Patents Assigned to Airbus Helicopters Deutschland GmbH
  • ROTARY WING AIRCRAFT WITH A SLIDING ELEMENT, IN PARTICULAR A SLIDING DOOR OR A SLIDING WINDOW
    Publication number: 20180148157
    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: Application
    Filed: November 16, 2017
    Publication date: May 31, 2018
    Applicants: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERS
    Inventors: Aurelien VAYSSIERE, Pierre FRUITET, Fabrice JOUSSELLIN, Robert SIENICKI, Bartlomiej TAZBIR, Michal MROZ, Bernhard REIN
  • Rotor system of a rotary wing aircraft
    Patent number: 9975630
    Abstract: A rotor system of a rotary wing aircraft, such as a helicopter, is provided. The rotor system includes a rotor mast, a rotor hub and at least four, angularly generally even distributed rotor blades and swash plate struts for pitch and subsequently flap control. The rotor blades are pairwise to each other with zero offset to the rotor hub. The rotor hub is provided with a hollow bearing with at least one further bearing inside. A first pair of rotor blades is mounted on the hollow bearing and is pivotable in a first flap direction generally perpendicular to the rotation axis. A second pair of rotor blades is mounted inside the hollow bearing on the at least one further bearing and is pivotable in a second flap direction generally perpendicular to the first flap direction and the rotation axis, and independently of the first pair of rotor blades.
    Type: Grant
    Filed: June 12, 2014
    Date of Patent: May 22, 2018
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Kaspar Von-Wilmowsky
  • ACTUATABLE EMERGENCY EXIT DOOR AND AN AIRCRAFT OR SPACE CRAFT WITH A PRESSURIZED CABIN HAVING SUCH AN ACTUATABLE EMERGENCY EXIT DOOR
    Publication number: 20180134366
    Abstract: An actuatable emergency exit door with a door actuating device that comprises at least two connection rods that are pivotally mountable to an associated structural frame that is adapted for accommodating the actuatable emergency exit door in closed state, the at least two connection rods being provided for enabling an opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening, wherein at least one door-mounted goose neck-shaped structure is mountable to the associated structural frame for enabling an initial translational opening movement and subsequently a swiveling opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening. The invention is further related to an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door.
    Type: Application
    Filed: October 17, 2017
    Publication date: May 17, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Christoph MERKEL, Stephen WARD, Michal VINARSKY, Florian NAUMANN
  • Tail assembly for a rotorcraft, rotorcraft and method of manufacture of a strengthened tail assembly
    Patent number: 9963226
    Abstract: A tail assembly for a rotorcraft. The tail assembly is manufactured to include at least one transition structure provided in the tail assembly. The transition structure is longitudinally arranged between a longitudinal median boom portion and a tail fin. A power transmission shaft of the rotorcraft extends at least partly externally above a longitudinal median boom portion of the tail assembly. The transition structure includes at an entering region a cut-out elevation step, where is made a passing through opening for the power transmission shaft.
    Type: Grant
    Filed: February 26, 2016
    Date of Patent: May 8, 2018
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventors: Christian Wehle, Justus Steger, Marc Nothen, Stefan Probst, Antonia Horstmann
  • Control system for controlling collective and cyclic pitch of rotor blades of a multi-blade rotor in a rotary-wing aircraft
    Patent number: 9950787
    Abstract: The invention is related to a control system for controlling collective and cyclic pitch of rotor blades of a multi-blade rotor 1a in a rotary-wing aircraft, the control system comprising a swash plate assembly with at least one non-rotating plate and at least one rotating plate that is mounted rotatably to the at least one non-rotating plate, the at least one rotating plate and the at least one non-rotating plate being mounted to a non-rotating sliding sleeve, wherein a spherical bearing is provided on the non-rotating sliding sleeve, wherein at least one non-rotating stop arm is provided for non-rotatably connecting the at least one non-rotating plate to the non-rotating sliding sleeve.
    Type: Grant
    Filed: July 29, 2015
    Date of Patent: April 24, 2018
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Benedikt Bammer
  • AIRCRAFT WITH A PLURALITY OF AIRCRAFT DOORS
    Publication number: 20180106074
    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: Application
    Filed: October 16, 2017
    Publication date: April 19, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Stephen WARD
  • Aircraft with a subfloor region that accommodates an auxiliary compartment
    Patent number: 9932104
    Abstract: An aircraft with a fuselage and a floor structure that is arranged inside the fuselage, the floor structure and the fuselage defining a subfloor region between the floor structure and a fuselage underside of the fuselage, the subfloor region accommodating at least one auxiliary compartment, wherein an equipment bay with at least one auxiliary equipment is arranged within the subfloor region, the at least one auxiliary equipment being at least essentially stowable in the equipment bay in a stow mode and the at least one auxiliary compartment being at least partly arranged in a region between the equipment bay and the floor structure such that the at least one auxiliary compartment separates the equipment bay from the floor structure.
