Patents Examined by Jamie S Stehle
  • Patent number: 9845150
    Abstract: A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.
    Type: Grant
    Filed: February 11, 2013
    Date of Patent: December 19, 2017
    Assignee: Kitty Hawk Corporation
    Inventor: Ilan Kroo
  • Patent number: 9126693
    Abstract: Systems, methods, and devices are provided for assisted takeoff of an aerial vehicle. The aerial vehicle may takeoff using a first control scheme and switch to a second control scheme for normal flight when a takeoff threshold is met. The first control scheme optionally does not use integral control while the second control scheme may use integral control. The aerial vehicle may determine that a takeoff threshold is met, based on an output to a motor of the aerial vehicle and/or an acceleration of the aerial vehicle.
    Type: Grant
    Filed: April 21, 2014
    Date of Patent: September 8, 2015
    Inventors: Jun Shi, Xu Yang Pan
  • Patent number: 9096315
    Abstract: An apparatus for recovering kinetic energy released during and aircraft landing after ground contact, for ground and/or flight operation, comprising at least one energy converter for conversion of the kinetic energy into another energy form, where the energy converter is located in the area of the nose landing gear and/or in the area of the main landing gear of the aircraft. At least one energy storage system is provided for receiving and releasing at least a part of the converted kinetic energy. The apparatus has a high degree of multiple utilization and enables, for example, maneuvering of a landed aircraft on the taxiway independently of the engines, where the aircraft is substantially moved with the braking energy recovered during the landing process. Since the main engines are no longer required for maneuvering, there is a considerable potential for saving energy and the use of motor-operated tow vehicles is eliminated.
    Type: Grant
    Filed: September 4, 2012
    Date of Patent: August 4, 2015
    Assignee: Airbus Operations GmbH
    Inventor: Christian Seibt
  • Patent number: 9096325
    Abstract: According to one embodiment, a method of managing pilot and copilot control of engine power in an aircraft includes receiving, from a first pilot input device, a first signal representative of a pilot selection of an increase power position or a decrease power position and receiving, from a second pilot input device, a second signal representative of a pilot selection of an increase power position or a decrease power position. One of the first signal and the second signal is prioritized. An aircraft engine is then instructed to change power output based on the prioritized signal.
    Type: Grant
    Filed: November 18, 2013
    Date of Patent: August 4, 2015
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Erik Oltheten, James M. McCollough, Peter F. Scheidler, Jeffery S. Greenwood
  • Patent number: 9090327
    Abstract: An intermediate support structure for the cockpit of an aircraft is provided. The intermediate support structure includes a raised floor and at least one structural element extending as an arch above the raised floor, the arched structure being adapted to hold in position at least one item of equipment in the upper part of the cockpit. The intermediate support structure also includes a fastener for mounting the intermediate support structure onto a fuselage primary structure, where the fuselage primary structure defines a portion of the cockpit of the aircraft.
    Type: Grant
    Filed: July 3, 2012
    Date of Patent: July 28, 2015
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Marc Tomasi, Patrick Lieven, Romain Delahaye
  • Patent number: 9056684
    Abstract: An aircraft includes a heat absorbent material carried by an airfoil susceptible to ice buildup and a transmitter spaced apart from the heat absorbent material. A method includes the process of transmitting the heat energy from the transmitter to the heat absorbent material that in turn warms the airfoil to break apart ice buildup.
    Type: Grant
    Filed: March 16, 2012
    Date of Patent: June 16, 2015
    Assignee: Textron Innovations Inc.
    Inventors: James M. McCollough, Roger Aubert
  • Patent number: 9027883
    Abstract: A shock control fairing for mounting a junction between adjoining aircraft surfaces. The fairing has a cross-sectional profile which varies along the length of the fairing. The cross-sectional profile of the fairing has a maximum area at a location which, when mounted to an aircraft, is substantially proximal to a location on the surface of the aircraft at which a shock would be expected to develop without the fairing.
