Patents Assigned to Airbus Helicopters Deutschland GmbH
  • AIRCRAFT WITH A SAFETY DISTANCE DISPLAY APPARATUS
    Publication number: 20200217968
    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: Application
    Filed: November 19, 2019
    Publication date: July 9, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Lieven DESMET
  • ATTACHMENT OF A LANDING GEAR
    Publication number: 20200216169
    Abstract: A bracket for connecting a traverse of a landing gear to a cabin of a helicopter. A landing gear retainer is fixed around the traverse coaxially to the longitudinal direction of the traverse and at least one cabin clamp mount is fixed to the cabin. The landing gear retainer is in between the cabin and upper and lower pendulum bolts and upper and lower pendulum bearings. A pendulum is in longitudinal direction of the traverse hinged to the landing gear retainer. The invention is further related to an application of such brackets.
    Type: Application
    Filed: March 17, 2020
    Publication date: July 9, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Kaspar VON-WILMOWSKY, Johannes MARKMILLER
  • Method of correcting an inappropriate countersink in a composite component
    Patent number: 10695995
    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: Grant
    Filed: May 26, 2017
    Date of Patent: June 30, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Thomas Joachim, Andreas Rack, Josef Lindenmeier, Tim Schoenicke
  • Shrouded rotary assembly from segmented composite for aircraft
    Patent number: 10683087
    Abstract: A shrouded rotor assembly for an aircraft. The shrouded rotor assembly comprises a stator hollow structure comprises formed from a plurality of composite angular segments. Each composite angular segment includes: a core arched section of a central hub casing, a peripheral rim section of an external hollow duct and a pair of angularly opposed sliced portions, respectively for one of a pair of guide vanes. The resulting stator hollow structure is a unitary one-piece, integrating together continuously the composite angular segments. The invention typically applies e.g. to aircrafts such as rotary wing aircrafts.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: June 16, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Stefan Probst, Marc Nothen, Christian Wehle
  • FOREIGN OBJECT IMPACT PROOF WINDSHIELD ASSEMBLY
    Publication number: 20200180748
    Abstract: A vehicle with a vehicle frame and a windshield assembly that is mounted to the vehicle frame and closes an associated opening provided in the vehicle frame. The windshield assembly comprises at least one flexible element and at least one windshield. The at least one flexible element connects the at least one windshield to the vehicle frame for at least partially absorbing loads resulting from an impact on the at least one windshield. The at least one flexible element connects the at least one windshield to the vehicle frame such that the at least one windshield pivots relative to the vehicle frame by means of the at least one flexible element upon occurrence of an impact on the at least one windshield such that the at least one flexible element defines a hinge element.
    Type: Application
    Filed: October 7, 2019
    Publication date: June 11, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Christian REICHENSPERGER, Mikko SCHNIZER, Lars WOLTERS
  • ATTACHMENT FOR SUSPENDING AN AIRCRAFT ENGINE
    Publication number: 20200180773
    Abstract: An attachment for attaching an aircraft engine with a first receiving element to an aircraft structure with a second receiving element may include at least three fasteners and a stacked layer. Stacked layer may include at least two sheets, at least three holes through the stacked layer, a first connecting portion that includes a first hole of the at least three holes, a second connecting portion that includes second and third holes of the at least three holes, and a suspension portion that is located between the first connecting portion and the second connecting portion.
    Type: Application
    Filed: October 17, 2019
    Publication date: June 11, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Martin BLACHA, Marc SCHELCHER, Adriana GARCIA RIOS
  • VERTICAL TAKE-OFF AND LANDING MULTIROTOR AIRCRAFT WITH AT LEAST EIGHT THRUST PRODUCING UNITS
    Publication number: 20200164972
    Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight thrust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.
    Type: Application
    Filed: October 17, 2019
    Publication date: May 28, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Uwe KIESEWETTER, Christian REICHENSPERGER, Lukasz PALUSZEK, Klaus KICKER
  • Pitch control device for a ducted tail rotor of a rotorcraft
    Patent number: 10654559
    Abstract: A pitch control device for a ducted tail rotor of a rotorcraft. The pitch control device comprises a control input member with a disc-shaped central component and at least two connecting arms that extend radially from the disc-shaped central component, wherein the disc-shaped central component is provided for being mounted to an associated pitch control shaft of the ducted tail rotor, and a control transfer member with a ring-shaped connector and at least two push rods that extend axially from the ring-shaped connector, wherein each one of the at least two push rods is provided for being coupled to an associated pitch lever of a rotor blade of the ducted tail rotor.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: May 19, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Julius Vogl, Gerald Kuntze-Fechner, Victoria Otto
  • Control system for controlling at least collective pitch of rotor blades of a multi-blade rotor in a rotary-wing aircraft
    Patent number: 10654568
    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: Grant
    Filed: July 21, 2017
    Date of Patent: May 19, 2020
    Assignee: AIRBUS HELICOPTER DEUTSCHLAND GMBH
    Inventors: Benedikt Bammer, Gerald Kuntze-Fechner
  • Actuatable emergency exit door and an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door
    Patent number: 10647403
    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: Grant
    Filed: October 17, 2017
    Date of Patent: May 12, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Christoph Merkel, Stephen Ward, Michal Vinarsky, Florian Naumann
  • COMPOUND HELICOPTER WITH A FIXED WING ARRANGEMENT
    Publication number: 20200140072
    Abstract: A compound helicopter with a fuselage and at least one main rotor that is at least adapted for generating lift in operation, the at least one main rotor being arranged in an upper region of the fuselage, wherein at least one propeller is provided that is at least adapted for generating forward and/or backward thrust in operation. The at least one propeller is mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing and at least one lower wing. An upper stub wing arrangement is provided in the upper region of the fuselage, the at least one upper wing of the fixed wing arrangement being mounted to the upper stub wing arrangement.
