Patents Assigned to AIRBUS HELICOPTER
  • DOOR SYSTEM WITH A DECELERATION MECHANISM
    Publication number: 20200270926
    Abstract: A deceleration mechanism for a door system. In particular, a door system that is adapted to control an opening of a door module that separates compartments of an aircraft, the door module comprising a door panel that performs a rotational movement above a floor structure of the aircraft during an opening of the door module, comprises a deceleration mechanism that comprises a bolt, a bolt moving mechanism that is attached to the bolt, a latch mechanism that is removably connected to the bolt moving mechanism an activation mechanism that is attached to the latch mechanism, and a brake element that is rigidly attached to the bolt.
    Type: Application
    Filed: November 19, 2019
    Publication date: August 27, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Thomas TENDYRA, Uwe RENNER, Xaver PASCOE, Markus BUEHLMEYER, Stephen WARD, Guido BORCHERS
  • POWER-ASSISTED CRANK DEVICE, AND AN AIRCRAFT
    Publication number: 20200269969
    Abstract: A crank device provided with an upstream lever and with a downstream lever. The crank device includes a phase shifter system connected to the upstream lever and to the downstream lever so that movement in rotation of the upstream lever about an axis of rotation induces movement in rotation of the downstream lever about the axis of rotation, the phase shifter system comprising a linear actuator mechanism carried by the upstream lever, the linear actuator mechanism having an outlet rod, the outlet rod having only one degree of freedom of movement in translation relative to the upstream lever, the outlet rod being connected via an outlet helical connection to the downstream lever so that movement in translation of the outlet rod generates movement in rotation of the downstream lever about the axis of rotation.
    Type: Application
    Filed: February 27, 2020
    Publication date: August 27, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventor: Olivier HONNORAT
  • MULTIROTOR AIRCRAFT THAT IS ADAPTED FOR VERTICAL TAKE-OFF AND LANDING
    Publication number: 20200269975
    Abstract: A multirotor aircraft 10 that is adapted for vertical take-off and landing, comprising a fuselage, a thrust producing units assembly that is provided for producing thrust in operation, and a forward-swept wing that comprises a portside half wing and a starboard side half wing. Each one of the portside and starboard side half wings comprises an inboard section that is connected to the fuselage and an outboard section that forms a wing tip. The inboard sections of the portside and starboard side half wings form a central wing region. The portside and starboard side half wings are respectively connected in the region of their wing tips to an associated outboard wing pod that supports at least two non-tiltably mounted thrust producing units of the thrust producing units assembly.
    Type: Application
    Filed: December 3, 2019
    Publication date: August 27, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel FINK, Uwe KIESEWETTER, Klaus KICKER
  • Device for regulating the speed of rotation of a gas generator shaft of a rotorcraft turboshaft engine, a rotorcraft provided with such a device, and an associated method of regulation
    Patent number: 10752342
    Abstract: A regulator device for regulating a speed of rotation, of a shaft of a gas generator of at least one turboshaft engine of a rotorcraft. The rotorcraft has at least one main rotor for regulating at least lift and/or propulsion for said rotorcraft in the air; a control member for controlling a collective pitch of the blades of said at least one main rotor, said control member serving to generate a control setpoint for said collective pitch; at least one turboshaft engine suitable for driving rotation of said at least one main rotor, said at least one engine producing, at least temporarily, a drive torque that is transmitted to said at least one main rotor; and measurement means for taking at each instant a measurement of said drive torque transmitted by said at least one engine to said at least one main rotor.
    Type: Grant
    Filed: December 8, 2017
    Date of Patent: August 25, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventors: Setareh Taheri, Nicolas Certain
  • Method of driving a main rotor of a rotorcraft in the context of simulating a failure of one of the engnes of the rotorcraft
    Patent number: 10748441
    Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.
