Patents Examined by Tien Dinh
  • Patent number: 9657816
    Abstract: A drive link includes a first bearing housing, a second bearing housing, and a central portion coupled between the first bearing housing and the second bearing housing. The central portion includes a central radial bearing configured such that the central portion twists in response to cocking of the first bearing housing relative to the second bearing housing.
    Type: Grant
    Filed: November 1, 2013
    Date of Patent: May 23, 2017
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Michael Burnett, Christopher Foskey, Joel McIntyre
  • Patent number: 9656526
    Abstract: Ground vehicles that may include flight capability are described. In some examples, a vehicle frame may include a fuel tank with a main tank and at least two auxiliary tanks, with the main tank disposed substantially along the centerline of the vehicle, and the at least two auxiliary tanks extending upward and outward from the main tank. In some examples, vehicles may include a chassis, a cage attached to the chassis, a front wheelbase attached to the chassis and/or cage, a rear wheelbase attached to the chassis and/or cage, a ground steering mechanism connected to the front wheelbase and/or the rear wheelbase, a motor connected to a propeller, and a propeller shroud at least partially encircling the propeller.
    Type: Grant
    Filed: September 8, 2014
    Date of Patent: May 23, 2017
    Assignee: Paragrine Systems, LLC
    Inventor: Robert Nolan
  • Patent number: 9650122
    Abstract: A balloon equipped with photovoltaic means exhibiting an active face intended to receive solar rays and comprising an envelope, characterized in that the envelope comprises at least: a first zone transparent to solar rays; a second reflecting zone for said solar rays; a third zone comprising said photovoltaic means, the active face of which is directed toward the inside of said envelope; the second and third zones being positioned and cooperating in such a way as to reflect the solar rays in the direction of said third zone.
    Type: Grant
    Filed: November 21, 2012
    Date of Patent: May 16, 2017
    Assignee: THALES
    Inventors: Jean-Philippe Chessel, Jean-Pierre Prost
  • Patent number: 9653637
    Abstract: An apparatus is provided that comprises photovoltaic cells provided on a first rotatable member, an electric motor having an axial shaft, and a second rotatable member provided with an impeller. The photovoltaic cells capture and convert the solar energy into electrical energy. The electric motor is connected to and is in electric communication with the photovoltaic cells for powering the electric motor. The electric motor converts the electrical energy into mechanical energy for rotating the photovoltaic cells in a first direction about a central axis and for rotating the axial shaft connected to an impeller in a second direction about the central axis. The rotating axial shaft rotates the impeller at high revolutions per minute which generates a flow of air that is directed to the rotating photovoltaic cells on the first rotatable member. The photovoltaic cells are cooled by the air-flow and operate at a lower temperature.
    Type: Grant
    Filed: December 8, 2009
    Date of Patent: May 16, 2017
    Inventors: William Edward Lee, Robert F. Pienkowski
  • Patent number: 9650132
    Abstract: In accordance with the invention, a flying machine is provided comprising at least two passive lift elements arranged substantially radial-symmetrically about a yaw axis of the flying machine, wherein the passive lift elements are configured to jointly generate a torque at the yaw axis upon movement of the flying machine substantially in parallel to the yaw axis. The flying machine further comprises active lift generating means, which are arranged substantially at distal ends of the passive lift elements.
    Type: Grant
    Filed: December 5, 2014
    Date of Patent: May 16, 2017
    Assignee: METEOMATICS GMBH
    Inventor: Martin Johannes Fengler
  • Patent number: 9650156
    Abstract: An unmanned aerial vehicle (UAV) pin array release and capture chamber system includes a chamber assembly having two parallel plates of pin arrays from which a plurality of pins extend and retract vertically opposite each other so as to release and capture a UAV. The pin arrays are separated from each other by a space having two vertical and two horizontal sides, and the space is sized so as to receive the UAV. Each pin arrays may be housed in a pin array chamber enclosure. The chamber assembly may be attached to a moving object, such as an aircraft, or may be stationary with respect to a ground surface.
    Type: Grant
    Filed: November 26, 2014
    Date of Patent: May 16, 2017
    Inventor: Jeffrey Alan McChesney
  • Patent number: 9643717
    Abstract: A control system (20) for controlling pitching stabilizer means of an aircraft, said system (20) being provided with at least one outlet shaft (21) and with a first actuator (31) and a second actuator (36). The first and second actuators (31 and 36) are different, and the first actuator (31) is a slow actuator having a first driving portion that moves at a first speed, the second actuator (36) being a fast actuator having a second driving portion that moves at a second speed faster than the first speed, said control system (20) comprising a control device (50) connected to the first actuator (31) and to the second actuator (36) in order to cause said outlet shaft (21) to be driven either by the first driving portion (32) and/or by the second driving portion (37).