    Type: Application
    Filed: October 7, 2019
    Publication date: May 7, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Martin BLACHA
  • Attachment of a landing gear
    Patent number: 10625848
    Abstract: A bracket (24) for connecting a traverse (20) of a landing gear to a cabin of a helicopter. A landing gear retainer (5) is fixed around the traverse (20) coaxially to the longitudinal direction of the traverse (20) and at least one cabin clamp mount (7) is fixed to the cabin. The landing gear retainer (5) is in between the cabin and upper and lower pendulum bolts (12, 13) and upper and lower pendulum bearings (18, 19). A pendulum (9) is in longitudinal direction of the traverse (20) hinged to the landing gear retainer (5). The invention is further related to an application of such brackets (24).
    Type: Grant
    Filed: September 18, 2014
    Date of Patent: April 21, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Kaspar Von-Wilmowsky, Johannes Markmiller
  • DOOR OPENING SYSTEM WITH A DECELERATION MECHANISM
    Publication number: 20200115028
    Abstract: A door opening system with a deceleration mechanism may be adapted to control an opening of a door module that includes a door panel and a door frame. Deceleration mechanism may include strap that connects door panel with door frame, spool, and spool. Spool may receive one end of strap, is biased to roll up a first portion of strap, and adapted to perform a first unwinding of the first portion of strap. Spool may receive a second end of strap, is biased to roll up a second portion of strap, and adapted to perform a second unwinding of the second portion of strap from spool. Spool may include a braking apparatus that is adapted to decelerate the second unwinding when a velocity of the second unwinding is above a predetermined threshold.
    Type: Application
    Filed: October 9, 2019
    Publication date: April 16, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Thomas TENDYRA, Stephen WARD, Guido BORCHERS, Uwe RENNER, Xaver PASCOE, Markus BUEHLMEYER
  • Method of controlling an artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system
    Patent number: 10577083
    Abstract: A method of controlling an artificial force feel generating device for generation of an artificial feeling of force on an inceptor that is adapted for controlling a servo-assisted control unit of a vehicle control system, wherein the artificial force feel generating device comprises at least one force generating device that is mechanically connected to the inceptor for generating a tactile cue force acting in operation on the inceptor, and wherein a safety device is provided for limiting authority of the at least one force generating device, the method comprising at least the steps of: monitoring usage of the safety device during operation of the artificial force feel generating device, determining a current accumulated fatigue of the safety device on the basis of the monitored usage, and re-configuring the at least one force generating device on the basis of the current accumulated fatigue.
    Type: Grant
    Filed: May 16, 2018
    Date of Patent: March 3, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Boris Grohmann, Thomas Rohr
  • MULTIROTOR AIRCRAFT WITH A THRUST PRODUCING UNIT THAT COMPRISES AN AERODYNAMICALLY OPTIMIZED SHROUDING
    Publication number: 20200062377
    Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein a carrier beam is at least mounted at a leading edge region of the cylindrical air duct to the shrouding such that the carrier beam is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, the at least one electrical engine being mounted to the carrier beam.
    Type: Application
    Filed: June 12, 2019
    Publication date: February 27, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Christian REICHENSPERGER, Uwe KIESEWETTER, Petr SCHEJBAL, Lukasz PALUSZEK, Klaus KICKER, Martin BLACHA
  • MOUNTING SYSTEM FOR A PRESSURE SEAL OF AN AIRCRAFT DOOR
    Publication number: 20200062371
    Abstract: An aircraft door, and, more particularly, to a mounting system for a pressure seal of an aircraft door. A mounting system may include an outer skin, a pressure seal, a clamping component, a pressure seal fastener having a head and a threaded shank, a nut, a mounting support having a clearance hole that is adapted to prevent a rotational and axial movement of the pressure seal fastener, and mounting support fasteners. Mounting support fasteners removably attach the mounting support to the outer skin. The head of the pressure seal fastener is connected to the mounting support such that a rotational and axial movement of the pressure seal fastener is prevented. The nut is removably attached to the threaded shank of the pressure seal fastener, thereby removably clamping the pressure seal between the clamping component and the mounting support.
    Type: Application
    Filed: July 10, 2019
    Publication date: February 27, 2020
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Thomas HACKENBERG, Thomas THIESS, Dirk TROTT
  • Rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel
    Patent number: 10556662
    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: Grant
    Filed: July 21, 2017
    Date of Patent: February 11, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel Fink, Andreas Rack, Helmut Fietz
  • Artificial force feel generating device for a vehicle control system of a vehicle and, in particular, of an aircraft
    Patent number: 10556668
    Abstract: An artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system, the inceptor being adapted for controlling a servo-assisted control unit of the vehicle control system via a mechanical linkage, wherein at least one first force generating device and at least one second force generating device are mechanically connected to the inceptor, the first force generating device being provided for generating a nominal force acting in operation on the inceptor and the second force generating device being provided for generating a tactile cue force acting in operation on the inceptor, the first and second force generating devices being arranged in parallel. The invention relates further to an aircraft comprising such an artificial force feel generating device.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: February 11, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Boris Grohmann, Thomas Rohr, Jens Klaubert
  • Method of manufacturing a control cuff for a rotor blade of a hinge and bearingless rotor
    Patent number: 10532811
    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: Grant
    Filed: December 13, 2016
    Date of Patent: January 14, 2020
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventors: Joerg Radekopf, Philipp Meierling, Ulrich Denecke
  • Aircraft with a hot air exhaust that comprises two pivotally mounted exhaust sections
    Patent number: 10527000
    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: Grant
    Filed: November 30, 2016
    Date of Patent: January 7, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Christian Wellhausen