Patents Examined by Galen L. Barefoot
  • Patent number: 6698690
    Abstract: A two layer door is provided. The first layer is made of a plurality of metallic members with a portion of the metallic members having one or more channels adapted to receive one or more armor panels. The second layer is made of the channels of the metallic members and armor panels disposed within the channels. The door also has one or more pivotally attached panels to the door that are adapted to open at a preselected pressure differential across the door. The door is also available as a kit.
    Type: Grant
    Filed: December 4, 2002
    Date of Patent: March 2, 2004
    Assignee: Alcoa Inc.
    Inventors: Miloslav Novak, Andrew B. Trageser, Russell S. Long, Jerri F. McMichael, Eric F. M. Winter, Kenneth B. Balazic
  • Patent number: 6698688
    Abstract: Apparatus and methods for actuating rotatable members are disclosed. In one embodiment, an assembly for actuating a rotatable member includes an extendible actuator having a first end and a second end, and a drive member having a first portion pivotally coupled to the second end, and a second portion non-pivotally coupled to the rotatable member. The second portion of the drive member is spaced apart from the first portion. The drive member further includes a third portion spaced apart from the first and second portions in a non-linear orientation. The assembly further includes a reaction link having an anchoring end pivotally coupled to the first end of the extendible actuator, and a driving end pivotally coupled to the third portion of the drive member.
    Type: Grant
    Filed: April 29, 2003
    Date of Patent: March 2, 2004
    Assignee: The Boeing Company
    Inventor: Kelly T. Jones
  • Patent number: 6695254
    Abstract: A tilting rotor of a convertible aircraft comprises, between the mast and the hub, a constant velocity drive mechanism and pivoting arrangement comprising two gimbals, each of which is driven by the mast and pivots about one respectively of two diametral axes by two diametrically opposite bearings. Each gimbal is also hinged to the hub by ball joint connections diametrically opposite and centred respectively in a radial plane passing through the axis of the mast and through the diametral axis about which the other gimbal pivots. The two resulting trains transmitting torque between the mast and the hub have substantially the same torsional rigidity, and one at least of the components of each torque transmission train exhibits a flexibility in deformation about the axis of rotation of the hub.
    Type: Grant
    Filed: February 28, 2003
    Date of Patent: February 24, 2004
    Assignee: Eurocopter
    Inventors: Elio Zoppitelli, Etienne Rampal
  • Patent number: 6695253
    Abstract: To fold/unfold blades of a rotor, at least one variable-length linear actuator is removably attached to two blades locked in the flight position. A first blade is unlocked, and the actuator is actuated to vary its length and bear against the other blade which remains locked. This causes the first blade to pivot about its pivot axis and move to a folded position where it is again locked. The other blade is then unlocked and the actuator once again actuated but this time bearing against the first blade. In this way the other blade pivots into the folded position where it is again locked. The two locked folded blades may be connected to each other by a link rod. Rotors with three blades, four blades, five and six blades can be folded/unfolded with only two actuators.
    Type: Grant
    Filed: February 27, 2003
    Date of Patent: February 24, 2004
    Assignee: Eurocopter
    Inventors: Michel Romani, Marcel Cayol
  • Patent number: 6695252
    Abstract: A missile or projectile tail section includes an outflow device and a number of deployable fins. The outflow device may be a base bleed device that includes a slow-burning propellant which fills the vacuum created by the projectile's motion through the air. Use of the outflow device may allow the projectile range to be extended by up to 20%. The fins are stowed canted relative to planes that include the axis of the tail section. By canting or tilting the fins relative to the axis of the tail section, increased space is made in the tail section for the outflow device. Although the fins are stowed canted relative to the tail section, they may be configured so as to be deployed such that the axis of the tail section is substantially within the planes of the fins.