    Type: Grant
    Filed: May 1, 2014
    Date of Patent: May 9, 2017
    Assignee: Airbus Helicopters
    Inventors: Boris Grohmann, Thomas Buro
  • Patent number: 9643716
    Abstract: An air vehicle, an actuator assembly and a method of manufacture are provided in order to incorporate the actuator assembly within the outer mold line of the air vehicle. In regards to an air vehicle, the air vehicle includes a primary structure and a movable structure configured to be controllably moved relative to the primary structure. The air vehicle also includes an actuator assembly configured to cause the movable structure to be positioned relative to the primary structure. The actuator assembly includes an actuator housing and an actuation mechanism. The actuation mechanism is at least partially disposed within the actuator housing and is configured to provide for relative movement between the primary structure and the movable structure. At least a portion of the actuator assembly is built into at least one of the primary structure and the movable structure so as to be within an outer mold line of the air vehicle.
    Type: Grant
    Filed: April 1, 2014
    Date of Patent: May 9, 2017
    Assignee: The Boeing Company
    Inventors: James Joseph Sheahan, Jr., Donald V. Drouin, Jr.
  • Patent number: 9637215
    Abstract: A pressure bulkhead made of fiber composite material for an aircraft fuselage for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure. The bulkhead comprises a first area element, at least one second area element and a plurality of core elements. The first area element has a plurality of receptacles. Each receptacle is configured to receive a core element. The core elements are received in the receptacles between surfaces facing one another of the first area element and of the at least one second area element. The surfaces facing one another of the first area element and of the at least one second area element are connected to one another in regions without core elements.
    Type: Grant
    Filed: November 24, 2014
    Date of Patent: May 2, 2017
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Paul Joern, Karim Grase, Ichwan Zuardy, Alexei Vichniakov, Bernd Schwing
  • Patent number: 9637223
    Abstract: An afterbody flow control system is used for aircraft or missile flow control to provide enhanced maneuverability and stabilization. A method of operating the flow control system is also described. The missile or aircraft comprises an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.
    Type: Grant
    Filed: April 27, 2012
    Date of Patent: May 2, 2017
    Assignee: Orbital Reseach Inc.
    Inventors: Jack DiCocco, Troy Prince, Mehul Patel, Tsun Ming Terry Ng
  • Patent number: 9630718
    Abstract: An improved overhead storage system for use in an aircraft includes a variable opening overhead storage bin that is configured to automatically open to an initial open position when a latch mechanism is released, to open further to a second open position when a force is applied to the bin, and to return to the initial open position when the force is removed. The variable opening overhead storage bin includes a first stop device configured to stop the bin at the initial open position, and a second stop device configured to stop the bin at the second open position. When in the initial open position, the variable opening overhead storage bin is angled to retain stowed articles within the bin. When the variable opening overhead storage bin is further opened to the second open position, the passenger's hands are in a better position to control articles stowed within the bin.
    Type: Grant
    Filed: February 6, 2015
    Date of Patent: April 25, 2017
    Assignee: The Boeing Company
    Inventors: Stephen Lee Scown, Paul Joseph Wilcynski, Jeffrey Scott Heaton
  • Patent number: 9616988
    Abstract: An energy-absorbing (EA) beam member and having a cell core structure is positioned in an aircraft fuselage proximate to the floor of the aircraft. The cell core structure has a length oriented along a width of the fuselage, a width oriented along a length of the fuselage, and a depth extending away from the floor. The cell core structure also includes cell walls that collectively define a repeating conusoidal pattern of alternating respective larger and smaller first and second radii along the length of the cell core structure. The cell walls slope away from a direction of flight of the aircraft at a calibrated lean angle. An EA beam member may include the cell core structure and first and second plates along the length of the cell core structure on opposite edges of the cell material.
    Type: Grant
    Filed: February 3, 2015
    Date of Patent: April 11, 2017
    Assignee: THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
    Inventor: Justin D. Littell
  • Patent number: 9611042
    Abstract: Systems and methods for securing an emergency exit door on an armrest of a seat are provided. A system includes a latch connected to an armrest of a seat of a vehicle. The latch is moveable relative to the armrest between a stowed position and a deployed position. The latch is structured and arranged to engage an edge of a door that is associated with an exit of the vehicle to hold the door on the armrest.
    Type: Grant
    Filed: November 19, 2015
    Date of Patent: April 4, 2017
    Assignee: INTERNATIONAL BUSINESS MACHINES CORPORATION
    Inventors: Rhonda L. Childress, Kim A. Eckert, Jente B. Kuang, David B. Kumhyr, Ryan D. McNair
  • Patent number: 9611026
    Abstract: A three-dimensional structural framework having inflatable rings and a T-shaped cross-section along a plane passing through an axis of revolution of the inflatable rings in an inflated state. Shape-stabilizing elements are provided to stabilize the shape of the structural framework in space. Two inflatable rings are connected by at least one shape-stabilizing element. The structural framework is preferably used to produce stratospheric balloons.
