Patents Assigned to Airbus Operation
  • 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
  • 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
  • DEVICE AND METHOD FOR PICKLING AND SIMULTANEOUSLY CHECKING A PART BY ACOUSTIC MEANS
    Publication number: 20130333475
    Abstract: A device for implementing a method for pickling/stripping and for simultaneously non-destructively checking a part (100), the device including: a. an energizing laser head capable of generating pulsed energisation (212) on the surface of a part (100, 300) according to an energy spectrum adapted for the detachment of the particles (231) adhering to the surface; b. a detection laser head (220) connected to the energizing laser head and capable of measuring the response of the part to a pulse generated by the energizing head.
    Type: Application
    Filed: January 25, 2012
    Publication date: December 19, 2013
    Applicant: AIRBUS OPERATIONS (S.A.S)
    Inventors: Hubert Voillaume, Benjamin Campagne, Franck Benthouhami
  • MOVABLE JOINING DEVICE FOR CONNECTING STRUCTURAL COMPONENTS OF AN AIRCRAFT
    Publication number: 20130334289
    Abstract: A movable joining device for connecting structural components of an aircraft, with joining means moveably arranged on a guiding device situated on the outside of the structural components so as to fixedly connect joining edges of the structural components positioned adjacent to each other, wherein the joining means includes a welding unit that can move on the rail-like guiding device, and is equipped with a special so-called bobbin tool as a tool for friction stir welding.
    Type: Application
    Filed: October 5, 2012
    Publication date: December 19, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • 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 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
  • MODULAR CABIN SEGMENT, CABIN FOR A VEHICLE AND VEHICLE WITH A CABIN
    Publication number: 20130334369
    Abstract: A modular cabin segment for a vehicle includes a first lateral segment module that accommodates a first toilet arrangement with at least one toilet compartment and a second lateral segment module, wherein in each case an outer lateral face of the first segment module and of the second lateral segment module is designed to adapt in each case to an inner wall of a cabin of the vehicle so as to correspond to the aforesaid. At least one of the modules includes at least one cabin attendant seat that on one side is held on the at least one module so that it can be pivoted on an axis. In this manner very good integration of many different functions in the manner of a construction kit is achieved in order to be able to accommodate a greater number of passenger seats elsewhere within the limited space provided in a cabin.
    Type: Application
    Filed: August 16, 2013
    Publication date: December 19, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Ralf Schliwa, Maria Strasdas
  • AIRCRAFT WITH REDUCED ENVIRONMENTAL IMPACT
    Publication number: 20130334365
    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: Application
    Filed: August 22, 2013
    Publication date: December 19, 2013
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventors: Pierre-Emmanuel Gall, Guillaume Gallant
  • METHOD FOR OPTIMISING THE DESIGN OF MANHOLE OPENINGS ON AN AIRCRAFT
    Publication number: 20130338973
    Abstract: Method for optimising the design of sealing rings of internal manhole covers which close the manhole openings over the inner surface of the skin of an aircraft structure, the surface that is in contact with the inner surface of the skin being the optimized surface of said sealing rings, the method including dividing the outer contour and the inner contour of the optimised surface into n points; grouping into families Fi the sealing rings of each manhole opening; generating the curves that are best adapted to the set of points taken for the outer contour and for the inner contour of each sealing ring for each one of the families Fi; generating a ruled surface among the curves generated for each one of the families Fi.
    Type: Application
    Filed: January 10, 2013
    Publication date: December 19, 2013
    Applicant: AIRBUS OPERATIONS S.L.
    Inventor: Airbus Operations S.L.
  • 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
  • Method of manufacture by superplastic forming and by fishplating of a rib for an aerodynamic fairing of an aircraft engine mounting pylon
    Patent number: 8607453
    Abstract: The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs (46) for an aerodynamic fairing of an engine mounting device, including: production, for each rib (46), of a given rib preform (46a) by superplastic forming; and in respect of at least one of the ribs (46) of the group having a smaller size than that of the preform (46a), division of the latter into four preform parts (56a-56d) each incorporating one of the four corners of the quadrilateral formed by the preform, followed by the joining of the four parts to one another so as to obtain the rib.