    Type: Grant
    Filed: September 18, 2002
    Date of Patent: February 24, 2004
    Assignee: Raytheon Company
    Inventor: Richard Dryer
  • Patent number: 6695256
    Abstract: A cryogenic propellant depletion system for maximizing cryogenic propellant use in a space launch vehicle. The cryogenic propellant depletion system utilizes a plurality of pressure measurements to monitor one or more parameters of the cryogenic propellant in a feed line interconnecting a cryogenic propellant storage tank to the launch vehicle's engine. In this regard, the cryogenic depletion system includes a processor and supported logic to determine a head pressure supplied by the cryogenic propellant in the feed line and the mass of the cryogenic propellant in the feed line. The cryogenic depletion monitoring system is operative to determine these propellant parameters irrespective of a two-phase flow existing in the feed line. Finally, the system is configured to initiate engine shut down when at least one of the determined propellant parameters falls below a minimum threshold value.
    Type: Grant
    Filed: January 25, 2002
    Date of Patent: February 24, 2004
    Assignee: Lockheed Martin Corporation
    Inventors: Peter Zeender, Joseph Patrick Wurst
  • Patent number: 6691950
    Abstract: Device and system for the automatic control of a helicopter. The automatic control device (6) comprises a vertical objective law (A) in respect of the pitching axis, which automatically determines a control command (UT1) for operating the tilting of the disk of main rotor of the helicopter, a speed limitation law (B) for limiting the airspeed of the helicopter with respect to at least one limit value, detection means (10) for automatically detecting whether the airspeed reaches the limit value, and toggling means (11) for, in order to select the objective law (A, B) whose control command (UT1, UT2) is used for the pitching axis, automatically toggling from the first law (A) to the second law (B), when the detection means (10) detect that the airspeed has reached the limit value.
    Type: Grant
    Filed: September 27, 2002
    Date of Patent: February 17, 2004
    Assignee: Eurocopter
    Inventor: Marc Salesse-Lavergne
  • Patent number: 6685139
    Abstract: An emergency opening cylinder of a passenger door of an airplane is provided. An existing emergency opening cylinder is adapted at the lowest expenditures and with an insignificant increase in weight with respect to its operating characteristic to the load situation of an emergency opening of the door against the force of gravity. A ventilation bore of the emergency opening cylinder leads into a collecting chamber which has an outlet valve controllable by a control.
    Type: Grant
    Filed: December 16, 2002
    Date of Patent: February 3, 2004
    Assignee: Eurocopter Deutschland GmbH
    Inventors: Stefan Blum, Thomas Nickl, Wolfgang Spellmeier
  • Patent number: 6682021
    Abstract: The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic fluid flow over a surface. More specifically, the present invention provides a system and method to control aerodynamic or hydrodynamic fluid flow behavior of a ducted fluid flow using very-small-scale effectors. The system and method for actively manipulating and controlling fluid flow over a surface includes the placement of arrays of very-small-scale effectors on ducted surfaces bounding the ducted fluid flow. These very-small-scale effectors are actively manipulated to control the flow behavior of the ducted fluid flow and prevent flow separation within the primary fluid flow.
    Type: Grant
    Filed: April 5, 2002
    Date of Patent: January 27, 2004
    Assignee: Lockheed Martin Corporation
    Inventors: Philip P. Truax, Daniel N. Miller, Jeffrey W. Hamstra, Patrick J. Yagle
  • Patent number: 6682016
    Abstract: A thermal management system for an aircraft fuel system includes a plurality of fuel pressure sources. A spool valve is fluidly connected to the pressure sources and is movable between a plurality of positions in response to the pressure sources. An oil cooler is fluidly connected to the spool valve with fuel flowing through the spool valve to the oil cooler in response to the spool valve being in one of the positions. The fuel tank is fluidly connected to the spool valve with fuel flowing to the spool valve to the fuel tank in response to the spool valve being in another of the positions. The spool valve moves to a closed fuel tank output position response to the pressure sources. The spool valve includes a housing having a bore with the plurality of pressure inputs and oil cooler and fuel tank outputs fluidly connected to the bore. A spool is disposed within the bore and is movable axially relative thereto between oil cooler, open fuel tank and the closed fuel tank outward positions.
