Patents Examined by Anna L. Gordon
  • Patent number: 12263939
    Abstract: An apparatus is for attaching an aerodynamically functional film to a surface of a body around which flow passes. The apparatus includes: a self-adhesive, redetachable positioning film having positioning aids for the exact positioning of the positioning film on the surface of the body around which flow passes and having at least one application area for the aerodynamically functional film that is to be applied.
    Type: Grant
    Filed: November 27, 2020
    Date of Patent: April 1, 2025
    Assignee: LUFTHANSA TECHNIK AG
    Inventors: Oliver Oeser, Dirk Trottnow, Andreas Flanschger, Kai-Christoph Pfingsten
  • Patent number: 12258125
    Abstract: A lift system for an aircraft includes a first galley cart, a second galley cart, a floor deck, and a frame. The frame defines a first storage zone, a second storage zone, and a third storage zone that are stacked. A bottom end of the first storage zone is aligned with the floor deck, a top end of the second storage zone is aligned with the floor deck, and a bottom end of the third storage zone is aligned with a top end of the first storage zone. The lift system also includes a first lift configured to move the first galley cart from the first storage zone to the second storage zone and a second lift configured to move the second galley cart from the first storage zone to the third storage zone.
    Type: Grant
    Filed: January 26, 2022
    Date of Patent: March 25, 2025
    Assignee: The Boeing Company
    Inventors: Sergey D. Barmichev, Aaron J. Kutzmann
  • Patent number: 12252241
    Abstract: A Stability and Control Augmentation System (“SCAS”) module includes a SCAS actuator. The SCAS actuator has a substantially cylindrical hydraulic chamber having a first and second regions. A piston is arranged for linear motion in first and second directions along an axis of the hydraulic chamber. The SCAS module also includes a valve system for controlling a flow of a hydraulic fluid into the hydraulic chamber. The valve system has: at least one supply line arranged to provide a first fluid flow path to the first region of the hydraulic chamber and/or a second fluid flow path to the second region of the hydraulic chamber, and a moveable valve member arranged to have a position between a first and second positions.
    Type: Grant
    Filed: October 4, 2022
    Date of Patent: March 18, 2025
    Assignee: MICROTECNICA S.R.L.
    Inventors: Domenico Tafuni, Simone Allevi
  • Patent number: 12246833
    Abstract: A sealing device for covering an aperture in a wing part of an aircraft is disclosed having an interface section for fixedly mounting the sealing device to a surface of the wing part adjacent the aperture, a connecting section, and a cover section for covering at least a part of the aperture. The connecting section is arranged between the interface section and the cover section and connects the interface section and the cover section. The connecting section is adapted to resiliently hold the cover section in a predetermined orientation relative to the interface section to cover at least a part of the aperture. The cover section comprises a contact portion for contacting a surface of an actuation element that protrudes through the aperture.
    Type: Grant
    Filed: June 1, 2023
    Date of Patent: March 11, 2025
    Assignee: AIRBUS OPERATIONS GmbH
    Inventors: Bernhard Schlipf, Atra Gemilang
  • Patent number: 12246838
    Abstract: An aircraft cabin (100) is disclosed. The aircraft cabin (100) comprises a plurality of pairs of seat units (120) positioned along an aisle (101). Each aisle seat unit (122A) comprises an aisle seat (125A) and an aisle footwell (126A) and each non-aisle seat unit (123A) comprises a non-aisle seat (127A) and a non-aisle footwell (128A). The aisle seat unit (122A) and non-aisle seat unit (123A) are positioned with respect to one another such that the aisle seat (125A) faces towards a first end of the cabin (100) and has direct access to the aisle (101), the non-aisle seat (127A) faces towards a second, opposite end of the cabin (100). The aisle seat unit (122A) is oriented at an angle with respect to the non-aisle seat unit (123A) to provide the non-aisle seat unit (123A) with an aisle access path (129A) between the non-aisle seat (127A) and the aisle footwell (126A).
    Type: Grant
    Filed: September 16, 2020
    Date of Patent: March 11, 2025
    Assignee: Safran Seats GB Limited
    Inventor: Jurre Miedema
  • Patent number: 12240590
    Abstract: An actuator assembly for moving a movable aerodynamic surface of an aircraft is disclosed including an input section for introducing an externally provided rotary motion into the actuator assembly, and a geared rotary actuator having at least one actuator slice having a planetary gear with a sun gear couplable to the input section, a fixed gear attachable to a fixed component of the aircraft and an output gear couplable with the movable aerodynamic surface. At least one clutch is connected to the geared rotary actuator and is configured to couple the movable surface with the input section and to selectively decouple the movable surface from the input section, such that it is freely movable.
