Patents Examined by Keith L. Dixon
  • Patent number: 10377468
    Abstract: A modular brake and rudder control system usable in an aircraft. The modular system mounts atop the flight deck floor without penetrating through the floor when the system is operatively connected to the aircraft's fly-by-wire brake and rudder systems. Pedal assemblies extending from the housing are rotatable and longitudinally moveable relative to the housing. A brake control system fully contained in the housing is connected to the pedal assemblies and provides a signal via an electrical connector to the fly-by-wire brake system upon rotation of the pedals. A rudder control system is fully contained in the housing and is operable independent of the brake control system. The rudder control system detects longitudinal motion of the pedal assemblies and provides a signal via an electrical connector to the fly-by-wire rudder system.
    Type: Grant
    Filed: March 8, 2017
    Date of Patent: August 13, 2019
    Assignee: Mason Electric Company
    Inventors: Fred Carner, Bijan Salamat
  • Patent number: 10377482
    Abstract: A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle system which has removable wing sections which allow for re-configuration with different wing section types, allowing for configurations adapted for a particular flight profile. A method of customizing a configuration of an unmanned aerial vehicle based upon flight profile factors such as duration, stability, and maneuverability.
    Type: Grant
    Filed: May 1, 2016
    Date of Patent: August 13, 2019
    Assignee: Transition Robotics, Inc.
    Inventors: Jeffrey Kyle Gibboney, Pranay Sinha
  • Patent number: 10358215
    Abstract: An aircraft (2) comprising a launch tube (14) extending along at least part of a length of a wing of the aircraft (2), and through which an item (24) may be launched from the aircraft (2). The launch tube (14) comprises an opening (22) at a distal end of the wing (6).
    Type: Grant
    Filed: June 21, 2016
    Date of Patent: July 23, 2019
    Assignee: BAE Systems plc
    Inventor: Andrew Charles White
  • Patent number: 10358211
    Abstract: A rotor apparatus is provided and includes a first rotor shaft disposed to rotatably support a first rotor, a second rotor shaft disposed to rotatably support a second rotor and first and second bearing elements disposed to support the first rotor shaft within the second rotor shaft and to pre-load the first rotor shaft in one of tension and compression and the second rotor shaft in the other one of tension and compression.
    Type: Grant
    Filed: January 2, 2014
    Date of Patent: July 23, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Yuriy Gmirya
  • Patent number: 10358226
    Abstract: In order to bring a turbofan engine closer to the lower surface of a wing box, the disclosure herein foresees an assembly for an aircraft including a mount for mounting a rigid structure of an engine strut to the wing box, the mount including an upper wing mount including a fitting secured to the upper surface of the wing box.
    Type: Grant
    Filed: May 4, 2016
    Date of Patent: July 23, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Olivier Pautis
  • Patent number: 10330166
    Abstract: The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.
    Type: Grant
    Filed: October 3, 2017
    Date of Patent: June 25, 2019
    Assignee: Textron Innovations Inc.
    Inventors: Taeoh Lee, David E. Heverly, II, Matthew W. Hendricks, Maurice Griffin, Michael R. Smith
  • Patent number: 10329015
    Abstract: Generally, an inventive aircraft (1) having at least a first lift body (2) and a second lift body (3) each controllably configurable to correspondingly generate an amount of lift (4) sufficient to remain aloft at a first elevation (5) and a second elevation (6) a sufficient distance apart (7) to subject the first lift body (2) and the second lift body (3) to sufficiently disparate fluid flow characteristics (8) to propel the aircraft (1).
    Type: Grant
    Filed: May 18, 2012
    Date of Patent: June 25, 2019
    Inventor: Henry C. DeBey
  • Patent number: 10322820
    Abstract: An unmanned aerial vehicle (UAV) system comprises a hangar structure configurable to mount on a host platform. The hangar structure comprises electrical circuits comprising a charging circuit and a communications circuit. The UAV system further comprises a plurality of stackable UAVs. The plurality of stackable UAVs comprise respective batteries and control circuits. The plurality of stackable UAVs are configured to cooperate with the charging circuit to charge the batteries and to cooperate with the communications circuit to communicate with the control circuits while the plurality of stackable UAVs are in a stacked configuration within the hangar structure.