    Type: Grant
    Filed: November 5, 2008
    Date of Patent: May 12, 2015
    Assignee: Airbus Operations Limited
    Inventor: Neil John Lyons
  • Patent number: 9022318
    Abstract: A hydraulic drive for an aircraft includes: a gear, a first hydraulic pump and a second hydraulic pump, wherein the gear is installed in a gear housing and wherein the first hydraulic pump and the second hydraulic pump in each case are installed in a pump housing that is affixed to the gear housing, or the two together are installed in a pump housing that is affixed to the gear housing; a hydraulic supply device including a first and a second hydraulic system for operating actuators of the aircraft; and a monitoring and drive device, with the hydraulic supply device including a first hydraulic drive for coupling the latter to a first engine, and a second hydraulic drive for coupling the latter to a second engine, wherein each hydraulic drive includes: a gear drive shaft for coupling the respective hydraulic drive to an engine output shaft of the respective associated engine; two hydraulic pumps that are coupled to a gear output shaft, in each case with a connection device for connecting the hydraulic pump to
    Type: Grant
    Filed: September 17, 2008
    Date of Patent: May 5, 2015
    Assignee: Airbus Operations GmbH
    Inventor: Juergen Laude
  • Patent number: 9010681
    Abstract: A supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame, the beam and the half-frame being formed of composite materials. The half frame has an open section, and the half-structure defines a structure selected from the group consisting of: the beam and the front half-frame form a one-piece part; the beam has an extension with an open section, the shape of which matches that of the front half-frame, the extension being attached to the half frame; and the front half-frame has an extension with an open shape, the shape of which matches the beam, wherein the extension is attached to the beam.
    Type: Grant
    Filed: October 29, 2012
    Date of Patent: April 21, 2015
    Assignee: Aircelle
    Inventors: Alexandre Bellanger, Florent Bouillon, Laurent Dubois
  • Patent number: 8998125
    Abstract: A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft.
    Type: Grant
    Filed: June 15, 2010
    Date of Patent: April 7, 2015
    Assignee: Textron Innovations Inc.
    Inventors: Charles Hollimon, Dudley E. Smith, David Ludolph
  • Patent number: 8991741
    Abstract: There is described a convertiplane comprising: a pair of semi-wings; at least two rotors which may rotate about relative first axes and tilt about relative second axes together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and being, in use, substantially parallel to longitudinal direction in aeroplane mode; convertiplane further comprises at least two through openings within which said rotor may tilt, when said convertiplane moves, in use, between said helicopter and said aeroplane mode.
    Type: Grant
    Filed: July 27, 2012
    Date of Patent: March 31, 2015
    Assignee: Agustawestland S.p.A.
    Inventor: James Wang
  • Patent number: 8979036
    Abstract: Disclosed is a vertical rudder control system for an aircraft. The system is comprised of a rudder trim compensation generator that is configured to generate a rudder trim compensation order to set the position of the rudder bar of the aircraft to a neutral position in which the rudder bar is controlled with nil (i.e., zero) pilot effort. The vertical rudder control system includes a flight control calculator for calculating rudder control orders to maintain the nil effort rudder bar position, with the calculation of the rudder control orders being based on a sum of the rudder bar position, determined by a detection unit, and the rudder trim compensation order. The rudder control orders are received by a rudder operating unit, which is used to deflect the vertical rudder by a deflection value based on the rudder control orders.
    Type: Grant
    Filed: September 14, 2012
    Date of Patent: March 17, 2015
    Assignee: Airbus Operations SAS
    Inventors: Patrice Brot, Pierre Fabre
  • Patent number: 8973860
    Abstract: A method, apparatus, system, and computer system to facilitate aerial recovery of an air vehicle are disclosed. In various embodiments, a drogue is established in a drogue recovery orbit and an air vehicle is recovered with the drogue. Establishment of the drogue in a drogue recovery orbit may include establishment of a mothership in a mothership recovery orbit or actuating control surfaces on the drogue. Recovering the air vehicle may include maneuvering the drogue and the air vehicle in a cooperative manner to facilitate recovery of the air vehicle or utilizing a homing device on the drogue to guide the air vehicle. The various techniques disclosed may be modified to compensate for wind.
    Type: Grant
    Filed: October 30, 2012
    Date of Patent: March 10, 2015
    Assignee: Brigham Young University
    Inventor: Randal W. Beard
  • Patent number: 8973869
    Abstract: A landing gear retraction/extension device includes a hydraulic actuator, a hydraulic circuit, a hydraulic pump, an electric motor, and a driver. Part of the hydraulic circuit is provided such that heat is exchangeable between operation oil and each of the electric motor and the driver. The driver supplies power to the electric motor before landing of an aircraft such that an operation oil temperature is higher than a predetermined temperature upon the landing of the aircraft.
