Patents Examined by Richard R Green
  • Patent number: 11518533
    Abstract: A front engine attachment system for an aircraft engine, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam has front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate. Each link-rod system is fastened to the intermediate plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.
    Type: Grant
    Filed: May 19, 2020
    Date of Patent: December 6, 2022
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Thomas Deforet, Rémi Lansiaux, Olivier Dubois, Jacky Puech
  • Patent number: 11518500
    Abstract: Aircrafts having foldable wings are disclosed. An example aircraft includes a fixed wing portion, a foldable wing tip, and a hinge interface to pivotally couple the foldable wing tip and the fixed wing portion. The hinge interface has a first hinge defining a hinge axis that is substantially parallel to a fuselage centerline. The first hinge has a first dimension in a spanwise direction and a second dimension in a chordwise direction. The first dimension is greater than the second dimension.
    Type: Grant
    Filed: November 11, 2019
    Date of Patent: December 6, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Mark Steven Good, Steven Paul Walker
  • Patent number: 11518526
    Abstract: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the acoustic panel or panels.
    Type: Grant
    Filed: October 17, 2019
    Date of Patent: December 6, 2022
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Alain Porte, Jacques Lalane, Gregory Albet, Maxime Zebian, Arnaud Bourhis
  • Patent number: 11518542
    Abstract: A system for landing an unmanned aerial vehicle has an unmanned aerial vehicle and a ground-based platform. A guide structure for receiving the unmanned aerial vehicle is mounted on the ground base platform. The guide structure has an inner diameter greater than a smallest outer diameter of the unmanned aerial vehicle landing gear and less than the largest outer diameter of the unmanned aerial vehicle landing gear.
    Type: Grant
    Filed: December 13, 2019
    Date of Patent: December 6, 2022
    Assignee: HOVERFLY TECHNOLOGIES, INC.
    Inventors: Alfred D. Ducharme, Adam Stepien, Jason Tabor, Lucas Colt Whitaker, Daniel J. Burroughs
  • Patent number: 11518509
    Abstract: A tethered aerial vehicle, connected to an anchorage system in the ground level through a cord, comprising a pair of fixed wings; and a drive assembly. The drive assembly comprises at least two actuators configured to tilt the axle of the propellers. The fixed wings define a center hole located close to a gravitational center of the aerial vehicle. Within the edges of the center hole located close to the gravitational center of the aerial vehicle is a gimbal anchored to the fixed wings' structure. The drive assembly is located within the edges of the center hole and attached to the gimbal in a manner that the gimbal interfaces the connection between the fixed wings and the drive assembly. The drive assembly comprises of at least two propellers mounted on the same axle (“coaxial propellers”) driven by a counter-rotating motor. The coaxial propellers are configured to rotate in opposite directions with respect to each other.
    Type: Grant
    Filed: July 25, 2019
    Date of Patent: December 6, 2022
    Assignee: ALTAVE INDUSTRIA, COMERCIO E EXPORTACAO DE AERONAVES S.A.
    Inventors: Davi Ferreira De Castro, Waldir Vieira, Alejandro Arturo Rios Cruz, Bruno Avena De Azevedo, Isamel Costa Neto, Davi Lima De Mesquita, Lenardo Vieira Costa, Leonardo Nogueira, Michelle Bueno Garcia, Raphael Galate Baptista Ribeiro
  • Patent number: 11518505
    Abstract: Disclosed herein is a VTOL tilt-wing aircraft that serves as a 4-6 passenger airliner for scheduled service between city centers and that is optimized for travel distances from 100-500 miles fully loaded with passengers and fuel. The VTOL aircraft solves technical, cost, and time problems inherent in other forms of transportation, including, but not limited to, rail, passenger airlines, and helicopters. The VTOL aircraft (1) takes off and lands like a helicopter, (2) flies fast like a jet, and (3) costs less than or comparable to a helicopter.
    Type: Grant
    Filed: June 28, 2021
    Date of Patent: December 6, 2022
    Assignee: Transcend Air Corporation
    Inventors: Gregory O. Bruell, Peter H. Schmidt
  • Patent number: 11505315
    Abstract: The flying object according to one embodiment comprises: a main body; a main wing formed on a side surface of the main body; a duct-shaped first propulsion part which is provided outside the main wing and can be tilted; a second propulsion part arranged behind the main body; horizontal tail wings formed on both side surfaces of the second propulsion part; and a control part for controlling the movement of the first propulsion part, second propulsion part, and horizontal tail wings, wherein the control part controls the second propulsion part and the horizontal tail wings according to the tilt angle of the first propulsion part.
    Type: Grant
    Filed: April 12, 2019
    Date of Patent: November 22, 2022
    Inventors: Sung Ho Chang, Yu Shin Kim, Seong Wook Choi, Young Shin Kang, Am Cho
  • Patent number: 11505304
    Abstract: Example aircraft spoiler actuation systems and related methods are disclosed herein. An example spoiler actuation system includes a rotary actuator, a first output shaft coupled to the rotary actuator, a second output shaft coupled to the rotary actuator, the first output shaft opposite the second output shaft, a first actuator rod coupled to the spoiler at a first location, and a second actuator rod coupled to the spoiler at a second location, the second location spaced apart from the first location. The rotary actuator is operatively coupled to the first actuator rod via the first output shaft and to the second actuator rod via the second output shaft to cause the spoiler to move between one of a stowed position and a raised position or the stowed position and a drooped position.
