Patents Assigned to Lockheed Corporation
  • Patent number: 10669742
    Abstract: The combination padlock is of the type having a shackle, a dial for rotating a drive cam having a gate slot, a plurality of rotatable wheels or tumblers each with gate slots, and a fence for allowing the shackle to be opened when all of the gate slots are aligned with the fence. In carrying out the method, the dial is manipulated to sequentially align the gate slot of each wheel with the fence by incremental movement thereof and while the gate slot of the drive cam is aligned with the fence, applying force between the shackle and casing to measure movement of the shackle relative to the casing at each increment position of at least two of the wheels to determine the combination number of each wheel and/or to open the shackle. A frame is provided with structure for releasably securing the casing member in a first embodiment, and the shackle member in a second embodiment, to the frame wherein the unsecured shackle member or casing member is free to move relative to the frame.
    Type: Grant
    Filed: December 18, 1990
    Date of Patent: June 2, 2020
    Assignee: Lockheed Corporation
    Inventor: Andrew O. Williams
  • Patent number: 6673449
    Abstract: A method of making heat engine components, such as rocket nozzle throats, includes forming a body having at least one surface, wherein the body is made of a refractory metal, and compressing a ceramic powder between a die and the at least one surface of the body, with sufficient heat and pressure to densify and thus form a solid ceramic coating on the at least one surface of the body. Nozzle throats made according to the invention have bodies made of refractory metals, such as tantalum, and ceramic coatings on the inner surfaces of the annular bodies, wherein the ceramic coatings are made of ceramic materials such as tantalum carbide.
    Type: Grant
    Filed: May 21, 2002
    Date of Patent: January 6, 2004
    Assignee: Lockheed Corporation
    Inventors: Salvatore Thomas Bruno, Christopher Anthony Koch, Yazdan Paul Mantilla, Sanjay B. Prasad, Jerome Paul Wittenauer, Deborah Lynn Yaney, Joseph Zegarski
  • Patent number: 6017491
    Abstract: Elastomeric compositions having incorporated therein certain specific compounds and/or compositions which are non-toxic but render the metals to which the compositions are applied resistant to corrosion, particularly, when in a salt environment.
    Type: Grant
    Filed: June 11, 1998
    Date of Patent: January 25, 2000
    Assignees: Products Research & Chemical, Lockheed Corporation
    Inventors: Ahmed Sharaby, Robert N. Miller
  • Patent number: 5912643
    Abstract: A Passive Navigation System (PNS) provides continuous updating of position, velocity, and attitude information of a vehicle without recourse to radiating or external navigation aids. The system accurately computes navigation information with the utilization of gravity sensors, gravimetric maps, vertical position, and velocity measurements. Sensor and map data are optimally processed by real time filtering to compute the best position, velocity, and attitude of the vehicle. The products of measured gravity gradients and the velocity of the vehicle are integrated over time to obtain a north, east, down gravity vector components which are combined with corresponding components obtained from a vertical deflection map in a complementary filter. North and east components of the combination are compared with the corresponding components from the vertical deflection map, while the down component of the gravity is compared to the down value obtained from a gravimeter.
    Type: Grant
    Filed: May 29, 1997
    Date of Patent: June 15, 1999
    Assignee: Lockheed Corporation
    Inventors: Sung-Leung Chew, Joseph N. Dmytrasz, Joseph Gatta, Henry F Ritchie, Donald L. Sumner
  • Patent number: 5806789
    Abstract: A fairing for an aircraft is provided, having a roll axis with a turret coupled to the front end of the fairing for rotation about the roll axis. An opening is formed through the front end of the turret in which a tracking member is supported for rotation between forward and rearward positions about a pitch axis transverse to the roll axis. The tracking member has a cavity with a primary optical mirror at one end and a transparent shield at an opposite end with a primary optical axis extending between the mirror and shield. The shield is slanted to minimize wind turbulence when the tracking member is located in a rearward position.
    Type: Grant
    Filed: August 22, 1995
    Date of Patent: September 15, 1998
    Assignee: Lockheed Corporation
    Inventors: Jesse M. Boulware, Roger F. Marquardt
  • Patent number: 5793889
    Abstract: A method and system of image modulation detection of an aircraft exhaust plume by time sequence differentiation is provided. The method comprises the steps of forming two sequential images of the field of view in which an exhaust plume to be detected is located, and forming a differential image from the sequential images showing components of the aircraft's exhaust plume that are modulating at a rate greater than the frame rate of the detection system. The nonmodulating components such as the sky hills, and even the missile body are eliminated from the differential image. Only the plume remains and only the plume is detected. Therefore there is not false alarm note. Each image is formed by a plurality of pixels, wherein each pixel images a portion of the field of view. A value is assigned to each pixel in each of the sequential images that corresponds to one or more characteristics of the pixel.
