Patents Assigned to Airbus Operations
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Patent number: 8751070Abstract: Disclosed is a method and system for aiding the piloting of an aircraft to climb to a safety altitude situated above an existing low-height flight trajectory comprised of a lateral trajectory and a vertical trajectory, in which the safety altitude is the altitude of the aircraft that avoids collision of the aircraft with surrounding terrain. The aircraft is guided along the existing lateral trajectory of the low-height flight trajectory in a horizontal plane; and the aircraft is brought to the safety altitude by subjecting the aircraft to a climb mode in a vertical plane, which causes the aircraft to climb according to a climb slope which is greater than or equal to a maximum slope according to the existing vertical trajectory of the low-height flight trajectory.Type: GrantFiled: February 13, 2007Date of Patent: June 10, 2014Assignee: Airbus Operations SASInventors: Fabien Silly, Pascale Louise-Babando, Vincent Markiton
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Patent number: 8751512Abstract: A method and a device for managing information in an aircraft, including at least one device for outputting information for the crew and a plurality of equipment items adapted to transmit information items capable of being outputted on the output device. After a plurality of information items from the plurality of equipment items has been acquired and a context has been determined according to a predetermined model, the plurality of information items is filtered according to at least one rule, the at least one rule being associated with the context for selection of at least one information item. At least one selected information item is then outputted on the output device.Type: GrantFiled: September 10, 2010Date of Patent: June 10, 2014Assignee: Airbus Operations S.A.S.Inventors: Yannick Deleris, Alexandre Broquet, Fabien Pascal
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Patent number: 8746614Abstract: A method for actuating at least one positioning flap on each wing of an aircraft, which positioning flap is actuated by at least two flap coupling devices each including a flap actuator device, where at least on one flap actuator device for each positioning flap a brake mechanism is arranged by means of whose actuation an adjustment state of the respective flap actuator device can be locked, including the steps of: actuating each brake mechanism of a positioning flap individually, subsequently actuating the flap actuator device by means of the drive motor, in the case of a change in the adjustment state of the positioning flap by a predetermined extent, terminating actuation of the positioning flap concerned, and a system for implementing the method.Type: GrantFiled: December 30, 2008Date of Patent: June 10, 2014Assignee: Airbus Operations GmbHInventor: Mark Heintjes
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Patent number: 8746625Abstract: Embodiments pertain to a flap adjusting system including a regulating flap mounted on an airfoil using at least two bearing devices and movable relative to the airfoil, and an adjusting device. The adjusting device includes an actuator and adjusting kinematics with a drive rod that couples the actuator to the regulating flap using a first and a second joint, as well as a load sensor. The adjusting kinematics are configured such that, at a maximum adjustment travel of the regulating flap, the second joint between the drive rod and the regulating flap is adjusted by an angle less than 50% of the angle by which the first joint is adjusted. The load sensor is arranged in at least one adjusting device and in the second joint, which couples the drive rod to the regulating flap. The load sensor is configured to measure the forces in this load path.Type: GrantFiled: May 13, 2012Date of Patent: June 10, 2014Assignee: Airbus Operations GmbHInventors: Martin Recksiek, Stefan Greif, Robert Schwinn
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Patent number: 8747952Abstract: A coating material includes: (A) a compound of formula (I) Ra4-nSiXan??(I), wherein: Xa is a hydrolysable radical; Ra is a non-hydrolysable radical; n is 2, 3 or 4; (B) a compound of formula (II) wherein: Xb is a hydrolysable radical; Rb is a non-hydrolysable radical without an epoxide function, an acryloxy function, a methacryloxy function and an isocyanate function; Yb is a non-hydrolysable radical with a crosslinkable function; p is 2 or 3; q is 1 or 2; the sum of p and q is less than or equal to 4; (C) a crosslinking agent; (D) an organozirconium, organotitanium or organoaluminum compound containing hydrolysable organic radicals; (E) a hydrolysis catalyst; (F) crosslinkable prepolymers of epoxy and epoxysiloxane resins, (G) optional corrosion inhibitors; (H) optional compounds for reducing the reactivity of component (D); wherein n and the sum of p +q are not at the same time each 4.Type: GrantFiled: January 18, 2008Date of Patent: June 10, 2014Assignee: Airbus Operations GmbHInventors: Wolfgang Papendick, Ottmar Schramm, Dominik M Raps
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Patent number: 8745965Abstract: A flexible cable guide is provided that includes, but is not limited to a first chain link with a first longitudinal axis, a front region and a tubular first inner surface that extends in longitudinal direction, and a second chain link with a second longitudinal axis, a rear region and a tubular second inner surface that extends in longitudinal direction. The front region of the first chain link is connected to the rear region of the second chain link pivotably about a pivoting axis that extends perpendicular to the longitudinal axes of the chain links, such that it can be pivoted leftward and rightward referred to the first longitudinal axis up to a maximum pivoting angle.Type: GrantFiled: May 21, 2012Date of Patent: June 10, 2014Assignee: Airbus Operations GmbHInventors: Detlef Tiegs, Sten Gatzke