    Type: Grant
    Filed: September 14, 2017
    Date of Patent: June 18, 2019
    Assignee: SparkCognition, Inc.
    Inventors: Syed Mohammad Amir Husain, John Rutherford Allen
  • Patent number: 10301037
    Abstract: Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method for establishing situational awareness during formation flight includes exchanging transponder signals between at least two aircraft, establishing two-way communication links between the at least two aircraft, exchanging telemetry data between the at least two aircraft, and assigning the roles of a leader and a follower to the aircraft.
    Type: Grant
    Filed: March 21, 2016
    Date of Patent: May 28, 2019
    Assignee: SUNLIGHT PHOTONICS INC.
    Inventors: Sergey V. Frolov, Michael Cyrus, Allan J. Bruce, John P. Moussouris
  • Patent number: 10293925
    Abstract: Systems, methods, and computer program products for directional force weighting of an active vibration control system involve arranging a plurality of force generators in an array, identifying individual component forces corresponding to force outputs of each of the plurality of force generators, determining a combination of the individual component forces that will produce a desired total force vector, and adjusting the outputs of each of the plurality of force generators such that the combination of the individual component forces are at least substantially similar to the desired force vector.
    Type: Grant
    Filed: January 17, 2014
    Date of Patent: May 21, 2019
    Assignee: LORD Corporation
    Inventors: Mark R. Jolly, Paul R. Black, Doug A. Swanson, Doug G. Pedersen
  • Patent number: 10293959
    Abstract: Systems, methods, devices, and non-transitory media of the various embodiments provide for a volumetric approach to determining orbital encounters that may determine the number of encounters over a specified length of time. Such information may be used to determine how often during an orbit or period of time an object might trigger a conjunction warning for a neighboring satellite. The various embodiments may be used as a planning and characterization tool to estimate satellite encounter rates for a prospective orbit regime and may provide an efficient, in-line approach to assess the number of encounters occurring within a user-specified span of time.
    Type: Grant
    Filed: July 7, 2016
    Date of Patent: May 21, 2019
    Assignee: Analytical Graphics Inc.
    Inventors: Salvatore Alfano, Daniel Oltrogge
  • Patent number: 10279933
    Abstract: The invention relates to an androgynous coupling device (10) for connecting modules, in particular for constructing a spacecraft of modular design, wherein, in order to connect the modules, the coupling device (10) can be coupled to an identically constructed further androgynous coupling device and has a plurality of coupling elements (30, 32). It is provided that the androgynous coupling device (10) has a covering element (18) which covers the coupling elements (30, 32) in a passive state of the coupling device (10), wherein a first of the coupling elements (30) can be moved outwardly through the covering element (18) for active coupling to the identically constructed further coupling device. The invention furthermore relates to a module, in particular a module for constructing a spacecraft of modular design, having at least one such coupling device (10).
    Type: Grant
    Filed: March 30, 2015
    Date of Patent: May 7, 2019
    Assignee: Rheinisch-Westfälische Technische Hochschule (RWTH) Aachen
    Inventors: Martin Anand Lakshmanan, Marc André Adomeit, Patric Seefeldt, Viktor Reimer
  • Patent number: 10279914
    Abstract: A seat belt arrangement for a seat assembly of an aircraft for securing a passenger in a seat during travel. The seat belt arrangement comprises: a seat belt including at least a first belt portion to extend across a body part of the passenger seated on the seat; and a fastener member provided on the first belt portion, especially at a first end region of the first belt portion, for operation by the passenger to fasten and to release the seat belt across the body part of the passenger. A second end region of the first belt portion is anchored at a footing of the seat assembly or at a floor structure of the aircraft directly.
    Type: Grant
    Filed: April 13, 2015
    Date of Patent: May 7, 2019
    Assignee: Airbus Operations GmbH
    Inventor: Benjamin Fragnière
  • Patent number: 10272997
    Abstract: Loads from the propeller-gearbox-engine assembly are transferred to an airframe directly, without concentrated internal structure. In preferred embodiments this is accomplished using a lightweight, structurally efficient hub and gearbox that transfer their rotor loads directly to the nacelle OML (Out Mold Line) monocoque. By keeping the load path direct and at the largest diameter, the structure achieves higher stiffness and strength efficiency than conventional point loaded internal frames.