    Type: Grant
    Filed: May 25, 1995
    Date of Patent: August 11, 1998
    Assignee: Lockheed Corporation
    Inventor: Boyd B. Bushman
  • Patent number: 5782432
    Abstract: A variable area exhaust nozzle 26 is provided. The variable area exhaust nozzle 26 includes a nozzle opening 30 and a plurality of nozzle flaps 38 and 40. The nozzle opening 30 has a cylindrical area and a circumference. The plurality of nozzle flaps 38 and 40 are supported about the circumference of the nozzle opening 30. The nozzle flaps 38 and 40 have an axis of rotation 52. The nozzle flaps 38 and 40 are positioned to rotate into the nozzle opening 30 to decrease the cylindrical area of the nozzle opening 30 and to rotate out of the nozzle opening 30 to increase the cylindrical area of the nozzle opening 30. The nozzle flaps 38 and 40 rotate to vary the cylindrical area of the nozzle opening 30 and to reduce the forces required to rotate the nozzle flaps 38 and 40.
    Type: Grant
    Filed: December 13, 1995
    Date of Patent: July 21, 1998
    Assignee: Lockheed Corporation
    Inventor: Kevin J. Renshaw
  • Patent number: 5726798
    Abstract: A method and apparatus are provided for emitting a laser like monochromatic narrow beam of light at a selected wavelength from a heated emitter member having a plurality of parallel layers while reducing emission at other wavelengths of light. The parallel layers are overlaid with each other. Each of the parallel layers extends transversely for a particular width. A heat source stimulates the emitter member to emit photons, which are determined by the composition of materials within the emitter member. The emitter member emits monochromatic light at a selected wavelength in response to the photon emissions. The selected wavelength of the monochromatic light is determined by the width of the layers of the emitter member. Light at other wavelengths does not transmit through and their emissivity also decreases.
    Type: Grant
    Filed: December 1, 1995
    Date of Patent: March 10, 1998
    Assignee: Lockheed Corporation
    Inventor: Boyd B. Bushman
  • Patent number: 5692481
    Abstract: A method and apparatus for reducing contaminants in exhaust gases of an internal combustion engine are provided wherein the a light source is provided for producing radiant energy which converts oxygen in air inducted into the internal combustion engine to ozone. The ozone increases the efficiency of combustion of fuel by the internal combustion engine thereby reducing the amount of hydrocarbons and carbon monoxide in the exhaust gases.
    Type: Grant
    Filed: December 19, 1995
    Date of Patent: December 2, 1997
    Assignee: Lockheed Corporation
    Inventor: Robert N. Miller
  • Patent number: 5672184
    Abstract: A coal gasification system has a pulse detonation device. The pulse detonation device is employed to discharge hot exhaust pulses into the coal gasifier. Also, a pulse detonation device discharges reverse flow pulses into a ceramic candle filter system to dislodge particulate build up on the candles. The pulse detonation device utilizes a rotatable core feed cylinder. The core feed cylinder is carried within an inner side wall of the stationary annular detonation chamber. The core feed cylinder has ports in the side wall that will register with ports in the inner side wall of the annular detonation chamber at least once each revolution. Fuel is introduced through valves mounted to the outer side wall of the annular detonation chamber.
    Type: Grant
    Filed: December 15, 1994
    Date of Patent: September 30, 1997
    Assignee: Lockheed Corporation
    Inventor: Louis G. Hunter, Jr.
  • Patent number: 5665973
    Abstract: A plurality of transparent members are provided each of which has an elongated flat portion with a tip portion at one end forming an obtuse angle relative to the elongated flat portion with the tip portion having a narrowed end, and a spot of material located on the tip portion that fluoresces in the presence of blacklight. The spots of the plurality of transparent members are of different sizes respectively. Also provided is a flat transparent member having a series of spaced apart lines of different lengths with dimension numbers formed next to the lines respectively. The lines and numbers fluoresce in the presence of blacklight. The plurality of transparent members and the flat transparent member are coupled together for movement relative to each other.
    Type: Grant
    Filed: October 25, 1995
    Date of Patent: September 9, 1997
    Assignee: Lockheed Corporation
    Inventor: Terry L. Christenson
  • Patent number: 5642118
    Abstract: An apparatus for providing broadbanded electromagnetic radiation attenuation is disclosed. The apparatus comprises a surface mount to which a plurality of protuberances are mounted. Each protuberance is further made up of a plurality of impedance sheets that are substantially concentric one with another. The impedance sheets are directionally shaped so as to enhance absorption of any polarization of plane wave radiation from any incidence direction including near grazing incidence. The impedance sheets have impedance values which are tapered with higher impedance values belonging to the sheets farther away from the concentric center. These sheets may be either substantially spherical, hemispherical, or circular cylinders. The distance separating neighboring impedance sheets is selected according to the shortest wavelength for which good electromagnetic attentuation is desired.
    Type: Grant
    Filed: May 9, 1995
    Date of Patent: June 24, 1997
    Assignee: Lockheed Corporation
    Inventor: Richard Scott Grannemann
  • Patent number: 5637946
    Abstract: An electrical device functions as a thermally energized DC power source. The device has a base plate of conductive metal. A number of electrode points protrude upward from the base plate, terminating in a sharp edge. A collection plate of conductive metal is positioned above the sharp upper edges of the electrode points. The gap between the electrode points and between the collection plate and the electrode points is electrically insulated. An electrical potential exists between the base plate and the upper collection plate while the device is at and above room temperature. The potential difference increases as the temperature increases.
