Patents Examined by Rodney Bonnette
  • Patent number: 11987367
    Abstract: An aerospace surface heating apparatus includes opposing layers formed from a thermoplastic containing in excess of 20% by volume of an inorganic filler material, and at least one electrically powered heating element located between the opposing layers. A method for making a heater for an aerospace component includes forming an electrical heating element on a layer of glass fiber reinforced thermoplastic film substrate, applying two opposing thermoplastic layers on opposing sides of the intermediate layer, and applying heat and pressure to the layers to join the layers together, in which the thermoplastic material contains an inorganic filler material.
    Type: Grant
    Filed: April 5, 2019
    Date of Patent: May 21, 2024
    Assignee: GKN Aerospace Services Limited
    Inventor: Stephen Goodfellow Jones
  • Patent number: 11987354
    Abstract: A flow deflector for an aerial vehicle system has a flow deflector body, a clip arranged in an interior of the flow deflector body, and a spring within the clip. The flow deflector body includes a first portion at a forward end shaped to engage a surface of an aerial vehicle body and a second portion at an aft end shaped to engage a surface of a booster engine. The flow deflector body can include a plurality of body segments arranged to form the flow deflector body. The clip may be configured to fit around and engage a portion of an aft flange of the aerial vehicle body. The spring can be preloaded and arranged to press on the aft flange when the clip engages the portion of the aft flange.
    Type: Grant
    Filed: May 9, 2022
    Date of Patent: May 21, 2024
    Assignee: Raytheon Company
    Inventors: Keith A. Elkins, Gary Lee Lidstone, Frank P. Johansen, Paul T. Hudak
  • Patent number: 11987344
    Abstract: An electromechanical rudder system control using electromagnetic actuators provides dual redundancy to comply with safety demands. Diversity of possible interconnection distribution allows the manufacturer to choose the proper configuration to satisfy aircraft safety design, hardware savings and overall system quality improvements. A dual channel rudder system architecture includes reconfigurable electronic controllers used to control plural electromechanical primary actuators for rudder control, and a distribution of aircraft and cockpit sensors through the electronic controllers to guarantee minimum required safety standards in case of loss of input data. The plural electromechanical actuators driving a rudder surface are arranged in independent and redundant load paths.
    Type: Grant
    Filed: July 13, 2020
    Date of Patent: May 21, 2024
    Assignee: Embraer S.A.
    Inventors: Marcelo Galvão, Daniel Paulo de Tarso Ferreira, Marcos Vinicius Campos
  • Patent number: 11981455
    Abstract: A mobility vehicle transfer platform includes an elevation passage provided in a structure provided with a take-off and landing site for an air mobility vehicle and having an internal space extending in the vertical direction to be connected to the take-off and landing site and to allow a ground mobility vehicle to be elevated or lowered through the internal space to be connected to or separated from the air mobility vehicle, and an elevation unit provided in the internal space of the elevation passage, having an elevation portion selectively connected to the ground mobility vehicle and configured for elevating or lowering the ground mobility vehicle in the elevation passage when the ground mobility vehicle is connected to the elevation portion.
    Type: Grant
    Filed: March 14, 2022
    Date of Patent: May 14, 2024
    Assignees: Hyundai Motor Company, Kia Corporation
    Inventors: Sang Heon Lee, Dong Eun Cha, Jin Ho Hwang
  • Patent number: 11975843
    Abstract: The present invention relates to an assembly of individual seats intended to be installed in an aircraft cabin, the assembly comprising: —a first seat and a second seat, a central console arranged between the first seat and the second seat, the central console comprising a first foot area and a second foot area extending in two opposite directions, —a seat surface width of the first seat being smaller in a portion of the seat opposite the second foot area in relation to a width of a portion of the seat surface opposite the first foot area so as to increase a space between the seat surface of the first seat and the second foot area.