    Type: Grant
    Filed: October 18, 2019
    Date of Patent: November 22, 2022
    Assignee: The Boeing Company
    Inventors: Kevin Tsai, Donald Drew Reinhart
  • Patent number: 11505310
    Abstract: A flow body for a vehicle having a flow surface, as well as a skin system attached to the flow surface is proposed. The skin system has a top layer and a foam arrangement positioned between the flow surface and the top layer, wherein the top layer includes an elastic, surface-like material, wherein the foam arrangement includes a first layer of an elastic, compressible open cell foam, wherein the foam arrangement is bonded to the top layer. The skin system has a static shape in an unloaded state, in which the shape defines an outer surface geometry that directly follows the geometry of the respective flow surface, and the skin system has a deflected shape when the flow body is subjected to turbulent air flow. The deflected shape at least temporarily compresses the foam arrangement.
    Type: Grant
    Filed: December 13, 2018
    Date of Patent: November 22, 2022
    Assignee: AIRBUS OPERATIONS GmbH
    Inventors: Bernd Ruppert, Volker Robrecht
  • Patent number: 11498655
    Abstract: A pressure bulkhead for the pressure-tight axial closure of a pressurized fuselage of an aircraft or spacecraft that can be put under an internal pressure, comprises a pressure dome, which is designed with a concave inner surface and a convex outer surface; inspection hatches, which each form an aperture in the pressure dome from the inner surface to the outer surface; and pressure covers for pressure-tight closure of the inspection hatches, wherein the pressure covers each have a cover and a pressure seal, wherein the cover is designed for the repeatedly releasable fixing of the pressure cover on the concave inner surface over the inspection hatch and wherein the pressure seal is formed at the edge of the cover for the pressure-tight closure of the cover with the pressure dome.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: November 15, 2022
    Assignee: Premium Aerotec GmbH
    Inventors: Sergej Zeeb, Sergiu Irimie
  • Patent number: 11498682
    Abstract: An arrangement of individual seats intended to be installed in an aeroplane cabin includes at least one module of two seats disposed opposite one another, said module having a longitudinal elongation direction, characterized in that said arrangement further comprises: a console disposed between the two seats of the module; a screen connected to each seat, each screen being mounted on a screen support; the screen supports being movable between a stowed position and a deployed operating position, in which the screen supports are positioned substantially edge-to-edge and form a partition wall between the two seats located opposite one another.
    Type: Grant
    Filed: March 29, 2018
    Date of Patent: November 15, 2022
    Assignee: Safran Seats
    Inventors: Jeremy White, Nicholas Sandham, Richard Seale, Omar Chraibi
  • Patent number: 11492102
    Abstract: A wing having a main wing section with a forward spar and an aft spar extending through an internal cavity. The forward and aft spars are spaced apart and delimiting a dry segment of the internal cavity. A winglet is rotatably coupled to the main wing section by a cant hinge defining a cant axis about which the winglet rotates relative to the main wing section between an extended position in which the winglet is aligned with the main wing section, and a folded position in which the winglet is rotated about the cant axis. A linkage assembly disposed in the dry segment is pivotably mounted to one of the forward and aft spars and is coupled to the cant hinge. The linkage assembly is displaceable to apply a force to move the winglet between the extended position and the folded position during flight of the aircraft.
    Type: Grant
    Filed: February 20, 2020
    Date of Patent: November 8, 2022
    Inventors: Fengfeng Xi, Amin Moosavian, Jose Vieira De Sa, Gabriel H. Campos Naranjo
  • Patent number: 11492099
    Abstract: An aircraft having a fuselage with a nose and a flat tail at opposite ends and a pair of wings extending therefrom. A pair of nacelles are detachably connected to the top of respective ones of the wings to be spaced from the fuselage to establish an air flow space therebetween. Each wing-mounted nacelle includes a plurality of fans, a corresponding plurality of electric motors to drive the fans, and dividers that separate the fans from one another. Each wing-mounted nacelle also includes a pair of rotatable air inlet slats at an air intake end and a pair of rotatable air exhaust flaps at an air exhaust end that are rotated relative to one another to control horizontal propulsive thrust, thrust vectoring and thrust reversing of the aircraft. A third nacelle is mounted on top of the flat tail of the fuselage between a pair of horizontal turbo generators.
    Type: Grant
    Filed: April 19, 2019
    Date of Patent: November 8, 2022
    Assignee: Wright Electric, Inc.
