Patents Examined by Theresa M. Wesson
  • Patent number: 6450442
    Abstract: An impulse radar guidance system and method for use with a spinning projectile. The system and method tracks the flight of the spinning projectile using an all-weather radar or tracker. A linearly polarized asymmetric waveform is transmitted at the projectile that comprises a series of repeating pulses having a relatively strong, short, positive electric field pulse followed by a relatively weak, long, negative electric-field baseline. The projectile contains a dipole antenna having a switching diode disposed between respective halves thereof.
    Type: Grant
    Filed: September 30, 1997
    Date of Patent: September 17, 2002
    Assignee: Raytheon Company
    Inventors: Arthur J. Schneider, James G. Small
  • Patent number: 6186039
    Abstract: A spacecraft launch system includes a support assembly and a seat coupled to a hinge having a hinge axis. In operation, the support assembly and the seat rotate about the hinge axis to move the spacecraft from a horizontal position to a vertical position for launching. The launch system may incorporate an alignment technique that includes alignment members and actuators.
    Type: Grant
    Filed: February 25, 1998
    Date of Patent: February 13, 2001
    Assignee: Kistler Aerospace Corporation
    Inventors: George E. Mueller, Aaron Cohen, Dale D. Myers, Henry O. Pohl
  • Patent number: 6123289
    Abstract: An aerodynamic device, such as a projectile includes an elongated forebody, and an aft section secured to the forebody. The aft section acts as a d control device, and includes a connecting member that extends integrally in a conically shaped flared section, for generating a lift force to help stabilize the projectile during forward flight. The aft section further includes a flange that extends from the flared section, and that provides velocity decay and optimal drag, in order to limit the projectile flight and descent within a predetermined safety or emergency range. The flared section is defined between an innermost edge positioned adjacent to the connecting member, and an outermost edge positioned adjacent to the flange.
    Type: Grant
    Filed: April 20, 1998
    Date of Patent: September 26, 2000
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Leon Manole, William Rice, Stewart Gilman, John Dineen, Frank Renner, Mark Young, Anthony Farina
  • Patent number: 6119573
    Abstract: Carbon fiber material and carbon fiber material that is saturated with hydrocarbon solid-liquid phase change material may be used as thermal management materials for providing a thermally conductive interface between a heat source and its housing. Such carbon fiber material may also be used for mechanical isolation of the heat source from its housing. Carbon fibers used in the carbon fiber material may be unidirectionally oriented to provide for low friction, thus optimizing critically controlled friction tolerances. Additionally the carbon fiber material saturated with hydrocarbon solid-liquid phase change material may be used to transfer heat into the an inherently nonconductive medium.
    Type: Grant
    Filed: January 27, 1997
    Date of Patent: September 19, 2000
    Assignee: Raytheon Company
    Inventors: Thomas J. Berens, David W. Campbell, Peter J. Drake, Timothy R. Knowles, Timothy B. Mellor
  • Patent number: 6112667
    Abstract: A mine placement system is provided for determining mine launch parameters ased on launcher vehicle position, speed, and direction and on latitude. The system includes an input module for receiving launcher vehicle position, speed, and direction having a settable aim point. The input module is connected to a processor module which continuously calculates the trajectory of the mine as the launch ship maneuvers. The processor module having a vectorizer, a decoder, a time processing unit and gyroprocessing unit drives a launch display having steering cursors and a range display. The steering cursors and range display provide maneuver information to the ship's operator to steer the ship to a launch window which will allow a mine to deploy to the set aim point. In addition to displaying the set aim point, the display also shows the present actual mine placement point based on the launch ships present location and velocity. Whenever a mine is launched, the system records the actual mine placement point.
    Type: Grant
    Filed: December 15, 1997
    Date of Patent: September 5, 2000
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Vernon P. Bailey, Edward J. Hilliard, Jr.
