Patents Assigned to Airbus Helicopters
  • Method for constructing a rotor blade intended for a rotorcraft, blade and rotorcraft
    Patent number: 11691719
    Abstract: A blade in which the aerodynamic profiles of a blade root, a blade neck and a central part of a profiled zone of the blade respectively comprise a leading edge section and a trailing edge section that are symmetrical to each other relative to an axis of symmetry. The present disclosure also concerns a method for constructing such a blade. The axis of symmetry is perpendicular to a segment connecting the leading edge to the trailing edge of each profile and is positioned in the middle of the segment. An intermediate upper surface section and an intermediate lower surface section connect the leading edge section and the trailing edge section in order to respectively form a lower surface of the aerodynamic profile.
    Type: Grant
    Filed: May 24, 2021
    Date of Patent: July 4, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Alexandre Madeira, Francois Malburet, Lionel Roucoules
  • Method and a system for monitoring a lubricated mechanical system
    Patent number: 11691762
    Abstract: A method and a system for monitoring a mechanical system, the mechanical system including a lubrication system provided with a reservoir containing a lubricating liquid, with a lubrication circuit designed to lubricate the mechanical system, as well as with a particle detection device arranged in the lubrication circuit. The detection device makes it possible, in particular, to count the number of particles flowing through the lubrication circuit and/or the flow rate of the particles. Comparing that number or that flow rate with a first threshold makes it possible to determine a risk of damage affecting the mechanical system and to anticipate the maintenance or reinforced monitoring operations that possibly need to be performed.
    Type: Grant
    Filed: September 10, 2020
    Date of Patent: July 4, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventor: Gilles Belhabib
  • ACTUATOR FOR AVIATION APPLICATIONS
    Publication number: 20230202649
    Abstract: An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.
    Type: Application
    Filed: April 15, 2021
    Publication date: June 29, 2023
    Applicant: AIRBUS HELICOPTERS TECHNIK GMBH
    Inventors: Jan Haar, Uwe Arnold, Martin Meunier, Carsten Wintjen, Matthias Müller, Werner Pflüger
  • ROTARY WING AIRCRAFT WITH AT LEAST TWO ROTORS AND A PROPULSION UNIT
    Publication number: 20230192279
    Abstract: A rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; and a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition.
    Type: Application
    Filed: November 17, 2022
    Publication date: June 22, 2023
    Applicants: AIRBUS HELICOPTERS, AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Jerome GENEIX, Mikolaj LUSZCZYNSKI
  • HUMAN AND/OR NON-HUMAN CARGO ATTACHMENT DEVICE FOR USE WITH A ROTORCRAFT
    Publication number: 20230183044
    Abstract: A human and/or non-human cargo attachment device for a rotorcraft. The device comprises a mounting interface with a carrier device and an attachment that is rigidly mounted to the carrier device for attachment to a rotorcraft rope or cable. A device body is mounted to the carrier device. The device body has a stationary body section and a movable body section. The stationary body section is stationarily arranged on the carrier device and comprises a plurality of rotatable attachment hooks for attachment of human or non-human external cargo. The movable body section is movably arranged on the carrier device for enabling movements of the movable body section relative to the stationary body section between a locking position and a release position.
    Type: Application
    Filed: November 16, 2022
    Publication date: June 15, 2023
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Christoph HEIDER, Dominik VOGEL, Stefan SALZBURGER, Alexandru DINCA
  • Method for controlling a hybrid helicopter in the event of an engine failure
    Patent number: 11673680
    Abstract: The present invention relates to a control method in case of engine failure of a hybrid helicopter having a power plant connected to at least one lift rotor and to at least one propeller, said lift rotor having a plurality of first blades and said at least one propeller having a plurality of second blades. The method comprises the following steps: (i) measuring a forward speed of the hybrid helicopter, (ii) on condition that said forward speed is greater than a first speed threshold and that each engine has failed, automatically implementing a first emergency piloting mode comprising a step for automatic reduction by an automatic piloting system of a pitch of said second blades toward an objective pitch making said at least one propeller produce a motive power which is transmitted to the lift rotor.
    Type: Grant
    Filed: December 4, 2020
    Date of Patent: June 13, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Paul Eglin, Remy Huot, Antoine Conroy
  • LUBRICATING LIQUID MANIFOLD FOR A CRANKPIN OF AN EPICYCLIC GEAR TRAIN, GEARBOX AND AIRCRAFT
    Publication number: 20230167896
    Abstract: A lubricating liquid manifold for a crankpin of an epicyclic gear train. The epicyclic gear train is lubricated by a lubrication system conveying a first flow of a lubricating liquid towards the manifold and a second flow of the lubricating liquid towards a member to be lubricated. The manifold comprises a hollow body provided with an inlet port intended to receive the first flow and an outlet port designed such that the first flow is conveyed towards a guide device connected to the crankpin. The manifold comprises a barrier comprising a shoulder connected to the body and a deflector protruding radially outwards from the body so as to form, with the shoulder, a diversion space for diverting the second flow and preventing it from penetrating into the manifold.