    Type: Grant
    Filed: February 23, 2022
    Date of Patent: March 4, 2025
    Assignee: Airbus Operations GmbH
    Inventor: Christoph Winkelmann
  • Patent number: 12221209
    Abstract: A leading edge assembly for an aircraft wing. The leading edge assembly includes a housing configured to be connectable to a fixed wing section of the wing, the housing formed with a first opening connecting an exterior of the housing with an interior of the housing, an actuating element movably connected to the housing, such that the actuating element is movable between a first position and at least one second position. The actuating element extends through the first opening and includes a first section arranged in the interior of the housing and a second section arranged at the exterior of the housing. The actuating element is configured to be connectable to a high lift device.
    Type: Grant
    Filed: August 27, 2020
    Date of Patent: February 11, 2025
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Dennis Krey, Bernhard Schlipf, Peter Lücken, Florian Lorenz
  • Patent number: 12221218
    Abstract: An engine vibration isolation subframe for aircraft includes a forward frame and a forward beam connected to the forward frame. The forward beam includes a first end configured to connect to a first engine and a second end configured to connect to a second engine. An aft frame is disposed aft of the forward frame and includes a first aft beam connected to the aft frame and the first engine and a second aft beam connected to the aft frame and the second engine, where the second aft beam is disposed substantially opposite the first aft beam. At least one forward isolator assembly is connected to the forward frame and at least one aft isolator assembly is connected to the aft frame.
    Type: Grant
    Filed: January 11, 2023
    Date of Patent: February 11, 2025
    Assignee: Textron Innovations Inc.
    Inventors: Rory Derik Cooper, Travis Elliot Smith
  • Patent number: 12208881
    Abstract: An actuator system for actuating movement of a control surface of an aircraft wing includes a common input rail connectable to a means for providing movement to said input rail. The system also includes: a plurality of rotary geared actuators “RGAs”; a common output rail connectable to said control surface; wherein each of said plurality of RGAs is connected to said input rail by an individual input clutch and also connected to said output rail by an individual output clutch, and wherein the input clutch functions independently of the output clutch.
    Type: Grant
    Filed: April 12, 2022
    Date of Patent: January 28, 2025
    Assignee: GOODRICH ACTUATION SYSTEMS LIMITED
    Inventor: Stephen Harlow Davies
  • Patent number: 12208913
    Abstract: In order to improve liquid hydrogen storage on aircraft, a liquid hydrogen tank is integrated into the fuselage of the aircraft. At least one portion of the tank wall is formed by specially adapted tank skin panels and/or a pressure bulkhead. The parts forming the tank wall are strengthened to contain a tank pressure of about 3 bar.
    Type: Grant
    Filed: June 27, 2022
    Date of Patent: January 28, 2025
    Assignee: Airbus Operations GmbH
    Inventors: Peter Linde, Matthias Hegenbart
  • Patent number: 12195204
    Abstract: Material transfer interfaces for space vehicles, and associated systems and methods are disclosed. A representative system includes a first coupler configured to be carried by a first space vehicle, and a first valve device carried by the first coupler. The system further includes a second coupler configured to be carried by a second space vehicle and a second valve device carried by the second coupler. The first coupler includes rotatable and translatable latch arms positioned to engage with and connect to the second coupler. The first valve device incudes a moveable probe that is insertable into the second valve device when the latch arms of the first coupler are connected to the second coupler to transfer fluid between the first and second valve devices.
    Type: Grant
    Filed: July 13, 2022
    Date of Patent: January 14, 2025
    Assignee: Orbit Fab, Inc.
    Inventors: Alexander Deuitch, Srinivasan A. Suresh, Logan Fettes, James Cho
  • Patent number: 12157562
    Abstract: A helicopter is described comprising: a tail boom; a fin projecting from the tail boom; and a tailplane arranged at the tail boom and transversal to the fin; at least one of the fin and the tailplane defining a first aerodynamic surface generating a first aerodynamic force; at least one first element transversal to the first aerodynamic surface; and a second aerodynamic surface generating a second aerodynamic force, connected to the first element, facing and spaced from the first aerodynamic surface; the second aerodynamic surface is spaced from the other of the fin and the tailplane.
    Type: Grant
    Filed: December 23, 2020
    Date of Patent: December 3, 2024
    Assignee: LEONARDO S.P.A.
    Inventors: Luca Medici, Stefano Melone
  • Patent number: 12157565
    Abstract: A wing having a wing box (20) defining a first wing profile with a first leading edge, a first trailing edge, a first top surface and a first bottom surface; a first appendage hinged on the wing box and defining a second wing profile, in turn comprising an end wall and a second trailing edge, a second top surface and a second bottom surface; the first appendage is movable between: a first position, in which the first and the second wing profiles are contiguous with each other and a second position, in which the second bottom surface and second top surface are respectively separated from the first bottom surface and first top surface; the wing box comprises a first spar having a curved section in a plane orthogonal to the associated first axis; the end wall is curved and arranged abutting against the first spar at least along the second top surface and the second bottom surface when the first movable appendage is in the first position.
    Type: Grant
    Filed: October 31, 2019
    Date of Patent: December 3, 2024
    Assignee: LEONARDO S.P.A.
