Patents Examined by Tye William Abell
  • Variable-lift ability device comprising an anti-stratification diffuser
    Patent number: 11524760
    Abstract: A variable-liftability device includes a pressurized hermetically sealed chamber accepting a gas of density lower than the density of the air; a mixer arranged at least partially inside the hermetically sealed chamber and configured to introduce air into the hermetically sealed chamber.
    Type: Grant
    Filed: February 10, 2021
    Date of Patent: December 13, 2022
    Assignee: THALES
    Inventors: Emmanuel Du Pontavice, Martin Raynaud, Jean-Baptiste Billard
  • Spacecraft propulsion devices and systems with microwave excitation
    Patent number: 11527387
    Abstract: A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.
    Type: Grant
    Filed: January 31, 2021
    Date of Patent: December 13, 2022
    Assignee: MOMENTUS SPACE LLC
    Inventors: Jason Hummelt, Joel Sercel, Philip Mainwaring, James Small, Matthew Parman
  • Location for unmanned aerial vehicle landing and taking off
    Patent number: 11526178
    Abstract: A UAV location management method for use with a flight management system is provided, where the method comprises providing a location for at least one unmanned aerial vehicle (UAV) for at least one of: landing, taking-off and loading, providing at least a first weight-sensitive UAV pad at the UAV location, assigning a gross weight limit to each UAV scheduled to take-off from the first weight-sensitive UAV pad, the gross weight limit being based on a safety factor and at least one of: (i) a characteristic of the UAV; (ii) a characteristic of a power source of the UAV; (iii) a scheduled flight path for the UAV; and (iv) a weather condition, monitoring a weight exerted on the first weight-sensitive UAV pad when the UAV is positioned on the UAV pad, and transmitting a halt-flight signal to the flight management system for the UAV where the weight exceeds the gross weight limit.
    Type: Grant
    Filed: October 1, 2021
    Date of Patent: December 13, 2022
    Assignee: Drone Delivery Canada Corp.
    Inventors: Paul Di Benedetto, Gregory Colacitti
  • Airdrop azimuth control system
    Patent number: 11511869
    Abstract: A parachute system includes a payload support configured to operably support a payload below a parachute and an azimuth control device mounted to the payload support and/or the payload. The azimuth control device is configured to operably impart a yaw rotation to the payload in order to adjust an azimuth of the payload. The azimuth control device may include a thrust producing fluid jet device, a thrust producing propeller device, and/or a manipulatable control surface, among others.
    Type: Grant
    Filed: December 15, 2021
    Date of Patent: November 29, 2022
    Inventor: Roy L. Fox, Jr.
  • Shock strut assemblies for landing gear
    Patent number: 11498666
    Abstract: A shock strut assembly for a landing gear may comprise a strut cylinder, a strut piston configured to telescope relative to the strut cylinder, and a locking system. The locking system may be configured to restrict rotation of the strut piston relative to the strut cylinder in response to compression of the shock strut assembly.
    Type: Grant
    Filed: December 16, 2020
    Date of Patent: November 15, 2022
    Assignee: Goodrich Corporation
    Inventors: Amir Fazeli, Susanne M. Reber
  • Brake assembly with drive capabilities for landing gear
    Patent number: 11498664
    Abstract: A landing gear system includes a wheel rotatably coupled to an axle about an axis. A torque tube is rotatably mounted to the axle about the axis such that the axle extends through a central portion of the torque tube. A rotor is fixed in rotation about the axis relative to the wheel, and a stator is fixed in rotation about the axis relative to the torque tube. The landing gear assembly further includes a clutch assembly selectively reciprocal between an engaged state and a disengaged state. The stator is fixed in rotation about the axis relative to the torque tube when the clutch assembly is in an engaged state. When the clutch assembly is in a disengaged state, the stator is rotatably about the axis relative to the torque tube.
    Type: Grant
    Filed: July 10, 2020
    Date of Patent: November 15, 2022
    Assignee: SAFRAN LANDING SYSTEMS CANADA INC.