    Type: Grant
    Filed: October 21, 2008
    Date of Patent: April 30, 2019
    Inventor: Abe Karem
  • Patent number: 10266257
    Abstract: There is provided a propeller-type vertical take-off and land aircraft with a torque removal and balancing function, the aircraft comprising: a body; a body support frame to support the body; at least one main rotor blade provided out of the body; a rotation rotor coupled centrally to the main rotor blade; a rotation drive axis operatively coupled to the rotation rotor; a main rotor motor operatively coupled to the rotation drive axis; and a counter-torque and balancing wheel disposed under the body support frame to be coupled to a torque-removal inverse motor to be configured to rotate in an opposite direction to a rotation of the main rotor blade, wherein the counter-torque and balancing wheel is housed in the body.
    Type: Grant
    Filed: December 10, 2015
    Date of Patent: April 23, 2019
    Inventor: Sung Ho Nam
  • Patent number: 10266277
    Abstract: The invention relates to a system (2) for generating non-propulsive energy in an aircraft, including: an auxiliary power unit (20) including a gas turbine (21) and a fuel cell (22); a pathway (23) for the intake of outside air into the aircraft; an exhaust pipe (24) of the gas turbine, the system being characterized in that the air intake pathway (23) includes a pipe (230) for cooling the fuel pipe, in that the pipe is in fluid communication with the exhaust pipe (24) of the gas turbine such that the ejection of the gas from the gas turbine into the exhaust pipe causes a suction of the air outside the aircraft into the cooling pipe (230) by Venturi effect. The invention also relates to a method for generating non-propulsive energy.
    Type: Grant
    Filed: November 25, 2014
    Date of Patent: April 23, 2019
    Assignee: SAFRAN POWER UNITS
    Inventors: Jean-Francoise Rideau, Stephane Vaillant
  • Patent number: 10259570
    Abstract: An electrically actuated braking system for an aircraft, comprising: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a motor controller for generating a drive signal for the EMAbrake; and a braking control unit for generating a braking force command signal for the EMAC, wherein the braking control unit and the EMAC are disposed together with the EMAbrake in a common line replaceable unit (LRU).
    Type: Grant
    Filed: November 26, 2014
    Date of Patent: April 16, 2019
    Assignee: Airbus Operations Limited
    Inventors: George Iordanidis, John Rees
  • Patent number: 10259582
    Abstract: An aircraft galley is provided, including a first galley unit that includes meal carts, cabinets and a countertop-height work area and a second galley unit that includes a countertop-height work area and a plurality of deployable crew seats and with the first galley unit defines a crew work/interaction area. A passenger interaction screen is positioned for viewing by passengers boarding the aircraft and passing through the galley into a passenger cabin. A plurality of lavatories are positioned in a like plurality of corners of the galley and having respective major walls positioned at an oblique angle to a longitudinal axis of the aircraft and with respective doors angled away from the crew work/interaction area.
    Type: Grant
    Filed: August 24, 2016
    Date of Patent: April 16, 2019
    Assignee: B/E Aerospace, Inc.
    Inventors: Ting-Yu Chen, Glenn Johnson
  • Patent number: 10252807
    Abstract: An ice protection system includes an aircraft surface and a gutter defined in the aircraft surface between raised rails. The gutter includes a mouth that narrows into a trailing portion of the gutter. The mouth is configured to channel water runback rivulets into the trailing portion of the gutter. The gutter can be a first gutter of a plurality of side by side gutters, each including a respective mouth narrowing into a respective trailing portion, wherein the gutters are separated from one another by respective rails.
    Type: Grant
    Filed: July 8, 2016
    Date of Patent: April 9, 2019
    Assignee: Goodrich Corporation
    Inventor: Tommy M. Wilson, Jr.
  • Patent number: 10239631
    Abstract: A system and method for an aircraft receptacle. The aircraft receptacle comprises an actuator connected to a number of latches and a tension spring connected to the number of latches. The actuator is part of an actuation system. The elastic member holds the number of latches in a disengaged position after failure of the actuation system.
    Type: Grant
    Filed: July 13, 2015
    Date of Patent: March 26, 2019
    Assignee: The Boeing Company
    Inventors: Brian Lewis, Bruce M. Whiteman, Christopher Mark Alley