Patents Assigned to Airbus Helicopters Deutschland GmbH
  • External load mass rope of a rotorcraft
    Patent number: 9845154
    Abstract: An external load mass rope for attachment to a cargo hook device of a rotorcraft that comprises at least one first cargo hook and at least one second cargo hook, the external load mass rope comprising at least one first rope leg and at least one second rope leg, wherein the at least one first rope leg is adapted for attachment to the at least one first cargo hook and the at least one second rope leg is adapted for attachment to the at least one second cargo hook, characterized in that at least one of the first and second rope legs comprises an associated length adjustment unit that is adapted to shorten or lengthen the at least one of the first and second rope legs in operation on the basis of associated operating parameters.
    Type: Grant
    Filed: May 13, 2015
    Date of Patent: December 19, 2017
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventors: Michael Behrens, Markus Wahnfried
  • METHOD OF CORRECTING AN INAPPROPRIATE COUNTERSINK IN A COMPOSITE COMPONENT
    Publication number: 20170341322
    Abstract: A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of: Preparing a repair patch; Arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; Pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and Fixing the repair patch in the inappropriate countersink.
    Type: Application
    Filed: May 26, 2017
    Publication date: November 30, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Thomas JOACHIM, Andreas RACK, Josef LINDENMEIER, Tim SCHOENICKE
  • MULTI-BLADE ROTOR FOR A ROTARY WING AIRCRAFT
    Publication number: 20170341742
    Abstract: A multi-blade rotor for a rotary wing aircraft, comprising a plurality of rotor that is connected to an associated rotor head via a plurality of flexbeam elements, wherein at least one flexbeam element of the plurality of flexbeam elements comprises an asymmetrical flexbeam root that is mounted to the associated rotor head.
    Type: Application
    Filed: May 17, 2017
    Publication date: November 30, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Gerald KUNTZE-FECHNER, Martin ORTNER, Victoria OTTO, Christeline SALMON, Eugen RINK, Rupert PFALLER
  • RETRACTION / EXTENSION OF A LANDING GEAR IN AN AIRCRAFT
    Publication number: 20170341738
    Abstract: A telescoping strut for a retractable landing gear in an aircraft. The telescoping strut comprises a pre-pressurized and central extension chamber extending along the telescoping strut and a surrounding retraction chamber. For retraction, an hydraulic generation architecture of the aircraft feeds a single input/output passage of the surrounding retraction chamber with a overcoming fluid pressure that overwhelms a extension positive pressure in the central extension chamber and opposes the effect of the pre-pressurizing. The retraction system is for instance for a rotorcraft.
    Type: Application
    Filed: May 25, 2017
    Publication date: November 30, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Wolfram GRIESER
  • ROTARY WING AIRCRAFT WITH AN INTERFACE FRAME JOINING THE FUSELAGE TAIL BOOM AND THE TAIL CONE
    Publication number: 20170327200
    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: Application
    Filed: January 26, 2017
    Publication date: November 16, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Stefan PROBST, Philipp WALCH, Marc NOTHEN, Christian BUXEL, Romed SCHWEIZER, Thomas WUERFL
  • EXTRACTION DEVICE FOR EXTRACTING A TRIM WEIGHT FROM A ROTOR BLADE
    Publication number: 20170305003
    Abstract: An extraction device for extracting a trim weight from a rotor blade, comprising a supporting tube that is at least partly provided with a female thread, and a threaded rod that is at least partially arranged in the supporting tube, wherein the threaded rod is coupled to a fixing element that is adapted for being detachably fixed to the trim weight and that is at least partially provided with a male thread which engages at least partially the female thread of the supporting tube, and wherein the threaded rod is at least partly plastically deformable.
    Type: Application
    Filed: April 25, 2017
    Publication date: October 26, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Alois TANNHAEUSER
  • PROPELLER ASSEMBLY WITH AT LEAST TWO PROPELLER BLADES
    Publication number: 20170297677
    Abstract: A propeller assembly with at least two propeller blades that are interconnected by associated connection means, the associated connection means defining a common pitch axis for the at least two propeller blades in operation, each one of the at least two propeller blades comprising associated leading and trailing edges that define a respective chord and quarter chord line thereof, wherein the common pitch axis is arranged with a predetermined offset relative to the quarter chord line of each one of the at least two propeller blades, and wherein the associated connection means is adapted to enable, at least in operation in a non-axial inflow field, a passive pitch adjustment of the at least two propeller blades around the common pitch axis.
