Patents Assigned to Airbus Helicopters Deutschland GmbH
  • ROTORCRAFT WITH A STABILIZER WING
    Publication number: 20200339253
    Abstract: A rotorcraft, and, more particularly, to a rotorcraft with a fuselage having a center line, at least one main rotor that generates vortices during operation, and a stabilizer wing, whereby the stabilizer wing has a planform that reduces the unsteady aerodynamic loads caused by the wake of the at least one main rotor. In particular, the stabilizer wing may be provided with a left wing tip, a right wing tip, a quarter chord line with a non-zero curvature, such that an interaction between the vortices generated by the at least one main rotor and the quarter chord line is spread out over time, a leading edge that is arc-shaped, and a trailing edge that is arc-shaped.
    Type: Application
    Filed: February 27, 2020
    Publication date: October 29, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Martin EMBACHER, Tobias RIES, Christian ECKERT, Thomas KNEISCH
  • Rotary wing aircraft with an interface frame joining the fuselage tail boom and the tail cone
    Patent number: 10807697
    Abstract: A rotary wing aircraft comprising a fuselage tail boom, a tail cone and an interface frame, the interface frame in turn having a connecting structure directly attached to the tail cone by means of a tail cone mechanical connection and a connecting sleeve fitting axially the fuselage tail boom, the connecting sleeve and the fuselage tail boom being directly attached by means of a one boom mechanical connection; the interface frame thereby joining the fuselage tail boom and the tail cone.
    Type: Grant
    Filed: January 26, 2017
    Date of Patent: October 20, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Stefan Probst, Philipp Walch, Marc Nothen, Christian Buxel, Romed Schweizer, Thomas Wuerfl
  • Jettisonable emergency exit for a vehicle
    Patent number: 10807706
    Abstract: A jettisonable emergency exit for a vehicle, comprising an outer peripheral edge that is adapted to be accommodated in an associated frame provided in a vehicle, wherein at least one emergency exit retention means and at least one emergency exit locking device are integrated into the outer peripheral edge, the at least one emergency exit retention means comprising at least one non-retractable pivot finger around which the jettisonable emergency exit is rotatable in an emergency mode, and the at least one emergency exit locking device comprising at least one locking hook that is adapted for locking the jettisonable emergency exit in an associated locking position in normal operation mode and for releasing the jettisonable emergency exit in an associated retracted position in the emergency mode.
    Type: Grant
    Filed: June 1, 2016
    Date of Patent: October 20, 2020
    Assignees: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTER
    Inventors: Fabrice Joussellin, Aurelien Vayssiere, Pierre Fruitet, Laure-Anne Mathieu, Hassene Heboub, Philippe Benentendi
  • Vibration filter mechanism for arranging between a piece of equipment and an aircraft fuselage, and a seat fitted with such a mechanism
    Patent number: 10787264
    Abstract: A vibration filter mechanism between a fuselage and a piece of equipment of the aircraft. The filter mechanism comprises a pair of filter members, each secured with a first structure that is to be connected to the fuselage and with a second structure of the piece of equipment. Each filter member is secured with the first structure via a first pivot type connection having one degree of freedom to move in rotation and with the second structure via a second pivot type connection having one degree of freedom to move in rotation. The filter mechanism includes resilient return means for deforming during relative movement in rotation between at least one of the filter members and the first structure. The resilient return means presents a predetermined stiffness suitable for generating a return force opposing the relative movement in rotation between at least one of the filter members and the first structure.
    Type: Grant
    Filed: April 27, 2018
    Date of Patent: September 29, 2020
    Assignees: AIRBUS HELICOPTERS, AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Julien Guitton, Anne-Claire Chapuis-Desplanques, Ambrosius Weiss, Thomas Manfredotti
  • Composite materials enabling non-destructive testing
    Patent number: 10789700
    Abstract: The invention is related to composite materials that enable the detection of imperfections through non-destructive testing. The composite material may include several constituent materials. One of these constituent materials may include cavities of a predetermined or random shape that are arranged at predetermined or random locations. Another constituent material may at least partially fill at least some of these cavities during manufacturing of the composite material. A method for non-destructively detecting imperfections in such a composite material may involve receiving an image of the composite material that shows at least some cavities and detecting imperfections in the composite material based on an inspection of the image.
