Patents Examined by Michael Kreiner
  • Patent number: 9884681
    Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.
    Type: Grant
    Filed: January 12, 2017
    Date of Patent: February 6, 2018
    Inventors: Tao Wang, Tao Zhao, Hao Du, Mingxi Wang
  • Patent number: 9845162
    Abstract: The present disclosure provides a system, method, and apparatus for a protective finish for an airfoil. In one or more embodiments, the disclosed method involves providing a sheath, and applying the sheath to the surface of the airfoil. In one or more embodiments, the sheath wraps around the surface of the airfoil from the leading edge of the airfoil towards the trailing edge of the airfoil. In at least one embodiment, the sheath covers approximately 50 percent to approximately 70 percent of the chord length of the airfoil. In some embodiments, the sheath is manufactured from at least one polymer, such as a polyurethane and/or a floropolymer. In one or more embodiments, the airfoil is a winglet, a raked wing tip, and/or a wing.
    Type: Grant
    Filed: May 3, 2013
    Date of Patent: December 19, 2017
    Inventor: Darrell D. Campbell, Jr.
  • Patent number: 9828085
    Abstract: Aircraft fuselages are disclosed herein. An example apparatus includes a fuselage of an aircraft having a first section and a second section to which a tail assembly is to be coupled. The second section is aft of the first section and is to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly. A first width of the first section decreases from a front to a rear of the first section, and a second width of the second section is substantially constant.
    Type: Grant
    Filed: November 28, 2016
    Date of Patent: November 28, 2017
    Inventor: Bruce Raymond Detert
  • Patent number: 9821917
    Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades. The aft engine also includes a nacelle encircling the plurality of fan blades with one or more structural members extending between the nacelle and the mean line of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: November 21, 2017
    Inventors: Thomas Lee Becker, Kurt David Murrow, Patrick Michael Marrinan, Brandon Wayne Miller
  • Patent number: 9815552
    Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (“UAV”) in which the fuselage of the UAV is center mounted and at least some of the motors are configured to encompass at least a portion of the fuselage. In such a configuration, the stator and rotor of the motor extend around a perimeter of the fuselage, the propellers are coupled to an outer perimeter of the rotor, and the propellers extend radially outward away from the fuselage. Likewise, a closed wing may be coupled to the fuselage and positioned to encompass the radially extending propellers and at least a portion of the fuselage.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: November 14, 2017
    Assignee: Amazon Technologies, Inc.
    Inventor: Ricky Dean Welsh
  • Patent number: 9815550
    Abstract: A taxiing system for an aircraft including an undercarriage having a wheel, includes an electric motor associated with the wheel, an electric controller of the electric motor, connected to an output of an electrical power supply, and a taxiing control computer configured to determine control instructions for the electric motor and to transmit these instructions to the electric controller. The taxiing control computer is configured to receive braking of the aircraft commands during the taxiing of the aircraft and to determine control instructions for the electric motor corresponding to operation of the motor in generator mode when it receives a braking command. The electric controller is connected to an energy absorber making it possible to absorb the electric energy produced by the electric motor when the latter is operating in generator mode.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: November 14, 2017
    Assignees: AIRBUS SAS, Airbus Operations S.A.S.
    Inventors: Yann Nicolas, Philippe Tatry, Matthieu Bradier, Nicolas Sanz
  • Patent number: 9809316
    Abstract: An evacuation system is provided. The system may comprise a girt coupled to a door sill and an evacuation slide. The evacuation slide may comprise a head end coupled to the girt, an extension, a hinge portion coupled between the head end and the extension, and a lane diverter coupled to the evacuation slide. A method is also provided. The method may include opening a door to expose a door sill, inflating the evacuation slide with the evacuation slide coupled to the door sill, bending a hinge portion of the slide in response to a door sill height being less than or equal to a predetermined height, and redirecting a slide lane to a side exit.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: November 7, 2017
    Inventors: Drew Hartman, Jaro Volny
  • Patent number: 9802712
    Abstract: The invention refers to a quick released system for coupling (1) and drogue (2) assembly comprises a crown coupling connector (4) suitable for being fixed to the coupling (1) and comprising cavities (14); a plurality of balls (3) housed in the cavities (14) with an emerging part and radially movable; a crown drogue connector (5) suitable for being fixed to the drogue (2), configured to engage and disengage the coupling connector (4) and comprising first recesses (26); and a crown locking ring (6) rotatable between a locked and a released position and comprising second recesses (31). The second recesses (31) are arranged in correspondence with the first recesses (26) when the system is in a released position and, the locking ring (6) in contact with the balls (3) and the first recesses (26) engaged with the emerging part of the balls (3) when the system is in a locked position.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: October 31, 2017
    Assignee: Airbus Defence and Space, S.A.