  • Patent number: 6085630
    Abstract: The construction and arrangement of the projectile bearing surface interfaces rearward and forward of a recessed surface chamber of the projectile interface conjointly with the interfaces of bore wall areas segmented by recessed bore chambers which in conjunction effect the deployment/transport/dispersement/development/modulation and transformation of explosive propellant charges sequentially primed and activated rearward and forwardly of the projectile along the bore and in bore wall chambers captively converting high static gas pressure to expansively relieved dynamic propellant gas pressure directly at the projectile reducing firearm barrel recoil while energizing projectile movement along the bore in a closed-system of thermodynamic propellant energy for free flight purposes.
    Type: Grant
    Filed: August 26, 1998
    Date of Patent: July 11, 2000
    Inventor: John R. Manis
  • Patent number: 6082679
    Abstract: An active control method and apparatus for encouraging the early destruction of trailing vortices formed by a lifting body having at least two control surfaces on each side and creating multiple vortex pairs is provided. The method includes actuating the control surfaces in a manner leading to the direct excitation of one or more of the Transient Growth Mechanism, the Short Wavelength Instability, the Long Wavelength Instability, and the Crow Instability to result in the accelerated breakup of the trailing vortices.
    Type: Grant
    Filed: November 5, 1997
    Date of Patent: July 4, 2000
    Assignee: The Boeing Company
    Inventors: Jeffrey D. Crouch, Philippe R. Spalart
  • Patent number: 6079669
    Abstract: A dual pivot expandable lavatory for use in limited spaces such as on an airplane. The lavatory may be positioned proximate the doorway area of the airplane, and is provided with a primary and a secondary pivotable module. Each module is pivotably attached to a stationary assembly conventionally affixed to the ceiling and floor of the airplane. During take-off and landing both modules are locked, by means of a locking system, in a stowed position within the stationary assembly. During routine flight, the locking system is unlocked and both modules are pivoted into a deployed position within the doorway area. A flight attendant's seat may be affixed to the exterior of the primary module. If the seat is used, an additional support foot is affixed to the primary module to accommodate the additional loading on the lavatory.
    Type: Grant
    Filed: March 24, 1997
    Date of Patent: June 27, 2000
    Assignee: The Boeing Company
    Inventors: James J. Hanay, Richard J. Laconte, Allan B. Lewis, William C. Quan, Peter J. Arnold
  • Patent number: 6079666
    Abstract: In a missile which employs a terminal homing seeker and a proportional navigation guidance law the space rate of change of boresight error, i.e., the boresight error slope, is one of the predominant error sources.It has been found that the boresight error slope is proportional to the curvature of the seeker open loop transfer characteristic. Accordingly, the boresight error slope sensor senses the curvature of the seeker open loop transfer characteristic. This is accomplished by intermittently dithering the seeker instantaneous field-of-view about the line of sight at a rate too great for the normal tracking loop to respond. Thus the open loop transfer characteristic is obtained while leaving the normal tracking loop unperturbed. The curvature of the open loop transfer characteristic is then obtained in real time by computing the "second differences" from the measured open loop transfer characteristic.
    Type: Grant
    Filed: April 25, 1986
    Date of Patent: June 27, 2000
    Inventor: Alton B. Hornback
  • Patent number: 6065384
    Abstract: The present invention relates to weapon systems that accelerate projectiles using gases generated by the rapid combustion of a solid propellant, in particular, such a weapon system is able to vary the barrel exiting velocity of the projectile through a barrel venting means. In one embodiment, a front venting means exhausts gas generated by combusting propellant from behind the accelerating projectile and redirects a portion of the exhausted gas either to at least one fixed volume, to the front of the projectile, or to a combination of at least one fixed volume and to the front of the projectile. Redirecting some of the exhausted gas to the front of the projectile restrains the projectile, thereby slowing the projectile, and thus further decreasing the muzzle velocity of the projectile. In another embodiment, gas from behind the projectile is exhausted into a fixed volume, thereby decreasing projectile acceleration, and thus, the muzzle velocity of the projectile.