    Type: Application
    Filed: October 17, 2022
    Publication date: June 1, 2023
    Applicant: AIRBUS HELICOPTERS
    Inventors: Mathieu CHARRIER, Jerome BELMONTE, Adrien ESCOFFIER, Sebastien ROBERT, Maxime MALTINTI
  • HEIGHT INDICATOR HAVING A PIECEWISE LINEAR HEIGHT SCALE
    Publication number: 20230168107
    Abstract: A height indicator for an aircraft, the height indicator being provided with a controller controlling a display means to display a height scale and a pointer. The height scale is able to move in relation to the pointer along an axis on the display means, the height scale being a piecewise linear scale comprising several graduated sections, each graduated section having its own linear scale, each graduated section having a scale factor different from a scale factor of another graduated section, each scale factor representing the quotient between a distance on the graduated section along axis and a corresponding actual height.
    Type: Application
    Filed: October 17, 2022
    Publication date: June 1, 2023
    Applicant: AIRBUS HELICOPTERS
    Inventors: Jean-Pierre BAUDRY, Jeremy BLAISE
  • System and method for air filtration with self-cleaning filter medium for an aircraft engine
    Patent number: 11661205
    Abstract: A method for supplying air to an engine of an aircraft via an air supply system of the aircraft. A dynamic air intake vent of the system can be closed by a closure member that is movable between a closed position and an open position. A static air intake vent is equipped with a filter medium. During flight, the method comprises an unfiltered operating mode that comprises the following steps: positioning of the closure member in the open position, and, during a phase of forward travel of the aircraft, dynamic intake of a flow of air, then transfer of a first portion of the flow of air to the engine and a second portion of the flow of air to the filter medium in order to clean the filter medium.
    Type: Grant
    Filed: May 17, 2021
    Date of Patent: May 30, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventor: Benoit Fayard
  • Power transmission system
    Patent number: 11661194
    Abstract: A power transmission system that is adapted to transmit forces from a motor to a component comprises an externally threaded shaft 551 that is rotatably attached to the motor, an internally threaded fastener that is movably attached to the externally threaded shaft, a first element, and a second element that is movably attached to the first element at a second joint and that is rigidly attached to the component at a third joint.
    Type: Grant
    Filed: December 5, 2019
    Date of Patent: May 30, 2023
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Marc Cortes-Fargas, Wouter Beckers, Juergen Fischer, Thomas Kellner
  • HUMAN AND/OR NON-HUMAN CARGO ATTACHMENT DEVICE FOR USE WITH A ROTORCRAFT
    Publication number: 20230159168
    Abstract: A human and/or non-human cargo attachment device for a rotorcraft, comprising: a mounting interface with a mounting base carrier 11d that is removably attachable to an associated attachment for attachment to a rotorcraft rope or cable; a connecting member that is spaced apart from the mounting base carrier; and a plurality of lateral attachments which are connected to the mounting base carrier and the connecting member; wherein each lateral attachment of the plurality of lateral attachments forms a main lashing point for attachment of human external cargo and comprises an associated inner web that is connected to the mounting base carrier and the connecting member; and wherein the associated inner webs of the plurality of lateral attachments are spaced apart from each other in peripheral direction of the mounting base carrier and form a tube-shaped inner region.
    Type: Application
    Filed: October 17, 2022
    Publication date: May 25, 2023
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Dominik VOGEL, Christoph HEIDER, Stefan SALZBURGER, Alexandru DINCA
  • Stiffener skeleton for a firewall arrangement of a rotary wing aircraft
    Patent number: 11655017
    Abstract: A stiffener skeleton that is configured to be mounted to an upper deck of a rotary wing aircraft in a maintenance phase, comprising an upper stiffening structure with a plurality of supporting arms for providing upside stiffening support, and a lateral stiffening structure with a plurality of supporting legs for providing lateral stiffening support, wherein the plurality of supporting arms and the plurality of supporting legs form a self-supporting frame structure.
    Type: Grant
    Filed: June 17, 2021
    Date of Patent: May 23, 2023
    Assignees: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERS
    Inventors: Aurelien Vayssiere, Nicolas Montil, Mathieu Gester, Hubert Neukirch, Pascal Jervaise, Markus Kammerer, Pierre Arnould
  • Rotary wing aircraft with an asymmetrical rear section
    Patent number: 11655021
    Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, a shrouded duct that is arranged in the aft region, and a propeller that is rotatably mounted to the shrouded duct, wherein the rear section extends between the front section and the shrouded duct and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.
