Patents Assigned to AIRBUS HELICOPTER
  • Patent number: 10710709
    Abstract: A mechanical system for transmitting rotary motion between at least two shafts movable in rotation respectively about a first axis and a second axis, the first and second axes intersecting, the mechanical system including a bevel gear set made up of a first bevel gear having teeth and movable in rotation about the first axis and a bevel wheel having teeth and movable in rotation about the second axis, the teeth of the first bevel gear and of the bevel wheel respectively being suitable for co-operating in complementary manner with one another, the first bevel gear, referred to as a “power” gear, presenting a first defining pitch surface of conical shape, and the bevel wheel presenting a second defining pitch surface of conical shape.
    Type: Grant
    Filed: September 11, 2017
    Date of Patent: July 14, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventors: Olivier De Meerschman, Matthias Gatti
  • Patent number: 10710156
    Abstract: A method of fabricating parts out of metallic, intermetallic, ceramic, ceramic matrix composite, or metal matrix composite material with discontinuous reinforcement, includes melting or sintering powder particles by means of a high-energy beam. The powder used is a single powder of particles that present sphericity lying in the range 0.8 to 1.0 and of form factor lying in the range 1 to ?2, each powder particle presenting substantially identical mean composition, and the grain size distribution of the particles of the powder is narrowed around the mean diameter value d50% in such a manner that: (d90%?d50%)/d50%?0.66; and (d50%?d10%)/d50%?0.33; with a “span”: (d90%?d10%)/d50%?1.00.
    Type: Grant
    Filed: June 30, 2014
    Date of Patent: July 14, 2020
    Assignees: SAFRAN AIRCRAFT ENGINES, EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCE, AIRBUS HELICOPTERS
    Inventors: Christophe Colin, Laetitia Kirschner
  • Patent number: 10712424
    Abstract: An aircraft, to a system, and to a method of geolocation for calculating the current coordinates at least in longitude and in latitude of a current position of an aircraft. Such an invention makes it possible to calculate the current coordinates in latitude and in longitude corresponding to the current position of the aircraft on the basis firstly of first and second coordinates in latitude and in longitude of two ground stations and secondly of first and second transmission directions of the radio signals.
    Type: Grant
    Filed: March 1, 2019
    Date of Patent: July 14, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventor: Herve Dutruc
  • Patent number: 10711487
    Abstract: An aircraft with a plurality of aircraft doors, each aircraft door comprising at least one lock lever that is provided for engaging a counterpart in an engaged state for locking a respective aircraft door relative to the aircraft, wherein a real-time monitoring device is provided for generating a real-time representation of the at least one lock lever and the counterpart, the real-time representation being suitable for determining whether the at least one lock lever is in the engaged state.
    Type: Grant
    Filed: October 16, 2017
    Date of Patent: July 14, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Stephen Ward
  • Publication number: 20200217658
    Abstract: A method of assisting in piloting an aircraft having a fuselage, the aircraft having a first side arrangement and a second side arrangement, which arrangements are disposed laterally on either side of the fuselage, and each of them participates in the movement of the aircraft. During an assistance phase, the method includes the following steps: measuring a value of a first ground clearance of the first side arrangement and a value of a second ground clearance of the second side arrangement; and displaying on a screen at least one symbol that varies as a function of the variation in the value of the first ground clearance and/or of the variation in the value of the second ground clearance.
    Type: Application
    Filed: December 5, 2019
    Publication date: July 9, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventor: Kamel ABDELLI
  • Publication number: 20200216169
    Abstract: A bracket for connecting a traverse of a landing gear to a cabin of a helicopter. A landing gear retainer is fixed around the traverse coaxially to the longitudinal direction of the traverse and at least one cabin clamp mount is fixed to the cabin. The landing gear retainer is in between the cabin and upper and lower pendulum bolts and upper and lower pendulum bearings. A pendulum is in longitudinal direction of the traverse hinged to the landing gear retainer. The invention is further related to an application of such brackets.
