Patents Examined by Valentina Xavier
  • Patent number: 11667386
    Abstract: A system for communicating between passenger seats and an aircraft galley. The system may include a control unit including a display area for interfacing with a crew member. The system may include a plurality of devices, each positioned at a respective passenger seat. The control unit may be adapted to display on the display area data related to a particular order, including a location of an associated passenger seat. The control unit may be further adapted to transmit to a particular device associated with the order notifications concerning a status of the particular order.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: June 6, 2023
    Assignee: B/E Aerospace, Inc.
    Inventors: William J. Godecker, Nicolaas Van Zwieten, Michael Kemery, Eid-Beng Goh
  • Patent number: 11661202
    Abstract: An aerial vehicle of a box wing design adapted for vertical takeoff and landing using mounted thrust producing elements. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses one or more thrust producing elements on both of the right and the left sides. The aerial vehicle may have one or more front thrust producing elements and one or more rear thrust producing elements on both of the right and the left sides of a main vehicle body.
    Type: Grant
    Filed: March 14, 2022
    Date of Patent: May 30, 2023
    Assignee: Joby Aero, Inc.
    Inventors: JoeBen Bevirt, Alex Stoll
  • Patent number: 11655043
    Abstract: An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.
    Type: Grant
    Filed: July 13, 2021
    Date of Patent: May 23, 2023
    Assignee: DUXION MOTORS, INC.
    Inventors: Sheikh Fazle Rabbi, Rick Ralph Pilgrim, Kyle Reuben Genge, Trevor Forward, Adam Keating, Richard Robert Roper, Bryan Gabin Lobo
  • Patent number: 11655032
    Abstract: A system for boarding a plurality of passengers onto a passenger vehicle having a plurality of unassigned seats is disclosed. In various embodiments, the system includes a first passenger seat and a first occupancy indicator, the first occupancy indicator associated with the first passenger seat; a second passenger seat and a second occupancy indicator, the second occupancy indicator associated with the second passenger seat; and a processor connected to a communication link and to the first occupancy indicator and to the second occupancy indicator, the processor being configured to receive reservation data from a computing device having a seating reservation application engine installed thereon, the computing device configured for connection to the communication link and the seating reservation application engine configured to activate the first occupancy indicator or the second occupancy indicator.
    Type: Grant
    Filed: March 19, 2020
    Date of Patent: May 23, 2023
    Assignee: B/E Aerospace, Inc.
    Inventors: Rebecca Stoner, Eric Johannessen
  • Patent number: 11655055
    Abstract: The embodiments herein disclose a retrofitted or in built or add-on kit/device for airborne vehicles to reduce the aerodynamic drag thereby increasing performance parameters/metrics of the vehicles. Drag reduction is achieved through shape/contour optimization, and/or heat/energy/fluid addition to the flow in neighbourhood of the vehicle. The device is designed with an external surface to offers the minimum drag. The device is configured to deposit heat/energy/fluid in neighbourhood of flying vehicle in several ways by generating/injecting hot gases in neighbourhood of vehicle for energy/heat addition, thereby causing maximum drag reduction. Heat/energy/fluid is added through the nozzles in the add-on kit/device.
    Type: Grant
    Filed: February 19, 2019
    Date of Patent: May 23, 2023
    Inventor: Vikrant Sharma
  • Patent number: 11643226
    Abstract: Provided herein are various enhancements to spacecraft or other vehicles, including spacecraft docking mechanisms and vehicle mating systems. In one example, a vehicle mating mechanism includes a latch assembly of a vehicle having soft capture elements and hard capture elements. The soft capture elements accept a bar element of a mating vehicle and retain the bar element to within an envelope that provides a soft capture with the mating vehicle. The hard capture elements move within the envelope to engage the bar element and draw the bar element toward the vehicle to provide a hard capture with the mating vehicle. The vehicle mating mechanism can also include a cup-cone interface element of the vehicle that mates with a cup-cone interface element of the mating vehicle during the hard capture to establish an alignment between the vehicle and the mating vehicle.