    Type: Grant
    Filed: September 14, 2012
    Date of Patent: March 10, 2015
    Assignee: Sumitomo Precision Products Co., Ltd.
    Inventors: Yasuto Onomichi, Taku Kondo, Shogo Hagihara, Ryo Takaki, Takaaki Onishi
  • Patent number: 8960609
    Abstract: An airfoil tip vortex mitigation device comprising an intake port disposed in a first surface of an airfoil and an exit port in fluid communication with the intake port and disposed in a second surface of the airfoil where air pressure is less than at the first surface when the airfoil is producing lift. The channel and exit port are positioned and configured to direct diverted air in such a way as to weaken an airfoil tip vortex that's produced by the airfoil when the airfoil is producing lift.
    Type: Grant
    Filed: December 15, 2011
    Date of Patent: February 24, 2015
    Assignee: Lockheed Martin Corporation
    Inventors: Perry Wooden, Ruble E. Moor, Eric F. Charlton, Daniel N. Miller, Edwin L. Blosch, Jeffrey J. Azevedo
  • Patent number: 8939398
    Abstract: The invention relates to an engine assembly for aircraft in which the coupling device comprises a fore aerodynamic structure having a cradle equipped with an aerodynamic cowling, the cradle being hinge mounted on the air intake of the engine, and the fan cowls being mounted to move on the cradle so as to be able to occupy an open position as well as a closed position in which they are supported by the air intake and by a thrust reverser. According to the invention, when the cowls are in open position, the cradle adopts a first configuration in which its aft end rests on a span of the engine mounting structure, and when the cowls are in closed position, the cradle, borne by said cowls, adopts a second configuration in which it is lacking any direct mechanical link with the other elements of the engine mounting structure.
    Type: Grant
    Filed: July 25, 2012
    Date of Patent: January 27, 2015
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Benoit Letay, Andrés Toro, Adrien Venet
  • Patent number: 8915467
    Abstract: The disclosure relates to Aeronautics, more particularly relating to wing planforms that reduce wing drag substantially in aircraft driven by propellers or other rotors in tractor configuration. An aircraft comprising a wing and propeller system (1), said system comprising wing planform (2) characterized into wing chord regions (3) behind each propeller/rotor (5) whose length is relatively varied with respect to length of wing chord regions (4) at outboard of the propeller/rotor (5) towards wing tip and/or at inboard of the propeller (5) towards fuselage, and plurality of propellers (5) fixed ahead of wing leading edge such that induced drag is reduced by exploiting the velocity field generated by the slipstream of the propeller (5). Also, provides for a method of optimizing wing and propeller system and a method reducing induced drag, among other possible parameters of interest.
    Type: Grant
    Filed: July 5, 2010
    Date of Patent: December 23, 2014
    Assignee: Jawaharlal Nehru Centre for Advanced Scientific Research
    Inventors: Roddam Narasimha, Suresh Madhusudan Deshpande, Chandrashekarappa Praveen, Belur Raghavan Rakshith
  • Patent number: 8882048
    Abstract: A processing and delivery system is in space around a celestial body having a magnetic field. The system includes at least one facility having supplies and configured for in-space recycling and manufacturing to produce processed objects utilizing space debris objects and the supplies. The system includes at least one space vehicle configured to deliver the space debris objects from their orbits to the at least one facility using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver new supplies to the at least one facility from other orbits using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver the processed objects from the at least one facility to their destination orbits using electrodynamic propulsion.
    Type: Grant
    Filed: May 20, 2011
    Date of Patent: November 11, 2014
    Inventors: Eugene M. Levin, Joseph A. Carroll, Jerome Pearson
  • Patent number: 8864072
    Abstract: A structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection.
    Type: Grant
    Filed: May 12, 2011
    Date of Patent: October 21, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Jens Telgkamp, Wolfgang Schulze, Thomas Kruse
  • Patent number: 8844896
    Abstract: Gimbal system, including method and apparatus, for mounting a gimbal apparatus to a support platform with a mount assembly. The mount assembly may include first and second bar assemblies that are rotationally coupled to each other by a pair of gears.
    Type: Grant
    Filed: June 7, 2011
    Date of Patent: September 30, 2014
    Assignee: FLIR Systems, Inc.
    Inventor: Daniel Pettersson