    Type: Grant
    Filed: October 11, 2016
    Date of Patent: August 18, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventors: Guillaume Dumur, Regis Rossotto, Hilario Vieira
  • SYSTEM AND A METHOD FOR DETECTING WEAR OF A BALL-JOINT CONNECTION DEVICE OF A ROD, A ROTOR ASSEMBLY, AND AN AIRCRAFT
    Publication number: 20200256377
    Abstract: The present invention relates to a detection system for detecting wear of a ball-joint connection device of a pitch rod. The detection system includes at least one measurement assembly, said at least one measurement assembly having at least one deformation gauge for placing on said pitch rod, said detection system comprising at least one electrical conditioning circuit connected to at least one said deformation gauge and to at least one electrical energy source, said electrical conditioning circuit being configured to generate a measurement signal that varies as a function of deformation of said at least one deformation gauge and as a function of said wear.
    Type: Application
    Filed: February 12, 2020
    Publication date: August 13, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventor: Florent DEPROUW
  • Method for monitoring and detecting the formation of degradation in at least one moving part of a rotating mechanism and associated system
    Patent number: 10739317
    Abstract: A method for monitoring and detecting the formation of damage in at least one moving part of a rotary mechanism forming all or part of a kinematic transmission chain of an engine torque, the rotary mechanism equipping an aircraft, the method being implemented by a monitoring and detection system including at least one vibration sensor for measuring accelerations in at least one direction and generating a vibration signal as a function of time, the at least one vibration sensor being secured to a fixed casing of the aircraft and arranged near the rotary mechanism, at least one measuring member for measuring an angular position of the at least one moving part, each moving part including at least one degree of rotational freedom around a rotation axis.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: August 11, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventors: Herve Morel, Jonathan Rodriguez
  • Thrust producing unit with at least two rotor assemblies and a shrouding
    Patent number: 10737766
    Abstract: A thrust producing unit for producing thrust in a predetermined direction, comprising a shrouding and at least two rotor assemblies, wherein the shrouding defines an internal volume, and wherein a first rotor assembly of the at least two rotor assemblies defines a first rotor axis and a second rotor assembly of the at least two rotor assemblies defines a second rotor axis, the first and second rotor axes being one of: (i) coaxially arranged, and (ii) inclined by associated inclination angles with respect to the predetermined direction, the associated inclination angles being comprised in a range between ?60° and +60°, and preferably amounting to 0°, and wherein the first rotor assembly is arranged outside of the internal volume of the shrouding.
    Type: Grant
    Filed: January 24, 2018
    Date of Patent: August 11, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Sebastian Mores, Uwe Kiesewetter, Marius Bebesel
  • Control member, a rotary wing aircraft, and a method
    Patent number: 10737775
    Abstract: A control member that is operable by a pilot to vary thrust from a thrust system of an aircraft. The control member comprises a stick and a movable assembly including a grip. The grip is linked to the stick via a helical link, rotation of the grip about the stick giving rise to movement in translation of the grip together with the movable assembly along the stick, the grip being movable in translation in both a first direction in translation and in a second direction in translation that is opposite to the first direction in translation.
    Type: Grant
    Filed: November 30, 2017
    Date of Patent: August 11, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventors: Jean-Romain Bihel, Zouhair Sassi
  • Servo control, rotor and aircraft
    Patent number: 10738803
    Abstract: A servo-control. The servo-control comprises at least one body as well as a power shaft and a control piston arranged in each body, the at least one body and the power shaft respectively forming two power members. One of the power members bears at least on end-stop member and the power member without an end-stop member bears a passivation actuator. The passivation actuator comprises a passivation shaft which bears an end-stop and a passivation piston, the passivation piston being arranged to be mobile in longitudinal translation in an enclosure, an elastic system being arranged between the passivation piston and the enclosure.