    Type: Grant
    Filed: February 3, 2016
    Date of Patent: April 3, 2018
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Michael Behrens, Markus Wahnfried, Frank Loeser, Sebastian Mores
  • ROTARY WING AIRCRAFT WITH A STRUCTURAL ARRANGEMENT THAT COMPRISES AN ELECTRICALLY CONDUCTIVE CONNECTION
    Publication number: 20180085782
    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: Application
    Filed: September 27, 2017
    Publication date: March 29, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Andreas RACK, David ROSPLESCH, Dietrich JONKE
  • Energy absorbing system for absorbing energy of an object in a vehicle in a crash situation
    Patent number: 9925942
    Abstract: An energy absorbing system that is adapted for absorbing energy of an object in a vehicle in a crash situation by decreasing acceleration and force acting on the object in the crash situation, the energy absorbing system comprising at least one plastically deformable energy absorber that is plastically deformable in the crash situation. A mass-dependent self-adjusting mechanism is provided, the mass-dependent self-adjusting mechanism being adapted for adjusting, on the basis of an underlying mass of the object, a required compensation force that is to be provided by the energy absorbing system in the crash situation for plastically deforming the at least one plastically deformable energy absorber in order to decrease the acceleration and force acting on the object.
    Type: Grant
    Filed: July 15, 2016
    Date of Patent: March 27, 2018
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Marius Herrmann, Roberto Gusmini, Frank Seidel, Marius Klinkner
  • ADJUSTMENT OF TRACK AND BALANCE OF A MULTI-BLADE ROTOR
    Publication number: 20180072412
    Abstract: A multi-blade rotor of a rotary wing aircraft, the multi-blade rotor comprising at least one rotor blade that defines a pitch axis and that is provided with an associated pitch-control lever that is operatively coupled to a pitch link rod, the pitch link rod defining a longitudinal axis, wherein the associated pitch-control lever comprises an accommodation that is located on the longitudinal axis of the pitch link rod at a predetermined distance from the pitch axis of the at least one rotor blade, the pitch link rod being operatively coupled to the associated pitch-control lever at the accommodation of the associated pitch-control lever, wherein the predetermined distance is adjustable in order to enable adjustment of track and balance of the multi-blade rotor.
    Type: Application
    Filed: September 14, 2017
    Publication date: March 15, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Moritz BUESING
  • AIRCRAFT WITH AN EMERGENCY FLOATATION SYSTEM
    Publication number: 20180057153
    Abstract: An aircraft with an emergency flotation system, the emergency flotation system being activated upon an emergency landing of the aircraft on water, for preventing at least sinking of the aircraft, characterized in that a capsizing avoidance buoyancy system is provided, the capsizing avoidance buoyancy system being activated if predetermined activation criteria are satisfied and only after activation of the emergency flotation system upon an emergency landing of the aircraft on water, for preventing at least capsizing of the aircraft.
    Type: Application
    Filed: July 27, 2017
    Publication date: March 1, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Johann RAPPL
  • Aircraft with an engine having a by-pass air inlet opening and a bleed air outlet
    Patent number: 9902500
    Abstract: An aircraft having at least one first and one second engine, each engine comprising a main air inlet opening, a by-pass air inlet opening and a bleed air outlet, said main air inlet opening being provided with an inlet barrier filter for filtering a main air stream through said main air inlet opening into the engine, said by-pass air inlet opening being provided with a by-pass door that is operable by an associated operating element to enable a by-pass air stream through said by-pass air inlet opening into the engine, and said bleed air outlet being provided for creating an outgoing bleed air stream going out of the engine in operation, at least one associated operating element being controllable by an outgoing bleed air stream.
    Type: Grant
    Filed: June 4, 2015
    Date of Patent: February 27, 2018
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventors: Michael Stadler, Ralf Braeutigam
  • ROTARY WING AIRCRAFT WITH A FUSELAGE THAT COMPRISES AT LEAST ONE STRUCTURAL STIFFENED PANEL
    Publication number: 20180043982
    Abstract: A rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel, the structural stiffened panel comprising a stressed skin and a stiffening framework that is rigidly attached to the stressed skin, wherein the stressed skin comprises an inner skin, an outer skin and a core element assembly that is arranged between the inner skin and the outer skin, the core element assembly comprising at least one viscoelastic core element and at least one intermediate core element that are tessellated, wherein the at least one viscoelastic core element is provided for noise and vibration damping.
    Type: Application
    Filed: July 21, 2017
    Publication date: February 15, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel FINK, Andreas RACK, Helmut FIETZ
  • CONTROL SYSTEM FOR CONTROLLING AT LEAST COLLECTIVE PITCH OF ROTOR BLADES OF A MULTI-BLADE ROTOR IN A ROTARY-WING AIRCRAFT
    Publication number: 20180044008
    Abstract: A control system for controlling at least collective pitch of rotor blades, of a multi-blade rotor with a rotor shaft in a rotary-wing aircraft, the control system comprising a non-rotating sliding sleeve that is mountable to the rotor shaft such that the non-rotating sliding sleeve is axially displaceable coaxially to an associated rotor axis on the rotor shaft, at least one actuator arm that is pivotally mounted to the non-rotating sliding sleeve and adapted for axially displacing the non-rotating sliding sleeve that is mounted to the rotor shaft upon activation, and at least one hinge support that is adapted for a hinged support of the at least one actuator arm.