    Type: Grant
    Filed: April 20, 2020
    Date of Patent: May 7, 2024
    Assignee: Safran Seats
    Inventors: Franck Jasny, Charles Ehrmann, Laurent Ligonniere, Daniele Guerra, Blong Siong
  • Patent number: 11964758
    Abstract: An airfoil of an aerodynamic surface including: a control surface having an upper surface and a lower surface, and an actuator configured to elevate or lower the control surface, wherein at least a portion of one of the upper surface and the lower surface of the control surface is auxetic with a negative Poisson ratio, and the other of the upper surface and the lower surface of the control surface includes a material with a higher Poisson ratio.
    Type: Grant
    Filed: July 1, 2022
    Date of Patent: April 23, 2024
    Assignee: Airbus Operations, S.L.U.
    Inventors: Álvaro Jara Rodelgo, Alfonso Parra Rubio, Pablo Vázquez Sánchez, Esteban Martino González
  • Patent number: 11964756
    Abstract: An aeronautical apparatus is disclosed that has two pairs of wings: an aft pair and a fore pair. Each wing has a thrust-angle motor. An assembly is coupled to each thrust-angle motor. Assemblies coupled to the fore wings have a propeller motor with a propeller and a landing element which is a wheel or a landing foot. When in forward flight, the propeller rotational axis is parallel to the longitudinal axis of the fuselage and the landing element is pointing toward the aft of the aeronautical apparatus to limit the drag presented by the landing element. When in vertical flight or hovering, the propeller rotational axis is perpendicular to the longitudinal and transverse axes of the fuselage and the landing element is deployed downward to facilitate landing.
    Type: Grant
    Filed: July 4, 2021
    Date of Patent: April 23, 2024
    Assignee: Aerhart, LLC
    Inventor: Kevin Burns
  • Patent number: 11958639
    Abstract: A supporting frame for aerospace applications comprises a plurality of rods, which are arranged along two bases substantially parallel and opposite each other, and along two sides, which are substantially parallel and opposite to each other and are coupled to each other via the two bases; the rods are coupled to each other in a mutually rotating manner by nodes so as to be able to configure the supporting frame between a deployed operating condition and a compacted operating condition; the nodes are spaced apart from one another in the deployed operating condition and are each hinged to at least two of the rods; in the compacted operating condition, each of the nodes is placed side by side with two adjacent nodes so as to form, together, two supporting members arranged at opposite longitudinal ends of the supporting frame and each being ring-shaped.
    Type: Grant
    Filed: December 5, 2019
    Date of Patent: April 16, 2024
    Assignee: Thales Alenia Space Italia S.p.A. Con Unico Socio
    Inventors: Stefano Ferroni, Antonia Simone, Marco Nebiolo
  • Patent number: 11958622
    Abstract: A method includes controlling an electric motor of a hybrid-electric powerplant for an aircraft using an EPC (electric powertrain controller) and controlling a heat engine of the hybrid-electric powerplant using an ECU (engine control unit). The method includes performing at least one of the following to protect the hybrid-electric powerplant: using the ECU to power down the electric motor, and/or using the EPC to power down the heat engine.
    Type: Grant
    Filed: May 15, 2020
    Date of Patent: April 16, 2024
    Inventors: Richard A. Poisson, Paul C. Imel, Leonid Guerchkovitch
  • Patent number: 11952130
    Abstract: A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.
    Type: Grant
    Filed: March 25, 2021
    Date of Patent: April 9, 2024
    Assignees: Airbus Operations GmbH, Airbus Defence and Space GmbH
    Inventors: Peter Linde, Elmar Bonaccurso
  • Patent number: 11952113
    Abstract: A wing lock and deployment apparatus for an air launched vehicle includes a ball screw and driver acted on by a single actuation event. The disclosed wing lock and deployment apparatus is capable of unlocking deployable wings of an air launched vehicle, deploying deployable wings of the air launched vehicle from a stored position, and locking deployable wings of the air launched vehicle in a deployed position in sequential order with the one single actuation event.
