Patents Assigned to Airbus Helicopters
  • Actuating system for an actuatable door and an actuatable door having such an actuating system
    Patent number: 10526064
    Abstract: An actuating system for an actuatable door that comprises at least one latching device with a latching hook that is adapted for locking the actuatable door in a closed position, the latching hook being pivotally mounted to an associated pivot bearing and connected to a pivotable mechanical transmission element via a coupling link, which is pivotally mounted to the latching hook and to the pivotable mechanical transmission element, the pivotable mechanical transmission element being coupled to a rotatable latching shaft, wherein rotation of the rotatable latching shaft in operation results in pivoting of the pivotable mechanical transmission element and pivoting of the latching hook around the associated pivot bearing, wherein the pivotable mechanical transmission element is mounted onto the rotatable latching shaft. The invention is further related to an actuatable door having such an actuating system.
    Type: Grant
    Filed: January 13, 2016
    Date of Patent: January 7, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Darko Starman
  • Aircraft autopilot system and method, and an aircraft
    Patent number: 10528046
    Abstract: An autopilot system comprising an onboard unit. The onboard unit has a plurality of sets of sensors that are redundant and mutually independent, together with a plurality of calculation channels, each calculation channel being connected to the sensors of one of the sets of sensors and receiving data coming from the sensors. A supervisor is connected to the sensors of a set of sensors, the supervisor having the function of coupling at most one of the calculation channels to the control members, the supervisor having the function of decoupling the coupled channel from the control members in the event that the current behavior of the aircraft departs from predetermined predicted behavior.
    Type: Grant
    Filed: February 8, 2018
    Date of Patent: January 7, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventor: Thierry Vieux
  • Multi-blade rotor for a rotary wing aircraft
    Patent number: 10518874
    Abstract: A multi-blade rotor for a rotary wing aircraft, comprising a plurality of rotor that is connected to an associated rotor head via a plurality of flexbeam elements, wherein at least one flexbeam element of the plurality of flexbeam elements comprises an asymmetrical flexbeam root that is mounted to the associated rotor head.
    Type: Grant
    Filed: May 17, 2017
    Date of Patent: December 31, 2019
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Gerald Kuntze-Fechner, Martin Ortner, Victoria Otto, Christeline Salmon, Eugen Rink, Rupert Pfaller
  • Electric control member, a rotary wing aircraft, and a method
    Patent number: 10518870
    Abstract: An electric control device having manipulation means. The electric control device has a first measurement system and a second measurement system respectively taking a first measurement and a second measurement of the current position of the manipulation means. A processor unit compares the first and second measurements in order to generate a control signal as a function of said current position, said processor unit considering that the manipulation means are in a neutral position when the first and second measurements do not correspond to the same position for the manipulation means.
    Type: Grant
    Filed: October 9, 2017
    Date of Patent: December 31, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Marc Salesse-Lavergne, Kamel Abdelli, Olivier Sellier, Jean-Romain Bihel
  • MODULAR SUBFLOOR ARRANGEMENT FOR AN AIRCRAFT
    Publication number: 20190389592
    Abstract: A modular subfloor system comprises first longitudinal structural frames, lateral regions, and a modular tank system that is connected to the first longitudinal structural frames. The modular tank system comprises a bottom shell, an upper panel, second longitudinal structural frames arranged between the bottom shell and the upper panel and transversal structural frames that are arranged between the bottom shell and the upper panel. The transversal structural frames and the second longitudinal structural frames form compartments. The modular tank system further comprises tank bladders arranged in at least some of the compartments and sealing elements that seal the upper panel, the bottom shell, and the at least some of the compartments of the modular tank system.
    Type: Application
    Filed: June 18, 2019
    Publication date: December 26, 2019
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Gottfried HUEBNER, Stefan PROBST, Frank LOESER, Robert SEILER
  • METHOD AND A DEVICE FOR LIMITING TORQUE ON A ROTORCRAFT HAVING AT LEAST THREE MOTORS WITH NON-EQUAL POWER DISTRIBUTION
    Publication number: 20190382124
    Abstract: A method for limiting torque on a rotorcraft. The rotorcraft comprises an installation having a rotor, the installation including at least three motors driving a power transmission gearbox, the MGB including a rotor mast for moving the rotor. The method comprises a step of determining a engine torque limit for each of at least the three motors, each engine torque limit being established by a control computer of the aircraft by taking into consideration the distribution among the at least three motors of the total power (Ptot) delivered by the at least three motors for enabling the rotorcraft to operate.
    Type: Application
    Filed: June 12, 2019
    Publication date: December 19, 2019
    Applicant: AIRBUS HELICOPTERS
    Inventors: Lucie MASSOT, Valerie TROUILLET
  • Adaptive flight control system for the yaw and thrust flight controls of a hybrid helicopter
    Patent number: 10507905
    Abstract: An adaptive flight control system for controlling the pitch of blades of a propulsive propeller of a hybrid helicopter as a function of the return value of the pitch. The adaptive flight control system comprises control means supplying the pitch control order, a piloting member controlling variation of the pitch, and piloting means applying a control gain in order to transform the control order into a setpoint, and transmitting the setpoint to the piloting member. The piloting means include information return means applying a return gain that is variable to the return value of the variation of the pitch to the piloting means, also modifying the control gain as a function of the return value.