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Method and device for generating an optimum aerodynamic configuration of an aircraft during a flight
Patent number: 8746623Abstract: A process and device for the automatic flight optimization of the aerodynamic configuration of an aircraft. The device (1) includes means (7, 8, 10) for determining and applying to the spoilers (6) of the aircraft commands for providing the aircraft with an optimum aerodynamic configuration.Type: GrantFiled: February 26, 2010Date of Patent: June 10, 2014Assignee: Airbus Operations SASInventor: Frédéric Sauvinet -
Patent number: 8746611Abstract: Lightning protection arrangement for diverting a current, caused by a lightning strike, from an electronic unit which is fitted to an aerodynamic fairing of an aircraft. The device includes an electrically conductive mounting plate which is arranged on an outer side of a CFRP sandwich panel of the aerodynamic fairing. Furthermore, the device has an electrically conductive rear plate which is arranged on an inner side of the CFRP sandwich panel of the aerodynamic fairing and is connected electrically to the mounting plate. In this respect, a first group of attachment means provided for the electronic unit connects the electrical unit electrically to the rear plate. An electric current generated during a lightning strike is diverted with low resistance from the electrical unit via the rear plate and the mounting plate onto the fuselage of the aircraft.Type: GrantFiled: January 28, 2011Date of Patent: June 10, 2014Assignees: Airbus Operations GmbH, Airbus Operations (S.A.S.)Inventors: Frederic Therond, Thomas Frontzek
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Patent number: 8746615Abstract: An aircraft landing gear is arranged such that in its deployed position it is configured to reduce, during the approach on landing, the noise generated by the interaction of the landing gear and the air flowing past the landing gear. Various means are described to reduce the amount of turbulent air flow generated in the region of the landing gear, including inverting and fairing the nose-gear shock-absorbing leg, providing faired twin in-line oleos and providing fairings that produce shielding air curtains.Type: GrantFiled: August 28, 2008Date of Patent: June 10, 2014Assignee: Airbus Operations LimitedInventor: Christopher Neil Wood
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Patent number: 8746280Abstract: A controllable valve is provided for a low-flammability fluid within an aircraft with at least one magnetic coil which, upon brief electrical excitation, moves a structural element provided therein from a first position to a second position in which the structural element is held by a permanent magnet after completion of the electrical excitation of the magnetic coil.Type: GrantFiled: March 17, 2010Date of Patent: June 10, 2014Assignee: Airbus Operations GmbHInventor: Lars Hoffmann
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Patent number: 8750708Abstract: A layout apparatus for communicating includes, but is not limited to, a structural device, a first signal adjustment device and a radio device. The structural device is designed for configuring the layout of a room, and the first signal adjustment device is adapted for the electrical-optical conversion of an antenna signal. Furthermore, the first signal adjustment device and the radio device are arranged in the structural device, and the radio device is connected to the first signal adjustment device in such a manner that the antenna signal can be transmitted and/or received as a radio signal.Type: GrantFiled: June 25, 2010Date of Patent: June 10, 2014Assignee: Airbus Operations GmbHInventors: Tim Fuss, Daniel Glaser
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Patent number: 8748784Abstract: A surface heating system is provided. The surface heating system includes a heatable surface element with a supporting structure on which a conductive layer is arranged that is completely covered by a cover layer. A first induction coil is configured separately of the heatable surface element and is connectable to an AC voltage source.Type: GrantFiled: May 14, 2012Date of Patent: June 10, 2014Assignee: Airbus Operations GmbHInventors: Hans-Achim Bauer, Andre Zybala
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Publication number: 20140152088Abstract: A system for determining a cabin layout in a cabin of a vehicle, includes a system for contactless transfer of power with primary magnetic elements and secondary magnetic elements that each overlap with at least one primary magnetic element. Based on sequentially providing power to primary magnetic elements and measuring at least one electric value in the powered primary magnetic element overlapping states of secondary magnetic elements and primary magnetic elements can be determined. By determining overlapping states for all primary magnetic elements in the cabin the number and positions of all secondary magnetic elements and all vehicle components attached thereto can be collected. The system avoids powering two contiguous primary magnetic elements to prevent a wrong determination of an overlapping state.Type: ApplicationFiled: November 27, 2013Publication date: June 5, 2014Applicant: Airbus Operations GmbHInventors: Hans-Achim Bauer, Andre Zybala, Christian Rathge, Christian Koker, Gunnar Jonas