    Type: Grant
    Filed: September 28, 2022
    Date of Patent: April 9, 2024
    Assignee: The Boeing Company
    Inventors: Keith Ryan Hollen, Nathan Adam Kostelecky, Bryan Michael Loris, Jonathan David Gettinger, Alexander McGregor, Everett Ryan Eaton, Michael L. Oleshchuk
  • Patent number: 11952088
    Abstract: A method at a Unmanned Aerial Vehicle (UAV), and a UAV, adapted therefore, is adapted for enabling assisting in a rescue mission, where the method comprise: initiating a first localization of at least one body or object; initiating an analysis, for determining, at least partly based on the first localization of the at least one body or object, a need for activities, and initiating the determined activities, comprising applying floatable foam to an area on or in close proximity to the at least one body or object, while applying, to the floatable foam, a recognizable means capable of assisting in a second localization of the at least one body or object.
    Type: Grant
    Filed: July 16, 2018
    Date of Patent: April 9, 2024
    Assignee: Telefonaktiebolaget LM Ericsson (publ)
    Inventors: Peter Ökvist, Tommy Arngren
  • Patent number: 11945571
    Abstract: A piloting device arranged to be integrated in a pre-existing aircraft that includes original systems comprising both a flight control system and an autopilot system is distinct from and autonomous relative to the original systems and includes a positioning unit and a control unit. The positioning unit is arranged to produce positioning data for the pre-existing aircraft. The control unit is arranged to perform a geofencing function from the positioning data produced by the positioning unit and to produce an alternative piloting setpoint for the pre-existing aircraft. The alternative piloting setpoint is adapted to supplement both a manual piloting setpoint produced by a pilot of the pre-existing aircraft via the flight control system and also an autopilot setpoint produced by the autopilot system.
    Type: Grant
    Filed: December 19, 2019
    Date of Patent: April 2, 2024
    Inventors: Alexandre Guyamier, Julien Farjon, Nicolas Cadalen
  • Patent number: 11945592
    Abstract: An aircraft propelled by at least one turbojet engine on which power can be bled or injected via a high-pressure and/or low-pressure turbine shaft and including at least one gas turbine to provide power transients, having a system for converting and transporting electrical energy wherein each of the high-pressure and/or low-pressure turbine shafts is connected to a first doubly-fed asynchronous machine delivering, a first three-phase AC voltage over an AC distribution grid and a second polyphase AC voltage for a first AC/DC bidirectional converter supplying a DC voltage over a DC distribution grid, at least one second DC/AC bidirectional converter connected to the DC distribution grid converting this DC voltage into a third polyphase AC voltage supplying at least one second doubly-fed asynchronous machine engaged with a rotation shaft of the gas turbine, the second doubly-fed asynchronous machine further delivering a fourth polyphase AC voltage over the AC distribution grid.
    Type: Grant
    Filed: October 22, 2019
    Date of Patent: April 2, 2024
    Assignee: SAFRAN
    Inventors: Jean-Philippe Hervé Salanne, Stéphane Petibon, Florent Rougier, René Meunier, Meriem Abdellatif
  • Patent number: 11945598
    Abstract: A vapor-to-air heat exchanger for an aircraft powerplant that includes: a pressurized vapor source supplying vapor; and a condenser including a condenser inlet in fluid communication with the pressurized vapor source to receive the vapor, a condenser outlet, and at least one pneumatic vessel defining a cavity in fluid communication between the condenser inlet and the condenser outlet. The pneumatic vessel is reversibly inflatable to be configurable between a collapsed vessel configuration and an inflated vessel configuration. A volume of the cavity is greater in the inflated vessel configuration than in the collapsed vessel configuration. The pneumatic vessel is inflatable from the collapsed vessel configuration to the inflated vessel configuration when the cavity is pressurized by the vapor.
