Patents Assigned to Airbus Operation
  • WATER SUPPLY WITH A BIDIRECTIONAL UV DISINFECTION DEVICE
    Publication number: 20140166566
    Abstract: A water disinfection system includes a water disinfection device, having a UV light generator for the UV treatment of water, and a water pipe, having a first pipe portion and a second pipe portion and a third pipe portion which branches off between the first and the second pipe portion. The water disinfection device includes a first water connection and a second water connection. The first water connection is connected to the first pipe portion. The second water connection is connectable to a water reservoir which is to be provided. The second pipe portion is connectable to a water source which is to be attached. The third pipe portion is connectable to a tap for water, so as to be able in this way to provide an improvement in the water quality.
    Type: Application
    Filed: February 11, 2014
    Publication date: June 19, 2014
    Applicant: Airbus Operations GmbH
    Inventors: Axel Schreiner, Paolo Cavarero, Hannes Müller, Ralf Menshausen, Markus Wirth, Michael Rempe, Carlos Rosero
  • Improved Aircraft Windshield Assembly
    Publication number: 20140166809
    Abstract: An aircraft windshield assembly includes at least one window pane, a frame against which the pane bears, at least one flange for clamping the pane against the frame, and at least one cavity delimited between the pane, the frame and the flange. A member of profiled cross-section substantially fills the cavity and over at least part of its periphery has formations in relief in the form of flutes which with a facing surface define seal-forming baffles.
    Type: Application
    Filed: December 4, 2013
    Publication date: June 19, 2014
    Applicant: AIRBUS OPERATIONS S.A.S.
    Inventor: Francis Dazet
  • Flap System For An Aircraft, Method For Adjusting The Lift Of An Aircraft And Aircraft Comprising A Main Wing And At Least One Flap System
    Publication number: 20140166819
    Abstract: A flap system for an aircraft includes a flow body, a trailing flap and a movement means. The flow body includes an upper surface and a lower surface, the lower surface having a recess. The movement means is attachable to the flow body and the trailing flap. The trailing flap includes a shape that corresponds to the recess in the lower surface. The movement means is adapted for conducting at least a chordwise movement of the trailing flap such that it is movable out of and into the recess of the flow body in absence of a gap between the leading edge of the trailing flap and the flow body. Thereby, a clear increase in a lift coefficient may be achieved, while at the same time maintaining a low complexity and a high reliability of the flap system.
    Type: Application
    Filed: December 19, 2013
    Publication date: June 19, 2014
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Efstratios Saliveros, Hendrik Friedel
  • TOILET AREA FOR AN AIRCRAFT CABIN, IN PARTICULAR FOR A FLYING WING AIRCRAFT
    Publication number: 20140165285
    Abstract: A toilet area for an aircraft cabin comprising an access door and housing a toilet bowl. The toilet area also comprises an evacuation exit, the access door occupying a closed position in the toilet area in a toilet configuration and a folded position in the toilet area in an evacuation configuration. Usage in particular in a flying wing aircraft is provided.
    Type: Application
    Filed: December 18, 2013
    Publication date: June 19, 2014
    Applicant: Airbus Operations (SAS)
    Inventors: Yves Durand, Bernard Guering
  • METHOD, APPARATUS AND COMPUTER PROGRAM PRODUCT FOR MODELLING THE NON-LINEAR STRUCTURAL RESPONSE OF A COMPONENT
    Publication number: 20140168219
    Abstract: A method, apparatus and computer program product for modeling the non-linear structural response of a component. The non-linear structural response is modeled using a two-step global-local finite element analysis method, which employs a linear global analysis step, a linear intermediate analysis step and a non-linear local analysis step. The boundary conditions applied in the intermediate step are derived in part from the linear global analysis and the boundary conditions applied in the local analysis are derived in part from the global and intermediate analyses.
    Type: Application
    Filed: December 18, 2013
    Publication date: June 19, 2014
    Applicant: AIRBUS OPERATIONS LIMITED
    Inventors: Shumit DAS, Jean Philippe NAVARRO, Martin KEMPENEERS, Vincent BOZON
  • FIBRE LAYING MACHINE COMPRISING A ROLLER WITH PIVOTING RINGS
    Publication number: 20140165337
    Abstract: A fibre laying machine includes a laying head with a roller able to pivot about an axis of rotation and to apply a plurality of preimpregnated fibres to an application surface by rolling over the application surface. The fibres are distributed along a lower generatrix of the roller and in contact with an exterior surface of the roller over an angle of wrap. The roller includes a cylindrical body, pivoting rings around the body, and means for immobilizing the pivoting rings with respect to the body in a direction parallel to the axis of rotation. The pivoting rings are able to pivot independently of one another.
    Type: Application
    Filed: December 13, 2013
    Publication date: June 19, 2014
    Applicant: Airbus Operations SAS
    Inventor: Denis De Mattia
  • Profiled Strip As A Fire Indication Device In An Aircraft
    Publication number: 20140166810
    Abstract: A door for a storage compartment of an aircraft includes a door leaf and a profiled strip connected to an edge of the door leaf. The profiled strip includes openings that provide a path for gas exchange such that smoke from the storage compartment is detectable outside of the storage compartment by passing the profiled strip.
