Patents Examined by Joseph W. Sanderson
  • Patent number: 10781863
    Abstract: A locking mechanism for locking a driveshaft in cooperative engagement with an apparatus includes a drive portion coupled to the driveshaft and a driven portion coupled to the apparatus. The drive portion of the locking mechanism includes a housing with a first engagement portion, a ball cage with a plurality locking balls contained at least partially therein, and a chock biased away from the housing by a chock spring. The chock includes an outer wall configured to push the locking balls outward in a locked position and allow inward movement in an unlocked position. Movement of the chock, and therefore locking, is controlled by an actuator rod extending through a center of the locking mechanism. The driven portion includes a second engagement portion configured to cooperatively engage and receive torque from the first engagement portion, and a locking groove configured to receive a portion of each of the plurality of locking balls therein.
    Type: Grant
    Filed: May 6, 2018
    Date of Patent: September 22, 2020
    Assignee: Textron Innovations Inc.
    Inventors: Colton Gilliland, Mark Alan Przybyla
  • Patent number: 10773833
    Abstract: A panel structure for use in a deployable and cantilevered solar array structure is provided. A panel includes first and second planar panel sections and an intermediate panel section connecting the first and second sections. The planar panel sections are capable of being situated with respect to one another so as to have a V-tent-like shape when the panel is in a deployed state and to be coplanar when the panel is in a stowed state. When in the V-tent-like shape, the intermediate section of the panel extends in a straight line that is collinear or parallel to the longitudinal axis of the cantilevered solar array structure when deployed. The V-tent-like shape produces A panel structure that has a relatively high moment of inertia, is stiff, and can provide a large area for supporting solar cells.
    Type: Grant
    Filed: July 30, 2014
    Date of Patent: September 15, 2020
    Assignee: MMA DESIGN, LLC
    Inventors: Thomas Jeffrey Harvey, Toby Justin Harvey, Ryan M. VanHalle
  • Patent number: 10773792
    Abstract: An air flow channeling yaw control device includes a vane cover, a vane array, and an actuator. The vane array includes a plurality of vanes, each of the plurality of vanes comprising a first edge and a second edge, the first edge being hingedly coupled to the vane cover and the second edge being hingedly coupled to a wing of an aircraft. The wing includes a leading edge and a trailing edge. The actuator is configured to move the plurality of vanes from a retracted position into a deployed position. The plurality of vanes, when moved into the deployed position, are configured to direct a flow of air flowing over the leading edge of the wing through channels created by the plurality of vanes. The plurality of vanes, when moved into the retracted position, are configured to retract within the wing.
    Type: Grant
    Filed: March 2, 2018
    Date of Patent: September 15, 2020
    Assignee: Lockheed Martin Corporation
    Inventor: Mark D. Buchholz
  • Patent number: 10766608
    Abstract: An aircraft landing gear structure includes a retract actuator and a shrink mechanism. The retract actuator is configured to transition a strut assembly of the aircraft landing gear structure between an extended configuration and a retracted configuration via the shrink mechanism, thereby reducing the overall longitudinal length of the strut assembly. The retract actuator is also configured to retract the aircraft landing gear into a stowage area of the aircraft during flight, via a retraction mechanism. The retraction mechanism may be a walking beam that rotates about a retraction axis to retract the aircraft landing gear structure, while simultaneously actuating the shrink mechanism, such as via a drive link coupling the retraction mechanism and the shrink mechanism. The shrink mechanism may be mechanically slaved to the retraction mechanism. The shrink mechanism may be a locking link assembly.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: September 8, 2020
    Assignee: The Boeing Company
    Inventors: Mitchell Loren Ray Mellor, James E. Cusworth
  • Patent number: 10766597
    Abstract: A privacy door assembly for installation in an aircraft relative to a flight deck door of the aircraft includes a door frame having a first post and a second post, where the second post comprises a latch recess. The privacy door assembly also includes a privacy door rotatably coupleable to the first post via a set of hinges, where the privacy door comprises a decompression latch arranged to engage the latch recess when the privacy door is in a closed position within the door frame, and where the decompression latch is configured to disengage from the latch recess in response to a decompression detected on a forward side of the privacy door.
