Patents Examined by Galen Barefoot
  • In-flight refueling system, damping device and method for preventing oscillations in in-flight refueling system components
    Patent number: 7007894
    Abstract: An in-flight refueling system, damping device and method are provided for enhancing the stability of an elongate hose extending from a tanker aircraft during an in-flight refueling operation. The various embodiments of the system, device, and method provide a passive, integrated damping device that may generate electrical energy from changes in disposition of the elongate hose and then using the electrical energy generated to impart mechanical damping forces to a portion of the elongate hose. Thus, the embodiments may minimize the occurrence of oscillations in the elongate hose as it extends from the tanker aircraft during an in-flight refueling operation.
    Type: Grant
    Filed: September 21, 2004
    Date of Patent: March 7, 2006
    Assignee: The Boeing Company
    Inventors: John F. Takacs, Stephen M. Stecko
  • Insulating baffle for a floor shear truss
    Patent number: 7007892
    Abstract: An insulation baffle for a mobile platform. The baffle is secured to a structure separating different lobes of the mobile platform. The baffle includes a main body portion and at least one blow out portion. A perimeter of the blow out portion is defined by at least one recess. The recess also forms a web portion that connects the blow out portion with the main body portion. A depth of the recess is predetermined such that the web portion formed by the recess will sever when a pressure differential between the different lobes exceeds a predetermined threshold. When the web portion severs at least a section of the blow out portion separates from the main body portion to air to pass between the lobes so that the pressure differential is reduced to approximately zero.
    Type: Grant
    Filed: March 23, 2004
    Date of Patent: March 7, 2006
    Assignee: The Boeing Company
    Inventor: Gregory A. Tubbs
  • Turbojet designed to be fixed onto the AFT part of the fuselage of an aircraft, in upper position
    Patent number: 7007890
    Abstract: The turbojet according to the invention is designed to be fixed onto the upper part of the aft section of the fuselage of an aircraft using at least one coat hanger, the turbojet comprising a fan, a forward casing, an aft casing, accessories arranged around the periphery of the forward casing, the forward casing comprising attachment points, for the coat hanger. The attachment points are arranged so that the turbojet can be installed indifferently on either side of the aircraft fuselage, accessories being arranged on the casing so that they are accessible from the outside of the fuselage regardless of which side the installation is done.
    Type: Grant
    Filed: November 12, 2004
    Date of Patent: March 7, 2006
    Assignee: Snecma Moteurs
    Inventors: Bruno Beutin, Didier Yvon, Georges Mazeaud, Fabien Burdin
  • Flexible airfoils and method
    Patent number: 7007889
    Abstract: An airfoil for use in kites, movable wing aircraft and fixed wing aircraft has a straight spar inserted into a sleeve in the arcuate leading edge of a flexible wing panel. The resultant forces on the spar dynamically shape the airfoil. The airfoil is reinforced by battens between the leading edge and the trailing edge of the wing panel. Flight control is maintained through control lines warping the airfoil.
    Type: Grant
    Filed: June 15, 2004
    Date of Patent: March 7, 2006
    Inventor: Richard Charron
  • Flying body for firing from a tube with over-caliber stabilizers
    Patent number: 7004425
    Abstract: A missile to be fired from a barrel contains a tail, a tail sleeve attached to the tail, a stop element fixed to the tail sleeve, and a movable structural part disposed at the tail. Fin assembly wings are provided and are to be released from a subcaliber launch position to an overcaliber functional position by the movable structural part moving toward the stop element through a given distance. A pressure area is disposed between the tail end surface and the movable structural part. A propellant gas enters the pressure area during the firing of the missile, for moving the movable structural part away from the tail end surface against the stop element after firing. Bearing shafts are supported by the tail sleeve, the fin assembly wings are configured as a wrap around tail fin assembly held about the bearing shafts.
    Type: Grant
    Filed: February 6, 2003
    Date of Patent: February 28, 2006
    Assignee: Diehl Munitionssysteme GmbH & Co. KG
    Inventors: Shinichi Okada, Sadao Okawa, Masato Shinomiya, Makoto Mochizuki
  • Ice detection assembly installed on an aircraft
    Patent number: 7000871
    Abstract: Ice detection assembly (100) designed for installation on an aircraft, comprising a vibrating finger (110) and a mast (120), the vibrating finger (110) extending into the air from the mast (120) and capable of being vibrated by vibration means at a resonant frequency that is sensitive to an ice deposit on its surface, characterised in that it comprises a cooling system capable of cooling at least part of the detection assembly (100).
    Type: Grant
    Filed: December 3, 2003
    Date of Patent: February 21, 2006
    Assignee: Auxitrol S.A.