    Type: Grant
    Filed: December 7, 2017
    Date of Patent: August 11, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventors: Clement Coiec, Jean-Romain Bihel, Arnaud Groll
  • Gearbox casing, a gearbox, and an aircraft
    Patent number: 10737777
    Abstract: An upper casing with a hollow shell made of composite materials. The shell was a side wall that extends in elevation from a housing flange to a housing collar, the side wall including at least one cutout. The upper casing includes an internal liner that is inserted inside the shell and that is fastened to an inside face of the shell, the liner comprising a base and a top, together with at least two legs extending in elevation from the base to the top, the liner further comprising at least one equipment support in register with a cutout, each equipment support being for carrying a removable piece of equipment of the upper casing.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: August 11, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventors: Cyril Sola, Thierry Rey, Jean-Victor Lapeyre, Philippe Moniot, Laurent Bourdier
  • DIRECTIONAL LIGHTING FITTED TO AN AIRCRAFT, AND AN ASSOCIATED LIGHTING METHOD
    Publication number: 20200247557
    Abstract: A directional lighting system fitted to an aircraft and comprising firstly a light source mounted on a motor-driven support and secondly a control device serving to control the motor-driven support. According to the invention, such a directional lighting system comprises a selector member for selecting a pointing target that is to be pointed to, a camera for acquiring a plurality of images of the surroundings outside the aircraft, image processor means for identifying the selected pointing target, a calculation unit configured to calculate the current coordinates of the pointing target, and a servocontrol member of the control device for servocontrolling the position of the motor-driven support to occupy an angular orientation as determined by the calculation unit.
    Type: Application
    Filed: December 10, 2019
    Publication date: August 6, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventor: Marc SALESSE-LAVERGNE
  • Regulation system for controlling the vibratory behavior and/or the twisting stability of a drivetrain, a rotorcraft fitted with such a regulation system, and an associated regulation method
    Patent number: 10730613
    Abstract: A regulation system for controlling the vibratory behavior in twisting and/or the twisting stability of a drivetrain of a rotorcraft, the regulation system comprising two regulation loops that are interleaved one in the other, the two regulation loops being arranged “in cascade” relative to each other to regulate firstly a first speed of rotation NG of a gas generator of at least one turboshaft engine driving said drivetrain in rotation, and secondly a second speed of rotation NTL of a free turbine of the engine(s).
    Type: Grant
    Filed: June 13, 2018
    Date of Patent: August 4, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventor: Anthony Leonard
  • EN ROUTE FLUID TRANSMITTING APPARATUS
    Publication number: 20200239154
    Abstract: An en route fluid transmitting apparatus for transmitting a fluid from a transmitting entity to a probe of a receiving vehicle includes a funnel, a hose and a thrust producing device. Thrust producing device includes a main body that is rigidly attached to the funnel, and at least two rotors that are connected to the main body for producing thrust. The thrust producing device is adapted to move the funnel freely in any direction to a predetermined position relative to the probe where the funnel engages with the probe.
    Type: Application
    Filed: November 18, 2019
    Publication date: July 30, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Yann LE CADET, Samuel PELLERIN
  • METHOD AND APPARATUS FOR CONFIGURING SCREEN DISPLAYS
    Publication number: 20200239157
    Abstract: Controlling and reconfiguring a display system that includes at least two screens that are installed in a cockpit of an aircraft in case of a failure of one of the screens. For example, a control unit of the display system may detect occurrence of a screen failure. In response to detecting the screen failure, the control unit may determine whether a critical flight relevant information has not been displayed on an operational screen during a predetermined period of time, and in response to determining that the critical flight relevant information has not been displayed on the operational screen during the predetermined period of time, command display of a message on the operational screen that suggests displaying the critical flight relevant information on the operational screen.
    Type: Application
    Filed: December 4, 2019
    Publication date: July 30, 2020
    Applicants: AIRBUS HELICOPTERS, AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Valerie JUPPET, Fanny STUTZMANN, Marie CHARBONNEAU, Jorrit VAN DER SPEK, Olga GONZALEZ-VALBUENA
  • Directional lighting fitted to an aircraft, and an associated lighting method
    Patent number: 10723482
    Abstract: A directional lighting system fitted to an aircraft and comprising firstly a light source mounted on a motor-driven support and secondly a control device serving to control the motor-driven support. According to the invention, such a directional lighting system comprises a selector member for selecting a pointing target that is to be pointed to, a camera for acquiring a plurality of images of the surroundings outside the aircraft, image processor means for identifying the selected pointing target, a calculation unit configured to calculate the current coordinates of the pointing target, and a servocontrol member of the control device for servocontrolling the position of the motor-driven support to occupy an angular orientation as determined by the calculation unit.