    Type: Grant
    Filed: March 26, 2018
    Date of Patent: September 8, 2020
    Assignee: The Boeing Company
    Inventors: Sami Movsesian, Steven H. Sauer
  • Patent number: 10766596
    Abstract: A privacy door assembly for installation in an aircraft relative to a flight deck door of the aircraft includes a door frame having a first post and a second post, where the second post comprises a latch recess. The privacy door assembly also includes a privacy door rotatably coupleable to the first post via a set of hinges, where the privacy door comprises a decompression latch arranged to engage the latch recess when the privacy door is in a closed position within the door frame, and where the decompression latch is configured to disengage from the latch recess in response to a decompression detected on a forward side of the privacy door.
    Type: Grant
    Filed: March 26, 2018
    Date of Patent: September 8, 2020
    Assignee: The Boeing Company
    Inventors: Sami Movsesian, Steven H. Sauer
  • Patent number: 10759539
    Abstract: A system comprises a heat source. The system also comprises a bladder comprising opposing thin-walled sheets and a fluid flow conduit defined between the opposing thin-walled sheets. The fluid flow conduit comprises an inlet and an outlet. The system further comprises a first fluid line coupled to the heat source and the inlet of the bladder. The system additionally comprises a second fluid line coupled to the heat source and the outlet of the bladder. The system also comprises fluid flowable through the first fluid line from the heat source to the inlet, from the inlet through the fluid flow conduit to the outlet, and through the second fluid line from the outlet to the heat source.
    Type: Grant
    Filed: March 30, 2018
    Date of Patent: September 1, 2020
    Assignee: The Boeing Company
    Inventors: Jeffrey H. Knapp, Chad N. Blundell, Mason A. Giovannoni
  • Patent number: 10752340
    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: August 9, 2017
    Date of Patent: August 25, 2020
    Assignee: Lockheed Martin Corporation
    Inventors: Brian T. Rosenberger, Eric Frederick Charlton, Daniel N. Miller
  • Patent number: 10745125
    Abstract: Provided is a hovering vehicle capable of safely moving while hovering from the ground. A hovering vehicle includes: at least six impellers including six or more impellers provided below an operator cab, for blasting, downward in a z direction, air taken in from the air intake space between the impellers and the operator cab; at least six motors including six or more motors for driving the six or more impellers; and an electricity storage unit for supplying power to the six or more motors. The hovering vehicle is allowed to hover from the ground by the air blasted from three or more of the six or more impellers, and the six or more impellers are arranged on the circumference of a circle with the center passing through an axis parallel to the z direction.
    Type: Grant
    Filed: November 29, 2019
    Date of Patent: August 18, 2020
    Assignee: TATSUMI RYOKI CO., LTD
    Inventor: Toyoshi Kondo
  • Patent number: 10737797
    Abstract: An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a propulsion system. The propulsion system includes a plurality of electric fans integrated into the wing and oriented to generate thrust along a vertical direction, the plurality of electric fans arranged along a length of the wing and including an outer-most electric fan along a transverse direction relative to the fuselage. The outer-most electric fan is at least one of a variable pitch fan or a variable speed fan to provide increased stability to the aircraft.
    Type: Grant
    Filed: September 8, 2017
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Kurt David Murrow, Darek Tomasz Zatorski, Andrew Breeze-Stringfellow, Dominic Barone
  • Patent number: 10737776
    Abstract: A method for equalizing rolling moments at high advance ratios is disclosed including impelling an aircraft in a forward direction at an airspeed by means of a thrust source and rotating a rotor of the aircraft at an angular velocity with respect to the airspeed effective to cause a positive total lift on each blade due to air flow over the blades in the retreating direction when the blade is moving in the retreating direction. The rotor includes an even number of blades placed at equal angular intervals around the rotor hub. One or both of cyclic pitch and rotor angle of attack are adjusted such that a rolling moment of the retreating blade due to reverse air flow is between 0.3 and 0.7 times a rolling moment on the advancing blade due to lift.
    Type: Grant
    Filed: February 26, 2018
    Date of Patent: August 11, 2020
    Assignee: Skyworks Global Inc.