    Type: Grant
    Filed: November 10, 1997
    Date of Patent: May 23, 2000
    Assignee: Widlin Corporation
    Inventors: Jeffrey Michael Widder, Roger Allen Sherman, Steven Vance Medlin
  • Patent number: 6058847
    Abstract: A mine neutralisation vehicle comprises a first portion to which propulsion units are attached by which propulsion units the vehicle is positioned. Pivotally connected to the first section is a second section containing a shaped charge warhead. By means of the pivot connection the shaped charge can be directed at a mine, for example a buried mine, while the main body of the vehicle is maintained in a horizontal direction.
    Type: Grant
    Filed: July 10, 1998
    Date of Patent: May 9, 2000
    Assignee: GEC-Marconi Limited
    Inventor: Richard Adams
  • Patent number: 6047926
    Abstract: This invention overcomes the disadvantage of the prior systems and produces a high velocity specially formed and constituted pressure aerodynamic stream system for efficiently and effectively removing ice from an aircraft. The specially formed stream system includes a stream within a stream, wherein a deicing fluid such a glycol is entrained within and encased by a surrounding jacket of entraining fluid such as air. This deicing is now known as coaxial stream/stream within a stream deicing. The special nozzle allows the stream to maintain fluid separation over its flight path so that aircraft contact is made by to be known as coaxial stream/stream within a stream deicing. The coaxial stream/stream within a stream deicing is further enhanced by pressurizing the stream to deliver the stream as a high pressure, high velocity stream to improve the aerodynamic sweeping action of the airstream.
    Type: Grant
    Filed: June 17, 1997
    Date of Patent: April 11, 2000
    Assignee: AlliedSignal Inc.
    Inventors: John Stanko, Lowell Pearson
  • Patent number: 6042049
    Abstract: A guidable flying body of the type in which a pitch control signal from a station remote from the flying body is received by the flying body to control the pitch of the flying body. The flying body is provided with height control in which the height of the flying body is sensed from the flying body and, as the flying body approaches a predetermined minimum height, the pitch control signals are so modified after reception by the flying body that the flying body is controlled to maintain at least said predetermined minimum height.
    Type: Grant
    Filed: January 9, 1976
    Date of Patent: March 28, 2000
    Assignee: Short Brothers PLC
    Inventor: James W. McIlroy
  • Patent number: 6036144
    Abstract: The disclosed launch systems are formed from mass producible elements that integrate propulsion, pneumatics and structural systems. In one embodiment, a launch system (10) includes multiple stages (12-16) where each stage includes a number of generally wedge-shaped segments (54). Alternating segments (54) form liquid fuel and oxidizer tanks. Each fuel and oxidizer tank pair is associated with a thruster (70). The resulting plurality of thrusters (70) are disposed about a common aerospike thrust structure (30-34). The segments (54) are connected to an internal, hollow structural spine (26) that can also interface with an internal umbilical tower (46). The segments (54) together with their associated thrusters and related components can be mass produced, thereby increasing competition among suppliers, reducing design costs and timeframes.
    Type: Grant
    Filed: October 3, 1997
    Date of Patent: March 14, 2000
    Assignee: Lockheed Martin Corporation
    Inventor: David S. Sisk
  • Patent number: 6021975
    Abstract: An imaging self-referencing target tracker (10) for a laser weapon (12). The weapon generates a first beam of radiation (14) that engages a target (16) to form a beam hit spot (20) thereon. In a first embodiment, a target illuminator (22) (variant 1) illuminates the target with a second beam of radiation (23a). An optics subsystem (30) receives and separately images the first and second beams (23b, 24) of radiation. In a second embodiment, a blocking filter (40) is implemented rather than an illumination laser to pass only radiation at the target wavelength, thereby ensuring that the first and second beams of radiation are separately imaged. A controller (32) is programmed to steer the first and second beams of radiation to the desired target aim point (18) in response to information from the imaged first and second beams of radiation.