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Publication number: 20140151511Abstract: An aircraft includes at least two aircraft fuselages and two elongate main wings, wherein the main wings each have an extension direction which are at an angle to one another that differs from zero. Each of the two main wings is connected to the at least two aircraft fuselages. The main wings can thus be equipped mechanically simply and so as to have a low weight, and at the same time the transmission of forces between the wings and the fuselages is performed via a plurality of connections, and this leads to a relatively low material stress.Type: ApplicationFiled: December 4, 2013Publication date: June 5, 2014Applicant: Airbus Operations GmbHInventor: Gerd Heller
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Publication number: 20140151500Abstract: A device for intermediate fastening between an aircraft fuselage and an aircraft landing gear is provided. The device includes at least one semi-open support structure comprising a pair of webs, which are substantially parallel to each other. The webs comprise first support means intended to receive the main pivot shaft of the landing gear and second support means intended to receive the stay joint or joints of the landing gear. The device includes two support structures linked together by a central box structure. The central box structure includes a front wall, a rear wall and linking walls linking those two walls.Type: ApplicationFiled: December 2, 2013Publication date: June 5, 2014Applicant: Airbus Operations S.A.S.Inventors: Daniel Bellet, Guillaume Gallant
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Publication number: 20140151309Abstract: A water supply system includes a first pipe, a water reservoir, and a Venturi pipe having a first Venturi nozzle terminal, a second Venturi nozzle terminal and a Venturi nozzle branch arranged between the first and second Venturi nozzle terminal. The first Venturi nozzle terminal is connected via the first pipe to the water reservoir. The first Venturi nozzle terminal is connectable to a second pipe to fill the water reservoir. The branch of the Venturi pipe is connectable to a third pipe to supply taps. Water flows through the Venturi pipe from the first Venturi nozzle terminal to the second Venturi nozzle terminal when the water reservoir is filled, and water flows through the Venturi pipe from the second Venturi nozzle terminal to the Venturi nozzle branch during the supply procedure, to provide a water supply system which requires less maintenance and is less temperamental.Type: ApplicationFiled: February 7, 2014Publication date: June 5, 2014Applicant: Airbus Operations GmbHInventors: Axel Schreiner, Paolo Cavarero, Hannes Müller, Ralf Menshausen, Markus Wirth, Michael Rempe, Carlos Rosero
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Publication number: 20140150902Abstract: A valve for regulating the pressure of a gas flow in a duct according to two pressure levels includes a gate whose position is controlled by an actuator with two chambers and a first control means with a first set point pressure P1 making it possible to position the gate in a first regulated position by comparing a pressure Pav downstream of the gate and the first set point pressure P1. The valve further includes a second control means with a second set point pressure P2 making it possible to position the gate in a second regulated position by comparing the pressure Pav downstream of the gate and the second set point pressure P2 and permutation means for making the first control means or the second control means communicate alternately with one of the chambers of the actuator.Type: ApplicationFiled: December 4, 2013Publication date: June 5, 2014Applicant: Airbus Operations S.A.S.Inventor: Guillaume Pirat
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Patent number: 8740144Abstract: A passenger supply arrangement provides a communications system and comfort system for a passenger of an aeroplane. The passenger supply arrangement includes a presentation surface configured to be integrated into a backrest of a passenger seat of an aeroplane and a passenger supply module configured to be disposed above the passengers seats of the aeroplane. The passenger supply module includes at least one projector configured to project an image onto the presentation surface. The image includes a monitoring area for playback of video and an operating area for displaying and for actuation of operating elements of the passenger supply module.Type: GrantFiled: April 29, 2011Date of Patent: June 3, 2014Assignee: Airbus Operations GmbHInventors: Robert Alexander Goehlich, Holger Frauen, Cihangir Sayilgan
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Patent number: 8740148Abstract: The invention relates to a device for limiting the deflection of a door (1), particularly a hatch or a freight door, arranged in a fuselage cell (3) of an aircraft, having at least one holding element (5) arranged preferably in the region of a door jamb (4) or in the region of a door leaf edge (7). In order to ensure deflection limitation for doors, hatches and freight doors in aircraft which can be triggered manually independently of an actuation of the normal locking system, it is proposed according to the invention that the at least one holding element (5) can, if there is a sufficient pressure difference ?p between the internal pressure pi prevailing in the fuselage cell (3) and the outside air pressure pa prevailing outside of the fuselage cell (3), be brought into engagement with at least one abutment (6) arranged in the region of the door leaf edge (7) or the door jamb (4).Type: GrantFiled: October 28, 2008Date of Patent: June 3, 2014Assignee: Airbus Operations GmbHInventor: Ronald Risch
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Patent number: 8739516Abstract: The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet.Type: GrantFiled: June 19, 2007Date of Patent: June 3, 2014Assignee: Airbus Operations SASInventors: Guillaume Bulin, Patrick Oberle
