Patents Examined by Michael B Kreiner
  • Land and aerial transportation vehicle and powertrain thereof
    Patent number: 11312194
    Abstract: A powertrain including an engine; a main drive shaft assembly; a primary clutch mechanism coupled to the engine and the a main drive shaft assembly, the primary clutch mechanism being operable to connect or disconnect the main drive shaft assembly and the engine; an axle shaft coupled transversely to the main drive shaft assembly; a secondary clutch mechanism having a driving member coupled to an end of the axle shaft; a drive wheel coupled to a first driven member of the secondary clutch mechanism; and an air propulsion unit coupled to a second driven member of the secondary clutch mechanism. The secondary clutch mechanism being operable to engage or disengage the first driven member and/or the second driven member to the driving member so as to connect or disconnect the drive wheel and/or the air propulsion unit to the axle shaft. A vehicle including the powertrain.
    Type: Grant
    Filed: November 29, 2019
    Date of Patent: April 26, 2022
    Inventor: Zhen Gang Ker
  • Inflatable structure deployment
    Patent number: 11312466
    Abstract: A system for deploying an inflatable structure may include a balloon defining an envelope having a first stiffness, a valve assembly including a control valve, and a reactor defining a chamber having a second stiffness, the valve assembly disposed in fluid communication between the chamber and the envelope, the control valve selectively actuatable to control fluid communication between the chamber and the envelope, the second stiffness of the chamber greater than the first stiffness of the envelope, and the reactor foldable onto itself along the chamber and elastically deformable to unfold in response to an increase in pressure in the chamber.
    Type: Grant
    Filed: September 14, 2021
    Date of Patent: April 26, 2022
    Assignee: LTAG SYSTEMS LLC
    Inventors: Jonathan T. Slocum, Alexander H. Slocum
  • Joint joining an aircraft wing to an aircraft body
    Patent number: 11305862
    Abstract: A joint joining an aircraft wing to an aircraft body employs a splice panel that is engaged in surface engagement with a skin panel on a side of the aircraft body and is engaged in surface engagement with a leg panel extending upwardly from the aircraft wing. A plurality of fasteners extend through the splice panel and the leg panel and extend through the splice panel and the skin panel. The plurality of fasteners attach the splice panel to the skin panel and attach the splice panel to the leg panel and thereby attach the skin panel to the leg panel. After fastener holes have been drilled through the splice panel and the leg panel to attach the splice panel to the leg panel, the splice panel can be removed from the leg panel. This provides easy access to the fastener holes drilled through the leg panel for deburring of the fastener holes.
    Type: Grant
    Filed: December 20, 2019
    Date of Patent: April 19, 2022
    Assignee: The Boeing Company
    Inventors: Mark R. McLaughlin, Jenny Young, Drew-Daniel T. Keefe, Charles B. Lockin, David H. Leibov
  • Wing for an aircraft
    Patent number: 11299266
    Abstract: A wing for an aircraft includes, but is not limited to, a wing body having a wingtip, a leading-edge, and a trailing edge. The wingtip comprises an outboard-most portion of the wing body. The leading-edge is disposed along a forward portion of the wing body and is configured to cause a vortex to extend off the trailing edge at a location inboard of the wingtip when the aircraft is flown sub-sonically at a predetermined angle of attack. The trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip at a position that corresponds with the location where the vortex extends off the trailing edge.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: April 12, 2022
    Assignee: Gulfstream Aerospace Corporation
    Inventors: George Hicks, Donald Howe, Gregory Howe, Joe Gavin
  • Ducted rotor blade tip extension
    Patent number: 11286037
    Abstract: A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a tip extension affixed at the tip end of the at least one rotor blade, wherein the tip extension comprises a plurality of flexible elements and the rotor blade has a fixed extended length based on the tip extension. The tip extension may provide a clearance distance between the tip extension and the rotor duct.
    Type: Grant
    Filed: October 12, 2018
    Date of Patent: March 29, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Robert Glenn Vaughn, Michael J. Ryan, Brent Randal Achttien, Kirk L. Groninga, Daniel B. Robertson, Matthew Edward Louis
  • Ducted rotor blade tip extension
    Patent number: 11286036
    Abstract: A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a tip extension affixed at the tip end of the at least one rotor blade, wherein the tip extension is comprised, at least in part, of a flexible material and the rotor blade has a fixed extended length based on the tip extension. The tip extension may provide a clearance distance between the tip extension and the rotor duct.
    Type: Grant
    Filed: October 12, 2018
    Date of Patent: March 29, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Kirk L. Groninga, Daniel B. Robertson, Matthew Edward Louis, Robert Glenn Vaughn, Michael J. Ryan, Brent Randal Achttien
  • Systems and methods for aircraft structure surface covers
    Patent number: 11279468
    Abstract: An aircraft surface cover is provided. The aircraft surface cover includes a cover member that is configured to be removably secured to an aircraft structure. The cover member includes an exterior surface that has a microtextured surface including microtexture ribs that are configured to improve aerodynamic performance of the aircraft structure.
