Patents Assigned to Airbus
  • Publication number: 20210130003
    Abstract: A torque transmission system having multiple torque transmission pathways from a driving shaft to a driven shaft. The driving shaft extends from a lower segment to an upper segment via an intermediate segment, the driven shaft extending from a first segment to a second segment. The transmission system includes a nominal spline coupling that is operational in a nominal operating mode, a backup spline coupling between the driving shaft and the driven shaft that is inactive in the nominal operating mode, and a backup radial guide device between the driving shaft and the driven shaft that is inactive in the nominal operating mode.
    Type: Application
    Filed: October 15, 2020
    Publication date: May 6, 2021
    Applicant: AIRBUS HELICOPTERS
    Inventor: Damien GOUJET
  • Publication number: 20210132103
    Abstract: A method and apparatus for estimating an airspeed of a rotorcraft by analyzing its rotor. The rotorcraft includes a fuselage and a main rotor that is equipped with a plurality of blades and that rotates about an axis of a hub of the rotor, and in which the free end or “tip” of each blade describes a path in the vicinity of a tip-path plane. The method makes it possible to determine said airspeed of the rotorcraft in a frame of reference united with the tip-path plane by solving a model of the rotor that puts a pitch angle of at least one blade relative to the tip-path plane into relation with the airspeed of the rotorcraft and with an auxiliary speed. The auxiliary speed may be an induced velocity of the air flowing through the rotor or else an axial airspeed at the upstream infinity of the rotorcraft.
    Type: Application
    Filed: October 27, 2020
    Publication date: May 6, 2021
    Applicant: AIRBUS HELICOPTERS
    Inventor: Jean-Paul PETILLON
  • Publication number: 20210130001
    Abstract: The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.
    Type: Application
    Filed: October 27, 2020
    Publication date: May 6, 2021
    Applicant: Airbus Operations SAS
    Inventors: Julien Allain, Stéphane Dida, Jérome Colmagro, Olivier Dubois, Julien Moulis, Jacky Puech, Laurent Lafont
  • Patent number: 10994678
    Abstract: A method for the automated testing of electrical cabin loads in a cabin of an aircraft comprises activating at least one electrical cabin load in a predetermined operating mode via a test controller; recording an electric power consumption profile of the at least one electrical cabin load in the activated operating mode via a power controller of an electric power distribution system of the cabin of the aircraft, wherein the power controller regulates electric power consumption of the at least one electrical cabin load within the power distribution system; transmitting the recorded power consumption profile to the test controller; and comparing the recorded power consumption profile with a reference profile for the activated operating mode of the at least one cabin load via the test controller, in order to test the at least one electrical cabin load for operability.
    Type: Grant
    Filed: May 20, 2019
    Date of Patent: May 4, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Matthias Heinisch
  • Patent number: 10994380
    Abstract: A device for manipulating a hollow shaft configured to create a pivot link between a first element and a second element. The manipulation device comprises a cylindrical body having a diameter variable by radial contraction or radial expansion of the cylindrical body, a module for controlling the diameter of the cylindrical body configured so that the diameter of the cylindrical body has alternatively at least a first diameter suitable for the cylindrical body to be displaced in the hollow shaft and a second diameter suitable for the cylindrical body to be blocked in the hollow shaft. The cylindrical body comprises an end configured to protrude from the hollow shaft when the cylindrical body is blocked in the hollow shaft. The manipulation device allows the alignment of the orifices due to the end configuration of the cylindrical body.
    Type: Grant
    Filed: November 26, 2018
    Date of Patent: May 4, 2021
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Jérôme Colmagro, Aurélien Mauconduit, Julien Moulis
  • Patent number: 10994345
    Abstract: A drilling aid system which comprises a body with a first cavity, a shaft mounted to be able to rotate within the first cavity, a slider which has a proximal end mounted to be able to move in translation within the first cavity, where the slider has a second cavity which extends the first cavity, a collar that is able to move in translation on the shaft, a first compression spring having a first stiffness and pressing against the collar and against the proximal end of the slider, and a second compression spring having a second stiffness greater than the first stiffness, and pressing against the collar and against the proximal end of the body. A system of this kind makes it possible to make the user perceive that the end of the drilling operation is nigh and that therefore the force applied to the drill should be reduced.
    Type: Grant
    Filed: January 31, 2020
    Date of Patent: May 4, 2021
    Assignee: AIRBUS OPERATIONS SAS
    Inventor: Eric Farre
  • Patent number: 10994854
    Abstract: An aerodynamic aircraft wall has external and internal surfaces and is equipped with at least one vortex generator. The vortex generator has at least one active wall projecting with respect to the external surface of the aerodynamic wall. A connecting system connects the vortex generator to the aerodynamic wall. The connecting system includes at least one support having a base pressed firmly against the internal surface of the aerodynamic wall and a head which passes through the aerodynamic wall and collaborates with the active wall, at least one first fastener connecting the base of the support and the aerodynamic wall, at least one second fastener connecting the head of the support and the active wall.