    Inventors: Cyril Barre, David Lapeyronnie, Gurvan Salaun
  • Apparatus and method for maneuvering objects in low/zero gravity environments
    Patent number: 6994296
    Abstract: An apparatus and method that make use of electromagnetic energy to maneuver an object, such as stop, slow, and/or divert a vessel or projectile in low and zero-gravity environments. The apparatus comprises an element capable of generating a magnetic field in the zero or low-gravity environment, and an object capable of electromagnetically interacting with the magnetic field so that the object's speed and/or trajectory is altered when moving in proximity to the magnetic-field generating element. As such, the method entails maneuvering an object in a zero or low-gravity environment by generating a magnetic field in the zero or low-gravity environment, and then moving the object in proximity to the magnetic field such that the magnetic field alters the trajectory and/or speed of the object.
    Type: Grant
    Filed: June 9, 2004
    Date of Patent: February 7, 2006
    Inventor: Peter J. Schubert
  • Method and apparatus for controlling a vehicle
    Patent number: 6994297
    Abstract: A method of controlling movement of a vehicle including generating a fluid jet adjacent an aerodynamic surface of the vehicle, and changing at least one of a strength and a position of a shock wave traveling over the aerodynamic surface of the vehicle by directing the jet into a boundary layer flow of air attached to the aerodynamic surface.
    Type: Grant
    Filed: October 27, 2004
    Date of Patent: February 7, 2006
    Assignee: The Boeing Company
    Inventors: Ahmed A. Hassan, Garry Billman
  • Push release loop
    Patent number: 6988694
    Abstract: The invention is a device that push releasably retains one end of a rope (111) abutting against an intermediate part of the rope (103) to form a push releasable loop.
    Type: Grant
    Filed: May 14, 2003
    Date of Patent: January 24, 2006
    Assignee: Nalu Kai Incorporated
    Inventors: Christopher Carswell Barrs, Donald Lewis Montague, Alexander Pouchkarev
  • Aircraft control system
    Patent number: 6986486
    Abstract: This invention control system having: means (12) for detecting an irregularity in aircraft handling during flight; means (18) for causing temporarily a rigid body excitation in at least a portion of the aircraft; means (20) for monitoring an actual response to the excitation; means (22) for comparing the actual response and a target response to the rigid body excitation; and means (14) responsive to an output from the comparison means for determining the need for a modification of the current flight plan and for generating a corresponding control output. The invention also provides a corresponding method for controlling an aircraft.
    Type: Grant
    Filed: March 8, 2001
    Date of Patent: January 17, 2006
    Assignee: BAE Systems plc
    Inventor: Ian Thomas Darbyshire
  • VTOL aircraft external load drag reduction system
    Patent number: 6986484
    Abstract: A drag reduction system extends from an underside of a VTOL aircraft forward of a four-point sling system. The four-point sling system carries an external load close to an underside of the airframe and oriented along the aircraft longitudinal axis. The drag reduction system includes a retractable shield mounted beneath the underside of the aircraft which reduces drag of the external sling load and reduces the airloads on the external load.
    Type: Grant
    Filed: April 30, 2004
    Date of Patent: January 17, 2006
    Assignee: Sikorsky Aircraft Corporation
    Inventor: Mark Winfield Scott
  • Inertial reference system for an aircraft
    Patent number: 6986483
    Abstract: An inertial reference system for an aircraft includes two accelerometers and a gyrometer. One accelerometer is located at a front portion of the aircraft, the other is located at a rear portion of the aircraft. The gyrometer is located at a center portion of the aircraft. The system also includes a control computer linked to the accelerometers and to the gyrometer. The center portion can include the aircraft's center of gravity.
    Type: Grant
    Filed: November 17, 2003
    Date of Patent: January 17, 2006
    Assignee: Airbus France S.A.S.
    Inventor: Francois Kubica
  • Method and spoiler system for ensuring the aerodynamic continuity of the upper surface of an aircraft
    Patent number: 6981676
    Abstract: Method and spoiler system for ensuring the aerodynamic continuity of the upper surface of an aircraft wing. According to the invention, the spoiler 7 has a chord (C) of adjustable length and means (16, 19, 20) are provided for acting on the length of said chord when said spoiler (7) is in the retracted position.
    Type: Grant
    Filed: September 21, 2004
    Date of Patent: January 3, 2006
    Assignee: Airbus France
    Inventor: Jérôme Milliere
  • Active drag and thrust modulation system and methods
    Patent number: 6978767
    Abstract: A vehicle traveling through an environmental media such as air experiences drag. The drag is actively modulated by energy beams which may either increase or decrease the drag. The energy beams may provide either a chemical, acoustic or electromagnetic energy at a transition region between turbulent and laminar flows or at the leading edge of a laminar flow or in the direction of a crosswind in order to facilitate the respective increase or decrease in drag. If the vehicle is a sailing ship, areas of the sails are selectively roughened or widened to enhance the thrust derived from the wind. Furthermore, the keel or hull of the sailing ship may be modified to improve the hydrodynamic characteristics of the sailing ship. If the vehicle is an automobile, the tires or road surface may be selectively heated to improve the traction of the automobile.