    Inventor: Jorge Terron Blanco
  • Patent number: 9802697
    Abstract: The invention relates to an aircraft landing gear equipped with a steering device (7) for orienting the wheels (5), the steering device (7) comprising a body (8) in which is incorporated an electromechanical actuator (41) equipped with an electric motor (42). The landing gear is further equipped with damping means intended to limit the transmission of vibration from the wheel (5) to the rest of the landing gear (1) when the aircraft is on the ground. The body (8) of the steering device (7) is mounted with the ability to rotate with a limited amplitude of rotation. The damping means are mounted between the body (8) of the steering device (7) and the strut assembly (2) of the landing gear to damp the vibration between the body (8) of the steering device (7) and the strut assembly (2).
    Type: Grant
    Filed: October 7, 2015
    Date of Patent: October 31, 2017
    Inventors: Pierre-Yves Liegeois, Thierry Blanpain, Edouard Campbell
  • Patent number: 9802690
    Abstract: A cargo airship is disclosed. The cargo airship may include a hull configured to contain a gas and at least one propulsion assembly coupled to the airship and including a propulsion device. The cargo airship may further include a payload bay comprising an external cargo area located outside of the hull. The cargo airship may also include a cargo handling system including at least one hoisting mechanism configured to lift cargo into the external cargo area while the airship is hovering.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: October 31, 2017
    Inventors: John Goelet, Loginn Kapitan, Ron Hochstetler
  • Patent number: 9796488
    Abstract: Systems, methods, and apparatus for dual port ring compatible satellites are disclosed. In one or more embodiments, a method for removably attaching at least one spacecraft to a payload attach ring on a launch vehicle involves attaching a strongback of each of the spacecrafts to two respective payload ports of the payload attach ring on the launch vehicle. In one or more embodiments, the strongback of each of the spacecrafts is attached to each of the two respective payload ports via a respective beam mounted to a respective port adaptor plate. The method further involves separating the strongback of each of the spacecrafts from the two respective payload ports of the payload attach ring on the launch vehicle by using at least one mechanical actuator on each of the beams.
    Type: Grant
    Filed: October 2, 2015
    Date of Patent: October 24, 2017
    Assignee: The Boeing Company
    Inventors: Timothy Scott Cook, Robert Bruce Friend
  • Patent number: 9789969
    Abstract: An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member.
    Type: Grant
    Filed: November 11, 2016
    Date of Patent: October 17, 2017
    Assignee: SZ DJI Technology Co., Ltd.
    Inventor: Mingyu Wang
  • Patent number: 9777838
    Abstract: To reliably prevent entrance of electro-magnetic waves in a door that closes an opening portion formed in an airframe of an aircraft. A gasket seal 20 which is arranged between an opening portion 12 formed in an airframe of an aircraft and a door 13 for closing the opening portion 12, includes: a gasket seal body that is made of a rubber material; and conductive fiber 24 that covers a surface of the gasket seal body. When the door 13 is in a closed state, the gasket seal 20 whose surface is made conductive is abutted against a striker 30 provided on a skin 11 side of the airframe and made of a conductive material. The door 13 and the skin 11 of the airframe are electrically connected together via the conductive fiber 24 and the striker 30, and electro-magnetic waves can be reliably shielded.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: October 3, 2017
    Inventors: Yusaku Yahata, Takashi Yokoi, Keiichiro Doi, Mikishige Ibaragi
  • Patent number: 9771163
    Abstract: Short takeoff and landing aircraft are disclosed. An example fixed wing aircraft includes a primary power source to provide power to a propulsion unit, a secondary power source to provide power to the propulsion unit, and a detachable power coupling to transfer power to the secondary power source from a source external to the fixed wing aircraft during takeoff.