    Type: Grant
    Filed: September 5, 2002
    Date of Patent: January 27, 2004
    Assignee: Hamilton Sundstrand
    Inventor: George Peroulakis
  • Patent number: 6679452
    Abstract: Landing gear support assemblies and associated methods of installation. In one embodiment, a landing gear support assembly usable with an aircraft wing includes an aft trunnion support beam having a base portion, an aft trunnion support spaced apart from the base portion, and a shear center axis extending from the base portion toward the aft trunnion support. The aft trunnion support can be at least approximately vertically aligned with the shear center axis. The base portion can be configured to be attached at least proximate to the rear wing spar with a plurality of fuse pins configured to fail and release the aft trunnion support beam from the rear wing spar when the landing gear exerts a preselected force against the aft trunnion support.
    Type: Grant
    Filed: October 22, 2002
    Date of Patent: January 20, 2004
    Assignee: The Boeing Company
    Inventors: Justin D. Cottet, Michael J. Meneghetti, Brett D. Whitmer
  • Patent number: 6679457
    Abstract: A reaction wheel system is provided that includes at least two rotors. The first rotor is the primary rotor that provides the large output torques to the vehicle. The second rotor is a vernier control rotor. The primary rotor and vernier control rotor each rotate about a common axis. The vernier control rotor has an inertial mass that is less than the inertial mass of the primary rotor, and rotates independently of the primary rotor. Because the vernier control rotor can be rotated independently from the primary rotor, it can be used to significantly improve the performance of the reaction wheel system. Specifically, the vernier control rotor is used to provide relatively small output torques. These relatively small output torques can be used to reduce the disturbances created by motor ripple, provide precise torque output control and/or reduce the disturbances created by static friction.
    Type: Grant
    Filed: January 13, 2003
    Date of Patent: January 20, 2004
    Assignee: Honeywell International Inc.
    Inventors: Marc E. Meffe, Jack H. Jacobs
  • Patent number: 6679454
    Abstract: A radial sonobuoy launch system comprising a clam-shell launch tube and method for launching a sonobuoy. The clam-shell launch tube radially releases a sonobuoy and the clam-shell launch tube is reloaded during flight. The sonobuoys are pneumatically ejected about parallel to the airstream. A pressure boundary structure, having a door and a gate, maintains cabin pressure during reloading and launching. Support arms and drive arms evenly distribute the ejection accelerations from the firing mechanism and guide the trajectory of the sonobuoy during release. A clam-shell launch tube is capable of launching a multitude of differently sized sonobuoys.
    Type: Grant
    Filed: April 15, 2002
    Date of Patent: January 20, 2004
    Assignee: The Boeing Company
    Inventors: Mark L. Olsen, Jon W. Pitzer
  • Patent number: 6672543
    Abstract: Recovery of a towed body, in one embodiment in the form of a decoy which is initially stowed in a receptacle or canister and which is allowed to pay out behind an aircraft on a towing cable wrapped around a spindle, is accomplished by snaring or lassoing a portion of the towing cable and by dragging it to a further spindle which is driven so as to cause the lasso and a portion of the towing cable to wind up around the driven spindle. When a sufficient amount of the cable is wound around the driven spindle, the cable end secured to the canister is severed to allow all of the rest of the towing cable to be wound up. In one embodiment, a telescoping saddle or docking cradle is provided which extends from the canister to receive the retracted towed body so that it may be secured to the moving vehicle from whence it can be recovered, refurbished, and redeployed.
    Type: Grant
    Filed: December 20, 2001
    Date of Patent: January 6, 2004
    Assignee: BAE Systems Information and Electronics Systems Integration Inc.
    Inventors: Mark A. Carlson, James J. Jordan, John Russotti
  • Patent number: 6672540
    Abstract: A horizontal stabilizer actuator for a winged aircraft which is selectively pivotally controlled by a pilot or operator at a remote location in the aircraft and which has a primary load path responsive to the selective control by the pilot or operator for setting the pivoted position of the stabilizer and which has a secondary load path which is responsive to a failure in the primary load path to be automatically actuated to a condition locking the stabilizer in a fixed position.
    Type: Grant
    Filed: December 3, 2002
    Date of Patent: January 6, 2004
    Assignee: Rockwell Collins, Inc.