    Type: Application
    Filed: March 17, 2020
    Publication date: July 9, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Kaspar VON-WILMOWSKY, Johannes MARKMILLER
  • Publication number: 20200217968
    Abstract: An aircraft with a safety distance display apparatus that is configured to display a visual indication on an obstacle for representing a current distance between the aircraft and the obstacle, wherein the safety distance display apparatus comprises a first light source that emits a first light signal in a first predefined direction, and a second light source that emits a second light signal in a second predefined direction, and wherein the first light signal crosses the second light signal at a predetermined safety distance from the aircraft.
    Type: Application
    Filed: November 19, 2019
    Publication date: July 9, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Lieven DESMET
  • Patent number: 10695995
    Abstract: A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of: Preparing a repair patch; Arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; Pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and Fixing the repair patch in the inappropriate countersink.
    Type: Grant
    Filed: May 26, 2017
    Date of Patent: June 30, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Thomas Joachim, Andreas Rack, Josef Lindenmeier, Tim Schoenicke
  • Publication number: 20200200233
    Abstract: An epicyclic gear train comprising a sun gear, an outer ring gear, and a plurality of planet gears carried by a common planet carrier. The planet carrier comprises a support and a plurality of spindles carried by the support, each spindle having a carrier segment extending away from the support to a distal end, each planet gear being arranged around a the carrier segment. Each distal end is separated from another distal end that is adjacent thereto by a distance, and the epicyclic gear train includes a holder system for maintaining the distance within a predefined range regardless of the force applied to each spindle.
    Type: Application
    Filed: December 20, 2018
    Publication date: June 25, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventor: Michel VIALLE
  • Patent number: 10683087
    Abstract: A shrouded rotor assembly for an aircraft. The shrouded rotor assembly comprises a stator hollow structure comprises formed from a plurality of composite angular segments. Each composite angular segment includes: a core arched section of a central hub casing, a peripheral rim section of an external hollow duct and a pair of angularly opposed sliced portions, respectively for one of a pair of guide vanes. The resulting stator hollow structure is a unitary one-piece, integrating together continuously the composite angular segments. The invention typically applies e.g. to aircrafts such as rotary wing aircrafts.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: June 16, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Stefan Probst, Marc Nothen, Christian Wehle
  • Publication number: 20200183396
    Abstract: An industrial activity drone comprising an aerial vehicle having at least one rotor, an activity system, and a fastener device for fastening the activity system to the aerial vehicle. The activity system includes a structure, a computer, a work camera that is stationary relative to the aerial vehicle and that provides a view of a work zone, a distribution device having a plurality of compartments, and a turning motor enabling the distribution device to turn relative to the aerial vehicle. The industrial activity drone performs hovering flight so that the work camera faces a work zone and the distribution device is turned so that the compartment that is to be used faces the work zone, thereby performing one or more tasks.
    Type: Application
    Filed: December 11, 2018
    Publication date: June 11, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventors: Gauthier GIBERT, Nicolas IMBERT
  • Publication number: 20200182160
    Abstract: A regulator device for automatically regulating a power plant of a rotary wing aircraft having a turbine engine includes a computer system. The computer system, while implementation of an idling mode of operation of the turbine engine is requested and the aircraft is standing on ground, implements the idling mode of operation and operates the turbine engine in compliance with idling mode of operation as a function of operational and hierarchically ordered conditions either through a first mode of regulation by regulating a speed of rotation (Ng) of a gas generator of the turbine engine or through a second mode of regulation by regulating a speed of rotation (NTL) of a free turbine of the turbine engine.
    Type: Application
    Filed: October 15, 2019
    Publication date: June 11, 2020
    Applicant: Airbus Helicopters
    Inventor: Alban Corpron
  • Publication number: 20200180773
    Abstract: An attachment for attaching an aircraft engine with a first receiving element to an aircraft structure with a second receiving element may include at least three fasteners and a stacked layer. Stacked layer may include at least two sheets, at least three holes through the stacked layer, a first connecting portion that includes a first hole of the at least three holes, a second connecting portion that includes second and third holes of the at least three holes, and a suspension portion that is located between the first connecting portion and the second connecting portion.