    Type: Grant
    Filed: May 14, 2019
    Date of Patent: May 4, 2021
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Erwan Krier, Grégory De Oliveira, Thomas Bourdieu, Adrien Bas
  • Patent number: 10994827
    Abstract: A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.
    Type: Grant
    Filed: May 15, 2018
    Date of Patent: May 4, 2021
    Assignees: AIRBUS OPERATIONS GMBH, AIRBUS OPERATIONS LTD.
    Inventors: Christoph Winkelmann, Wilfried Ellmers, Stephen Briancourt, David Brakes
  • Patent number: 10994862
    Abstract: A modular element for an electrical power distribution network of an aircraft comprises a section of a bus comprising connection points at different locations distributed along its length. The bus section comprises interconnection points making it possible to link the modular element to other modular elements arranged longitudinally in series with the modular element. Electrical conductors of the bus section are housed in an enclosure corresponding to a structural part of the aircraft. This enclosure comprises openings facing the connection points of the bus section, so as to allow the connection of at least one electrical equipment item of the aircraft to the bus section by means of a local electrical link.
    Type: Grant
    Filed: July 31, 2018
    Date of Patent: May 4, 2021
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Jonathan Jacquemoud-Collet, Philippe Chapoulie, Gilles Millet, Philippe Pedoussaut, Damien Aguera
  • Patent number: 10994830
    Abstract: A flap actuating system for use in an aircraft comprises a carriage for supporting and guiding a flap which is engageable with and translationally movable along at least one linear bearing rail. A linear actuator of the flap actuating system has a linearly actuatable coupling element coupled to the carriage and a drive element configured to linearly actuate the coupling element in a direction substantially parallel to a movement direction of the carriage along the linear bearing rail. The drive element is arranged substantially parallel to the movement direction of the carriage along the linear bearing rail.
    Type: Grant
    Filed: October 15, 2018
    Date of Patent: May 4, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Rainer Gartelmann
  • Patent number: 10994861
    Abstract: A refueling system, comprising a drum rotatable to wind and unwind a hose, a carriage guiding the hose and lineally displaceable along a shaft parallel to the longitudinal direction of the drum so as to follow the movement of the hose along the drum. The shaft allows the displacement of the carriage along its length. A motor is coupled to the carriage and displaces the carriage along the shaft. A first position sensor communicates with the carriage to obtain its position. A second position sensor communicates with the drum to obtain the position of the hose. A control system is coupled to the first and the second sensor, to compare their obtained positions and to operate the motor.
    Type: Grant
    Filed: November 29, 2018
    Date of Patent: May 4, 2021
    Assignee: AIRBUS DEFENCE AND SPACE SAU
    Inventors: Martin Espinosa-Sanchez, Javier Valedeolmos Traba
  • Patent number: 10994493
    Abstract: A method and an apparatus for welding a first object to a second object, wherein the first object is produced from a thermoset and comprises a thermoplastic material outer layer, wherein the second object comprises at least one thermoplastic material outer layer. In addition, a layer of carbon nanotubes is applied to the thermoplastic material outer layer of the first object, and the second object is placed onto the first object. At least some of the thermoplastic material outer layer of the second object lies atop the applied layer of carbon nanotubes. In addition, a potential is applied to the layer of carbon nanotubes, such that an electrical current flows through the carbon nanotubes, wherein the thermoplastic material outer layer of the first object and the thermoplastic material outer layer of the second object are heated and are welded to one another.
    Type: Grant
    Filed: August 24, 2018
    Date of Patent: May 4, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Peter Linde, Brian Wardle
  • Patent number: 10995737
    Abstract: A method of producing a charge separation in a plasma having a low particle density which comprises a plurality of electrons and a plurality of positive ions. The method includes generating a magnetic field and passing the plasma having a low particle density along a first axis through the magnetic field. The magnetic field is generated having a component which is perpendicular to the first axis and is configured so as to deflect the plurality of electrons from the first axis and allow the plurality of positive ions to travel substantially undeflected along the first axis. Also provided is a magnetohydrodynamic generator and a low earth orbit thruster making use of the charge separation mechanism.
    Type: Grant
    Filed: May 12, 2016
    Date of Patent: May 4, 2021
    Assignee: AIRBUS DEFENCE AND SPACE LIMITED
    Inventors: Aaron Knoll, Paolo Bianco
  • Patent number: 10994832
    Abstract: A riblet film for reducing the air resistance of aircraft, comprising a suspension with magnetic particles enclosed therein. Depending on the pattern of a magnetic field acting on the riblet film, the magnetic field that is acting can be made visible, at least in certain regions, by changing the orientation of the magnetic particles. The riblet film allows an inspection of the aircraft structure located under the riblet film through the riblet film.