    Type: Grant
    Filed: September 20, 1995
    Date of Patent: June 10, 1997
    Assignee: Lockheed Corporation
    Inventor: Boyd B. Bushman
  • Patent number: 5632622
    Abstract: A method and an apparatus for simulator control include a training system (10) with indicators and controls (12) for interfacing with a trainee. A display (16) is used to display representations of preprogrammed units, each unit including a collection of detailed parameters for use with a selected training scenario. Selection of one of the representations results in configuring the training system (10) according to the detailed parameters of the unit associated with the selected representation.
    Type: Grant
    Filed: April 25, 1995
    Date of Patent: May 27, 1997
    Assignee: Lockheed Corporation
    Inventor: Robert L. Bothwell
  • Patent number: 5604196
    Abstract: Disclosed are three organic solvent cleaning formulations. In one embodiment, the formulation is methyl or ethyl lactate and propylene glycol methyl ether. In another embodiment, the formulation is methyl or ethyl lactate and propylene glycol propyl ether. In a third embodiment, the formulation is ethyl lactate and isoparaffins of isoundecane and isododecane with propylene glycol propyl ether added as a stabilizing agent.
    Type: Grant
    Filed: June 1, 1995
    Date of Patent: February 18, 1997
    Assignee: Lockheed Corporation
    Inventors: Henry J. Weltman, Tony L. Phillips
  • Patent number: 5585557
    Abstract: The invention is a system for determining the physical characteristics of an incident fluid flow stream over a surface of a vehicle relative to an axis thereof, the apparatus. In detail, the invention includes at least one first pressure sensor mounted on the surface, the at least one first pressure sensor for receiving dynamic pressure signals generated by the convected boundary layer of the fluid flow stream and providing an output signal representative thereof. At least one array of second pressure sensors (pressure transducers) is positioned down stream of the at least one first pressure sensors, the second sensors of the at least one array each of said second pressure sensors providing a second output signal representative of the above pressure signals received thereby. A computer system is adapted to receive the first and second signals and to calculate the angular direction of the fluid flow relative to the axis and the velocity thereof.
    Type: Grant
    Filed: May 12, 1995
    Date of Patent: December 17, 1996
    Assignee: Lockheed Corporation
    Inventors: Robert C. Loschke, James D. Revell, Frank J. Balena, Floyd O. Hickmon, III
  • Patent number: 5582365
    Abstract: A foreign object deflector for installation on the lower fuselage of an aircraft forward of equipment, such as antennas and radomes, which are to be protected by the deflector. During takeoff and landing, aircraft landing gear kick up various foreign objects, such as rocks, dirt and debris, which can damage or destroy the relatively fragile equipment. However, the foreign object deflector of the present invention deflects these foreign objects away from the equipment. Then, once the takeoff or landing is completed, the foreign object deflector is retracted and latched in place to minimize drag.
    Type: Grant
    Filed: October 14, 1994
    Date of Patent: December 10, 1996
    Assignee: Lockheed Corporation
    Inventor: John S. Simmons
  • Patent number: 5576030
    Abstract: The invention is an apparatus for forming fiber reinforced resin structures In detail, invention includes a fluid impervious outer first sheet. A mold surface is includes upon which can be supported a lay-up of at least one layer of fibrous material, and over which can be placed the first fluid impervious outer sheet and its edges marginally sealed upon the mold surface to form a chamber. A first vacuum port for drawing a vacuum upon the chamber is located in proximity to the lay-up. A first distribution medium is positioned between the fabric lay-up and the fluid impervious outer sheet for distributing resin into the lay-up. A second fluid impervious sheet is located between the first distribution medium and the first impervious sheet. A resin inlet port extends from the exterior of the chamber through the first and second impervious sheets an is in communication with the first distribution medium.
    Type: Grant
    Filed: October 2, 1995
    Date of Patent: November 19, 1996
    Assignee: Lockheed Corporation
    Inventor: James R. Hooper
  • Patent number: 5560569
    Abstract: A method and apparatus are disclosed for providing an aircraft thermal protection system for hypersonic cruise and space launch vehicles. A flexible outer skin formed from a metal super alloy is designed to flex and accommodate thermal growth in the vehicle structure. The flexible super alloy skin is made from a plurality of hexagonal shaped cups which are welded together at the edges in a honeycomb type of array with thermal expansion gaps provided between the outermost surfaces of the hexagonal cups. Gap covers extend across the thermal expansion gaps to reduce aerodynamic drag. The flexible outer skin extends over hexagonal shaped, high temperature ceramic blocks, which provide both an insulation layer and support for the outer skin. The flexible outer skin distributes airloads across various ones of the rigid ceramic blocks.
    Type: Grant
    Filed: April 6, 1995
    Date of Patent: October 1, 1996
    Assignee: Lockheed Corporation
    Inventor: Ronald P. Schmidt
  • Patent number: D375564
    Type: Grant
    Filed: September 13, 1991
    Date of Patent: November 12, 1996
    Assignee: Lockheed Corporation
    Inventor: John M. Perez