    Type: Grant
    Filed: December 10, 2019
    Date of Patent: July 28, 2020
    Assignee: AIRBUS HELICOPTERS
    Inventor: Marc Salesse-Lavergne
  • Passive pitch angle adjustment apparatus
    Patent number: 10723450
    Abstract: A rotor or propeller may have rotor blades and a passive pitch angle adjustment apparatus. The passive pitch angle adjustment apparatus may include levers, rods, and central rod. Levers may be connected to rotor blades and rotate them around a respective pitch axis. Rods may be connected to levers and mechanically link levers with each other via central point that is located outside rotor plane. Central rod may connect central point with base point that is located in a longitudinal direction of rotor axis. The passive pitch angle adjustment apparatus may enable a cyclic pitch adjustment of the rotor blades and block a collective pitch adjustment of the rotor blades.
    Type: Grant
    Filed: February 25, 2019
    Date of Patent: July 28, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Patrik Schmiedel, Harald Leitner, Julian Kraus, Ludwig Dannemann, Uwe Kiesewetter
  • REDUNDANT AND DISSIMILAR SYSTEM FOR MONITORING THE STATUS OF CONTROL CONTACTORS OF AN AIRCRAFT CONTROL STICK
    Publication number: 20200233449
    Abstract: A redundant and dissimilar system for monitoring the status of contactors of an aircraft control stick. This monitoring system comprises at least one electrical power source, at least one processor and several circuits for monitoring the status of the switches of the contactors. Each monitoring circuit comprises and electrical power source, a switch for each contactor, the switches of a contactor being connected to each other, and an electronic assembly provided with receivers arranged in series with each other. Each switch is arranged in parallel with at least one receiver so as to short-circuit the at least one receiver when the switch is in the closed state. Each processor measures and analyses an electrical feature of the electronic assembly, such as a mains voltage VE as the terminals of the electronics assembly, in order to determine the status of each switch.
    Type: Application
    Filed: February 23, 2018
    Publication date: July 23, 2020
    Applicant: AIRBUS HELICOPTERS
    Inventors: Pascal IZZO, Jean-Francois LAFFISSE
  • Rotary wing aircraft with a sliding element, in particular a sliding door or a sliding window
    Patent number: 10717513
    Abstract: A rotary wing aircraft with a fuselage that is equipped with at least one rail, comprising at least one sliding element, in particular a sliding door or a sliding window, that is slidably supported by the at least one rail, wherein the at least one sliding element is at least slidable along the at least one rail by means of an opening sliding movement into an opening movement direction from a fully closed position into a fully opened position, wherein a dampening unit is provided that dampens the opening sliding movement of the at least one sliding element upon reaching of the fully opened position.
    Type: Grant
    Filed: November 16, 2017
    Date of Patent: July 21, 2020
    Assignees: Airbus Helicopters Deutschland GmbH, Airbus Helicopters
    Inventors: Aurelien Vayssiere, Pierre Fruitet, Fabrice Joussellin, Robert Sienicki, Bartlomiej Tazbir, Michal Mroz, Bernhard Rein
  • DOOR LOCKING SYSTEM WITH A RAPID RELEASE MECHANISM
    Publication number: 20200224462
    Abstract: A door locking system for a door module that separates compartments in an aircraft. Door locking system has locking element that is adapted to maintain door panel of door module in a closed position. Door locking system further includes first and second mechanisms that are adapted to release door panel from the closed position in a normal and an abnormal mode, respectively. Second mechanism is spatially segregated from and operates independently of first mechanism. Second mechanism includes locking element release actuator, pressure sensor, and controller that directs locking element release actuator to act on locking element when pressure sensor detects a difference in pressure between the compartments that exceeds a predetermined threshold.
    Type: Application
    Filed: November 18, 2019
    Publication date: July 16, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Uwe RENNER, Xaver PASCOE, Markus BUEHLMEYER, Thomas TENDYRA, Stephen WARD, Guido BORCHERS