    Type: Grant
    Filed: August 1, 2018
    Date of Patent: May 4, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Peter Linde, Matthias Hegenbart
  • Patent number: 10994863
    Abstract: A method of predictive determination of a power needed by a rotary-wing aircraft to perform hovering flight in order to land. After measuring the current atmospheric pressure and the current temperature outside the aircraft, the method serves to estimate a predicted atmospheric pressure and a predicted temperature at the altitude where the hovering flight is to be performed. Thereafter, both a maximum power available from a power plant of the aircraft once the aircraft has reached the point where the hovering flight is to be performed, and also a power needed from the power plant in order to perform the hovering flight are calculated. Finally, the present invention serves to display the available maximum power and the power needed on an instrument of the aircraft and thereby warn the pilot of the aircraft when the power needed is close to or even greater than the maximum power available.
    Type: Grant
    Filed: July 17, 2019
    Date of Patent: May 4, 2021
    Assignee: AIRBUS HELICOPTERS
    Inventor: Serge Germanetti
  • Patent number: 10994846
    Abstract: A functional unit in a passenger cabin includes a support unit and a passenger seat system. The passenger seat system is formed in two parts and has an upper constructional unit and a lower constructional unit that are each separate components, the upper constructional unit arranged on the support unit and containing at least one backrest, and the lower constructional unit containing a seat frame, at least one seat element and restraint for the passenger on the seat. The seat frame is fastenable to seat rails on the floor of a passenger cabin. For the use position, the upper and lower constructional units are positioned such that a passenger seat is formed. In the use position, personal comfort for the individuals on the seats is not impaired as far as possible, and the division of the seat system into two parts cannot be seen by the user.
    Type: Grant
    Filed: March 28, 2018
    Date of Patent: May 4, 2021
    Assignee: Airbus Operations GmbH
    Inventors: Sönke Jacobsen, Marcus Stahlfast, Juliane Gerken, Sven Mittelstaedt, Julian Harpenau, Fabian Nowacki
  • Patent number: 10994825
    Abstract: A panel assembly with a panel and a stringer is disclosed. The stringer has a stringer foot and an upstanding stringer web. The stringer foot has a flange which extends in a widthwise direction between the stringer web and a lateral edge and in a lengthwise direction alongside the stringer web, and a foot run-out which extends between the flange and a tip of the stringer foot. The foot run-out is bonded to the panel at a foot run-out interface. Reinforcement elements, such as tufts, pass through the foot run-out interface. At least some of the reinforcement elements are inclined relative to the foot run-out interface.
    Type: Grant
    Filed: August 9, 2018
    Date of Patent: May 4, 2021
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Vimal Jaiswal, John Woolcock
  • Patent number: 10995780
    Abstract: An assembly for arrangement to the surface of an aerodynamic profile comprises an array of actuators, which are designed as piezo actuators and plasma actuators.
    Type: Grant
    Filed: November 30, 2017
    Date of Patent: May 4, 2021
    Assignees: Airbus Defence and Space GmbH, Airbus Operations GmbH
    Inventors: Ralf Caspari, Robert Weichwald, Emanuel Ermann, Gerd Heller, Detlev Konigorski, Stefan Schnäubelt, Nicole Jordan
  • Patent number: 10995529
    Abstract: A safeguarding arrangement for restricting the movability of at least one transport container storable or stored in a support structure receptacle. The transport container may be used for transporting goods, for example, in an aircraft, and may be stowed in the aircraft's galley area as a trolley. The safeguarding arrangement has a first safeguarding installation with at least one first safeguarding arrangement. The at least one first safeguarding arrangement allows the insertion or removal of the at least one transport container into the receptacle or from the receptacle, respectively, in its open position via an opening. The safeguarding arrangement overlaps a clean measure of the opening of the receptacle, at least zonally, in a hold position, in which the at least one transport container is held against removal from the receptacle. Further, the first safeguarding arrangement is formed variably with regard to its engagement depth into the receptacle.
    Type: Grant
    Filed: December 12, 2017
    Date of Patent: May 4, 2021
    Assignees: AIRBUS OPERATIONS GMBH, AIRBUS SAS
    Inventors: Craig Hogg, Krischan Bolle, Thomas Sütthoff, Daniel Hinrichs
  • Patent number: D917906
    Type: Grant
    Filed: September 17, 2019
    Date of Patent: May 4, 2021
    Assignee: AIRBUS INTERIORS SERVICES SAS
    Inventor: Bruno Cousin