Patents Represented by Attorney, Agent or Law Firm Terry J. Anderson
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Patent number: 6175336Abstract: A structural endcap antenna for a vertical tail of an aircraft. The endcap antenna comprises an outer skin having an inner surface and an antenna element disposed adjacent to the inner surface of the outer skin. The antenna element is in electrical communication with an RF signal source. Disposed adjacent to the antenna element is an inner support structure electrically bonded thereto. The antenna element and the inner support structure are excited by the RF signal source and provide structural support to the endcap antenna.Type: GrantFiled: December 27, 1999Date of Patent: January 16, 2001Assignee: Northrop Grumman CorporationInventors: Daniel Patrick Coughlin, Allen John Lockyer, Michael David Durham, Kevin Herman Alt, Peter Lacombe, Jayanth Nandalke Kudva, Keith Alan Olsen
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Patent number: 6174392Abstract: A method for repairing a multi-layered damage area in a multi-layered composite structure. The method first includes obtaining depth measurement data, and obtaining topographical measurement data by laser scanning the surface of the damage area. This depth measurement data and topographical measurement data are inputted into a microprocessor along with thickness data of each layer. All inputted information is correlated among itself to thereby internally produce a three-dimensional damage area display-replica and interpolate a two-dimensional pattern of each layer of the damage area and of the surface of the damage area. The damage area is removed by first projecting a two-dimensional laser pattern of the damage area thereat on the surface of the structure, and thereafter manually removing the area to produce a void. Repair is accomplished by projecting onto respective replacement material a two-dimensional laser image pattern of each layer and manually cutting that layer according to the appropriate pattern.Type: GrantFiled: March 4, 1999Date of Patent: January 16, 2001Assignee: Northrop Grumman CorporationInventor: Carl Andrew Reis
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Patent number: 6172645Abstract: A PCMCIA modem card which is connectable a host computer and utilizes an integrated, extendable antenna for wireless transmission and reception, is provided with a circuit board. The circuit board is provided with a cavity interior. The cavity extends to a first end of the circuit board. The modem card is further provided with communications circuitry which is formed on the circuit board. The modem card is further provided with an antenna structure which is in electrical communication with the communications circuitry. The antenna structure is translatable from a first position wherein the antenna structure is substantially disposed within the cavity and a second position wherein the antenna structure is extended from the cavity.Type: GrantFiled: February 6, 1998Date of Patent: January 9, 2001Assignee: Northrop Grumman CorporationInventors: Evan A. Hollander, Scott A. Stratmoen
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Patent number: 6170781Abstract: An aircraft door sealing system for use with an aircraft door. The aircraft door is movable between open and closed positions with respect to a door frame. The door has a peripheral door opening portion and a peripheral door seal portion. The door frame has a peripheral frame opening portion and a peripheral frame seal portion. The frame opening portion is aligned adjacent the door opening portion when the door is in the closed position. The frame seal portion is aligned adjacent the door seal portion when the door is in the closed position. The sealing system is provided with an elastic seal which is interposed between the door and the door frame. The seal is attached to the door seal portion and the frame seal portion. The seal is expandable and contractible for permitting movement of the door between the open and closed positions thereof. The seal has a pair of seal opening edges disposed between the door opening portion and the frame opening portion.Type: GrantFiled: January 21, 1999Date of Patent: January 9, 2001Assignee: Northrop Grumman CorporationInventors: David Eugene Sherrill, Robert Wade Chapman
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Patent number: 6173091Abstract: Absolute strain is measured by providing a coherent beam of light and separating the coherent beam of light into first and second beams which are in quadrature with one another and which have different polarization angles. The first and second beams are combined in a manner which maintains the different polarization angles thereof, so as to form a combined beam. The combined beam is then applied to a Fabry-Perot strain sensor so as to form a reflected combined beam. The reflected combined beam is then separated into first and second reflected beams having different polarization angles. The intensity of the first and second reflected beams is then sensed, so as to determine a change in the etalon length of the Fabry-Perot sensor. The change in etalon length is indicative of the absolute strain sensed.Type: GrantFiled: January 11, 2000Date of Patent: January 9, 2001Assignee: Northrop Grumman CorporationInventor: Stanley M. Reich