    Type: Grant
    Filed: January 22, 2019
    Date of Patent: March 22, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Michelle Crivella, Matthew Berden
  • Support member
    Patent number: 11279498
    Abstract: A support member configured to support a first structure within an aperture of a second structure is disclosed. The support member comprises a bracket for attaching the support member to the second structure; and a funnel part. The diameter of the base of the funnel is less than or equal to the diameter of the aperture, and is substantially equal to the diameter of a part of the first structure to be supported by the support member.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: March 22, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: David Petit, Eric Bonte, Daniel Peachey
  • Structure-reinforcing cargo compartment module
    Patent number: 11273898
    Abstract: A cargo compartment module for an aircraft, including at least one floor, at least one side wall that is connected to the floor, upper installation points for connecting the side wall to the main deck, in particular transverse supports of the main deck, lower installation points for connecting the side wall to frames and/or other structural elements of the aircraft, wherein the side wall has reinforcements such that the side wall in an installed state forms part of the load-bearing structure of the aircraft and/or supports the main deck.
    Type: Grant
    Filed: November 24, 2020
    Date of Patent: March 15, 2022
    Assignee: TELAIR INTERNATIONAL GMBH
    Inventor: Thomas Huber
  • Deployable aircraft flotation system
    Patent number: 11254421
    Abstract: A deployable aircraft flotation system. The deployable aircraft flotation system includes a pair of flotation members. The pair of flotation members are positioned on opposing sides of a bottom surface of an aircraft body. Each flotation member of the pair of flotation members has an inner layer that is made of a first buoyant material, an outer layer that is made of a second buoyant material, and a middle layer between the inner layer and the outer layer that is made of a rigid material. The flotation members can be moved from a stowed position, where they are stored in housings, to a deployed position, where they emerge and are positioned on the bottom of the plane.
    Type: Grant
    Filed: September 3, 2019
    Date of Patent: February 22, 2022
    Inventor: Delano Christian
  • Flexible radiative fin for a spacecraft
    Patent number: 11254452
    Abstract: A radiative fin for a spacecraft is disclosed having an end fitting of heat conductive material, configured to be mounted on the spacecraft, a flexible radiative laminate, connected to the end fitting at one end and having an opposite free end, at least one pyrolytic graphite sheet, and at least one heat emission layer in contact with the pyrolythic graphite sheet on at least part of the surface of the pyrolythic graphite sheet, and a flexible rod, extending from the end fitting along at least part of a side of the flexible radiative laminate and being affixed to the latter. The flexible rod is adapted to occupy a folded position and a deployed position and to exert, while in the folded position, a deployment torque adapted to bring the flexible rod back to the deployed position.
    Type: Grant
    Filed: June 21, 2019
    Date of Patent: February 22, 2022
    Assignees: AIRBUS DEFENCE AND SPACE SAS, AIRBUS DEFENCE AND SPACE NETHERLANDS B.V
    Inventors: Fabrice Mena, Bruin Benthem
  • Aircraft
    Patent number: 11247783
    Abstract: An aircraft includes a fuselage having a front, a center, and a rear section. A first mounting member is coupled to the front section. A second mounting member is coupled to the rear section. A first and a second wing are coupled to the center section. A plurality of power generator systems are included and coupled to the first or second mounting member. Each power generator system includes a power source, a first and a second propeller. The power source is configured to drive the first and second propeller. The first and second propeller have an axis of rotation, and are pivotable between a first and a second position. An amphibious landing gear system is coupled to an underside of the fuselage and has a flap and a bladder. The bladder is located under the flap, configured to inflate and deflate, and sized to provide buoyancy for the aircraft.
    Type: Grant
    Filed: March 8, 2021
    Date of Patent: February 15, 2022
    Assignee: HELENG INC.
    Inventor: Jack Ing Jeng
  • Aerodynamic seals
    Patent number: 11235855
    Abstract: An aerodynamic structure comprising an aerodynamic surface. The aerodynamic surface is formed by a first part of the aerodynamic structure; a second part of the aerodynamic structure; and a sealed gap between the first part and the second part. The sealed gap contains a sealant material and a support material.
    Type: Grant
    Filed: October 16, 2018
    Date of Patent: February 1, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: David Liversage, Darren Crew
  • Aircraft windowed structure
    Patent number: 11235853
    Abstract: A windowed structure includes a body having a frame with an outer wall extending between a first end and a second end. An inner wall extends from the outer wall. The inner wall is connected to the outer wall at the first end to define a proximal joint of the body delimiting a window opening extending through the body. A window element covers the window opening and defines an outer window surface and an inner window surface. The window element has an overlap segment overlaying the outer wall and attached thereto. An unobstructed portion of the window element is defined between the overlap segment and is unobstructed by the frame between the proximal joint.