    Type: Application
    Filed: July 21, 2017
    Publication date: February 15, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Benedikt BAMMER, Gerald KUNTZE-FECHNER
  • LOAD TRANSFER INTERFACE FOR A VEHICLE DOOR, IN PARTICULAR FOR AN AIRCRAFT CABIN DOOR
    Publication number: 20180030762
    Abstract: A load transfer interface for a vehicle door that comprises an outer skin and at least one beam that is connected to the outer skin, wherein the outer skin and the at least one beam define a vehicle door plane, the load transfer interface comprising at least one door stop fitting that is provided to transfer pressure loads from the vehicle door to an associated vehicle structural frame, the at least one door stop fitting being provided for rotation in an associated rotation plane, wherein the associated rotation plane is at least approximately parallel to the vehicle door plane. The invention is further related to an aircraft cabin door having such a load transfer interface, as well as to an aircraft having such an aircraft cabin door.
    Type: Application
    Filed: July 12, 2017
    Publication date: February 1, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Matthias SCHWAB
  • AIRCRAFT WITH A FUSELAGE AND A COMPOSITE TAIL BOOM
    Publication number: 20180022433
    Abstract: An aircraft with a composite tail boom that comprises at least partly a tubular tail boom cone with an outer skin and an inner skin, wherein the inner skin delimits a hollow interior of the composite tail boom, wherein a plurality of rod-shaped stiffening elements and a plurality of ring-shaped stiffening elements are arranged between the outer skin and the inner skin, the plurality of rod-shaped stiffening elements being oriented in longitudinal direction of the composite tail boom and the plurality of ring-shaped stiffening elements being distributed along the longitudinal direction in the tubular tail boom cone.
    Type: Application
    Filed: July 20, 2017
    Publication date: January 25, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Axel FINK
  • Aircraft framework structure with integral ventilation air duct
    Patent number: 9873512
    Abstract: An aircraft with a fuselage that comprises a framework structure having at least one hollow frame that is integrally formed in one piece and comprises fiber reinforced polymers, the at least one hollow frame defining an integrated ventilation air duct that is adapted for guiding ventilation air into the aircraft.
    Type: Grant
    Filed: July 28, 2015
    Date of Patent: January 23, 2018
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventors: Sebastian Mores, Johann Barnerssoi, Stefan Probst, Marco Schneeberger, Hartmut Jutt
  • Windshield wiper system
    Patent number: 9868419
    Abstract: A windshield wiper system (3) for vehicles. A windshield (1) has a curved surface. The system (3) comprises two wiper arms (14) and one wiper blade (5), one of said two wiper arms (14) being mounted to said oscillating gear drive (2), said wiper blade (5) being mounted by means of said two wiper arms (14) distal to said oscillating gear drive (2) for oscillation across the windshield (1). Said two wiper arms (14) have each along said curved surface of the windshield (1) a respectively pivotal wiper arm axis (8). At least one cranked fitting (16) and a prolongation fitting (7) are provided, said wiper blade (5) being mounted rotatable about a wiper blade rotation axis (9) by means of said wiper blade holder (21) and said wiper blade fit bolt (22) to said prolongation fitting (7). Said prolongation fitting (7) is mounted rotatable about prolongation fitting rotation axes (18).
    Type: Grant
    Filed: October 30, 2014
    Date of Patent: January 16, 2018
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Vitali Miller, Roland Luik
  • Drainage end cap device for draining fluid from a hollow space in a vehicle
    Patent number: 9862475
    Abstract: A drainage end cap device for draining fluid from a hollow space in a vehicle, comprising a mounting unit that is durably mountable in a super-imposed manner onto a drainage opening provided in an outer shell of a vehicle, wherein a drainage cap with a drainage channel is provided, the drainage cap being removably mountable to the mounting unit and the drainage channel being at least partly zigzagged over a longitudinal extension of the drainage cap.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: January 9, 2018
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventors: Helmut Fietz, Kaspar Von-Wilmowsky, Frank Singer
  • ROTARY WING AIRCRAFT WITH A FUSELAGE AND A NON-RETRACTABLE SKID-TYPE LANDING GEAR
    Publication number: 20170369159
    Abstract: A rotary wing aircraft with a fuselage and a non-retractable skid-type landing gear that is mounted to the fuselage, the non-retractable skid-type landing gear comprising at least one landing box, the at least one landing box being provided with a skid-type landing base member and an associated box shell that delimits an internal volume of the at least one landing box.
    Type: Application
    Filed: June 22, 2017
    Publication date: December 28, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Axel FINK