    Inventor: Darold B Cummings
  • Patent number: 11492108
    Abstract: An aircraft is configured with a propulsion system having a rotor with both cyclic and collective control, and an axis of rotation about which the propulsion system rotates with respect to the fuselage. A control system is configured to use torque generated through cyclic control of the rotor to reposition the propulsion system around the axis of rotation without the need for an independent actuator mechanism to rotate the propulsion system, thus reducing the weight and mechanical complexity of the aircraft. The control system may also utilize the torque provided by one or more rotors to position one or more wings with respect to the airflow over the aircraft, exerting torque on the aircraft to control the direction of the aircraft.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: November 8, 2022
    Assignee: VerdeGo Aero, Inc.
    Inventors: Richard Pat Anderson, Eric Richard Bartsch
  • Patent number: 11492925
    Abstract: A magnetic fire seal for a nacelle may comprise an exterior surface configured to form a sealing interface and an interior surface opposite the exterior surface. A fire-resistant material may be disposed between the exterior surface and the interior surface. A magnet may be located at the interior surface proximate the sealing interface. A portion of the fire-resistant material may be located between the magnet and the exterior surface.
    Type: Grant
    Filed: November 5, 2018
    Date of Patent: November 8, 2022
    Assignee: ROHR, INC.
    Inventor: Michael Sean Pretty
  • Patent number: 11492120
    Abstract: An ultra light weight aircraft composite galley architecture system and method comprises composite construction of a partially molded aircraft monument structure based on embedded load bearing hoops and beams used in conjunction with pre formed composite flat panel construction. An upper L shaped structural section mates with a lower inverted L shaped structural section forming a structure upon which additional panels are joined to form the complete composite galley. This system and method of construction produces a high strength aircraft monument capable of maintaining aircraft structural flight and crash load requirements without external monument extrusions for support. This galley architecture system and method of construction creates an aircraft monument with desirable reduction in weight with no loss of required structural strength.
    Type: Grant
    Filed: June 10, 2019
    Date of Patent: November 8, 2022
    Assignee: B/E Aerospace, Inc.
    Inventors: Peter J. L. Burd, Venkata P. S. Neti, Nicholas J. W. Pearce, Hayley L. Campbell
  • Patent number: 11485487
    Abstract: A rotorcraft, and, more particularly, to a rotorcraft with a fuselage having a center line, at least one main rotor that generates vortices during operation, and a stabilizer wing, whereby the stabilizer wing has a planform that reduces the unsteady aerodynamic loads caused by the wake of the at least one main rotor. In particular, the stabilizer wing may be provided with a left wing tip, a right wing tip, a quarter chord line with a non-zero curvature, such that an interaction between the vortices generated by the at least one main rotor and the quarter chord line is spread out over time, a leading edge that is arc-shaped, and a trailing edge that is arc-shaped.
    Type: Grant
    Filed: February 27, 2020
    Date of Patent: November 1, 2022
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Martin Embacher, Tobias Ries, Christian Eckert, Thomas Kneisch
  • Patent number: 11485488
    Abstract: A vertical take-off and landing aircraft includes a fixed wing airframe having opposed first and second wings extending from first and second sides, respectively, of a fuselage having opposed leading and trailing extremities, and a tail assembly located behind the trailing extremity. Vertical take-off and landing (VTOL) thrust rotors are mounted to the airframe providing vertical lift to the aircraft, and a forward thrust rotor is mounted to the airframe for providing forward thrust to the aircraft. At least one of VTOL thrust rotors is laterally tilted with respect to the airframe for providing vertical lift and yaw control authority to the aircraft.
    Type: Grant
    Filed: December 4, 2015
    Date of Patent: November 1, 2022
    Assignee: L3HARRIS LATITUDE LLC
    Inventors: Justin Armer, Carlos Murphy, Jason Michael K. Douglas
  • Patent number: 11485506
    Abstract: An aircraft including a fuselage and a propulsion assembly. The propulsion assembly includes at least one fan rotor placed behind the fuselage as an extension thereof along a longitudinal axis, and a nacelle which forms a fairing of the at least one fan rotor through which at least one air flow passes. The aircraft comprises a plurality of stator radial arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle. The radial arms comprise at least one variable-pitch movable portion configured to axially divert the air flow.
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: November 1, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Nicolas Jérôme Jean Tantot
  • Patent number: 11486308
    Abstract: An air inlet section for an enclosure for an aircraft engine is provided that includes an inner barrel panel, an outer barrel panel, a lipskin and a forward bulkhead. The lipskin extends between an inner barrel end and an outer barrel end. The inner barrel end is disposed proximate the forward end of the inner barrel panel and the outer barrel end is disposed proximate the forward end of the outer barrel panel. The forward bulkhead has a panel that extends between an outer radial end and an inner radial end. The inner barrel panel, the outer barrel panel, and the lipskin define an interior annular region, and the forward bulkhead defines a sub-portion of interior annular region. The outer radial end of the forward bulkhead panel is disposed forward of the inner radial end of the forward bulkhead panel.
    Type: Grant
    Filed: July 3, 2018
    Date of Patent: November 1, 2022
    Assignee: Rohr, Inc.
    Inventors: Jason K. Chen, Phillip Andelson