Patents Examined by Tien Dinh
  • Patent number: 9567062
    Abstract: An aircraft including a fuselage having a forward portion and an aft portion with a propulsion system mounted within the aft portion of the fuselage. A burst zone is defined that extends outward from the propulsion system. The aircraft includes a box wing extending from the aft portion of the fuselage to a forward portion of the fuselage that is disposed outside of the burst zone.
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: February 14, 2017
    Assignee: United Technologies Corporation
    Inventors: Jesse M. Chandler, Gabriel L. Suciu
  • Patent number: 9567111
    Abstract: Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling.
    Type: Grant
    Filed: August 14, 2015
    Date of Patent: February 14, 2017
    Assignee: MACDONALD, DETTWILER AND ASSOCIATES
    Inventors: Paul Roberts, Gavin Hay, Jason White, Geoffrey Sprawson
  • Patent number: 9562584
    Abstract: An oleo-pneumatic shock absorber having a casing, a rod slidably mounted in the casing, first and second fluids in the casing, and a gauge. The gauge has a substrate positioned on the shock absorber. The substrate has a first region with a slot sized to fit an ultrasonic transducer arranged to encompass a range of possible oil levels within the shock absorber, a second region corresponding to a range of possible extension states of the shock absorber and a third region comprising one or more traces. Each trace corresponds to a temperature value and is indicative of an optimum relationship between the oil levels and the range of extension states at the respective temperature value associated with the trace.
    Type: Grant
    Filed: November 1, 2012
    Date of Patent: February 7, 2017
    Assignee: Safran Landing Systems UK LTD
    Inventor: Kyle Schmidt
  • Patent number: 9561871
    Abstract: An aerial vehicle docking system includes a landing pad and an aerial vehicle. The landing pad has a concave landing surface and a depression. The aerial vehicle has landing gear and a protrusion. The protrusion is shaped to mate with the depression. The protrusion and the landing gear are positioned on a bottom surface of the aerial vehicle.
    Type: Grant
    Filed: May 7, 2014
    Date of Patent: February 7, 2017
    Assignee: DEERE & COMPANY
    Inventor: Ramanathan Sugumaran
  • Patent number: 9561843
    Abstract: The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements rapidly inflated and rigidized using an acrylic adhesive and UV light generated by combustion, which find use, for example, in rapidly deploying and supporting the wing of an aerial vehicle and wind turbine towers.
    Type: Grant
    Filed: November 16, 2015
    Date of Patent: February 7, 2017
    Assignee: TUFTS UNIVERSITY
    Inventors: Alfram V. Bright, Richard Wlezien
  • Patent number: 9561846
    Abstract: A bias gain system for aircraft rudder comprises a pair of connector ends receiving an actuation force from a bias actuator. A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar as a function of the actuation forces from the bias actuators. A mechanism comprises links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.
    Type: Grant
    Filed: July 26, 2011
    Date of Patent: February 7, 2017
    Assignee: LEARJET INC.
    Inventors: Harris K. Butler, III, Mihalis Veletas
  • Patent number: 9561858
    Abstract: Described are a parafoil for operation at high altitudes, in low density air, or at low airspeeds, and methods for opening same. The parafoil comprises flexible members connected to the parafoil canopy. When the parafoil canopy is in a stowed configuration, the members are deformed, storing elastic energy. When the canopy is released from its stowed configuration, the members spring back to their undeformed shapes, thereby opening or assisting with opening the canopy. The flexible members may also be attached to a base structure, which is attached to the payload. The members may comprise rods or hollow tubes that can be flexed using a fulcrum near the base structure, or a spacer plate, so that the ends connected to the canopy are restrained by a parachute bag containing the stowed or packed canopy. The parachute bag can be opened prior to or during detachment of the parafoil from the flight vehicle.
    Type: Grant
    Filed: June 22, 2016
    Date of Patent: February 7, 2017
    Assignee: World View Enterprises Inc.