    Type: Grant
    Filed: October 16, 2018
    Date of Patent: February 1, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Pier-Alexandre Pelletier, Guillaume Noiseux-Boucher, Sebastien Duval
  • Leading edge structure for a flow control system of an aircraft
    Patent number: 11220345
    Abstract: A leading edge structure (13) for a flow control system of an aircraft (1), including a double-walled leading edge panel having an inner wall element (45) and an outer wall element (47). Between the inner and outer wall elements (45, 47) are elongate stiffeners (49) spaced apart from one another. And, between adjacent stiffeners (49) are a hollow chamber (51). The outer wall element (47) includes micro pores (53). The inner wall element (45) includes passages (55) forming a fluid connection between the hollow chambers (51) and a vacuum system (15). An ice protection system in the stiffeners (49) includes hot air ducts (57) configured for connection to a hot air system (17), and the stiffeners (49) include hot air openings (59) forming a fluid connection between the hot air ducts (57) and the hollow chambers (51).
    Type: Grant
    Filed: December 27, 2018
    Date of Patent: January 11, 2022
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Christian Heck
  • Flow control system, flow control method, and aircraft
    Patent number: 11214359
    Abstract: A flow control system includes a movable wing attachable to a wing of an aircraft, and a plasma actuator mountable on a surface of the movable wing. The flow control system is configured to control air flow around the wing by having the changing of the steering angle of the movable wing work in conjunction with the operation of the plasma actuator.
    Type: Grant
    Filed: December 18, 2018
    Date of Patent: January 4, 2022
    Assignee: SUBARU CORPORATION
    Inventors: Maki Kikuchi, Hiroki Kato, Mitsuru Kono, Kentaro Yoshida, Nobuyuki Nakazato
  • Aerodynamics improvement device for an aircraft and aircraft equipped with such device
    Patent number: 11192639
    Abstract: An aircraft (5) including an aerodynamic surface (6), an aerodynamics improvement device with a first electrode (27) embedded beneath and electrically isolated from the aerodynamic surface (6), a second electrode (28) electrically isolated from the first electrode (27), a voltage generator (30) adapted to apply a voltage between the first and the second electrode, further comprising a layer of electrically insulating material (26) between the second electrode (28) and the aerodynamic surface (6). Methods for detecting ice on and de-icing an aerodynamic surface (6), and for delaying a boundary layer transition and separation from the aerodynamic surface.
    Type: Grant
    Filed: May 8, 2020
    Date of Patent: December 7, 2021
    Assignee: Airbus Operations S.L.
    Inventor: Raul Carlos Llamas Sandin
  • Land and aerial transportation vehicle and powertrain thereof
    Patent number: 11192412
    Abstract: A powertrain including an engine; a main drive shaft assembly; a primary clutch mechanism coupled to the engine and the a main drive shaft assembly, the primary clutch mechanism being operable to connect or disconnect the main drive shaft assembly and the engine; an axle shaft coupled transversely to the main drive shaft assembly; a secondary clutch mechanism having a driving member coupled to an end of the axle shaft; a drive wheel coupled to a first driven member of the secondary clutch mechanism; and an air propulsion unit coupled to a second driven member of the secondary clutch mechanism. The secondary clutch mechanism being operable to engage or disengage the first driven member and/or the second driven member to the driving member so as to connect or disconnect the drive wheel and/or the air propulsion unit to the axle shaft. A vehicle including the powertrain.
    Type: Grant
    Filed: November 29, 2019
    Date of Patent: December 7, 2021
    Inventor: Zhen Gang Ker
  • Method of determining an initial leading edge circle of airfoils of a blade and of improving the blade in order to increase its negative stall angle of attack
    Patent number: 11148794
    Abstract: A method of determining an initial leading edge circle for airfoils of a blade and of improving a blade, and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is determined and then increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.
    Type: Grant
    Filed: February 12, 2019
    Date of Patent: October 19, 2021
    Assignee: AIRBUS HELICOPTERS
    Inventors: Raphael Fukari, Paul Eglin
  • Propulsion system for an aircraft
    Patent number: 11149578
    Abstract: A propulsion system for an aircraft includes a turbomachine, a primary fan, and an electric machine. The turbomachine includes a first turbine and a second turbine, with at least one of the first turbine or second turbine operably connected to the electric machine and the second turbine driving the primary fan. The propulsion system additionally includes an auxiliary propulsor assembly configured to be mounted at a location away from the turbomachine and the primary fan. The electric machine is in electrical communication with the auxiliary propulsor assembly for transferring power with the auxiliary propulsor assembly during operation of the propulsion system.
    Type: Grant
    Filed: February 10, 2017
    Date of Patent: October 19, 2021
    Assignee: General Electric Company
    Inventors: Narendra Digamber Joshi, Michael Solomon Idelchik