    Type: Grant
    Filed: July 15, 2021
    Date of Patent: May 23, 2023
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Rupert Pfaller, Tobias Ries
  • Battery for an aircraft
    Patent number: 11658363
    Abstract: A battery for an aircraft. The present embodiments further relate to an aircraft with at least one such battery. The battery may include a battery casing with a casing wall that forms an interior volume, a plurality of battery cells that is arranged in the interior volume, and a functional layer that is arranged at the casing wall between the plurality of battery cells and the battery casing. The functional layer may include an intumescent material that, in case of a breach of the battery casing, is adapted to ensuring flame containment within the interior volume and mitigation of uncontrolled heat and gas emission from the interior volume through the breach of the battery casing.
    Type: Grant
    Filed: June 17, 2021
    Date of Patent: May 23, 2023
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Johannes Roethinger, Manuel Kempf, Maximo Henares-Extremera
  • Method for manufacturing an electrical harness
    Patent number: 11657931
    Abstract: A method for manufacturing an electrical harness comprising a reference member and a secondary member and at least one electric wire, a protective sheath and at least two shrink sleeves comprising a reference shrink sleeve and a secondary shrink sleeve. According to the disclosure, the method comprises at least the following steps: assembling of the electric wire, the protective sheath, the two shrink sleeves, the reference member and the secondary member, the two shrink sleeves being arranged in a non-contracted state; in a reference portion of the electrical harness, reference contraction of the reference shrink sleeve; in a secondary portion of the electrical harness, angular positioning of the secondary member according to a relative angular orientation; holding of the secondary member in position; and secondary contraction of the secondary shrink sleeve.
    Type: Grant
    Filed: June 17, 2021
    Date of Patent: May 23, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventor: Serge Pittau
  • Propeller provided with interchangeable blades and a method of mounting interchangeable blades on a propeller
    Patent number: 11649036
    Abstract: A propeller provided with interchangeable blades, and to a method of mounting such interchangeable blades on the propeller. The propeller comprises a hub, fastening fittings, rotation guide devices for guiding the fastening fittings in rotation relative to the hub, locking parts, and blades. The fastening fittings are configured to be assembled into the hub from the inside of the hub, and the locking parts lock respective ones of the fastening fittings onto the hub. The blades are fastened to respective ones of the fastening fittings outside the hub and can thus easily be replaced with other blades without removing the propeller.
    Type: Grant
    Filed: June 17, 2020
    Date of Patent: May 16, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Scott Grant, Mathias Fournier, Sylvain Berthalon
  • Radome cover shell and opening kinematic
    Patent number: 11643182
    Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail.
    Type: Grant
    Filed: October 22, 2020
    Date of Patent: May 9, 2023
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Jan Boehme, Yann Le Cadet, Martin Lazak
  • DISPLAY SYSTEM FOR AN AIRCRAFT
    Publication number: 20230126146
    Abstract: A display system for an aircraft, comprising at least one first display unit; at least one second display unit; a control unit that is configured to control the at least one first display unit and the at least one second display unit; and a storage unit with a main memory that is configured to store at least one configuration file, wherein the at least one configuration file is useable by the control unit for configuration of the at least one first display unit and the at least one second display unit, and wherein the at least one configuration file defines at least one displayable parameter for the at least one first display unit and the at least one second display unit.
    Type: Application
    Filed: July 15, 2022
    Publication date: April 27, 2023
    Applicant: AIRBUS HELICOPTERS
    Inventor: Herve LARMINIER
  • PASSENGER DISCOMFORT-AWARE FLIGHT CONTROL SYSTEM
    Publication number: 20230125334
    Abstract: A flight control system that is adapted for controlling movements of a rotary wing aircraft while considering passenger discomfort, to a rotary wing aircraft with such a flight control system, and to a method of operating a flight control system. The flight control system includes sensors configured to generate sensor data based on captured motions of the rotary wing aircraft, motion actuators that are adapted for inducing a translational and/or a rotational movement of the rotary wing aircraft about at least one of a yaw axis, a roll axis, or a pitch axis, and a passenger discomfort-aware control unit that is configured to generate, based on the sensor data, passenger discomfort-aware actuator control signals for controlling the motion actuators of the rotary wing aircraft.
    Type: Application
    Filed: September 16, 2022
    Publication date: April 27, 2023
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND
    Inventors: Oliver DIETERICH, Christian FISCHER, Robin LANTZSCH, Sueleyman OEZKURT, Walter FICHTER, Tobias RATH
  • Actuator provided with a fluid-damped fuse system, and a vehicle provided with the actuator
    Patent number: 11635121
    Abstract: An actuator provided with a motor for moving an output arrangement, the actuator including both an output lever and a fusible connection that acts up to a mechanical torque threshold to constrain the output arrangement and the output lever to move together in rotation about an axis of rotation. The actuator also includes a fluid damper device housed between the output lever and the output arrangement to act, following rupture of the fusible connection, to damp movement of the output lever relative to the output arrangement in rotation about the axis of rotation.
    Type: Grant
    Filed: March 15, 2021
    Date of Patent: April 25, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventor: Romain Nevers