    Type: Grant
    Filed: July 16, 2004
    Date of Patent: December 27, 2005
    Assignee: Bonutti IL, LLC
    Inventor: Peter M. Bonutti
  • Methods and apparatuses for controlling airflow proximate to engine/airfoil systems
    Patent number: 6978971
    Abstract: Methods and apparatuses for controlling airflow proximate to engine/airfoil systems are disclosed. In one embodiment, an aircraft system includes an airfoil and an engine unit at least proximate to the airfoil with a gap between a portion of the airfoil and a portion of the engine unit. The system can further include a flow control device proximate to the gap and positionable among at least three stationary positions, including a retracted position in which the gap has a first area through which fluid can flow, a first extended position in which the gap is at least approximately aerodynamically sealed, and a second extended position in which the gap has a second smaller area through which fluid can flow. A control system can be coupled to the flow control device to move the flow control device among these positions.
    Type: Grant
    Filed: June 15, 2004
    Date of Patent: December 27, 2005
    Assignee: The Boeing Company
    Inventor: Roy Dun
  • Cockpit door of aircraft
    Patent number: 6976658
    Abstract: A cockpit door comprises a hinge 20 provided to one surface and a latch device provided to the other side that can be operated only from the cockpit side. To the inside of a door panel is disposed a reinforcement member 110 formed by laminating multiple layers of sheets with thermoplastic adhesives, the sheets formed by laminating aromatic polyamide fiber onto a honeycomb panel and processing the same into sheet form. A titanium alloy reinforcement plate 400 is disposed to cover the gap G1 between the door body and flap 60. Mounting portions 150 and 160 are provided to the rim of the reinforcement member body 110, and rivet holes 180 are provided thereto. The mounting portion is bent 90 degrees and fixed to the frame by rivets.
    Type: Grant
    Filed: December 30, 2003
    Date of Patent: December 20, 2005
    Assignee: Jamco Corporation
    Inventors: Yasuo Sekikawa, Toshihisa Kasuya, Tadashi Watanabe
  • Method for controlling the flight of an aircraft
    Patent number: 6976656
    Abstract: A method for controlling an aircraft includes the steps of receiving acceleration data related to an acceleration of a front portion of the aircraft, and receiving pitch, roll, and/or yaw rate data related to a rate of a center portion of the aircraft. The method also includes a step of generating a pitch, roll, and/or yaw command based on the acceleration data and on the rate data.
    Type: Grant
    Filed: November 18, 2003
    Date of Patent: December 20, 2005
    Assignee: Airbus France S.A.S.
    Inventor: Francois Kubica
  • Deployment system for a moveable wing surface
    Patent number: 6974112
    Abstract: A deployment system for deploying a moveable wing surface (22) from a main wing section (8). The deployment system includes a plurality of swing arm assemblies (24,26) connecting the moveable wing surface (22) to the main wing section (8) and a drive means for deploying and retracting the moveable wing surface (22), wherein at least one of the swing arm assemblies (24,26) includes a swing arm (28) pivotably connected to the main wing (8) and a connector mechanism (34) for connecting the movable wing surface (22) to the swing arm (28).
    Type: Grant
    Filed: June 16, 2004
    Date of Patent: December 13, 2005
    Inventor: Michael Craig Broadbent
  • Spacecraft docking mechanism
    Patent number: 6969030
    Abstract: The present invention provides a docking mechanism that is capable of interfacing with Apogee Boost Motors (ABM) including Liquid Apogee Motors (LAM) of the satellite being captured to allow a servicing spacecraft to dock with a satellite that has no special docking features. The docking mechanism includes a compliant probe with spring-loaded fingers at its tip which is inserted into the LAM by the approach motion of the servicer spacecraft. When the probe tip has passed beyond the throat of the LAM the finger extend to trap the LAM on the probe thus achieving capture. The rigidization stage of docking is achieved by retracting the probe to pull the two spacecraft together. The docking mechanism includes abutment pads which interface with the launcher interface ring of the client spacecraft.
    Type: Grant
    Filed: July 14, 2004
    Date of Patent: November 29, 2005
    Assignee: Macdonald Dettwiler Space and Associates Inc.
    Inventors: Howard Martin Jones, Pat Malaviarachchi, Andrew Charles MacKenzie Allen, Mariano Ficocelli, Geoffrey William Frederick Sprawson
  • Nacelle chine installation for drag reduction
    Patent number: 6964397
    Abstract: An apparatus and a method for reducing drag over an aircraft wing assembly in operational angle of attack situations are disclosed. The aircraft wing assembly includes a wing and an engine nacelle mounted to the wing. A nacelle chine is mounted on an outboard side of the engine nacelle, and the nacelle chine is configured to reduce drag by redirecting at least a portion of fluid striking a forward end of the aircraft wing assembly such that a vortex is formed over the forward end of the aircraft wing assembly. The chine is coupled to a mounting base configured to be secured to an outer surface of the engine nacelle at a mounting position along an outer surface of the engine nacelle.
    Type: Grant
    Filed: July 18, 2003
    Date of Patent: November 15, 2005
    Assignee: The Boeing Company
    Inventor: Christopher A. Konings