    Type: Application
    Filed: March 28, 2017
    Publication date: October 19, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Uwe KIESEWETTER, Stefan HAISCH, Marius BEBESEL, Sebastian MORES
  • HELICOPTER WITH A FUSELAGE AND A COMPOSITE TAIL BOOM
    Publication number: 20170297675
    Abstract: A helicopter with a fuselage and a composite tail boom. The composite tail boom has at least a tubular tail boom cone and a composite attachment ring segment that defines a mating face which is connected to the fuselage at an associated connection interface by means of a plurality of tension members that are oriented longitudinally with respect to a longitudinal extension direction of the composite tail boom. The plurality of tension members are distributed over a perimeter of the composite attachment ring segment 7. The composite attachment ring segment has a clamp ring section with a plurality of tension member accommodations. The clamp ring section defines the mating face of the composite attachment ring segment 7. The plurality of tension members is at least partly accommodated in the plurality of tension member accommodations.
    Type: Application
    Filed: March 28, 2017
    Publication date: October 19, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Axel FINK
  • METHOD OF MANUFACTURING A CONTROL CUFF FOR A ROTOR BLADE OF A HINGE AND BEARINGLESS ROTOR
    Publication number: 20170283051
    Abstract: A method of manufacturing a control cuff for a rotor blade of a hinge and bearingless rotor. The method comprises at least the steps of: manufacturing an outer shell, manufacturing a stiffener member by means of an automated process, inserting the stiffener member into the outer shell, and bonding the stiffener member to the outer shell.
    Type: Application
    Filed: December 13, 2016
    Publication date: October 5, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Joerg RADEKOPF, Philipp MEIERLING, Ulrich DENECKE
  • Rotor drive system
    Patent number: 9758245
    Abstract: A rotor drive for a tail rotor of a helicopter is provided. The system includes a stator and a rotor mounted to the stator with a rotatable central carrier. Rotor blades are radially attached to the rotatable central carrier and each of the rotor blades is pivotable about their respective radial central axis for variation of blade pitch. At least one permanent magnet is provided on each rotor blade. A plurality of electromagnets is provided on the stator close enough to allow inductive interaction between the plurality of electromagnets and the at least one permanent magnet on each rotor blade. The permanent magnets are offset from the radial central axis in a direction perpendicular to the rotation plane for individual pitch control of the rotor blades by individual control of electric supply to the electromagnets.
    Type: Grant
    Filed: June 10, 2014
    Date of Patent: September 12, 2017
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Tobias Ries
  • Flexbeam unit for a hingeless or a hinge and bearingless multi-blade rotor of a rotary wing aircraft
    Patent number: 9751623
    Abstract: A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements that define a predetermined number of torsion elements and a ring-shaped connection zone for attachment to a rotor hub associated with a rotor shaft of the multi-blade rotor, each flexbeam element passing the ring-shaped connection zone in a tangential manner and uninterruptedly connecting a first torsion element to a second torsion element of the predetermined number of torsion elements, wherein each flexbeam element overlaps at least one in the circumferential direction of the ring-shaped connection zone immediately following flexbeam element and is overlapped by at least one in the circumferential direction of the ring-shaped connection zone immediately preceding flexbeam element.
    Type: Grant
    Filed: January 12, 2015
    Date of Patent: September 5, 2017
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Rupert Pfaller
  • Device for protecting an individual sitting on a seat, a seat, and a vehicle
    Patent number: 9745065
    Abstract: A protection device having a set of inflatable protection members including a neck airbag, a left lower airbag, a left upper airbag, a right lower airbag, and a right upper airbag. The protection device has a lower pocket provided with a lower base forming the neck airbag and two lower lateral branches forming the left lower airbag and the right lower airbag. An upper pocket at least partially secured to the lower pocket is provided with an upper base forming a head airbag and two upper lateral branches forming the left upper airbag and the right upper airbag. At least one longitudinal internal wall provide at least two “tubes” in each upper airbag, the upper pocket being in fluid flow communication with the lower pocket.
    Type: Grant
    Filed: March 9, 2015
    Date of Patent: August 29, 2017
    Assignees: AIRBUS HELICOPTERS, AIRBUS HELICOPTERS DEUTSCHLAND GMBH, SCHROTH SAFETY PRODUCTS GMBH
    Inventors: Tomas Santana-Gallego, Ulf Gruene
  • Aircraft with an air intake for an air breathing propulsion engine
    Patent number: 9731831
    Abstract: An aircraft with a fuselage that accommodates at least one air breathing propulsion engine, the fuselage having a maximum fuselage width determined in the region of the at least one air breathing propulsion engine and comprising at least one front fuselage cowling and at least one rear fuselage cowling that are each covering the at least one air breathing propulsion engine at least partly, the at least one front and rear fuselage cowlings being spaced apart from each other in a direction transverse to a longitudinal axis of the at least one air breathing propulsion engine by a predetermined cowling offset to define a dynamic air intake through which an intake air stream is supplied to the at least one air breathing propulsion engine in operation.