    Type: Grant
    Filed: August 27, 1997
    Date of Patent: February 8, 2000
    Assignee: TRW Inc.
    Inventor: Peter M. Livingston
  • Patent number: 6021715
    Abstract: A manifold (130) is configured to have a body portion (131) having at least one initiation port (132) for receiving an initiation device and at least one tapered boss (138) mounted on the body portion (131). The boss (138) has an elliptical cross-sectional configuration and a boss bore (140) for receiving a fuse or linear explosive charge (16) and it communicates with the initiation port (132). There is a clamp member (160) having an aperture (164) dimensioned and configured to generally conform to the boss (138), and tension means such as a set of bolts (166) for urging the clamp member (160) towards the manifold (130). There may be a bushing material (121) on the boss. The manifold (130) may be coupled to a separation device (23) that includes a frangible joint (24) through which is disposed an expansion member (110).
    Type: Grant
    Filed: March 31, 1998
    Date of Patent: February 8, 2000
    Assignee: The Ensign-Bickford Company
    Inventors: James E. Fritz, John A. Graham, Jon E. Rydberg, Steven L. Olson
  • Patent number: 6019313
    Abstract: An installation for connecting the output shaft of the engine and the input shaft of the transmission box together including a transmission shaft having a certain amount of flexural flexibility and including splines at one of its ends. The splined end being designed to be a sliding fit in a corresponding splined hub of the engine. Attaching the engine to the deck actualized by a system for articulated attachment which includes stand legs and rails fixed to the deck parallel to the shafts. The legs can slide with the engine after tilting.
    Type: Grant
    Filed: November 25, 1997
    Date of Patent: February 1, 2000
    Assignee: Eurocopter
    Inventors: Fran.cedilla.ois Robert Lenhart, Daniel Chaniot
  • Patent number: 6016990
    Abstract: A system for measuring the roll angle of a rotating projectile. The system includes a transmit system mounted on the projectile. The transmit system has a linearly polarized transmit antenna system, a first transmitter coupled to the transmit antenna system for transmitting a first transmit signal at a first frequency, and a second transmitter coupled to the transmit antenna system for transmitting a second transmit signal at a second frequency. The first frequency is different from the second frequency, and the first and second transmit signals are in phase coherency. The system further includes a receiver system located remotely from the projectile. The receiver system includes a linearly polarized receive antenna system for receiving the first transmit signal and the second transmit signal. A first receiver section is provided for receiving and downconverting the first transmit signal to provide a first receiver signal.
    Type: Grant
    Filed: April 9, 1998
    Date of Patent: January 25, 2000
    Assignee: Raytheon Company
    Inventor: James G. Small
  • Patent number: 6016992
    Abstract: A STOL aircraft has a fuselage 22 vertical 26 and horizontal 27 rear stabilizers and at least one wing made up of a lower primary airfoil 10 and an upper complementary airfoil 11 which, between them, form the inlet 12 and exhaust 14 air ducts. The craft is propelled by one or more cross flow fans 13 contained in a housing(s) 63 (FIG. 7) between the primary 10 and complementary 11 airfoils. The primary 10 and complementary 11 airfoils can be extended and flexed downwardly, by various means.
    Type: Grant
    Filed: April 18, 1997
    Date of Patent: January 25, 2000
    Inventor: Gordon Kolacny
  • Patent number: 6014932
    Abstract: A land mine arming/disarming system is provided in which a satellite or other airborne vehicle may remotely arm and/or disarm land mines via signals transmitted through atmospheric free space. In such a manner, land mines are less of a health hazard when conflict situations are not present.
    Type: Grant
    Filed: November 18, 1997
    Date of Patent: January 18, 2000
    Assignee: Technology Patents, LLC
    Inventor: Aris Mardirossian