    Type: Grant
    Filed: September 1, 2020
    Date of Patent: May 9, 2023
    Assignee: Lockheed Martin Corporation
    Inventors: Jonathan Michael Markcity, Christopher Leighton Brown
  • Patent number: 11643212
    Abstract: A frame member, a monument for a vehicle, and a vehicle are provided. The frame member includes an extrusion that has a spar with first and second opposing surfaces and first and second opposing ends. The spar includes a first retention lip extending from the first planar surface along the first end at an acute angle relative to the first planar surface. The spar includes a rub strip protrusion extending from the first planar surface between the first and second ends. The rub strip protrusion includes a third end and a second retention lip extending from a third surface facing the first retention lip. The second retention lip and the third surface form an acute angle. The extrusion also includes at least two panel protrusions extending from the second planar surface of the spar. A rub strip can include retention tabs with outward-facing notches that engage the first and second retention lips.
    Type: Grant
    Filed: November 12, 2018
    Date of Patent: May 9, 2023
    Assignee: The Boeing Company
    Inventors: Sougand Talebpour, Roland Mair, Russell W. Keck, Tomas Armenta, Paul T. Bridgeman, Franco M. Cagnina
  • Patent number: 11634210
    Abstract: A system for an unmanned aerial vehicle can include an altitude control system, which further includes a compressor assembly, a valve assembly, and an electronics assembly. The compressor assembly may include a driveshaft and a bearing assembly configured to rotate the driveshaft. The driveshaft may be formed from a first material and a compressor housing may be formed from a second material. The first and second materials may have different rates of thermal expansion. A dynamic preloading mechanism, such as a flexible plate, may be provided within the compressor assembly to exert a preloading force on the bearing assembly. Throughout the duration of the flight of the unmanned aerial vehicle, the preloading mechanism can continually compensate for differences in rates of thermal expansion between the first and second materials throughout.
    Type: Grant
    Filed: June 17, 2019
    Date of Patent: April 25, 2023
    Assignee: Aerostar International, LLC
    Inventors: Kevin Anderson, Nathan Winder
  • Patent number: 11618326
    Abstract: The present disclosure relates to an electrically powered aircraft comprising: a propulsion system; a navigation control system operatively coupled to said propulsion system to navigate the aircraft to a desired location; a rechargeable electrical power storage to power the aircraft during operation; and a power line charging unit comprising a current transformer operatively coupled to said rechargeable electrical power storage and remotely operable to engage a power line in flight to recharge said rechargeable electrical power storage and remotely disengage said power line once recharged.
    Type: Grant
    Filed: March 7, 2022
    Date of Patent: April 4, 2023
    Assignee: FERRARISPOWER CO., LTD.
    Inventor: Ja-Il Koo
  • Patent number: 11613379
    Abstract: A hard landing indicator mountable to a landing gear of an aircraft is provided. The landing gear has components displaceable toward each other upon the aircraft experiencing a landing. The hard landing indicator includes a first portion securable to one of these components and a second portion that projects outwardly from the first portion and oriented toward another component of the landing gear to be positioned within a path of displacement of the second component toward the first component. The second portion is impacted by this component upon this component being displaced during a hard landing of the aircraft. The impact leaves a visual mark on the second portion of the hard landing indicator to indicate that a hard landing has occurred. A landing gear equipped with and a method of installing such indicator are also provided.
    Type: Grant
    Filed: October 30, 2019
    Date of Patent: March 28, 2023
    Inventor: John J. C. Ferneley
  • Patent number: 11613385
    Abstract: This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.
    Type: Grant
    Filed: July 26, 2019
    Date of Patent: March 28, 2023
    Assignee: EnergeticX.net, L.L.C.
    Inventor: Mark C. Russell
  • Patent number: 11613370
    Abstract: An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The wing mounted rotor assemblies may have split nacelles, wherein a forward portion of the nacelle deploys along with the electric motor and the propeller.
    Type: Grant
    Filed: July 29, 2021
    Date of Patent: March 28, 2023
    Assignee: Joby Aero, Inc.
    Inventors: Joeben Bevirt, Alex Stoll
  • Patent number: 11608171
    Abstract: The invention discloses a large drone that is powered by solar energy. In addition, the drone includes a large, lightweight fuselage that not only keeps balance and stability but also reduces the required power during flight.
    Type: Grant
    Filed: April 28, 2020
    Date of Patent: March 21, 2023
    Assignee: PSJ International Ltd.