    Type: Grant
    Filed: September 9, 2015
    Date of Patent: August 15, 2017
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Sebastian Mores, Frank Loeser, Stefan Probst, Michael Matt
  • Short term, autonomous, electrical power supply system
    Patent number: 9725180
    Abstract: A short term, autonomous, electrical power supply system, particularly an emergency short term, autonomous, electrical power supply system. Said system comprises an actuator with an electrical motor (14), an electrical generator (15) for driving said electrical motor (14) of said actuator, a turbine (13) in driving engagement with said electrical generator (15), an generator (7) of combustible, fluidic energy, a fluid line (10) from said generator (7) to said turbine (13), a control unit (5), and an igniter (9) arranged inside said generator (7) and controlled by said control unit (5).
    Type: Grant
    Filed: August 22, 2014
    Date of Patent: August 8, 2017
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Christoph Hubner, Uwe Renner
  • Blade attachment for a bearingless rotor of a helicopter
    Patent number: 9718542
    Abstract: A blade attachment (1, 20) for a bearingless main rotor of a helicopter with an airfoil blade (2), a flexbeam (3, 21) including a flexbeam body (16, 17) and a flexbeam head (13) at an end of the flexbeam body (16, 17). A control cuff (4, 22) encloses and extends along at least a predominant portion of the flexbeam (3, 21). A separable junction arrangement between the flexbeam head (13), the control cuff (4, 22) and the root end of the airfoil blade (2) is mechanical with removable fasteners. The removable fasteners comprise a main bolt (7) and at least one supporting bolt (8).
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: August 1, 2017
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Gerald Kuntze-Fechner, Markus Bauer, Martin Ortner
  • Connection joint for attaching an airfoil blade to a helicopter's bearingless main rotor
    Patent number: 9714579
    Abstract: An airfoil blade (2) of a bearingless rotor of a helicopter. Said airfoil blade (2) has a pitch axis from a tip end to a root end and said root end is provided with junction means for a separable junction arrangement of said airfoil blade (2) with a flexbeam head (13), and a control cuff (4, 22). Said junction arrangement is mechanical with removable fasteners respectively removable connecting said root end of said airfoil blade (2) to said control cuff (4, 22) and said flexbeam head (13). Said root end comprises at least two openings (7, 8) being asymmetric with regard to said pitch axis.
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: July 25, 2017
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Gerald Kuntze-Fechner, Markus Bauer, Martin Ortner
  • COMPOUND ROTORCRAFT
    Publication number: 20170197709
    Abstract: A compound rotorcraft with a fuselage and at least one main rotor, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein at least one propeller is provided and mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region.
    Type: Application
    Filed: September 8, 2016
    Publication date: July 13, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel FINK, Martin BLACHA
  • Subfloor structure with an integral hull for a rotary wing aircraft
    Patent number: 9688381
    Abstract: The invention relates to a subfloor structure with an integral hull, for a rotary wing aircraft. The subfloor structure comprises an integral subfloor hull that defines in one piece, upward web portions acting as longerons and a bottom central portion offering both load bearing capabilities and aerodynamical loft features. The subfloor structure is useful for rotary wing aircrafts such as helicopters, and is e.g. made of composite and/or light alloy such as aluminum.
    Type: Grant
    Filed: December 22, 2014
    Date of Patent: June 27, 2017
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventor: Axel Fink
  • AIRCRAFT WITH A HOT AIR EXHAUST THAT COMPRISES TWO PIVOTALLY MOUNTED EXHAUST SECTIONS
    Publication number: 20170175673
    Abstract: An aircraft with at least one engine that generates a hot air flow in operation of the aircraft, wherein at least one hot air exhaust is provided for exhausting the generated hot air flow, the at least one hot air exhaust comprising at least one first exhaust section that is mounted in a rotatable manner to at least one second exhaust section via an associated off-axis swivel joint, wherein an actuating member is provided that is adapted for applying a turning moment to the at least one second exhaust section in operation of the aircraft in order to displace a longitudinal axis of the at least one second exhaust section with respect to a longitudinal axis of the at least one first exhaust section by a predetermined displacement angle.
    Type: Application
    Filed: November 30, 2016
    Publication date: June 22, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Christian WELLHAUSEN
  • MAINTENANCE STEP FOR A HELICOPTER
    Publication number: 20170121008
    Abstract: A maintenance step for a helicopter, comprising: a casing that is adapted for integration into a lateral shell of a fuselage of a helicopter, and a step member that is pivotally mounted to the casing, wherein a stirrup unit is pivotally mounted to the step member, the stirrup unit comprising at least a first and a second section, the second section being telescopically mounted to the first section.
    Type: Application
    Filed: October 27, 2016
    Publication date: May 4, 2017
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Christoph STEINDL, Dominik STROBEL