    Inventor: Robert Kyle Schmidt
  • Coaxial split torque gear box
    Patent number: 11498670
    Abstract: A gearbox system includes a first drive gear rotatable about an axis of rotation and a second drive gear disposed coaxial with the first drive gear and rotatable about the axis of rotation. An input shaft provides a first torque and includes an input gear. Driving pinions are operably connected to the input gear and positioned between the first drive gear and the second drive gear compliantly along a direction parallel to the axis of rotation. Each driving pinion drives the first drive gear in a first direction about the axis of rotation and drives the second drive gear in a second direction opposite the first direction about the axis of rotation. Each driving pinion transfers an equal second torque to the first drive gear and the second drive gear.
    Type: Grant
    Filed: August 2, 2016
    Date of Patent: November 15, 2022
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Thomas L. Sbabo, David A. Darrow, Jr.
  • Evacuation slide with safety gate readiness indicator
    Patent number: 11492129
    Abstract: An inflatable slide may comprise a ramp portion and a slide portion having a head end attached to the ramp portion and a toe end opposite the head end. A safety gate readiness indicator may be located between the head end of the slide portion and an entrance of the ramp portion. The safety gate readiness indicator may be configured to translate between a transverse position and an erect position.
    Type: Grant
    Filed: January 17, 2020
    Date of Patent: November 8, 2022
    Assignee: Goodrich Corporation
    Inventors: Timothy C. Haynes, Drew Hartman, Ryan Schmidt
  • Girt boarding aid for evacuation slide
    Patent number: 11485502
    Abstract: An evacuation slide for an aircraft may be deployable in a slide mode and a raft mode. The evacuation slide includes a head end and a toe end, with the head end having a mounting feature and the toe end being longitudinally opposite the head end. In response to the evacuation slide being in the slide mode, the head end of the evacuation slide is mounted to the aircraft via the mounting feature. In response to the evacuation slide being in the raft mode, the evacuation slide is detached from the aircraft and the mounting feature is a boarding aid, according to various embodiments.
    Type: Grant
    Filed: August 19, 2019
    Date of Patent: November 1, 2022
    Assignee: Goodrich Corporation
    Inventors: Timothy C. Haynes, Drew Hartman
  • Thrust vectoring coaxial rotor systems for aircraft
    Patent number: 11479354
    Abstract: A propulsion assembly for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The propulsion assembly includes a housing coupled to the fuselage of the aircraft. A coaxial rotor system includes a first rotor assembly and a second rotor assembly that are rotatable about a common axis of rotation. The first rotor assembly counter-rotates relative to the second rotor assembly. A motor assembly is operably associated with the coaxial rotor system. The motor assembly provides torque and rotational energy to the first rotor assembly and the second rotor assembly. A gimbal assembly couples the coaxial rotor system to the housing such that the coaxial rotor system is tiltable relative to the fuselage to generate a thrust vector.
    Type: Grant
    Filed: May 20, 2020
    Date of Patent: October 25, 2022
    Assignee: Textron Innovations Inc.
    Inventors: John Richard McCullough, Andrew Thomas Carter, Sung Kyun Kim, Matthew John Hill
  • Flight systems
    Patent number: 11479345
    Abstract: A propulsion device, including a platform configured to support a passenger thereon; a thrust engine coupled to the platform, wherein the thrust engine is configured to provide a thrust output substantially along a first axis; a deflector assembly positioned proximate the thrust output, wherein the deflector assembly includes two deflecting guides to divert the thrust output into at least two thrust vectors angled with respect to the first axis; an actuator coupled to each deflecting guide to controllably adjust a position of the deflecting guides with respect to the thrust engine; and a controller in communication with the actuator, wherein the controller is configured to operate the actuator in response to one or more signals from at least one of the passenger and a sensor coupled to the platform.
