Patents Assigned to Airbus Helicopters
  • 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
  • Method for controlling at least one aerodynamic stabilizer member of a hybrid helicopter, and a hybrid helicopter
    Patent number: 11634209
    Abstract: A method for optimizing the operation of at least one first propeller and of at least one second propeller of a hybrid helicopter. The method comprises the following step during a control phase: deflection, with an autopilot system, of at least one aerodynamic stabilizer member into a setpoint position having, with respect to a reference position, a target deflection angle that is a function of a setpoint deflection angle, the setpoint deflection angle being calculated by the autopilot system in order to compensate for a torque exerted by the lift rotor at zero sideslip.
    Type: Grant
    Filed: March 11, 2021
    Date of Patent: April 25, 2023
    Assignee: AIRBUS HELICOPTER
    Inventors: Paul Eglin, Remy Huot, Antoine Conroy
  • Aircraft with a safety distance display apparatus
    Patent number: 11635522
    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: Grant
    Filed: November 19, 2019
    Date of Patent: April 25, 2023
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Lieven Desmet
  • GEARBOX AND ASSOCIATED AIRCRAFT
    Publication number: 20230121921
    Abstract: A gearbox including an angular contact ball bearing comprising a first row of balls provided with a plurality of balls, a second row of balls provided with another plurality of balls, at least one inner ring and at least one outer ring. According to the invention, in a degraded operating mode of the bearing, the first row of balls is configured to transmit at least one first axial force oriented along a first axis and at least one second axial force oriented along a second axis opposite the first axis, the second row of balls transmitting no axial force.
    Type: Application
    Filed: September 15, 2022
    Publication date: April 20, 2023
    Applicant: AIRBUS HELICOPTERS
    Inventor: Laurent ZAMPONI
  • Structural arrangement with a fiber reinforced polymer component and a cold gas sprayed electrically conductive layer
    Patent number: 11629411
    Abstract: A structural arrangement comprising a fiber reinforced polymer component, a cold gas spraying electrically conductive layer, and a polyether sulfone foil arranged on the fiber reinforced polymer component, at least in a region between the fiber reinforced polymer component and the cold gas sprayed electrically conductive layer.
    Type: Grant
    Filed: December 7, 2020
    Date of Patent: April 18, 2023
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Andreas Rack
  • Thrust margin monitoring device for rotorcraft, rotorcraft and corresponding method
    Patent number: 11623741
    Abstract: A device for monitoring an available thrust margin of an anti-torque member of a rotorcraft as a function of flight conditions, said rotorcraft comprising a power plant driving at least one main rotor participating at least in the lift of said rotorcraft, said anti-torque member participating in the control of the yaw movements of said rotorcraft.
    Type: Grant
    Filed: December 17, 2020
    Date of Patent: April 11, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Laurent Berger, Guillaume Dumur, Damien Piger, Olivier Delecroix, Didier Delsalle
  • METHOD FOR HOVERING AN AIRCRAFT WITH RESPECT TO AN AXIS WITH A CONTROLLABLE PITCH ANGLE
    Publication number: 20230101964
    Abstract: A method for hovering an aircraft having at least one wing and at least one rotary wing and at least one propeller, the aircraft comprising an autopilot system. The method comprises keeping the aircraft hovering, with the autopilot system, in the setpoint position, keeping the aircraft hovering in this way comprising controlling, with the autopilot system, a pitch of blades of the at least one propeller irrespective of the setpoint pitch angle and controlling, with the autopilot system, a pitch of blades of the at least one rotary wing as a function at least of the setpoint pitch angle.
    Type: Application
    Filed: June 16, 2022
    Publication date: March 30, 2023
    Applicant: AIRBUS HELICOPTERS
    Inventor: Kamel ABDELLI
  • ROTOR BLADE WITH A SYSTEM FOR RETENTION AND FOR TAKE-UP OF SEPARATE STRESSES AND ROTOR PROVIDED WITH SUCH BLADES
    Publication number: 20230099429
    Abstract: A blade, for a rotor of an aircraft, comprising a hollow cylindrical sleeve, a stop fastened to the cylindrical sleeve, a profiled portion, and an anchoring device, a blade body and a hollow torsion box secured to the profiled portion. The anchoring device and the blade body are positioned inside the cylindrical sleeve. The anchoring device surrounds the stop in order to form a stop for the profiled portion parallel to a longitudinal axis of the blade. The hollow torsion box is secured to the profiled portion, and comprises a bearing zone in contact with an inner wall of the cylindrical sleeve, taking up the bending loads on the blade.
    Type: Application
    Filed: September 15, 2022
    Publication date: March 30, 2023
    Applicant: AIRBUS HELICOPTERS
    Inventors: Jean-Francois HIRSCH, Adrien PARIZEL
  • ANCHOR FOR SECURING AN AIRCRAFT TO A LANDING GRID AND AIRCRAFT
    Publication number: 20230094764
    Abstract: An anchor for an aircraft. The anchor comprises a jack comprising a housing and a head that is able to move in translation in relation to the housing along an elevation axis, the head having three degrees of rotational freedom respectively about a longitudinal axis as well as a transverse axis and the elevation axis, the anchor comprising a member for taking up forces surrounding the jack and provided with a fastening suitable for being secured to the aircraft.
    Type: Application
    Filed: August 17, 2022
    Publication date: March 30, 2023
    Applicant: AIRBUS HELICOPTERS
    Inventors: Christophe GAILLARD, Joel DURANTET, Nicolas RASPIC
  • Method of providing torque protection and/or thrust protection for propellers of a hybrid helicopter, and a hybrid helicopter
    Patent number: 11608165
    Abstract: A method of providing torque protection and/or thrust protection for the or each propeller of a hybrid helicopter. The hybrid helicopter includes a control system connected to the blades of each propeller and a thrust control configured to generate an order for modifying a pitch of the blades, which order is transmitted to the control system, the propeller(s) being driven in rotation by a mechanical transmission system of the hybrid helicopter. The method includes a step of having the control system keep the pitch of the blades of a propeller within at least one control envelope relating to a thrust generated by the propeller or to a torque exerted in the mechanical transmission system. In this way, the pitch of the blades of each propeller is kept between a lower limit and an upper limit of the control envelope.
    Type: Grant
    Filed: February 8, 2021
    Date of Patent: March 21, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Paul Eglin, Remy Huot
  • Method of controlling propellers of a hybrid helicopter, and a hybrid helicopter
    Patent number: 11608166
    Abstract: A method of controlling at least a first pitch of a first propeller and a second pitch of a second propeller of a hybrid helicopter, the hybrid helicopter having a thrust control and a yaw control that are configured to generate orders for modifying respectively a mean pitch component and a differential pitch component of the first pitch and of the second pitch, the hybrid helicopter having a collective pitch control for modifying a collective pitch component of main blades of the lift rotor. The method includes a step of: keeping with the control system the first pitch and the second pitch within a control domain that varies as a function of information relating to the collective pitch component.
    Type: Grant
    Filed: February 17, 2021
    Date of Patent: March 21, 2023
    Assignee: AIRBUS HELICOPTERS
    Inventors: Paul Eglin, Remy Huot