    Type: Grant
    Filed: February 28, 2019
    Date of Patent: September 29, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Christian Kommer, Markus Zellhuber, Philipp Meierling
  • POWER TRANSMISSION SYSTEM
    Publication number: 20200290851
    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: Application
    Filed: December 5, 2019
    Publication date: September 17, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Marc CORTES-FARGAS, Wouter BECKERS, Juergen FISCHER, Thomas KELLNER
  • INFORMATION PROJECTION AND CONTROL SYSTEM
    Publication number: 20200290751
    Abstract: An information projection and control system for projecting information onto a projection area provided by a vehicle door, comprising at least one control unit that generates information, for projection onto the projection area; at least one projection device that projects the generated information onto the projection area; and at least one movement sensor that detects movements in a sensing area associated with the projection area, wherein the at least one control unit is adapted to control generation of the generated information on the basis of the detected movements.
    Type: Application
    Filed: February 5, 2020
    Publication date: September 17, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Daniel WAFFLER, Uwe RENNER
  • MULTIROTOR ELECTRIC AIRCRAFT WITH REDUNDANT SECURITY ARCHITECTURE
    Publication number: 20200283134
    Abstract: A multirotor aircraft with at least two thrust producing units, the multirotor aircraft being adapted for transportation of passengers and comprising an aircraft operating structure that is adapted for operation of the multirotor aircraft in failure-free operating mode, and a redundant security architecture that is at least adapted for operation of the multirotor aircraft in case of a failure of the aircraft operating structure in operation, the redundant security architecture being provided to comply with applicable authority regulations and certification requirements regarding passenger transportation.
    Type: Application
    Filed: December 16, 2016
    Publication date: September 10, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Sebastian MORES, Christoph GEYER, Stefan HAISCH, Marius BEBESEL, Michael GEISS, Manfred BERNHARD
  • DOOR SYSTEM WITH A DECELERATION MECHANISM
    Publication number: 20200277815
    Abstract: A door system with a deceleration mechanism may be adapted to control an opening of a door module that separates compartments of an aircraft and includes a door panel and a door frame. During the opening of the door module, the door panel performs a rotational movement 389 above a floor structure of the aircraft. The deceleration mechanism is operable in a normal operation mode and a deceleration mode and comprises a hinge, a wedge-shaped component that is rotatably attached to the hinge, and an activation device. The activation device is coupled to the wedge-shaped component and switches the deceleration mechanism from operating in the normal operation mode to operating in the deceleration mode when a difference in pressure between the compartments exceeds a predetermined threshold.
    Type: Application
    Filed: November 19, 2019
    Publication date: September 3, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Thomas TENDYRA, Uwe RENNER, Xaver PASCOE, Markus BUEHLMEYER, Stephen WARD, Guido BORCHERS
  • HAPTIC ALERT MECHANISM FOR ALERTING AN AIRCRAFT PILOT, AND AN AIRCRAFT
    Publication number: 20200277082
    Abstract: A haptic alert mechanism. The mechanism includes an actuator. At least one arm of a movable stopping piece is connected to the actuator. A spring box is provided with an enclosure containing a pre-stressed torsion spring, said spring box being mounted to be movable in rotation about the axis of rotation. The enclosure includes at least one lug that is mounted to be movable in rotation about said axis of rotation. A finger of the torsion spring passes through an elongate orifice in a front flank of the enclosure to form a movable, resilient stop that is overridable.
    Type: Application
    Filed: February 27, 2020
    Publication date: September 3, 2020
    Applicants: AIRBUS HELICOPTERS, AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Boris GROHMANN, Christophe TEMPIER, William LAGREVOL, Marc SALESSE-LAVERGNE
  • MULTIROTOR JOINED-WING AIRCRAFT WITH VTOL CAPABILITIES
    Publication number: 20200269980
    Abstract: A multirotor aircraft that is adapted for vertical take-off and landing. The multirotor aircraft comprises a fuselage, a tail boom that is provided with a vertical fin, a thrust producing units assembly that is provided for producing thrust in operation, at least one lower wing which comprises a lower wing inboard section that is connected to the fuselage and a lower wing outboard section that forms a lower wing tip, and at least one upper wing which is connected to the vertical fin and which forms an upper wing tip. The at least one upper wing is joined to the at least one lower wing in a joined-wing configuration.
    Type: Application
    Filed: December 4, 2019
    Publication date: August 27, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel FINK, Uwe KIESEWETTER, Klaus KICKER
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • Aircraft with a plurality of aircraft doors
    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