    Type: Grant
    Filed: November 16, 2016
    Date of Patent: December 17, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Jean-Romain Bihel, Arnaud Groll, Romuald Biest, Zouhair Sassi
  • Rotary wing aircraft with a structural arrangement that comprises an electrically conductive connection
    Patent number: 10507491
    Abstract: A rotary wing aircraft that comprises a structural arrangement with at least one first fiber reinforced polymer component and at least one second fiber reinforced polymer component that are spaced apart from each other by an interspace and that are rigidly attached to an associated structural component, wherein the at least one first fiber reinforced polymer component and the at least one second fiber reinforced polymer component are at least partly interconnected by means of an electrically conductive connection, and wherein the electrically conductive connection comprises at least one sprayed layer of electrically conductive particles, the at least one sprayed layer of electrically conductive particles being provided in the interspace.
    Type: Grant
    Filed: September 27, 2017
    Date of Patent: December 17, 2019
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Andreas Rack, David Rosplesch, Dietrich Jonke
  • HYDROELASTIC DAMPER, AND AN AIRCRAFT
    Publication number: 20190367163
    Abstract: A hydroelastic damper comprising at least a first resilient assembly that is provided with a first inner strength member engaged at least in part in a first outer strength member, a first resilient member providing resilient return for the first outer strength member and the first inner strength member towards a rest position (POSREP). The hydroelastic damper comprises at least one hydraulic assembly provided with a first hydraulic chamber and a second hydraulic chamber in communication with each other via a connection provided in a first wall of the hydraulic assembly. A first floating piston is movable at least in translation along the longitudinal axis relative to the first inner strength member and to the first outer strength member, the first hydraulic chamber being defined at least by the first floating piston and the first wall in order to protect the first resilient member.
    Type: Application
    Filed: May 29, 2019
    Publication date: December 5, 2019
    Applicant: AIRBUS HELICOPTERS
    Inventors: Jean-Romain BIHEL, Damien SEQUERA, Jean-Pierre JALAGUIER
  • METHOD AND A DEVICE FOR DETERMINING AND DISPLAYING A FLYAWAY DISTANCE FOR A ROTORCRAFT WHILE TAKING ACCOUNT OF THE HEIGHT OF WAVES
    Publication number: 20190360805
    Abstract: A method and a device for determining and displaying a flyaway distance for a rotorcraft in the event of an engine of the rotorcraft failing, and while taking account of the height of waves being overflown by the rotorcraft. The method includes a first determination for determining a flyaway distance of the rotorcraft in the event of a failure of an engine and under current flying conditions, a second determination for determining a maximum altitude of the waves being overflown by the rotorcraft and displaying the flyaway distance and the maximum altitude on a display instrument of the rotorcraft indicating the relative height of the rotorcraft or else its altitude. A safety margin is preferably added to the maximum altitude of the waves, or else to the flyaway distance of the rotorcraft.
    Type: Application
    Filed: May 22, 2019
    Publication date: November 28, 2019
    Applicant: AIRBUS HELICOPTERS
    Inventor: Marc SALESSE-LAVERGNE
  • Maintenance step for a helicopter
    Patent number: 10486790
    Abstract: A maintenance step for a helicopter, comprising: a casing that is adapted for integration into a lateral shell of a fuselage of a helicopter, and a step member that is pivotally mounted to the casing, wherein a stirrup unit is pivotally mounted to the step member, the stirrup unit comprising at least a first and a second section, the second section being telescopically mounted to the first section.
    Type: Grant
    Filed: October 27, 2016
    Date of Patent: November 26, 2019
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GmbH
    Inventors: Christoph Steindl, Dominik Strobel
  • Flapping abutment mechanism for a lift assembly, a rotorcraft rotor including the abutment mechanism, and a rotorcraft
    Patent number: 10486804
    Abstract: An abutment mechanism for a lift assembly of an aircraft. The abutment mechanism comprises a single rigid link having variable travel, the link comprising a rod and a body, the rod being movable in translation relative to the body along the longitudinal direction through said travel, the abutment mechanism including a movement member for adjusting an amplitude of the travel as a function of at least one predetermined parameter, the link having two endpieces suitable for being hinged respectively to a said lift assembly and to a said drive system.
    Type: Grant
    Filed: March 24, 2016
    Date of Patent: November 26, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventor: Fabien Massal
  • Propeller assembly with at least two propeller blades
    Patent number: 10486794
    Abstract: A propeller assembly with at least two propeller blades that are interconnected by associated connection means, the associated connection means defining a common pitch axis for the at least two propeller blades in operation, each one of the at least two propeller blades comprising associated leading and trailing edges that define a respective chord and quarter chord line thereof, wherein the common pitch axis is arranged with a predetermined offset relative to the quarter chord line of each one of the at least two propeller blades, and wherein the associated connection means is adapted to enable, at least in operation in a non-axial inflow field, a passive pitch adjustment of the at least two propeller blades around the common pitch axis.
