Patents by Inventor Axel Fink

Axel Fink has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20240294251
    Abstract: A rotorcraft comprising a fuselage forming at least one lower lateral fuselage compartment with at least a first fitting, a second fitting, and a third fitting; and at least one non-retractable wheel-type landing gear that comprises: at least one wheel; a shock absorber with a shock absorber tube having an open end and an axially opposed closed end, and a shock absorber rod telescopically mounted to the shock absorber tube via the open end; a first fixation provided close to the open end on the shock absorber tube and connected to the first fitting; a second fixation provided close to the closed end on the shock absorber tube and connected to the second fitting; and a third fixation provided close to the closed end on the shock absorber tube and connected to the third fitting.
    Type: Application
    Filed: November 15, 2023
    Publication date: September 5, 2024
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel FINK, Reynaldo OIOLI-NETO
  • Publication number: 20240190557
    Abstract: A non-retractable wheel-type landing gear for a rotorcraft, comprising: at least one wheel; a shock absorber with a circumferential direction, which is connected to the at least one wheel and comprises a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; a mounting arm extending laterally from the shock absorber tube, the mounting arm being integrally formed with the shock absorber tube and adapted for attachment to a first fitting of a rotorcraft; and a link fixation extending laterally from the shock absorber tube, the link fixation being arranged in the circumferential direction of the shock absorber at an angle in a range from 45° to 120° with respect to the mounting arm and adapted for connection to a second fitting of the rotorcraft.
    Type: Application
    Filed: August 15, 2023
    Publication date: June 13, 2024
    Applicants: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERS
    Inventors: Axel FINK, Reynaldo OIOLI-NETO, Didier BERTIN
  • Publication number: 20240182160
    Abstract: A rotorcraft with at least one non-retractable wheel-type landing gear and a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one non-retractable wheel-type landing gear is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber connected to the at least one wheel and comprising a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; at least two mounting arms extending laterally from the shock absorber tube; and a mounting pin extending from the shock absorber tube toward a floor fitting provided at the inner floor, wherein the mounting pin is connected to the floor fitting.
    Type: Application
    Filed: August 14, 2023
    Publication date: June 6, 2024
    Applicants: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERS
    Inventors: Axel FINK, Aurelien ACHARD, Didier BERTIN
  • Publication number: 20240182161
    Abstract: A rotorcraft with at least one non-retractable wheel-type landing gear and a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one non-retractable wheel-type landing gear is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber connected to the at least one wheel and comprising a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; at least two mounting arms extending laterally from the shock absorber tube; and a mounting pin device extending laterally from the shock absorber tube and comprising a mounting pin connected to a floor fitting provided at the inner floor.
    Type: Application
    Filed: August 8, 2023
    Publication date: June 6, 2024
    Applicants: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERS
    Inventors: Axel FINK, Aurelien ACHARD, Didier BERTIN
  • Patent number: 11999469
    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 wherein balloons, the main floatation balloons comprise at least one front floatation balloon that is arranged in the front fuselage section 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: Grant
    Filed: June 17, 2021
    Date of Patent: June 4, 2024
    Assignees: AIRBUS HELICOPTERS DEUTSCHLAND GmbH, AIRBUS HELICOPTERS
    Inventors: Axel Fink, Pierre Pardoux, Dominique Mailliu
  • Publication number: 20230408702
    Abstract: A method for identifying blooming candidates in a Lidar measurement may include providing a distance-based histogram of points of a point cloud generated in the Lidar measurement. In the histogram, clusters of points having the same distance to a Lidar sensor carrying out the Lidar measurement are identified and intensities of the points of a cluster are evaluated. If the cluster contains points, the intensities of which exceed in each case a predefined limit value, those points of the cluster, the intensities of which do not exceed in each case the predefined limit value and in particular fall below the predefined limit value by more than a predefined threshold value, are classified as blooming candidates.