    Type: Grant
    Filed: February 11, 2022
    Date of Patent: April 2, 2024
    Inventor: Daniel Alecu
  • Patent number: 11945575
    Abstract: A retractable fuselage mounted landing gear assembly is disclosed. The landing gear assembly includes a main strut, a drag stay and a landing gear main fitting. A first end of the drag stay is attached to the main strut and a second end of the drag stay is connected to the fuselage. A first end of the landing main fitting is attached to the main strut and a second end of the main fitting is connected to the fuselage. When the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the fuselage via one or more of the drag stay and the main fitting.
    Type: Grant
    Filed: May 19, 2020
    Date of Patent: April 2, 2024
    Inventors: Christopher James Perkins, Marco Boscolo, Nicholas White, Xavier Matheis, Alexandre Legardez, Simon Roux, Sébastien Crouzet
  • Patent number: 11932378
    Abstract: Actuated assemblies comprise a base object, an actuated object, a rotary actuator, and a joint. The rotary actuator is configured to selectively pivot the actuated object relative to the base object. The rotary actuator comprises a housing that is operatively coupled to the base object, and an output gear that is configured to be selectively rotated relative to the housing. The joint comprises a crowned spline and a joint spherical bearing. The crowned spline is meshed with the output gear of the rotary actuator and is fixed relative to the actuated object. The joint spherical bearing comprises an outer race that is fixed relative to the base object, and an inner race that is positioned for rotational and pivotal movement within the outer race and that is fixed relative to the crowned spline.
    Type: Grant
    Filed: February 9, 2022
    Date of Patent: March 19, 2024
    Inventor: Kevin Raylin Tsai
  • Patent number: 11932400
    Abstract: An extension linkage for a wing flap can include at least one arm that includes two elements connected by a joint. The linkage can include an actuation mechanism, additional arms and/or each arm can include more than two elements, tie rods and/or cross pieces connecting two or more arms, and any other suitable components. The linkage functions to translate and rotate a body attached to one end of the arm relative to a primary structure attached to a second end of the arm. The linkage resides entirely within a space defined by the upper skin and the lower skin of the wing rearward of the mounting when in a retracted configuration.
    Type: Grant
    Filed: March 31, 2022
    Date of Patent: March 19, 2024
    Assignee: Joby Aero, Inc.
    Inventors: Joeben Bevirt, Gregor Veble Mikić, Joachim Grenestedt, Robert Thodal, Edward Stilson, Percy Pei, Drew Boggio
  • Patent number: 11919622
    Abstract: In an aspect, a cockpit assembly is presented. A cockpit assembly includes at least a door. A cockpit assembly includes an inceptor stick. An inceptor stick includes a sheath movably connected thereon. An inceptor stick includes an actuator communicatively connected to a sheath. An actuator is configured to move a sheath between at least a door of a cockpit and an inceptor stick.
    Type: Grant
    Filed: August 22, 2022
    Date of Patent: March 5, 2024
    Assignee: BETA Technologies, Inc.
    Inventors: Edward Hall, Richard Ward, Matthieu Lavoie
  • Patent number: 11912438
    Abstract: An unmanned vehicle module can include, in some aspects, a landing platform including a landing area for receiving an unmanned vehicle, wherein the landing area includes a predetermined charging region; a first charging plate; a second charging plate, wherein the first charging plate and the second charging plate are positioned in the predetermined charging region; an electrical energy storage device for connecting electrically with the first charging plate and with the second charging plate; and an unmanned vehicle alignment mechanism configured to move the unmanned vehicle into the predetermined charging region; wherein the unmanned vehicle alignment mechanism includes a first beam, a second beam, a third beam, a fourth beam, and an actuation device for actuating at least two of the first beam, the second beam, the third beam, and the fourth beam to push the unmanned vehicle into the charging region.
    Type: Grant
    Filed: January 31, 2019
    Date of Patent: February 27, 2024
    Assignee: H3 Dynamics Holdings Pte. Ltd.
    Inventors: Taras Wankewycz, Matthew Mehmet Crawford, Cher Chuan Lee, Bo Han, Harshavardhan Thakar