    Inventors: Pierre Abdel Nour, Paolo Brughera, Carlo Cassinelli
  • Patent number: 12151832
    Abstract: A heat transfer control structure includes: an outer shell having an outer surface and an inner surface, the outer shell being heated by airflow along the outer surface; an inner shell disposed opposed to the inner surface of the outer shell, the inner shell being configured to accommodate a payload therein; and a plate coupled to the inner shell such that the plate is opposed to the inner shell across a gap. The outer shell is coupled to the plate.
    Type: Grant
    Filed: May 19, 2021
    Date of Patent: November 26, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Kenta Katsunaga, Tadashi Inagaki
  • Patent number: 12151803
    Abstract: Presented are a method and apparatus for an aircraft flight surface actuation system including a motor having an output shaft. A gearbox is coupled with the output shaft, whereby a first driving force output via the motor is converted to a second driving force. A torque shaft assembly is driveably coupled with the gearbox. The torque shaft assembly includes a first tube, a second tube located at least partially through the first tube and located coaxial therewith, wherein the first tube comprises an axial preload operable to mitigate lateral deflection, and wherein the first tube comprises a torsional preload operable to mitigate torsional deflection. In addition, the aircraft flight surface actuation system includes an eccentric cam mechanism driveably coupled with the torque shaft assembly, and a flight surface coupled with the eccentric cam mechanism.
    Type: Grant
    Filed: May 22, 2020
    Date of Patent: November 26, 2024
    Assignee: Moog Inc.
    Inventor: Christopher A. Moore
  • Patent number: 12145739
    Abstract: An aircraft wingbox assembly is disclosed having a wingbox including an upper cover, a lower cover and a pair of spars; a plurality of ribs in the wingbox, wherein the ribs divide the wingbox into bays; and a fuel tank in the wingbox. All or part of the fuel tank is located in a first one of the bays between a first one of the ribs and a second one of the ribs. The fuel tank includes a tank wall and first and second tank lugs extending from the fuel tank wall. A first fastener attaches the first tank lug to the first one of the ribs; and a second fastener attaches the second tank lug to the second one of the ribs.
    Type: Grant
    Filed: February 24, 2022
    Date of Patent: November 19, 2024
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: William Tulloch
  • Patent number: 12139261
    Abstract: According to one implementation, a propulsion system includes a rotor, a motor and an anti-icing mechanism. The rotor has blades. The motor rotates the rotor. The anti-icing mechanism deices the blades using heat generated by driving of the motor. Further, according to one implementation, an aircraft includes the above-mentioned propulsion system. Further, according to one implementation, an anti-icing method of a rotor having blades includes deicing the blades using heat generated by driving of a motor for rotating the rotor.
    Type: Grant
    Filed: March 21, 2022
    Date of Patent: November 12, 2024
    Assignee: SUBARU CORPORATION
    Inventor: Kazuaki Kotani
  • Patent number: 12134102
    Abstract: An aircraft controlled by compressed air according to an embodiment of the present invention comprises: a fuselage (10) having main wings (20) on both sides thereof; a first nozzle (12) mounted to the roof of the fuselage (10); second nozzles (22) mounted on the top surfaces of the main wings (20); a first tank (31) disposed in the fuselage (10) or the main wings (20) and storing compressed air; and a main control valve (40) for controlling the compressed air so that the compressed air is provided to the first nozzle (12) or the second nozzles (22).
    Type: Grant
    Filed: June 26, 2020
    Date of Patent: November 5, 2024
    Assignee: CHANGINAVIATION CO., LTD.
    Inventors: Chang Mo Moon, Ji Ho Moon
  • Patent number: 12134469
    Abstract: A vertical takeoff and landing aircraft using a hybrid electric propulsion system and a control method therefor according to an embodiment of the present invention: performs control such that, during vertical takeoff and landing of an aircraft (1), a generator (20), a power management device (4), and a battery management system (60) simultaneously provide power to a motor (80); and performs control such that, during a cruise flight or transition flight of the aircraft (1), the thrust of a second propeller (82) is increased and a battery (62) of the battery management system (60) is charged with redundant power generated by the generator (20).
    Type: Grant
    Filed: October 29, 2019
    Date of Patent: November 5, 2024
    Assignee: CHANGINAVIATION CO., LTD
    Inventors: Chang Mo Moon, Ji Ho Moon
  • Patent number: 12116101
    Abstract: An example method for launching a high-altitude balloon includes securing a launch collar around a balloon envelope to form a choke point separating an upper portion of the balloon envelope from a lower portion of the balloon envelope. The balloon envelope is structurally secured to a launch platform via a tether that is coupled to the launch collar. The launch collar is configured such that release of the launch collar from the choke point releases the balloon envelope from the launch platform.
    Type: Grant
    Filed: May 4, 2023
    Date of Patent: October 15, 2024
    Assignee: URBAN SKY THEORY INC.
    Inventors: Jared Leidich, Mitchell W. Sweeney, Nolan G. Smith, Maxmillion J. W. McLaughlin, Andrew F. Antonio