raises the temperature of bearing surface of the stiffener and the adjacent receiving side of the skin to above the melting point of the matrix when pressure is applied thereby welding the stiffener to the skin.
    Type: Grant
    Filed: October 2, 2012
    Date of Patent: December 10, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Pierric Malasse, Florian Chotard
  • Device and method for regulating the humidity of a fuel cell
    Patent number: 8606436
    Abstract: A device and a method for controlling the air humidity in a fuel cell detect a step response in the output voltage of a fuel cell when the supply to electrical loads is interrupted, and determine parameters of the dynamic time characteristic from the detected step response, and thus calculate a capacitance of the fuel cell. As a function of any deviation from a predetermined capacitance, a humidity control unit is caused to increase or decrease the humidity. This makes in situ detection of the humidity balance of a fuel cell possible, and this can keep the electrical power thereof constant for a relatively long period, and this can increase the intervals between maintenance.
    Type: Grant
    Filed: July 20, 2012
    Date of Patent: December 10, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Karsten Roederer, Hansgeorg Schuldzig
  • Mirror arrangement for monitoring a passenger cabin of an aircraft
    Patent number: 8602571
    Abstract: A mirror arrangement (10) for monitoring a passenger cabin of an aircraft is disclosed, comprising at least one mirror element (40) for reflecting light and a mirror mount (20) for fastening the at least one mirror element (40) inside the passenger cabin, the mirror mount (20) comprising a holder (22), to which the at least one mirror element (40) is fastenable and which is displaceable relative to the passenger cabin.
    Type: Grant
    Filed: July 22, 2011
    Date of Patent: December 10, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Frank Klepka, Stephan Waetzold, Wolfgang Moeller