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Patent number: 6167859Abstract: A fracture-resistant, thermally stable intake or exhaust valve for an internal combustion (IC) engine. The valve has a stem portion and a head portion, both of which are formed of fiber reinforced ceramic matrix composite (FRCMC) material. This FRCMC material generally includes a polymer-derived ceramic resin in its ceramic state, fibers, and filler materials. Employing FRCMC material to form the valve is advantageous as FRCMC material is highly temperature resistant and temperature stable, thereby allowing for increased engine operating temperatures. FRCMC material is also ductile, thus making the valve fracture resistant. The FRCMC material is also flaw-insensitive in that any flaw within the structure of the valve will not result in cracking and failure. In addition, FRCMC valves are considerably lighter than the existing metal valves. This provides an opportunity to reduce the weight of the overall valve train, thereby increasing engine performance.Type: GrantFiled: December 19, 1997Date of Patent: January 2, 2001Assignee: Northrop Grumman CorporationInventors: Thomas Edward Strasser, Steven Donald Atmur
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Patent number: 6169730Abstract: A method for implementing a time division multiple access protocol for digital communications between a radio transceiver and a repeater or another radio transceiver has the steps of dividing a radio communication into a plurality of frames having a predetermined length of time; dividing each frame into: a plurality of downlink slots, each downlink slot containing a transmission from the repeater to the transceiver; and a plurality of uplink slots, each uplink slot containing a transmission from the transceiver to the repeater.Type: GrantFiled: May 15, 1998Date of Patent: January 2, 2001Assignee: Northrop Grumman CorporationInventors: William Edward Jacklin, Scott Alan Stratmoen
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Patent number: 6166686Abstract: A directional finding system for providing a corrected compass bearing based upon true north rather than magnetic north for a selected location. The true bearing is calculated by determining a present position with a GPS receiver or other location finding device, then selecting the deviation between true north and magnetic north for the present position from a store of magnetic deviation data, and finally correcting the magnetic bearing by the deviation to find a true bearing. The store of magnetic deviation data comprises the deviation between true north and magnetic north for any location. Additionally, the true bearing can be further corrected by a time-based magnetic deviation based upon the monotonic movement of the magnetic north pole. The true bearing is presented on a display along with the magnetic bearing and the present position.Type: GrantFiled: October 30, 1998Date of Patent: December 26, 2000Assignee: Northrop Grumman CorporationInventor: Jonathan Noel Lazar
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Patent number: 6167067Abstract: The present invention relates generally to an apparatus that increases the conversion efficiency of optical parametric oscillators and also reduces overall system size and susceptibility to vibration. The first embodiment of the present invention incorporates a PPLN OPO architecture which includes mirrored coatings on the entry surface area and exit surface area of a monolithic nonlinear optical medium. The coatings act as mirrors, however, the mirrors are actually affixed to the PPLN element. In the first embodiment of the present invention, the PPLN element is a dual grated element. The second embodiment of the present invention uses a single grated PPLN element.Type: GrantFiled: April 3, 1998Date of Patent: December 26, 2000Assignee: Northrop Grumman CorporationInventors: Ronald Kenneth Meyer, Jr., Michael L. Marable, Gerald P. Griffith