    Type: Grant
    Filed: May 25, 2011
    Date of Patent: December 17, 2013
    Assignee: AIRBUS Operations S.A.S.
    Inventors: Stephane Machado, Fabien Raison, Stephane Romani
  • 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
  • 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
  • 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
  • LEAKAGE DETECTION DEVICE AND AIRCRAFT WITH A BLEED AIR SYSTEM AND AT LEAST ONE LEAKAGE DETECTION DEVICE
    Publication number: 20130327127
    Abstract: A leakage detection device comprises a cuff of an elastic material for being circumferentially wrapped around a region of a fluid-carrying conduit, wherein the cuff has an inner surface and an outer surface, through which at least one opening extends. At least one holder that comprises at least one guide element for guiding a measuring element over the opening is arranged at the edge of the opening. In this way, the measuring element can be positioned at a predetermined radial distance from the opening.
    Type: Application
    Filed: June 8, 2012
    Publication date: December 12, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Terry OSTHUS, Stephan OETTLE
  • DEVICE FOR AN ADJUSTABLE FLAP OF A WING
    Publication number: 20130327887
    Abstract: The invention concerns a device for a adjustable flap adjustably mounted on a main wing surface of an aeroplane wing, in particular, a landing flap, with at least one adjustment unit for purposes of adjustment of the adjustable flap, which has an actuator arranged, or that can be arranged, on the main wing surface, and has a kinematic adjustment mechanism running between the actuator and the adjustable flap, wherein the adjustable flap is mechanically coupled with the actuator via the kinematic adjustment mechanism. At least one damping unit for purposes of damping a dynamic loading effected by the adjustable flap on the adjustment unit, which can occur as a result of a critical malfunction event occurring in the region of the adjustable flap, is arranged, or can be arranged, between the main wing surface and the adjustable flap.
    Type: Application
    Filed: November 26, 2012
    Publication date: December 12, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Werner DYCKRUP, Wilfried ELLMERS
  • AIRCRAFT OUTER SKIN HEAT EXCHANGER, AIRCRAFT COOLING SYSTEM AND METHOD FOR OPERATING AN AIRCRAFT OUTER SKIN HEAT EXCHANGER
    Publication number: 20130331019
    Abstract: An aircraft outer skin heat exchanger includes a first cooling air inlet and a first cooling air duct section, in which a first heat carrier fluid duct section is arranged. A cooling air conveying device is configured to convey a cooling air stream in such a way through the first cooling air inlet and the first cooling air duct section that the cooling air stream is subdivided by a first heat carrier fluid duct section, arranged in the first cooling air duct section, into two partial air streams which flow through the first cooling air duct section substantially parallel to one another and in the same direction.
    Type: Application
    Filed: May 14, 2013
    Publication date: December 12, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Markus PIESKER
  • 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
  • Dual flow turboshaft engine and improved hot flow nozzle
    Patent number: 8601788
    Abstract: An improved bypass turbojet engine includes a particularly shaped hot flow nozzle arranged about a particularly shaped type of boss. The boss is bulbous in shape and is connected by a first connecting surface to a turbine casing. The hot flow nozzle is formed as a single skin that extends in a rearward direction from an engine cowl, with the hot flow nozzle being connected to the engine cowl along a second connecting surface. The hot flow nozzle and the bulbous boss are positioned relative to one another to delimit a nominal nozzle throat section and a nominal outlet section for hot flow from a hot flow generator. The hot flow nozzle single skin is also approximately bulbous in shape and widens from the second connecting surface in a direction toward the engine cowl's external wall.
    Type: Grant
    Filed: May 22, 2008
    Date of Patent: December 10, 2013
    Assignee: Airbus Operations SAS
    Inventors: Franck Crosta, Damien Prat
  • 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