Patents Assigned to Airbus Helicopter Deutschland GmbH
  • Electrical battery monitoring device and battery
    Patent number: 11378627
    Abstract: A battery and an electrical battery monitoring device are disclosed having a first group of sensing switches connected in series on a first monitoring circuit, the sensing switches, a second group of electrical sensing switches connected in series on a second monitoring circuit, an input unit to provide an input to the first and second monitoring circuits, a monitoring unit to receive an output from the first and second monitoring circuits, wherein the monitoring unit receives at least two outputs from two measuring points of the first monitoring circuit, the two measuring points being separated by at least one sensing switch. The location of a defective battery cell may be early detected and precisely located by the monitoring of the battery cells in rows and columns.
    Type: Grant
    Filed: August 2, 2019
    Date of Patent: July 5, 2022
    Assignees: AIRBUS HELICOPTERS DEUTSCHLAND GmbH, AIRBUS DEFENCE AND SPACE GmbH
    Inventors: Philipp Weinreiter, Kristian Zimmermann
  • PITCH ANGLE BLOCKING DEVICE
    Publication number: 20220194570
    Abstract: A pitch angle blocking device for blocking the pitch angle of a multi-blade rotor that has neighboring first and second rotor blades in circumferential direction that extend from a rotor hub of a rotary-wing aircraft In non-operational mode of the rotary-wing aircraft. The present embodiments further relate to a multi-blade rotor of a rotary-wing aircraft that is adapted to receiving such a pitch angle blocking device, and to a rotary-wing aircraft with such a multi-blade rotor. The pitch angle blocking device comprises first and second attachment means that are configured to be non-rotatably and releasably attached to the first and second rotor blades spaced apart from the rotor hub, and a connecting device that non-rotatably connects the first attachment means with the second attachment means.
    Type: Application
    Filed: August 16, 2021
    Publication date: June 23, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Moritz BUESING, Bernward KAHL, Markus BAUER
  • ROTARY WING AIRCRAFT WITH A STABILIZER ARRANGEMENT
    Publication number: 20220185467
    Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, and a stabilizer arrangement that is arranged at the rear section in the aft region, wherein the rear section extends between the front section and the stabilizer arrangement and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.
    Type: Application
    Filed: August 18, 2021
    Publication date: June 16, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Rupert PFALLER, Tobias RIES
  • ROTARY WING AIRCRAFT WITH AN ASYMMETRICAL REAR SECTION
    Publication number: 20220185465
    Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, a shrouded duct that is arranged in the aft region, and a propeller that is rotatably mounted to the shrouded duct, wherein the rear section extends between the front section and the shrouded duct and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.
    Type: Application
    Filed: July 15, 2021
    Publication date: June 16, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Rupert PFALLER, Tobias RIES
  • ROTARY WING AIRCRAFT WITH AN ASYMMETRICAL FRONT SECTION
    Publication number: 20220185466
    Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, wherein the rear section extends between the front section and the aft region, the rotary wing aircraft comprising: a propeller that is rotatably mounted at the rear section in the aft region, a main rotor that is rotatably mounted at the front section, and a source of asymmetry that is connected to the front section such that the front section comprises at least in sections an asymmetrical cross-sectional profile in direction of the associated roll axis, wherein the source of asymmetry is configured to generate sideward thrust for main rotor anti-torque from main rotor downwash.
    Type: Application
    Filed: July 16, 2021
    Publication date: June 16, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Rupert PFALLER, Tobias RIES
  • COMPOUND HELICOPTER WITH BRACED WINGS IN JOINED-WING CONFIGURATION
    Publication number: 20220169372
    Abstract: A compound helicopter with braced wings in joined-wing configuration, a fuselage that extends from a front fuselage section to a rear fuselage section, and an emergency floatation system with main floatation balloons and lateral floatation balloons, wherein the main floatation balloons comprise at least one front floatation balloon that is arranged in the front fuselage section 4a and at least one rear floatation balloon that is arranged in the rear fuselage section, and wherein the lateral floatation balloons comprise at least one first lateral floatation balloon that is arranged close to an interconnection region of the first braced wing and at least one second lateral floatation balloon that is arranged close to an interconnection region of the second braced wing.