    Type: Application
    Filed: December 16, 2013
    Publication date: June 19, 2014
    Applicant: Airbus Operations GmbH
    Inventors: Falk Bajorat, Damian Mc Nally, Christoph Augenstein, Dirk Scheffler
  • METHOD AND APPARATUS FOR PRODUCTION OF COMPOSITE PREFORM
    Publication number: 20140166195
    Abstract: A method of producing a composite preform having a profile with variable profile height or width is provided. The method includes: providing a plurality of first fibre layers overlapping or upon one another in or substantially parallel to a primary plane; inserting a second fibre layer via a guide member between two of the first fibre layers at an edge region of the preform profile, such that the second fibre layer extends substantially parallel to the first fibre layers; and positioning the edge region of the preform profile, and thus respective edge regions of the first fibre layers, out of the primary plane to set or determine a dimension of the preform profile in the primary plane.
    Type: Application
    Filed: December 18, 2013
    Publication date: June 19, 2014
    Applicant: Airbus Operations GmbH
    Inventors: Jons Velten, Adam Andrae, Niels Deschauer, Tassilo Witte
  • OVERHEAD PANEL FOR AN AIRCRAFT COCKPIT AND AIRCRAFT INCLUDING SUCH A PANEL
    Publication number: 20140168907
    Abstract: The invention relates to an overhead panel able to be positioned in an aircraft cockpit, which includes an assembly of independent submodules (67), each of which is associated with a particular system or a particular function of the aeroplane, incorporated in a rigid self-supporting module (60), including a front face (65) to which the submodules (67) are attached, and two side faces fitted with peripheral electrical connectors (63) intended to be connected to different systems of the aeroplane. The invention also relates to a method of manufacture of such a panel.
    Type: Application
    Filed: January 10, 2012
    Publication date: June 19, 2014
    Applicant: AIRBUS OPERATIONS (S.A.S.)
    Inventor: Bernard Guering
  • ELECTRONICS STRUCTURE COMPRISING AT LEAST ONE BARRIER IMPERMEABLE TO FINE PARTICLES
    Publication number: 20140168871
    Abstract: An electronics structure includes at least one barrier impermeable to fine particles, interposed between at least one Electrical and/or Electronics (“E & E”) system and the frame of the structure. The barrier delimits, with the frame and the E & E system, a first area isolated from the outside of the electronics structure. The structure makes it possible to isolate sensitive electrical and electronic components from fine particles such as dust dispersed outside the electronics structure.
    Type: Application
    Filed: December 18, 2013
    Publication date: June 19, 2014
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Philippe Pons, Pierre Salles
  • Screwing Device And Use Of A Screwing Device
    Publication number: 20140165370
    Abstract: A screwing device includes a threaded hole that extends from an insertion opening to an end of the screwing device, which end is opposite the insertion opening. In the region of the insertion opening a first radial sealing element is arranged that by way of the insertion opening extends outwards in an axial direction of the hole. Spaced apart from the first sealing element in an axial direction of the hole a second radial sealing element is arranged in the screwing device with the internal diameter of the second radial sealing element being smaller than the external diameter of the threaded hole. In this manner a screwing device may be provided that is self-locking, exchangeable, and fluid-proof and that is suitable especially for vehicles and in particular for aircraft.
    Type: Application
    Filed: December 18, 2013
    Publication date: June 19, 2014
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Gerd Stahl, Frank Moeller
  • Authentication method for an electronic document and verification method of a document thus authenticated
    Patent number: 8756428
    Abstract: A computerized authentication method of an electronic document, in particular a file designed to be on-board an aircraft. The method includes generating a digital signature of the electronic document using a private key corresponding to a public key certified by a certifying authority, and sending via the Internet a time stamp request of the electronic document to a time stamping authority and receiving in response thereto a time-stamp signed by the certifying authority. The method includes sending via the Internet a request to an Online Certificate Statute Protocol (OCSP) server and receiving in response thereto a statute of the certificate of the public key, and adding to the electronic document of the digital signature, the time-stamp and the statute of the certificate to create an authenticated electronic document.
    Type: Grant
    Filed: February 12, 2008
    Date of Patent: June 17, 2014
    Assignee: Airbus Operations SAS
    Inventors: Julien Touzeau, Olivier Bastien
  • Method and device for detecting the jamming of an aircraft control surface
    Patent number: 8755956
    Abstract: The detection device includes, but is not limited to a device that is configured to determine a control error corresponding to the difference between a first control instruction and a control surface position, a second device that is configured to calculate the difference between this control error and a second control instruction in such a way as to form a comparison signal, and a third device that is configured to detect a jamming of the control surface if this comparison signal is greater than a threshold value.