    Inventor: Ching-Fuh Lin
  • Patent number: 11608195
    Abstract: The present invention relates to a resident space object orbit determination system comprising a high efficiency module for determining a resident space object's orbit and a highly efficient method for determining same. Applicants developed a method and system to determine the orbits of residence space objects including resident space objects that do not reflect energy that is directed at them and/or may be coated to minimize the ability to accurately see such resident space objects. Thus, a method, a module and a system for making such determinations that can easily and inexpensively be added to an early warning reentry system is provided.
    Type: Grant
    Filed: September 7, 2021
    Date of Patent: March 21, 2023
    Assignee: United States of America as represented by the Secretary of the Air Force
    Inventors: Daniel M. Dombrowski, Robert A. Bettinger
  • Patent number: 11603185
    Abstract: A mechanical synchronization device for a distributed system. A plurality of actuators actuate movement of control surface components of an aircraft. Each actuator has a first end coupled to a structure of the aircraft and a second end coupled to a control surface component, and a drive path from a motion provider to the control surface component, the control surface component being configured to move along the respective drive path. A power module controller is operable to simultaneously output motor drive power from a power module through an electrical bus to at least two of the motion providers in a synchronous or nearly synchronous manner to actuate movement of control surface components. The mechanical synchronization device is between at least two of the actuators and transfers torque between the actuators to maintain symmetry between the actuators. A load limiting device may limit the power transferred through the mechanical synchronization device.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: March 14, 2023
    Assignee: Parker-Hannifin Corporation
    Inventors: Eric A. Polcuch, David J. Bouman
  • Patent number: 11591066
    Abstract: Aspects relate to systems and methods for folding wings on an aircraft. An exemplary system includes a blended wing body, where the blended wing body includes a main body and at least a wing, a hinge located on the at least a wing and configured to allow folding of the at least a wing, an actuation system configured to fold the at least a wing, and a controller configured to control the at least an actuation system.
    Type: Grant
    Filed: October 15, 2021
    Date of Patent: February 28, 2023
    Assignee: Blended Wing Aircraft, Inc.
    Inventor: Blaine Knight Rawdon
  • Patent number: 11591109
    Abstract: Provided is an abnormality detection device for a rotary wing unit. The rotary wing unit includes a plurality of rotary wings that is coaxially disposed. The abnormality detection device includes a controller configured to acquire at least one of a correlation at the time of normal operation between operation parameters related to the rotary wings and a correlation at the time of abnormal operation between the operation parameters and detect abnormality of the rotary wing unit, based on a correlation at the time of actual operation between the operation parameters and at least one of the correlation at the time of normal operation and the correlation at the time of abnormal operation.
    Type: Grant
    Filed: August 14, 2019
    Date of Patent: February 28, 2023
    Assignees: TOYOTA JIDOSHA KABUSHIKI KAISHA, SkyDrive Inc.
    Inventors: Kenichi Yamamoto, Toshio Ando
  • Patent number: 11572148
    Abstract: Aircraft stringers having carbon fiber reinforced plastic (CFRP) material reinforced flanges are disclosed. An example stringer to be coupled to a skin of an aircraft comprises a flange. The flange includes a first portion of a first stiffening segment. The flange further includes a first portion of a second stiffening segment coupled to the first portion of the first stiffening segment. The flange further includes a CFRP reinforcement segment coupled to the first portion of the first stiffening segment and to the first portion of the second stiffening segment. The CFRP reinforcement segment strengthens the first portion of the first stiffening segment and the first portion of the second stiffening segment.
    Type: Grant
    Filed: June 4, 2018
    Date of Patent: February 7, 2023
    Assignee: THE BOEING COMPANY
    Inventor: Jiangtian Cheng
  • Patent number: 11572202
    Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.
    Type: Grant
    Filed: December 21, 2021
    Date of Patent: February 7, 2023
    Assignee: Planetary Systems Corporation
    Inventors: Walter Holemans, Ryan Williams
  • Patent number: 11565811
    Abstract: The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft; a cabin located within the main body and a transitional portion of the blended wing body; and a plurality of transparent panels in a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.
    Type: Grant
    Filed: January 28, 2022
    Date of Patent: January 31, 2023
    Assignee: Blended Wing Aircraft, Inc.
    Inventor: Mark Allan Page