    Type: Application
    Filed: September 8, 2021
    Publication date: December 21, 2023
    Inventors: David PETER, Matthias PFENDER, Markus ENZWEILER, Axel FINK, Philipp LEHNER
  • Patent number: 11820485
    Abstract: A rotary wing aircraft with a fuselage that comprises an upper primary skin and an aircraft upper deck arranged above the fuselage, wherein the aircraft upper deck comprises a firewall arrangement that defines a fire proof separation at least between at least one aircraft engine and an aircraft interior region, wherein the firewall arrangement comprises at least one funnel-shaped lower firewall that is arranged between the at least one aircraft engine and the upper primary skin of the fuselage, wherein the at least one funnel-shaped lower firewall converges from an outer perimeter to at least one inner collecting point, and wherein the outer perimeter is spaced apart from the upper primary skin of the fuselage.
    Type: Grant
    Filed: March 3, 2021
    Date of Patent: November 21, 2023
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel Fink, Manuel Kempf
  • Patent number: 11691722
    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: Grant
    Filed: December 3, 2019
    Date of Patent: July 4, 2023
    Assignee: AIRBUS URBAN MOBILITY GMBH
    Inventors: Axel Fink, Uwe Kiesewetter, Klaus Kicker
  • Patent number: 11591061
    Abstract: A boom for an aircraft, and, more particularly, to a tail boom for a helicopter, whereby the tail boom may comprise a watertight compartment and watertight bulkheads. The watertight bulkheads may close at least one end of watertight compartment. Watertight bulkhead may include attachment device, frame, and watertight fabric.
    Type: Grant
    Filed: December 2, 2020
    Date of Patent: February 28, 2023
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Axel Fink
  • 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
  • Publication number: 20220169361
    Abstract: A boom for an aircraft, and, more particularly, to a tail boom for a helicopter, whereby the tail boom may comprise a watertight compartment and watertight bulkheads. The watertight bulkheads may close at least one end of watertight compartment. Watertight bulkhead may include attachment device, frame, and watertight fabric.
    Type: Application
    Filed: December 2, 2020
    Publication date: June 2, 2022
    Inventor: Axel FINK
  • Publication number: 20210403139
    Abstract: A rotary wing aircraft with a fuselage that comprises an upper primary skin and an aircraft upper deck arranged above the fuselage, wherein the aircraft upper deck comprises a firewall arrangement that defines a fire proof separation at least between at least one aircraft engine and an aircraft interior region, wherein the firewall arrangement comprises at least one funnel-shaped lower firewall that is arranged between the at least one aircraft engine and the upper primary skin of the fuselage, wherein the at least one funnel-shaped lower firewall converges from an outer perimeter to at least one inner collecting point, and wherein the outer perimeter is spaced apart from the upper primary skin of the fuselage.
    Type: Application
    Filed: March 3, 2021
    Publication date: December 30, 2021
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel FINK, Manuel KEMPF
  • Patent number: 10981650
    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: Grant
    Filed: December 4, 2019
    Date of Patent: April 20, 2021
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel Fink, Uwe Kiesewetter, Klaus Kicker
  • Patent number: 10870488
    Abstract: A braced wing aircraft with a fuselage and a fixed wing arrangement, the fixed wing arrangement comprising at least two braced wings that are arranged laterally and opposite to each other on the fuselage, each one of the at least two braced wings comprising at least one upper wing and at least one lower wing which are staggered and interconnected at a predetermined transition region, the at least one upper wing being connected to the fuselage at an associated upper wing root and the at least one lower wing being connected to the fuselage at an associated lower wing root.
    Type: Grant
    Filed: October 8, 2018
    Date of Patent: December 22, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Martin Blacha, Axel Fink
  • 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
  • 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
  • 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
  • Patent number: 10457373
    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: Grant
    Filed: July 20, 2017
    Date of Patent: October 29, 2019
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Axel Fink
  • Publication number: 20190152603
    Abstract: A braced wing aircraft with a fuselage and a fixed wing arrangement, the fixed wing arrangement comprising at least two braced wings that are arranged laterally and opposite to each other on the fuselage, each one of the at least two braced wings comprising at least one upper wing and at least one lower wing which are staggered and interconnected at a predetermined transition region, the at least one upper wing being connected to the fuselage at an associated upper wing root and the at least one lower wing being connected to the fuselage at an associated lower wing root.
    Type: Application
    Filed: October 8, 2018
    Publication date: May 23, 2019
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Martin BLACHA, Axel FINK
  • Patent number: 10279885
    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: Grant
    Filed: March 28, 2017
    Date of Patent: May 7, 2019
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Axel Fink