    Type: Grant
    Filed: November 8, 2012
    Date of Patent: June 17, 2014
    Assignees: Airbus Operations S.A.S., Universite Bordeaux 1, Centre National de la Recherche Scientifique
    Inventors: Philippe Goupil, Rémy Dayre, Hervé Le Berre, Anca Gheorghe, Ali Zolghadri, Jérôme Cieslak, David Henry
  • Aircraft including pieces of electrical equipment and parts made of composite material
    Patent number: 8755164
    Abstract: The aircraft includes at least one piece of equipment and a composite material part to which the equipment is connected. It is arranged in such a manner that a fault current circuit of the equipment passes via the part.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: June 17, 2014
    Assignee: Airbus Operations (S.A.S)
    Inventors: Francois Pons, Nicolas Larrose
  • System for targeted local air humidification
    Patent number: 8752772
    Abstract: In order to increase the air humidity in a cabin region of an aircraft equipped with a plurality of seats, a device includes a plurality of humidifying units each arranged in spatial association with a partial number of the seats and a plurality of outlet openings. The humidifying units are each designed to enrich a supplied air stream with gaseous water. The outlet openings are designed to emit the air streams enriched by the humidifying units into the cabin region, such that a partial number of the outlet openings each receive one of the enriched air streams. The air temperature of the enriched air streams is controlled so that the local temperature in a target region served by the humidifying unit does not fall below a dew point.
    Type: Grant
    Filed: July 30, 2009
    Date of Patent: June 17, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Christian Schumacher, Walter Kulcke, Karin Thudt, Robert Schreiber
  • Method and device for updating the position of an aircraft
    Patent number: 8755995
    Abstract: The device (1) comprises a first system (3) which comprises means (14) for calculating the vector difference between a position generated by this first system (3) and a realignment position received from a second system (4), for one and the same date-stamping, and means (16) for adding this difference to any new position of the aircraft, generated by said first system (3), so as to obtain each time a realigned position.
    Type: Grant
    Filed: October 20, 2008
    Date of Patent: June 17, 2014
    Assignee: Airbus Operations SAS
    Inventors: Philippe Haas, Stephane Dattler, Julien Nico
  • Method of manufacturing a stiffened panel
    Patent number: 8752294
    Abstract: A method of manufacturing a stiffened panel, and a datum part for use in such a method. The method comprises: holding the panel with a jig; holding a datum part with the jig; engaging the panel and the datum part with a stringer; and joining the stringer to the panel. Preferably an additive process is used to form the datum part. By growing the datum part in a series of layers, the shape of each layer can be selected to enable the shape or size of the datum part to be optimised.
    Type: Grant
    Filed: May 23, 2008
    Date of Patent: June 17, 2014
    Assignee: Airbus Operations Limited
    Inventor: Alan Minshull
  • Aircraft fuel tank ventilation
    Patent number: 8753429
    Abstract: An aircraft fuel tank ventilation system includes a dehumidifying device disposed in flow communication between a vent open to the atmosphere and a fuel tank. A method of dehumidifying air introduced into an aircraft fuel tank via a ventilation system includes directing atmospheric air through a dehumidifying device disposed in flow communication between a vent of the ventilation system and the fuel tank, which removes water vapor from the air flowing from the vent towards the fuel tank. A method of regenerating a desiccant medium used to dehumidify air introduced into an aircraft fuel tank via a ventilation system includes directing air through the desiccant medium so as to dry the desiccant medium.
    Type: Grant
    Filed: July 9, 2010
    Date of Patent: June 17, 2014
    Assignee: Airbus Operations Limited
    Inventors: Joseph K-W Lam, David Parmenter, Simon Masters
  • AIRCRAFT COMPRISING AN ONBOARD WEATHER RADAR ANTENNA PROVIDED WITH INCLINED PANELS
    Publication number: 20140159949
    Abstract: An aircraft comprising a fuselage and a radome fixed to the fuselage. The radome defines a housing and the fuselage comprises a sealed bulkhead closing the housing. A weather radar antenna comprises a main panel. A plurality of peripheral panels are arranged around the main panel, inclined from a planar surface of the main panel and located on the same side of the planar surface. The housing contains the antenna which is mounted on the fuselage through a mechanical support fixed to the fuselage and to the weather radar antenna on the same side of the planar surface as the peripheral panels. A bird strike shield is located between the antenna and the sealed bulkhead. The shield comprises a dome with a top and a base, the base being fixed to the aircraft fuselage. An opening is formed at the top of the dome through which the mechanical support passes.
    Type: Application
    Filed: December 6, 2013
    Publication date: June 12, 2014
    Applicant: Airbus Operations (SAS)
    Inventor: Christophe Mialhe
  • AIRCRAFT LANDING GEAR
    Publication number: 20140158820
    Abstract: An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.
    Type: Application
    Filed: February 11, 2014
    Publication date: June 12, 2014
    Applicant: AIRBUS OPERATIONS LIMITED
    Inventors: Fraser WILSON, Jeremy BEDARRIDES, Vladimir PLATAGEA