    Inventor: Walter Gerd Oskar Sonneborn
  • Patent number: 10737760
    Abstract: Apparatus and systems provide for the construction of wing sections having a plurality of wing spars abutted against each other to form a contiguous multi-box wing spar layup. An aircraft wing includes a plurality of wing spars configured to be attached to an aircraft fuselage, an upper wing surface, and a lower wing surface. The plurality of wing spars are in a multi-box wing spar layup. The plurality of wing spars, the upper wing surface, and the lower wing surface are composite layers having continuous fibers.
    Type: Grant
    Filed: December 26, 2016
    Date of Patent: August 11, 2020
    Assignee: The Boeing Company
    Inventor: John H. Moselage, III
  • Patent number: 10723470
    Abstract: A boundary layer ingestion engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan mechanically linked to the turbine via at least one shaft. The linkage is configured such that rotation of the turbine is translated to the fan. The boundary layer ingestion engine further includes an exhaust duct fluidly connected to an outlet of the turbine. The exhaust duct is positioned radially inward of the fan.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: July 28, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Wesley K. Lord
  • Patent number: 10710715
    Abstract: A heavy payload, 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: April 30, 2018
    Date of Patent: July 14, 2020
    Assignee: W.Morrison Consulting Group, Inc.
    Inventor: William M. Yates
  • Patent number: 10703473
    Abstract: Provided is a hovering vehicle capable of safely moving while hovering from the ground. A hovering vehicle includes: at least six impellers including six or more impellers provided below an operator cab, for blasting, downward in a z direction, air taken in from the air intake space between the impellers and the operator cab; at least six motors including six or more motors for driving the six or more impellers; and an electricity storage unit for supplying power to the six or more motors. The hovering vehicle is allowed to hover from the ground by the air blasted from three or more of the six or more impellers, and the six or more impellers are arranged on the circumference of a circle with the center passing through an axis parallel to the z direction.
    Type: Grant
    Filed: November 29, 2019
    Date of Patent: July 7, 2020
    Assignee: TATSUMI RYOKI CO., LTD
    Inventor: Toyoshi Kondo
  • Patent number: 10689098
    Abstract: An adaptive landing gear assembly for a rotary wing aircraft, the adaptive landing gear assembly including a controller; a first landing gear support having a first ground contact element; and a second landing gear support having a second ground contact element; the controller independently controlling the first landing gear support and the second landing gear support.
    Type: Grant
    Filed: June 24, 2016
    Date of Patent: June 23, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Peter James Waltner
  • Patent number: 10689088
    Abstract: A fuselage includes a fuselage section with an inner surface having a non-circular contour and a spherical pressure bulkhead with an outer edge. The outer edge of the spherical pressure bulkhead is attached to the inner surface of the fuselage section and extends along a line, which is non-circular. The line extends in a three-dimensional space extending parallel to the inner surface of the fuselage section. An aircraft and a method for manufacturing a fuselage are also described.
    Type: Grant
    Filed: March 2, 2016
    Date of Patent: June 23, 2020
    Assignee: Airbus Operations GmbH
    Inventor: Dimitri Orlov
  • Patent number: 10676187
    Abstract: A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.
    Type: Grant
    Filed: March 7, 2017
    Date of Patent: June 9, 2020
    Assignee: The Boeing Company
    Inventor: Roger D. Bernhardt
  • Patent number: 10676203
    Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment.
    Type: Grant
    Filed: December 7, 2017
    Date of Patent: June 9, 2020
    Assignees: Airbus Operations S.A.S., AIRBUS SAS
    Inventors: Alain Porte, Patrick Oberle, Gregory Albet
  • Patent number: 10676181
    Abstract: An aircraft is provided including an airframe, an extending tail, a counter-rotating, coaxial main rotor assembly having an upper rotor assembly and a lower rotor assembly, and a translational thrust system including a propeller positioned at the extending tail. The translational thrust system is configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state and to generate power when in an autorotation state. A gearbox interconnects the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state. When the aircraft is in autorotation, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: June 9, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Erez Eller, Matthew T. Luszcz, William J. Eadie, Steven D. Weiner