Patents Examined by Joseph W. Sanderson
  • Patent number: 11761635
    Abstract: A rotating detonation combustor includes a nozzle coupled to the combustor body at or near the exhaust opening to choke the exhaust opening. A rotating detonation combustor may include a diverting plate positioned radially inward of the inlet annulus and inlet channels for diverting flow of a mixture in an axial direction. A rotating detonation combustor may include a combustor body including an outer shell at least partially defining a detonation combustion chamber and extending axially from a base toward an exhaust opening of the detonation combustion chamber. The base defines a passageway in fluid communication with the detonation combustion chamber and includes an inlet annulus for axially directing a second fluid into the passageway and a plurality of inlet channels for radially directing a third fluid into at least one of the passageway or the detonation combustion chamber, and the detonation combustion chamber is free of any inner body.
    Type: Grant
    Filed: October 3, 2019
    Date of Patent: September 19, 2023
    Assignee: University Of Cincinnati
    Inventors: Ephraim J. Gutmark, Vijay G. Anand, Andrew St. George, William Stoddard, Ethan Knight
  • Patent number: 11718392
    Abstract: Tail rotor control system is described for helicopters. A pedal position sensor operable by a pilot yields greater tail rotor RPM relative to the main rotor RPM, giving the pilot increased control over the vehicle. This proves especially useful in certain situations, such as high altitude, where increasing tail rotor speed from main rotor speed can give a pilot increased maneuverability and stability.
    Type: Grant
    Filed: June 24, 2021
    Date of Patent: August 8, 2023
    Assignee: Textron Innovations Inc.
    Inventors: Yann Lavallee, Scott D. Poster
  • Patent number: 11708151
    Abstract: A shrink mechanism for use with a landing gear of an aircraft. The landing gear includes an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation and a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder. The shrink mechanism incudes a first shrink link member pivotally coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member pivotally coupled to the outer cylinder, a drive member coupling the crank member to a walking beam of a landing gear retract mechanism, and a driven member coupling the crank member to the first shrink link member.
    Type: Grant
    Filed: March 1, 2021
    Date of Patent: July 25, 2023
    Assignee: The Boeing Company
    Inventors: Christopher M. Alley, Leanne M. Campbell, Gabriela K. Defrancisci, Gregory J. Vering, Aaron P. Knock, Mitchell Mellor, Justin D. Cottet
  • Patent number: 11702216
    Abstract: An aircraft including a rear wing attachment, connecting a primary structure of an aircraft pylon to its wing, and including at least one right-hand link connected to the wing by a first right-hand connecting element and to the primary structure by a second right-hand connecting element and configured to react loads oriented parallel to the vertical direction only, at least one left-hand link connected to the wing by a first left-hand connecting element and to the primary structure by a second left-hand connecting element and configured to react loads oriented parallel to the vertical direction only, a shear pin secured to the primary structure and housed in operation in a housing secured to the wing, the shear pin and the housing being configured to react loads oriented in a plane approximately perpendicular to the vertical direction.
    Type: Grant
    Filed: October 19, 2020
    Date of Patent: July 18, 2023
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Michael Berjot, Julien Cayssials
  • Patent number: 11685554
    Abstract: Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft.
    Type: Grant
    Filed: November 30, 2020
    Date of Patent: June 27, 2023
    Assignee: Northrop Grumman Systems Corporation
    Inventors: James Garret Nicholson, Daniel Carl Treachler, Oliver Benjamin Ortiz, James Dulin Reavill, Benjamin Michael Hekman, Robert Bryan Sullivan, Carlos Guillermo Niederstrasser, Mark Lieberbaum, Michael Joseph Glogowski, William A. Llorens, Kenneth Siu-Kin Chow, Peter Michael Cipollo
  • Patent number: 11649051
    Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.
    Type: Grant
    Filed: August 31, 2020
    Date of Patent: May 16, 2023
    Inventors: Paul E. Arlton, David J. Arlton
  • Patent number: 11623770
    Abstract: An assembly includes at least one first collection of a plurality of spacecraft intended to be fastened to a launcher during a launch phase, wherein the spacecraft are arranged about a central axis (Z) in a given transverse plane perpendicular to the central axis, the spacecraft having edges along a longitudinal axis and being moreover arranged in such a way that a spacecraft is linked to a neighboring spacecraft of the collection by one edge by means of at least one fastener (B) positioned on the edge, so as to mechanically hold the spacecraft to one another, and a satellites-launcher adaptor to which the spacecraft are fastened in a transverse plane.