    Type: Application
    Filed: June 17, 2021
    Publication date: June 2, 2022
    Applicants: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERS
    Inventors: Axel FINK, Pierre PARDOUX, Dominique MAILLIU
  • STIFFENER SKELETON FOR A FIREWALL ARRANGEMENT OF A ROTARY WING AIRCRAFT
    Publication number: 20220161915
    Abstract: A stiffener skeleton that is configured to be mounted to an upper deck of a rotary wing aircraft in a maintenance phase, comprising an upper stiffening structure with a plurality of supporting arms for providing upside stiffening support, and a lateral stiffening structure with a plurality of supporting legs for providing lateral stiffening support, wherein the plurality of supporting arms and the plurality of supporting legs form a self-supporting frame structure.
    Type: Application
    Filed: June 17, 2021
    Publication date: May 26, 2022
    Applicants: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERS
    Inventors: Aurelien VAYSSIERE, Nicolas MONTIL, Mathieu GESTER, Hubert NEUKIRCH, Pascal JERVAISE, Markus KAMMERER, Pierre ARNOULD
  • DRIVE SHAFT WITH AN INTEGRATED FLANGE
    Publication number: 20220154762
    Abstract: A drive shaft made from composite materials that comprises a hollow body and a flange that is integrally formed with the hollow body. The hollow body is adapted to rotating around an associated rotation axis and is made of a first composite material. The flange is made of a second composite material and arranged at an axial end of the hollow body. The flange comprises at least two separate plates that branch out from the hollow body at the axial end. The flange further comprises a mounting section that is configured to be mounted to an external component and comprises a plurality of holes that is adapted to accommodate coupling means.
    Type: Application
    Filed: August 18, 2021
    Publication date: May 19, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Rupert PFALLER, Moritz BUESING
  • DOOR FOR SEPARATING TWO ENVIRONMENTS WITH DIFFERENT PRESSURES
    Publication number: 20220136290
    Abstract: A door that is adapted to separating two environments with different pressures and to an aircraft with such a door. The door may include a door leaf, a door frame having a door stop and a roller, and an actuating system having a latch element and an inward-moving drive system. The inward-moving drive system may include a puller shaft and a puller that is non-rotatably attached to the puller shaft. The puller may include a guide rail that moves along the roller during a rotation of the puller such that the puller moves the door leaf in direction of the first environment thereby disengaging the latch element from the door stop.
    Type: Application
    Filed: August 20, 2021
    Publication date: May 5, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Thomas TENDYRA, Stefan BECKER, Torsten QUECK, Kai SIMON, Christian FERBER, Christoph MERKEL
  • RADOME COVER SHELL AND OPENING KINEMATIC
    Publication number: 20220126976
    Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail.
    Type: Application
    Filed: October 22, 2020
    Publication date: April 28, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Jan BOEHME, Yann LE CADET, Martin LAZAK
  • RADOME COVER SHELL AND OPENING KINEMATIC
    Publication number: 20220126977
    Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail. The radome shell opening kinematic further comprises a radome cover shell rotation stopper that can stop movement of the radome cover shell at the completely opened position.
    Type: Application
    Filed: December 3, 2020
    Publication date: April 28, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Jan BOEHME, Yann LE CADET, Martin LAZAK
  • BATTERY FOR AN AIRCRAFT
    Publication number: 20220123409
    Abstract: A battery for an aircraft. The present embodiments further relate to an aircraft with at least one such battery. The battery may include a battery casing with a casing wall that forms an interior volume, a plurality of battery cells that is arranged in the interior volume, and a functional layer that is arranged at the casing wall between the plurality of battery cells and the battery casing. The functional layer may include an intumescent material that, in case of a breach of the battery casing, is adapted to ensuring flame containment within the interior volume and mitigation of uncontrolled heat and gas emission from the interior volume through the breach of the battery casing.