    Type: Grant
    Filed: December 7, 2018
    Date of Patent: October 25, 2022
    Assignee: ZIPAIR
    Inventors: Chrystelle Charron, Frankie Zapata
  • Landing gear assembly for reducing drag on an aircraft
    Patent number: 11472538
    Abstract: The present disclosure provides a landing gear assembly for reducing drag on an aircraft. Landing gear assembly may include a proximal joint, a movable leg extending from the proximal joint, and a base attached to a distal end of the leg. The base may be configured to support the electric aircraft on an environmental surface. The landing gear assembly may transition between a deployed landing position and a collapsed flight position when landing and taking off to provide optimal aerodynamics of the aircraft.
    Type: Grant
    Filed: October 30, 2021
    Date of Patent: October 18, 2022
    Assignee: BETA AIR, LLC
    Inventor: Tyler Skroski
  • Cable-driven four-bar link leg mechanism
    Patent number: 11459094
    Abstract: A leg mechanism includes an articulated leg system (100), a passive device (130) and a cable (134). The articulated leg system (100) has a leg portion (128). The passive device (130) is coupled to the articulated leg system and is configured to apply a first force to a portion thereof. The cable (134) is coupled to the articulated leg system (100) and is configured to apply a second force, in opposition to the first force, to a portion thereof. When the cable (134) is drawn away from the articulated leg system (100), the second force moves the leg portion (128) in a first direction. When tension is released from the cable (134), the passive device (130) exerts the first force so as to move the leg portion (128) a second direction that is opposite the first direction.
    Type: Grant
    Filed: September 28, 2018
    Date of Patent: October 4, 2022
    Assignee: Georgia Tech Research Corporation
    Inventors: Claudio V. Di Leo, Mark F. Costello, Benjamin Leon, Julian Jose Rimoli, Michael B. Ward
  • Transformable hovering rotorcraft
    Patent number: 11453492
    Abstract: An aircraft including: a pair of wings rotatably coupled to opposing lateral sides of the fuselage and being rotatable relative to each other; a pair of servo motors, each connected to a corresponding wing and configured to rotate the corresponding wing in two rotational directions; a pair of thrust motors, each of which mounted on a corresponding wing; and a flight controller connected to the servo motors and to the thrust motors, and configured to control each servo motor and each thrust motor, such that the aircraft can be selectively operated in a cruising mode, such that the pair of wings are in a non-permanent-rotation-state about a yawing axis which extends at least substantially through the center of gravity, and a monocopter mode, in which the pair of thrust motors provide thrust in opposite directions so that the pair of wings are in a permanent-rotation-state about the yawing axis.
    Type: Grant
    Filed: February 12, 2018
    Date of Patent: September 27, 2022
    Assignee: SINGAPORE UNIVERSITY OF TECHNOLOGY AND DESIGN
    Inventors: Jun En Low, Thura Win Luke Soe, Chee How Tan, Danial Sufiyan Bin Shaiful, Shaohui Foong, Gim Song Soh
  • Systems and methods for soft cover attachment
    Patent number: 11447257
    Abstract: A softcover for an evacuation system may comprise a fabric panel. The fabric panel may define a plurality of apertures located proximate a first end of the first fabric panel. A plurality of straps may extend from a second end of the fabric panel. The straps may be configured to secure the fabric panel to a housing configured to receive an inflatable slide.
    Type: Grant
    Filed: July 6, 2018
    Date of Patent: September 20, 2022
    Assignee: Goodrich Corporation
    Inventors: Timothy C. Haynes, Drew Hartman
  • Pitch horn joint
    Patent number: 11447242
    Abstract: A rotor assembly includes a pitch spider, rotor blade assemblies, and pitch horn joints. The pitch spider has a body and pitch spider legs extending from the body. Each blade rotor assembly includes a rotor blade, a pitch adapter joined to the rotor blade and connecting the rotor blade to the rotor hub, and a pitch horn. Each pitch horn joint joins one of the rotor blade assemblies to a corresponding pitch spider leg. Each pitch horn joint includes a pitch horn joint bolt extending from the pitch horn of the rotor blade assembly to the pitch spider leg along a pitch horn joint axis, the pitch horn joint bolt fixed to the pitch horn; a spherical bearing having an inner ring and an outer ring; and a slider sleeve coupled to the spherical bearing, the slider sleeve enabling the pitch horn to translate along the pitch horn joint axis.