    Type: Grant
    Filed: June 12, 2019
    Date of Patent: April 11, 2023
    Assignee: THALES
    Inventors: Emmanuel Texier, Yves Durand, Jérôme Andy, Pascal Ribeyron, Julien Labarthe
  • Patent number: 11623769
    Abstract: A self-healing shield panel for protecting a spacecraft against High Velocity Particles (HVPs). The self-healing shield includes an exterior layer and an interior layer connected to define a cavity which contains a dilatant fluid with a plurality of spheroids. The kinetic energy from HVP impact is dispersed by the plurality of spheroids and absorbed by the dilatant fluid. The plurality of spheroids within the cavity move to block a puncture hole in the shield.
    Type: Grant
    Filed: January 20, 2021
    Date of Patent: April 11, 2023
    Inventors: Andreas Olafsrud, Austin Pham, Christian Williams, Frederick Herrmann
  • Patent number: 11598609
    Abstract: Seeker optics and a related method comprising: an objective for collecting and transmitting light from a target; at least one scattering surface; and a photo detector; wherein: the light transmitted from the objective at small off-boresight target angles propagates to and impinges upon the photo detector without impinging upon the scattering surface; the light transmitted from the objective at large off-boresight target angles propagates to, impinges upon and scatters upon the scattering surface; and the light scattered by the scattering surface propagates to and impinges upon the photo detector; whereby: the target may be detected and tracked at both small and large off-boresight angles, in a wide field of regard.
    Type: Grant
    Filed: March 12, 2015
    Date of Patent: March 7, 2023
    Inventor: Mikhail Gutin
  • Patent number: 11571938
    Abstract: A hybrid VTOL jet car comprising a light weight floatable chassis adapted for carrying a payload, a retractable tail section attached to a light weight floatable chassis at the rear end adapted for stabilizing the hybrid VTOL jet car, a plurality of wheels at the bottom of the hybrid VTOL jet car, a plurality of retractable wings on the sides of light weight floatable chassis, adapted for maneuvering the hybrid VTOL jet car. Further features may include a plurality of thrust-producing engines adapted for generating the thrust required for driving the hybrid VTOL jet car on a surface as well as in the air and a plurality of parachutes attached to the hybrid VTOL jet car to safely land the hybrid VTOL jet car under emergency.
    Type: Grant
    Filed: October 1, 2017
    Date of Patent: February 7, 2023
    Inventors: Andrew H B Zhou, Tiger T G Zhou, Dylan T X Zhou
  • Patent number: 11565833
    Abstract: After deploying its payload, the final stage of a launch vehicle is maneuvered to couple the nosecone of the launch vehicle to the ‘rear’, or ‘engine-end’ of the final stage. The nosecone covers the engine of the final stage, to protect the engine and related components from the heat of re-entry and the impact of landing. Placing the nosecone over the engine and orienting the combination such that the nosecone ‘leads’ the final stage during re-entry, places the center of gravity of the combination ahead of the center of pressure in the direction of travel. Accordingly, the combination is inherently stable as it re-enters the atmosphere and falls to earth. Parachutes and directional devices are used to provide a controlled soft landing.
    Type: Grant
    Filed: September 9, 2020
    Date of Patent: January 31, 2023
    Assignee: Planetary Systems Corporation
    Inventors: Walter Holemans, Ryan Williams
  • Patent number: 11565805
    Abstract: A method of delivering heavy payload using an autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.
    Type: Grant
    Filed: June 15, 2020
    Date of Patent: January 31, 2023
    Assignee: W. MORRISON CONSULTING GROUP, INC.
    Inventor: William M. Yates
  • Patent number: 11554857
    Abstract: A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.
    Type: Grant
    Filed: November 15, 2018
    Date of Patent: January 17, 2023
    Assignee: DronexusAero LLC
    Inventors: James Kaiser, William Vatis
  • Patent number: 11554854
    Abstract: A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.
    Type: Grant
    Filed: May 13, 2020
    Date of Patent: January 17, 2023
    Assignee: Lockheed Martin Corporation
    Inventors: Brian T. Rosenberger, Eric Frederick Charlton, Daniel N. Miller
  • Patent number: 11548635
    Abstract: The unmanned flight equipment includes an aerial vehicle capable of flying in an unmanned manner; a linear member configured to be suspended from the aerial vehicle and to hold a delivery target at a lower end thereof; a contact detection unit configured to detect contact with the delivery target or contact with the linear member; and a separation unit configured to separate the delivery target or the liner member based on a detection result of the contact detection unit.