    Type: Grant
    Filed: June 14, 2013
    Date of Patent: April 4, 2017
    Assignee: AIRBUS GROUP SAS
    Inventor: Jean-Francois Geneste
  • Patent number: 9604726
    Abstract: A balloon system is provided including a balloon envelope, a payload secured to the balloon envelope, a first parachute positioned within a parachute container, the parachute container secured to the payload, a first bridle line having a first end secured to the balloon system and a second end secured to the parachute container, a controller positioned on the balloon system, wherein when the controller receives a signal to deploy the parachute container, the controller is operable to cause the parachute container to be released downwardly from the payload.
    Type: Grant
    Filed: March 23, 2015
    Date of Patent: March 28, 2017
    Assignee: X Development LLC
    Inventor: Daniel Fourie
  • Patent number: 9604716
    Abstract: A movable panel such as an aileron is connected to a load-bearing structure such as a wing of an aircraft by hinges which comprise flexible, elastic plates which are juxtaposed and are provided at opposite angles so as to allow the panel to rotate in an easy manner in response to the movements of an actuator; the hinges are, however, rigid in regard to other loads, such as aerodynamic suction loads, such that inadmissible travel of the panel is avoided.
    Type: Grant
    Filed: December 10, 2014
    Date of Patent: March 28, 2017
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Christophe Casse
  • Patent number: 9604719
    Abstract: A device for lateral control of an aircraft includes a calculating unit for automatically applying, if conditions for turning of the aircraft are met, a symmetrical braking value at a brake assembly. Subsequently, in the course of the turn, the device automatically distributes this symmetrical braking value in differential braking between a braking device of the left main landing gear and a braking device of the right main landing gear of the aircraft. Distribution of the symmetrical breaking is performed as a function of current directional command orders in such a way as to maintain a constant overall braking level for, at least for directional command orders below a predetermined threshold.
    Type: Grant
    Filed: January 29, 2014
    Date of Patent: March 28, 2017
    Assignee: AIRBUS OPERATIONS S.A.S.
    Inventors: Matthieu Mayolle, Caroline Acanfora, Louis-Emmanuel Romana, Julien Fontan
  • Patent number: 9604724
    Abstract: A seating arrangement includes a seat with a seating surface and a top bunk disposed adjacent to the seat. The seat and the top bunk are configurable between a first configuration and a second configuration. In the first configuration, the seat accommodates a user in a seated position and the top bunk is stowed. In the second configuration, the seat and the top bunk form a bunk bed configured to accommodate users in prone positions. In the first configuration, the seating surface is disposed at a first predetermined height. In addition, in the second configuration, the seating surface is disposed at a second predetermined height that is lower than the first predetermined height.
    Type: Grant
    Filed: May 3, 2013
    Date of Patent: March 28, 2017
    Assignee: BOMBARDIER INC.
    Inventors: David Savard, Rene Bardier, Michael Oleson, Alfredo Suarez
  • Patent number: 9598169
    Abstract: This disclosure is directed to a single blade propeller and systems, devices, and techniques pertaining to assisting in critical stages of flight (e.g., takeoff, landing, emergency situations, etc.) in vertical takeoff and landing (VTOL) aircraft. The single blade propeller may be incorporated into fixed and rotary wing VTOL aircraft as part of a first propulsion system. The first propulsion system may include one or more single blade propellers driven by electric motors, combustion engines, and/or hybrid engines. Each of the single blade propellers may include a lift-producing blade and a counterweight opposite the lift-producing blade. As each of the single blade propellers spins, it may produce lift in a direction approximately perpendicular to the horizon to effect vertical flight.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: March 21, 2017
    Assignee: Amazon Technologies, Inc.
    Inventors: Louis LeRoi LeGrand, III, Ricky Dean Welsh, Walker Chamberlain Robb, Robert Roy Champagne, Jr., Daniel Buchmueller, Joshua White Traube, Gur Kimchi
  • Patent number: 9598166
    Abstract: A window of an aircraft having electromagnetic shielding performance and environment-resistant sealing performance, an aircraft, and an assembly method for a window of an aircraft are provided. A conductive seal member (60) is provided so as to face and surround the peripheral side surface of a window panel and is sandwiched between a conductive film (41) and an outer retainer (22). In the conductive seal member (60), thin wire materials (62) made of a conductive material such as aluminum are embedded in a seal member body (61) made of a material, such as silicone rubber, having an electric insulating property, waterproofness and pliability. An electromagnetic shielding effect, and environment-resistant sealing properties such as an electric insulating property and waterproofness can be both ensured by the conductive seal member (60).
    Type: Grant
    Filed: December 13, 2012
    Date of Patent: March 21, 2017
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Takashi Yokoi