    Type: Application
    Filed: October 17, 2019
    Publication date: June 11, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Martin BLACHA, Marc SCHELCHER, Adriana GARCIA RIOS
  • Publication number: 20200180748
    Abstract: A vehicle with a vehicle frame and a windshield assembly that is mounted to the vehicle frame and closes an associated opening provided in the vehicle frame. The windshield assembly comprises at least one flexible element and at least one windshield. The at least one flexible element connects the at least one windshield to the vehicle frame for at least partially absorbing loads resulting from an impact on the at least one windshield. The at least one flexible element connects the at least one windshield to the vehicle frame such that the at least one windshield pivots relative to the vehicle frame by means of the at least one flexible element upon occurrence of an impact on the at least one windshield such that the at least one flexible element defines a hinge element.
    Type: Application
    Filed: October 7, 2019
    Publication date: June 11, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Christian REICHENSPERGER, Mikko SCHNIZER, Lars WOLTERS
  • Publication number: 20200180755
    Abstract: The present invention relates to a hybrid helicopter comprising a fuselage, a main rotor, two wings situated on either side of said fuselage, and two propulsion propellers situated respectively on each wing. Each propulsion propeller is inclined, and when it rotates it generates a thrust force (Fd, Fg) along a thrust axis (Pd, Pg) that is inclined relative to a longitudinal direction (X) of said hybrid helicopter. As a result, a longitudinal component and a transverse component of said thrust force (Fd, Fg) of each propulsion propeller act, during hovering flight of said hybrid helicopter, to generate respective torques that combine to form a moment (Mstat) opposing a yaw torque (CR) of said hybrid helicopter.
    Type: Application
    Filed: December 11, 2018
    Publication date: June 11, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventor: Pierre PRUD'HOMME LACROIX
  • Publication number: 20200173372
    Abstract: A method and a system for stopping a gas turbine comprising a gas generator provided with rotary members and a combustion chamber. The gas turbine includes a fuel circuit controlled by calculation means in communication with a selector. The method includes a step of closing of the fuel circuit on order of the calculation means when the selector is positioned in a first position for causing the gas turbine to stop. If the gas turbine was not idling prior to the closure, or if it was idling, but for a length of time shorter than a threshold, then an electrical machine automatically rotates the rotary members for a limited duration.
    Type: Application
    Filed: November 26, 2019
    Publication date: June 4, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventors: Damien MARIOTTO, Stephane CERQUEIRA
  • Publication number: 20200172224
    Abstract: An aircraft of a modular type including: at least one rotor suitable for providing in full or in part propulsion and/or lift for the aircraft; at least one power plant of the combustion engine type or of the electric motor type; a main gearbox, for mechanically transmitting drive torque generated by the at least one power plant to the at least one rotor; and an avionics system for assisting in piloting the aircraft. In accordance with the invention, the avionics system is configured for automatically providing the assistance in piloting the aircraft when the aircraft has a first power plant only or when the aircraft has a first power plant and a second power plant.
    Type: Application
    Filed: November 19, 2019
    Publication date: June 4, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventor: Marc GAZZINO
  • Publication number: 20200164972
    Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight thrust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.
    Type: Application
    Filed: October 17, 2019
    Publication date: May 28, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Uwe KIESEWETTER, Christian REICHENSPERGER, Lukasz PALUSZEK, Klaus KICKER
  • Patent number: 10661890
    Abstract: A blade of a rotor for a rotary-wing aircraft is equipped with an outer covering extending along the span of the blade. This outer covering is provided with an extrados skin and with an intrados skin defining a cavity. The blade also includes a structure that extends into the cavity and connects the blade to a hub of the rotor. The cavity is filled with a filling material that includes at least one partition parallel to a chord of the blade and at least two independent blocks of filling material filling the cavity, thereby allowing the reduction of the torsional rigidity along the span of the blade.
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: May 26, 2020
    Assignee: Airbus Helicopters
    Inventors: Damien Reveillon, Laurent Bianchi
  • Patent number: 10655021
    Abstract: A method of fabricating an electrically conductive loaded powder of thermoplastic polymers. The method comprises the steps of making an original powder containing cores made of thermoplastic polymers and of making the loaded powder by using electrically conductive submicrometer filaments and wax, forming a plurality of particulate compounds each comprising one of the cores together with at least one of the filaments and a protective membrane of the wax.
    Type: Grant
    Filed: April 19, 2018
    Date of Patent: May 19, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventor: Philippe Joedicke