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Patent number: 6164598Abstract: In accordance with the present invention, there is provided an aerodynamic control surface apparatus for use with a wing assembly having a wing trailing edge. The control surface apparatus has an inboard section defined by a cordwise inboard side, a first trailing edge side, and a first tapering edge side disposed between the inboard and the fist trailing edge sides. The inboard section has an axis of rotation generally about the cordwise inboard side. The control surface apparatus further has an outboard section defined by a cordwise outboard side, a second trailing edge side, and a second tapering edge side disposed between the outboard and the second trailing edge sides. The outboard section has an axis of rotation generally about the cordwise outboard side. The control surface apparatus further has at least one adjustable spanwise member rotatably attached to the first and second tapering edge sides of the inboard and outboard sections.Type: GrantFiled: March 10, 1999Date of Patent: December 26, 2000Assignee: Northrop Grumman CorporationInventors: Kendall G. Young, Phil S. Zimmerman
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Patent number: 6160924Abstract: A method for forming a two-dimensional map of a three-dimensional object has the steps of mapping the three-dimensional object to an ellipsoid and then mapping the ellipsoid to a two-dimensional surface. Mapping of the three-dimensional object to the ellipsoid is accomplished by forming a plurality of generally parallel, generally planar slices of the three-dimensional objects which correspond to similar slices of the ellipsoid and projecting each point on the surface of a slice of the three-dimensional object to a corresponding point of the ellipsoid. Mapping the ellipsoid to two-dimensional surface may be done according to various different contemporary methodologies.Type: GrantFiled: August 12, 1998Date of Patent: December 12, 2000Assignee: Northrop Grumman CorporationInventor: Jonathan Noel Lazar
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Patent number: 6158672Abstract: In accordance with the present invention, there is provided a balanced high volume, low pressure paint spray gun. The spray gun is provided with a spray gun body connectable to a paint source and an air source. The spray gun is provided with a head insert engaged with the spray gun body. The head insert has a paint atomization chamber formed therein, a paint passage formed therethrough extending into the paint atomization chamber for receiving paint from the paint source, an atomization air passage and a shaping air passage for receiving air flow from the air source therethrough, and a balancing air passage formed therein extending into the paint atomization chamber. The spray gun further has a shaping air chamber defined by the spray gun body.Type: GrantFiled: January 12, 2000Date of Patent: December 12, 2000Assignee: Northrop Grumman CorporationInventor: Jorge Millan
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Patent number: 6157221Abstract: A three input comparator facilitates the comparison of a signal to the greater of two different reference voltages in a manner which mitigates propagation delay. A first differential pair of transistors facilitates comparison of the two reference voltages to one another, while second and third differential pairs of transistors facilitate comparison of the signal to the higher of the two reference voltages.Type: GrantFiled: March 23, 1999Date of Patent: December 5, 2000Assignee: Northrop Grumman CorporationInventors: Kenneth Duane Gorham, Daniel Joseph Blase
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Patent number: 6153291Abstract: A method of fiber preparation for discontinuous fiber-reinforced ceramic matrix composite and a coated discontinuous fiber prepared by this method. The method includes immersing a fiber spool in a resin and drip drying the fiber spool until any excess resin is removed. Next, the damp fiber is cut or chopped and heated to the green-state cure temperature of the resin. After the resin has cured, the product is a coated discontinuous fiber whereby the inner fiber filament bundle is held together by a cured resin shell and the individual filaments are held together by the resin.Type: GrantFiled: October 13, 1998Date of Patent: November 28, 2000Assignee: Northrop Grumman CorporationInventor: Thomas Edward Strasser
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Patent number: 6154451Abstract: In a multi-mode dual channlel data link there is provided a method for automatically controlling or allocating a predetermined amount of power to each of the dual channels. Two diverse product signal are transmitted from a master station down link to a plurality of ground stations. The ground stations receive the diverse product signals and individually determine the integrity of each product signal and transmit the product integrity information and a station identifier back to the master station. The master station processes the integrity information and reallocates a predetermined percentage of total power to be transmitted from each of the dual channels to achieve a predetermined product integrity at one or more of the plurality of ground stations.Type: GrantFiled: June 29, 1998Date of Patent: November 28, 2000Assignee: Northrop Grumman CorporationInventors: John Walter Zscheile, Jr., Bruce John Weber