    Inventors: Milad A. Shaheen, Robert V. Dreher
  • Patent number: 6669144
    Abstract: Access apparatus including an access device including at least one of a door and a window, the access device including at least one openable element; and opening apparatus adapted to open the at least one openable element in a presence of a pressure difference of a predefined magnitude between opposite sides of the access device.
    Type: Grant
    Filed: November 26, 2002
    Date of Patent: December 30, 2003
    Assignee: Rav Bariach Security Products Ltd.
    Inventor: Eyal Artsiely
  • Patent number: 6669145
    Abstract: A fluid-motion-powered modulated reflector apparatus is provided that modulates the frequency of a reflected radiation signal. Passing the apparatus through a fluid such as air causes rotational velocity of a chopping wheel or, in some instances, a polarizing filter rotatably connected to propeller blades. The radiation signal is modulated by the blocking effect of a chopping wheel or a fixed polarizing filter and a rotating polarizing filter. The apparatus also can include a frequency selector to control the rotational velocity of the chopping wheel or rotatable polarizing filter. A fluid-motion-powered modulated reflector system may include an array of fluid-motion-powered modulated reflectors, each differently modulated by a frequency selector to allow a position sensor, such as a duo-lateral photodiode position sensing detector, and position determining system, to locate and determine the position of each individual retroreflector simultaneously.
    Type: Grant
    Filed: December 30, 2002
    Date of Patent: December 30, 2003
    Assignee: The Boeing Company
    Inventor: Samuel I. Green
  • Patent number: 6669139
    Abstract: According to the invention, in this aircraft, the elements of the inertial reference system are separated according to whether they are intended for navigation (CI) or flight control (5, 6, 7). The accelerometers (5 and 6) intended for flight control are arranged at a vibration antinode, while the gyrometers (7) dedicated to flight control are placed at a vibration node. The accelerometers (5 and 6) and the gyrometers (7) are connected to the flight control computer (12) and their measurements serve as flight control parameters.
    Type: Grant
    Filed: January 6, 2003
    Date of Patent: December 30, 2003
    Assignee: Airbus France
    Inventor: Fran├žois Kubica
  • Patent number: 6669143
    Abstract: A passenger seat movable from an upright to a recline position without encroaching on an aft-seated passenger, and including a seat base for being attached to a supporting surface. A unitary seating element is provided and includes a pair of laterally-spaced apart seat frames carried by the seat base, the seat frames defining a curved shape corresponding to the profile of an anatomically-appropriate seat bottom and seat back. A curved, semi-rigid diaphragm support is carried between the seat frames in alignment with the curved shape of the seat frames and mounted for movement relative to the seat frames between a first, upright position and a second, reclined position. A diaphragm is positioned under tension on the diaphragm support for providing a continuous seat bottom and seat back support surface for a seat occupant. Stretchers are attached to and extend between opposite sides of the diaphragm support for maintaining the diaphragm support in a spaced-apart condition with the diaphragm in tension.
    Type: Grant
    Filed: November 27, 2002
    Date of Patent: December 30, 2003
    Assignee: B E Aerospace, Inc.
    Inventor: Glenn A. Johnson
  • Patent number: 6666403
    Abstract: A force-generating device employing a flared body and a surrounding shroud to define a duct of axially diminishing flow area defining a nozzle for accelerating and directing the discharge of a fluid at a cambered vane, a pressure dam depends from the bottom surface of the vane to entrap a portion of the fluid flowing chordwise along the bottom surface of the vane. A deflector formed on the enlarged end of the flared body and extending into the duct fluid outlet deflects the fluid stream to increase its velocity and direct it toward the vane. In another embodiment, a second deflector formed on the rim of the shroud and projecting into the duct deflects the discharge stream to further increase the velocity of the fluid stream and increase the angle of attack of the fluid stream impinging on the vane. In an alternative embodiment, the first shroud is enclosed in a second shroud to form a second duct of axially diminishing flow area defining a nozzle.
    Type: Grant
    Filed: February 11, 2002
    Date of Patent: December 23, 2003
    Inventor: Robert E. Follensbee