    Inventors: Jared Leidich, Taber Kyle MacCallum, Ty Bowen
  • Patent number: 9554552
    Abstract: A method and device for spraying dairy animals and in particular for spraying an udder region of dairy animals, including cows, during an at least partly or fully automatic milking process, includes providing a spray device mounted on a robot arm, the spray device including a spray nozzle with a spray opening, and a fluid channel feeding spray solution from an input port to the spray opening; pumping spray solution through the fluid channel towards the spray opening; heating the spray solution in a heating region of the fluid channel; and spraying the heated spray solution through the spray opening towards the udder region of the dairy animal.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: January 31, 2017
    Assignee: DeLaval Holding AB
    Inventors: Sten Mellberg, Henrik Olander
  • Patent number: 9555904
    Abstract: Gossamer apparatus and systems for use with spacecraft may include a deployable gossamer apparatus. The deployable gossamer apparatus may include a plurality rib members and gossamer material extending therebetween and may be configured in a stowed configuration and a deployed configuration. The rib members of the deployable gossamer apparatus store potential energy used for deployment of the deployable gossamer apparatus.
    Type: Grant
    Filed: August 9, 2013
    Date of Patent: January 31, 2017
    Assignee: ANALYTICAL MECHANICS ASSOCIATES, INC.
    Inventors: John Luther Abrams, Matthew Ernest Duchek
  • Patent number: 9550571
    Abstract: An accessible storage, rest, or work accommodation for an aircraft having a passenger cabin with a ceiling and a crown space above the ceiling, comprising: (a) a compartment in the crown space having at least one bunk; (b) an aperture in the passenger cabin ceiling, connecting the compartment to the passenger cabin; (c) a landing positioned below a floor of the compartment, below at least a portion of the aperture, inside the passenger cabin module; and (d) stairs or a ladder leading from the landing to a floor of the passenger cabin.
    Type: Grant
    Filed: June 27, 2014
    Date of Patent: January 24, 2017
    Assignee: The Boeing Company
    Inventors: Kim G. Ohlmann, Gregory J. Oakes, Anthony A. Harrington, Michael J. Olliges
  • Patent number: 9550559
    Abstract: Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has a flexible skin defining a first surface. The example apparatus also includes a flap movably coupled to the trailing edge. The flap defines a second surface. The first surface and the second surface form a substantially continuous surface when the flap is in a stowed position and when the flap is in a deployed position.
    Type: Grant
    Filed: July 8, 2013
    Date of Patent: January 24, 2017
    Assignee: The Boeing Company
    Inventors: Christopher K. Droney, Blaine K. Rawdon
  • Patent number: 9546008
    Abstract: Miniature release mechanisms constrain objects, such as deployables during the launch of space vehicles, such as small satellites and nanosatellites, and enable the release of the objects once a desired destination is reached by the space vehicle. Constraint and release of the objects are achieved by providing a secure threaded interface that may be released by the release mechanisms. The release mechanisms include a housing structure; a release block can include a threaded interface; one or more retracting pins; one or more release springs; a breakable link, such as a plastic link; a cable harness clamp; and a circuit board. The release mechanism can be 0.1875 inches (approximately 4.8 mm) thick.
    Type: Grant
    Filed: September 30, 2014
    Date of Patent: January 17, 2017
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Luis H. Santos Soto, Scott V. Hesh, John D. Hudeck
  • Patent number: 9540091
    Abstract: A high altitude lighter-than-air (LTA) system can include a zero-pressure balloon (ZPB) attached in tandem with one or more variable ballast air super-pressure balloons (SPB). The ZPB provides lift for the system while the SPB uses a centrifugal compressor to provide a variable amount of ballast air by pumping in or expelling out ambient air. A solar array coupled with an elongated ladder assembly can be coupled to a payload support for a payload carried by the LTA system. Various advanced performance targets relating to ascent rate, descent rate, range and maximum altitude are achievable with various scaled versions of the basic design of the LTA system. Advanced navigation and control techniques, such as efficient high altitude station-keeping approaches, are made possible with the LTA system.
    Type: Grant
    Filed: September 23, 2016
    Date of Patent: January 10, 2017
    Assignee: World View Enterprises Inc.