    Type: Grant
    Filed: March 31, 2014
    Date of Patent: September 26, 2017
    Assignee: The Boeing Company
    Inventor: Rich P. Ouellette
  • Patent number: 9771151
    Abstract: A rotor blade for a reaction drive type helicopter is provided. The rotor blade includes a main duct extending from a proximal end, couplable to and for fluid communication with a rotor hub, to a distal end for ducting a first air/gas stream from the rotor hub to the distal end. A nozzle is attached to an outlet of the main duct at the distal end for receiving the first air/gas stream from the main duct and releasing the first air/gas stream to propel the rotor blade. A circulation control is carried at a trailing edge of the blade. A trailing edge duct is carried intermediate the trailing edge and the main duct and is in fluid communication with the main duct by a partition with a plurality of orifices formed therein to bleed air from the main duct and generate a second air/gas stream therein with a pressure less than the pressure of the first air/gas stream. The trailing edge duct supplies the second air/gas stream to the circulation control.
    Type: Grant
    Filed: June 18, 2015
    Date of Patent: September 26, 2017
    Inventor: David J. White
  • Patent number: 9745046
    Abstract: An aircraft transparency assembly includes an aircraft transparency having at least one ply having an outer surface and an extended portion. The assembly also includes a pressure seal configured to engage the extended portion of the ply, wherein the pressure seal includes a pressure seal body and at least one integrated compression stop. The transparency assembly can also include an anti-static drain assembly including at least one flexible conductive element having a first end in electrical contact with the outer surface of the ply, for example with an optional conductive coating on the outer surface of the ply, and a second end configured to contact the pressure seal.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: August 29, 2017
    Assignee: PPG Industries Ohio, Inc.
    Inventors: Spencer B. Harrison, James V. Hartmann
  • Patent number: 9745049
    Abstract: A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: August 29, 2017
    Inventors: James Wilson, Alan Quayle, Paul Hadley
  • Patent number: 9731810
    Abstract: A system and method for improving fuel storage within the wing of an aircraft. In one exemplary embodiment, the system and method eliminate the traditional spars and ribs, and any spanwise and cordwise connecting vertical webs, within a wing. Instead, the system comprises a plurality of modified flared spars, each having a length defined by an angled hat section, to form a wing structure. The modified flared spars may also comprise one or more lengths defined by a specialized section configured to accommodate a portion of a box section, or any other internal component of the wing. The system and method may also involve a contiguous fuel bladder of any size/type. The fuel bladder for the wing may comprise a fabric coated or impregnated with an elastomeric material that may include a polyurethane dispersion layer combined with a sealant.
    Type: Grant
    Filed: September 22, 2015
    Date of Patent: August 15, 2017
    Inventors: Quinn Canole, William York, Jeffrey Bracken
  • Patent number: 9708081
    Abstract: A radiator for a satellite intended for being placed in geostationary orbit around the earth in a tilted plane relative to the plane of the ecliptic, includes at least one panel having at least one radiative surface, and including: a mounting foot supporting the panel; and control and motor elements for pivoting the mounting foot about an axis of rotation tilted relative to the radiative surface which is perpendicular to a radiation axis, the radiation axis and the axis of rotation being tilted relative to one another by a non-zero working angle, corresponding to the tilt angle of the plane of the orbit of the satellite relative to the plane of the ecliptic, the working angle being fixed, such that for any rotation of the mounting foot about the axis of rotation owing to the control and motor elements, the radiative surface remains parallel to the plane of the ecliptic.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: July 18, 2017
    Inventor: Philippe Cael
  • Patent number: 9701403
    Abstract: According to one embodiment, a rotorcraft yoke comprises a plurality of arms. The plurality of arms, in combination, comprise a plurality of fibrous plies extending continuously throughout all of the plurality of arms.
    Type: Grant
    Filed: February 18, 2014
    Date of Patent: July 11, 2017
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Amarjit Kizhakkepat, Levi Armstrong, Tyler Baldwin, Paul Oldroyd, Michael J. Southerland