    Type: Grant
    Filed: October 28, 2020
    Date of Patent: September 20, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Andrew Paul Haldeman, Paul Wayne Woolbright, Bryan Baskin
  • Multi-phased evacuation system
    Patent number: 11440668
    Abstract: An evacuation system may comprise a first plurality of tubes configured to inflate by an aspirator and pressure cylinder upon deployment from an aircraft. The evacuation system may further comprise a second plurality of tubes coupled to the first plurality of tubes. The second plurality of tubes may be configured to be in deflated state when the evacuation system is in a slide configuration. The second plurality of tubes may be configured to be in an inflated state when the evacuation system is in a raft configuration.
    Type: Grant
    Filed: October 8, 2019
    Date of Patent: September 13, 2022
    Assignee: Goodrich Corporation
    Inventors: Daniel Bahena, Timothy C Haynes
  • Anti-drive mechanism for rotary aircraft control
    Patent number: 11440653
    Abstract: One embodiment includes a swashplate assembly for a rotary aircraft, including: a rotating ring configured to rotate with a drive shaft of the rotary aircraft; a non-rotating ring coupled to the rotating ring and rotationally decoupled from the rotating ring, wherein the non-rotating ring does not rotate with the rotating ring and drive shaft; an outer casing disposed around the gearbox; and an anti-drive mechanism to maintain the outer casing rotationally stationary relative to the gearbox, the anti-drive mechanism including a key and slot system between the gearbox and the outer casing.
    Type: Grant
    Filed: June 5, 2020
    Date of Patent: September 13, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Terry K. Thompson, Mark Wiinikka, Bryan Baskin, Vince Calabrese, Samantha Renee Lucero
  • Mechanical link with preload verification
    Patent number: 11433994
    Abstract: A mechanical link (100) comprises a shaft (102). A first mounting interface (108) extends from the first end portion (104) of the shaft (102) and is not movable relative to the shaft (102). A second mounting interface (110) is threadably coupled with the second end portion (106) of the shaft (102). A tubular sleeve (114) circumscribes a portion of the shaft (102) and comprises a slot (116). A pin (112) extends from the shaft (102) and passes through the slot (116). A stop (124) is coupled with the second end portion (106) and fixed to the shaft (102). A washer (126) circumscribes a portion of the shaft (102) between the tubular sleeve (114) and the stop (124). A spring (122) biases the tubular sleeve (114) toward the stop (124). A first jam nut (132) is threadably coupled with the second end portion (106) between the second mounting interface (110) and the stop (124).
    Type: Grant
    Filed: July 17, 2019
    Date of Patent: September 6, 2022
    Assignee: The Boeing Company
    Inventor: Edward Joseph Nowakowski
  • Systems, assemblies, and methods for system for mitigating electrostatic discharge between space vehicles
    Patent number: 11434026
    Abstract: Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft and a second spacecraft as the first spacecraft approaches the second spacecraft may be accomplished using a passive electrostatic discharge mitigation device. In some embodiments, mitigation of static potential between the first spacecraft and the second spacecraft may be actively accomplished by an electric propulsion system provided on the first spacecraft. In some embodiments, mitigation may be provided by both actively and passively mitigating static potential between the first spacecraft and the second spacecraft.
    Type: Grant
    Filed: October 19, 2020
    Date of Patent: September 6, 2022
    Assignee: Northrop Grumman Systems Corporation
    Inventors: Christine A. Agathon-Burton, Matthew Alan Michel, Dewey Edwin Cochran, Ronald Lynn Graham, Gregg A. Herbert, William A. Llorens