    Type: Application
    Filed: June 17, 2021
    Publication date: April 21, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Johannes ROETHINGER, Manuel KEMPF, Maximo HENARES-EXTREMERA
  • Vehicle control system for autonomous, remotely-controlled, or manual operation of a vehicle
    Patent number: 11305787
    Abstract: A vehicle control system for controlling a vehicle and to a method of operating such a vehicle control system. The vehicle control system may include an inceptor adapted for controlling a servo-assisted control unit via a mechanical linkage, first and second force generating devices that are mechanically connected to the inceptor in parallel and provided for generating respective first and second forces that act in operation on the inceptor, a hands-on/off detection management unit, and a decoupling device that mechanically decouples the second force generating device from the inceptor based on a control signal from the hands-on/off detection management unit.
    Type: Grant
    Filed: June 11, 2020
    Date of Patent: April 19, 2022
    Assignees: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERS
    Inventors: Boris Grohmann, Thomas Rohr, Nicolas Avril, Axel Guse
  • Information projection and control system
    Patent number: 11292609
    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: Grant
    Filed: February 5, 2020
    Date of Patent: April 5, 2022
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Daniel Waffler, Uwe Renner
  • Door system with a deceleration mechanism
    Patent number: 11274484
    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: Grant
    Filed: November 19, 2019
    Date of Patent: March 15, 2022
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Thomas Tendyra, Uwe Renner, Xaver Pascoe, Markus Buehlmeyer, Stephen Ward, Guido Borchers
  • En route fluid transmitting apparatus
    Patent number: 11273926
    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: Grant
    Filed: November 18, 2019
    Date of Patent: March 15, 2022
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Yann Le Cadet, Samuel Pellerin
  • Composite laminate and load-introduction component for a load-introduction joint
    Patent number: 11274688
    Abstract: A composite laminate for connection to at least one attachment component in a load-introduction joint, said composite laminate comprising an opening that is adapted to receive a load-introduction component of said load-introduction joint, wherein a prefailure indication element is provided in the region of said opening, said prefailure indication element being modifiable by said load-introduction component in a prefailure mode of said load-introduction joint for indication of an impending function-affecting failure of said composite laminate. The invention is further related to a corresponding load-introduction component.
    Type: Grant
    Filed: March 20, 2019
    Date of Patent: March 15, 2022
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Moritz Buesing
  • AIRCRAFT WITH A FUEL STORAGE SYSTEM
    Publication number: 20220063830
    Abstract: An aircraft with a fuselage that accommodates a floor panel and a fuel storage system, wherein the fuel storage system comprises a tank system with at least one main tank 5a that is arranged underneath the floor panel; a cross ventilation system with a plurality of ventilation lines for venting the tank system, wherein the plurality of ventilation lines comprises at least one crossing ventilation line 11a that is routed from a first lateral side of the tank system to an opposite second lateral side of the tank system; and wherein the at least one crossing ventilation line is routed underneath or in the floor panel from the first lateral side of the tank system to the second lateral side of the tank system.
    Type: Application
    Filed: April 13, 2021
    Publication date: March 3, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Marcello BARRETO DE PINHO
  • MEASUREMENT APPARATUS FOR DETERMINING A BENDING MOMENT
    Publication number: 20220065738
    Abstract: A measurement apparatus for determining a bending moment acting on a hollow cylindrical body in a current state as well as to a method of operating such a measurement apparatus. The measurement apparatus may include a sensor support structure, a sensor arrangement with sensors, and a processing system. The processing system may determine displacements of the inner surface of the hollow cylindrical body relative to the sensors based on the distances measured in the current state compared to the distances measured during an initial undeformed state, and determine the bending moment acting on the hollow cylindrical body based on the displacements.
    Type: Application
    Filed: March 16, 2021
    Publication date: March 3, 2022
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Georg WURZEL, Johannes FIEK, Christoph GIERLICH
  • Thrust producing unit with at least two rotor assemblies and a shrouding
    Patent number: 11220325
    Abstract: A thrust producing unit for producing thrust in a predetermined direction, comprising at least two rotor assemblies and a shrouding that accommodates at most one of the at least two rotor assemblies, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein the air inlet region exhibits in circumferential direction of the cylindrical air duct an undulated geometry.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: January 11, 2022
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Uwe Kiesewetter, Sebastian Mores, Marius Bebesel, Rupert Pfaller