    Type: Grant
    Filed: March 28, 2017
    Date of Patent: November 26, 2019
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Uwe Kiesewetter, Stefan Haisch, Marius Bebesel, Sebastian Mores
  • Rotorcraft tail rotor, a rotorcraft fitted with such a tail rotor, and a method of statically and/or dynamically balancing a rotorcraft tail rotor
    Patent number: 10479494
    Abstract: A rotorcraft tail rotor comprising at least two blade elements, each blade element being suitable for pivoting about a collective pitch variation axis Z in order to vary the collective pitch of each blade element of the tail rotor, each blade element including at least one compensation weight comprising a projection emerging substantially perpendicularly to a main inertia axis of the blade element, the main inertia axis being parallel to a longitudinal direction of the blade element. In the invention, the tail rotor is wherein the compensation weight includes a deformable portion that is movable relative to the projection in a plane P that is parallel to the main inertia axis of the blade element.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: November 19, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Bernard Certain, Jeremy Jouve
  • Damper device and an aircraft
    Patent number: 10479493
    Abstract: A damper device provided with a first connection member, a second connection member, a resilient member, and a hydraulic system. The hydraulic system includes an outer casing and a rod, the first connection member being fastened in reversible manner to the outer casing, the resilient member being arranged around a projecting portion of the rod, the resilient member comprising at least one resilient means interposed between a first strength member and a second strength member, the first strength member being fastened in reversible manner to the outer casing, the second strength member being constrained to move in translation with the projecting portion, and the connection member being fastened in reversible manner to the projecting portion.
    Type: Grant
    Filed: August 8, 2016
    Date of Patent: November 19, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Damien Sequera, Jean-Pierre Jalaguier, Wojciech Gregorczyk
  • External anchoring harpoon for aircraft
    Patent number: 10479527
    Abstract: An external anchoring harpoon for an aircraft in order to anchor the aircraft on an anchor grid of a platform, the external anchoring harpoon comprises a frame connected to the aircraft, a harpoon head, and a deployment device for deploying the harpoon head. The deployment device comprises a cable, a movement device for moving the cable connected to the frame, the cable being connected to the harpoon head and to the movement device. The deployment device also comprises a main telescopic strut and two secondary telescopic struts so as to enable the harpoon head to be centered under the aircraft and so as to enable the harpoon head to be anchored to the anchor grid.
    Type: Grant
    Filed: September 25, 2017
    Date of Patent: November 19, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Olivier Bistuer, Jean Paul Renaud, Patrice Garcin, Pierre Prud'Homme Lacroix
  • Aircraft provided with a winch device
    Patent number: 10479502
    Abstract: An aircraft provided with a wing and a winch device. The winch device is provided with a hoist device that includes a storage drum and a motor member for winding a suspension member around the storage drum and for unwinding said suspension member off the storage drum. The hoist device is surrounded at least in part by a fairing of the winning, said hoist device being arranged in an inside volume of the wing at least in a position referred to as the “streamlined” position.
    Type: Grant
    Filed: May 24, 2017
    Date of Patent: November 19, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventor: Andre Barbieri
  • Jumpseat, and a vehicle provided with the jumpseat
    Patent number: 10479508
    Abstract: A jumpseat having a carrier structure comprising at least one seat pan. The jumpseat comprises a mounting structure provided with at least two arms having at least one degree of freedom to move in rotation about a stowage axis, said carrier structure being hinged to each arm by a pivot arrangement, said pivot arrangement being hinged to each arm about a folding axis, the folding and stowage axes being parallel to each other, said pivot arrangement giving the carrier structure at least one degree of freedom to move in rotation relative to the arms about an elevation axis.
    Type: Grant
    Filed: July 7, 2017
    Date of Patent: November 19, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventor: Jean-Francois Joffre
  • Rotor and an aircraft provided with such a rotor
    Patent number: 10479492
    Abstract: A rotor comprising a hub and a plurality of lift assemblies. Each lift assembly is connected to two adjacent lift assemblies respectively by a first damper and a second damper. The first damper is hinged to a lift assembly about a first axis, and the second damper is hinged to said lift assembly about a second axis. A first plane contains a lead-lag axis of the lift assembly and orthogonally to the pitch axis of the lift assembly. The first axis is situated in a volume lying between the first plane and an axis of rotation of the rotor, the second axis being positioned outside said volume.
    Type: Grant
    Filed: June 27, 2017
    Date of Patent: November 19, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Olivier Honnorat, Jean-Pierre Jalaguier
  • Resonator, and an aircraft fitted with the resonator
    Patent number: 10472055
    Abstract: A resonator having a support and a seismic mass. Movement means include a first electromagnetic assembly comprising a first electric coil that is not electrically powered. An actuator is connected to a processor unit, the processor unit electrically powering the actuator with adjustable electrical power. A resilient member is interposed between said seismic mass and said support.
    Type: Grant
    Filed: June 1, 2017
    Date of Patent: November 12, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Guillaume Inquiete, Paul Cranga, Simon Chesne