    Inventors: Taber Kyle MacCallum, Sebastian Padilla, Rodger Farley, Iain Beveridge, G. Ryan Lee, Tim Basta, Jared Leidich, John Straus, John Z. Maccagnano
  • Patent number: 9541364
    Abstract: An adaptive electronically steerable array (AESA) system comprises a plurality of arrays, each comprising a plurality of radiating elements, each array configured for placement on a forward-facing surface of a different one of a plurality of aerodynamic control surfaces on an interceptor. A plurality of radio frequency (RF) transmissive radome elements, each having an aerodynamic shape complementary to the aerodynamic control surface, are placed over one of the arrays. Control circuitry configures the arrays, independently or in concert, for RF target engagement and communication. Additional arrays may be positioned on side or aft-facing surfaces of the aerodynamic control surfaces for RF communication. The AESA system may be paired with an IR system for dual-mode operation.
    Type: Grant
    Filed: September 23, 2014
    Date of Patent: January 10, 2017
    Assignee: Raytheon Company
    Inventors: Andrew B. Facciano, Rodney H. Krebs, Michael S. Bielas, Cody D. Tretschok, Michael S. Spangler, Benjamin Mitchell
  • Patent number: 9540103
    Abstract: A vertical takeoff and landing aircraft includes rotors that provide vertical and horizontal thrust. During forward motion, the vertical lift system is inactive. A lift fan mechanism positions the fan blades of the aircraft in a collapsed configuration when the vertical lift system is inactive and positions the fan blades of the aircraft in a deployed configuration when the vertical lift system is active.
    Type: Grant
    Filed: June 24, 2014
    Date of Patent: January 10, 2017
    Assignee: Kitty Hawk Corporation
    Inventor: Geoffrey A. Long
  • Patent number: 9540098
    Abstract: A landing gear that comprises an axle (2) and a wheel (3, 3?). The wheel comprises a rim (4, 4?) mounted so as to rotate on the axle about a first axis of rotation (X), first blocks protruding from a lateral face (F, F?) of the rim, the first blocks being adapted to cooperate with a gearwheel (8) of a drive actuator (7) carried by the landing gear. The gearwheel is mounted rotatably about a second axis of rotation (Y) perpendicular to the first axis of rotation.
    Type: Grant
    Filed: October 2, 2014
    Date of Patent: January 10, 2017
    Assignee: MESSIER-BUGATTI-DOWTY
    Inventor: Nicolas Mazarguil
  • Patent number: 9533754
    Abstract: An aircraft comprises a wing assembly, a pod, and a pylon attaching the pod to the wing assembly. The pylon has a swept pylon flap, which is configured to unload the pylon and pod during flight of the aircraft, and also to create downward flow that counters a vortex trailing the pod.
    Type: Grant
    Filed: April 19, 2014
    Date of Patent: January 3, 2017
    Assignee: The Boeing Company
    Inventors: Stanley D. Ferguson, Ian J. Fialho, Richard C. Potter
  • Patent number: 9533768
    Abstract: An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.
    Type: Grant
    Filed: August 12, 2014
    Date of Patent: January 3, 2017
    Assignee: The Boeing Company
    Inventors: Sergey D. Barmichev, David W. Kirkbride, Mithra M. K. V. Sankrithi
  • Patent number: 9534540
    Abstract: An automatic emergency radar and proximity sensor activated protection system that could assist to prevent commercial, private, or military aircraft jet engines from being damaged or destroyed by the installment of a Shielding Blade Assembly which will immediately close when detection of objects such as; birds, debris, or other destructive elements try to enter through the engine intake while the aircraft is in FLIGHT causing the Internal Air Injection Unit (A.I.U.) to supply high volumes of air in order for the engine to stay operational and prevent it from stalling while in FLIGHT.
    Type: Grant
    Filed: April 30, 2014
    Date of Patent: January 3, 2017
    Inventor: Jose Antonio Tuero
  • Patent number: 9534563
    Abstract: A projectile for firing from a launcher includes a propulsion stage having non-axisymmetric boosters arranged about a longitudinal axis of the propulsion stage. The propulsion stage may further include a central booster about which the non-axisymmetric boosters are arranged.
    Type: Grant
    Filed: December 9, 2013
    Date of Patent: January 3, 2017
    Assignee: Raytheon Company
    Inventors: Andrew B Facciano, Juan Gonzalez, Robert T Moore, Michael S Alkema