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Patent number: 6150960Abstract: An integrated flight control indicator for providing visual information indicative of aircraft flight parameters has a sky arc and an earth arc which are visually distinguishable from one another. The sky arc and the earth arc cooperate to generally define a circle wherein the relative lengths of the sky arc and the earth arc indicate the pitch of the aircraft. A horizon line extends approximately between the two intersections of the sky arc and the earth arc so as to provide a visual indication of the roll of the aircraft. Other indicia are provided for indicating radar or barometric altitude, vertical speed, heading, ground track, minimum altitude break, etc. Thus, the present invention provides a visual indication suitable for use in instrument panel displays, heads-up display, and helmet-mounted displays.Type: GrantFiled: November 8, 1999Date of Patent: November 21, 2000Assignee: Northrop Grumman CorporationInventor: Theodore J. Voulgaris
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Patent number: 6148147Abstract: A heated resin supply hose for supplying molten resin in a molding process, such as a RTM process, includes a removable inner core tube or conduit that can be readily removed from reusable supply hose components after each injection cycle to make a molded article. The reusable hose components include a core-receiving conduit for slidably receiving the core conduit and a heating element on the core-receiving conduit as well as additional hose component layers. The used core conduit having residual resin therein is removed from the core-receiving conduit and replaced by a new core conduit that is inserted in the core-receiving conduit in making another molded article.Type: GrantFiled: September 4, 1998Date of Patent: November 14, 2000Assignee: Northrop Grumman CorporationInventor: Mike D. Durham
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Patent number: 6146484Abstract: A method of constructing a honeycomb structure generally undetectable by radar. The method includes winding first and second sheets of radar absorbent material onto a central roller. A first printer prints a plurality of parallel adhesive linear deposits on the first sheet of material as it passes across the first printer. A second printer prints a plurality of parallel adhesive linear deposits on the second sheet of material as it passes across the second printer. The first and second linear deposits are offset with respect to each other. The first and second sheet materials overlap one another during winding onto the central roller. Once the first and second sheets are overlapped onto one another, the adhesive deposits secure sheets together to form a non-expanded honeycomb structure. The non-expanded honeycomb structure is removed from the central roller and is expanded to form the expanded honeycomb structure.Type: GrantFiled: May 21, 1998Date of Patent: November 14, 2000Assignee: Northrop Grumman CorporationInventors: Shahriar Alam, Rodolfo E. Diaz
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Patent number: 6145791Abstract: Elastomeric transition sections (118, 124) are mounted between the upper and lower portions of a wing (100) and a control surface (102) hinged thereto. The elastomeric transition sections include elastomeric material (126) having a plurality of holes (128) formed therethrough. Flexible rods (134, 136) are secured to either the wing or the control surface and extend through the holes (128) in the elastomeric material (126). The elastomeric transition sections provide a smooth aerodynamic transition between the wing and the control surface while permitting the control surface to pivot about the hinge axis (108) to perform the control function.Type: GrantFiled: January 9, 1998Date of Patent: November 14, 2000Assignee: Northrop Grumman CorporationInventors: Joseph B. Diller, Nicholas F. Miller, Jr.
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Patent number: 6145186Abstract: A method of producing a capacitive electroacoustic transducer comprising the initial step forming a substrate having top and bottom surfaces each having a periphery thereof. A first electrode of the transducer is formed upon a portion of the top surface of the substrate. A diaphragm mounting ring of a conductive material is disposed about the periphery of the top surface and separated from the first electrode, and is sized to be thicker than the first electrode by a desired electrode separation distance. The diaphragm mounting ring is characterized by physical dimensions thereof. A compensation ring is aligned with the diaphragm mounting ring upon the bottom surface, and is formed of the same conductive material as the diaphragm mounting ring. The compensation ring is sized to have the same physical dimensions as the diaphragm mounting ring.Type: GrantFiled: October 30, 1998Date of Patent: November 14, 2000Assignee: Northrop Grumman CorporationInventor: Bob Ray Beavers