    Type: Grant
    Filed: March 28, 2019
    Date of Patent: January 10, 2023
    Assignee: Rakuten Group, Inc.
    Inventor: Takumi Yamato
  • Patent number: 11542000
    Abstract: A lightweight, pocket-sized unmanned aerial vehicle (UAV) that can be held in an outstretched hand by a user for take-off and landing of the UAV. The UAV comprises a semi-toroidal or a substantially toroidal hollow body that defines a duct. The UAV further comprises a motor for rotating a fan that directs air into and out of the duct enabling UAV to take flight. The UAV comprises a flight-control system that comprises at least two flight control surfaces that can alter the directed air as it flows through the duct for controlling the roll and pitch and optionally the yaw of the UAV during flight. The flight control system may be controlled by a microprocessor controller. The UAV further comprises a payload, with at least a wireless transmitter and receiver unit.
    Type: Grant
    Filed: April 13, 2020
    Date of Patent: January 3, 2023
    Assignee: CLEO ROBOTICS INC.
    Inventors: Omar Eleryan, Szymon Czarnota
  • Patent number: 11541992
    Abstract: A landing gear system 100 for an aircraft including: a landing gear 130 that is movable between an extended position and a retracted position, the landing gear includes an extendible strut 136; a position sensor 140 configured to detect a position of a part of the extendible strut and output a signal indicative of the position; and a landing gear controller 150 that is communicably connected to the position sensor and is configured, in use, to: receive the signal from the position sensor; and, on the basis of the signal, determine that the strut has extended and the landing gear is in contact with the ground and automatically cause performance of at least a portion of a procedure to move the landing gear from the extended position to the retracted position.
    Type: Grant
    Filed: February 25, 2020
    Date of Patent: January 3, 2023
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Sean Kerr, David Marles
  • Patent number: 11535366
    Abstract: According to one aspect of the present disclosure, an apparatus for shifting a center of gravity of an aircraft is disclosed. The apparatus includes a propulsion component, a moveable ballast component, and an assembly configured to translate the moveable ballast component. The propulsion component is configured to assist in transitioning the aircraft between a first mobility phase and a second mobility phase. The assembly is configured to translate the moveable ballast component between an aft position and a forward position of the aircraft based on the aircraft transitioning between the first mobility phase and the second mobility phase to shift the center of gravity of the aircraft along a longitudinal axis of the aircraft.
    Type: Grant
    Filed: March 25, 2020
    Date of Patent: December 27, 2022
    Assignee: AURORA FLIGHT SCIENCES CORPORATION, A SUBSIDIARY OF THE BOEING COMPANY
    Inventor: William Cooper Thalheimer
  • Patent number: 11530053
    Abstract: A reprovisionable spacecraft and reprovisioning subassemblies for mating with a reprovisionable spacecraft are both described. The reprovisionable spacecraft has one or more mechanical, thermal, data, and or electrical mating interfaces for attaching, powering, and communicating with a reprovisioning subassembly, which for one embodiment is a self-contained thruster unit. The self-contained thruster unit preferably comprises a fuel tank, control electronics, and a thruster assembly. Alternately, a reprovisioning subassembly can comprise a fuel tank and control electronics, a fuel tank, or a thruster. Also, a reprovisionable spacecraft may be carried into orbit without reprovisioning subassemblies attached, and then deployed after reprovisioning subassemblies have been attached to their respective mating interfaces. Reprovisioning utilizing a self-contained thruster unit or tank eliminates the large risk associated with refueling satellites in space.
    Type: Grant
    Filed: November 8, 2018
    Date of Patent: December 20, 2022
    Assignee: SKYCORP, INC.
    Inventors: Dennis Ray Wingo, Marco Colleluori
  • Patent number: 11530046
    Abstract: An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.
    Type: Grant
    Filed: June 19, 2018
    Date of Patent: December 20, 2022
    Assignee: NIPPON KAYAKU KABUSHIKI KAISHA
    Inventors: Yasuhiko Yagihashi, Hiroshi Nakamura, Koichi Sasamoto, Dairi Kubo, Takahiro Ooi