Patents Assigned to Space
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Patent number: 6370949Abstract: A wind velocity measurement system employs two different principles of physics to measure wind speed: (1) the aerodynamic force imparted to a low profile, rigidly mounted cylindrical rod, and (2) the vibrating frequency of the rod as vortices are shed from the rod's cylindrical surface. A set of strain gages is used as a common sensor for both measurements, and these provide force measurements imparted by the wind on the rod. The signals generated by the strain gages are fed to processing circuitry that calculates the wind speed and direction from the signals. The force measurement is proportional to the square of the wind speed. Since it is a vector quantity, it can also be used to derive wind direction. The vortex shedding frequency is a scalar quantity and is linearly proportional to wind speed. This frequency can be calculated by analyzing the force measurements generated by the strain gages over time.Type: GrantFiled: September 14, 1999Date of Patent: April 16, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Jan A. Zysko, Stanley O. Starr
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Patent number: 6372877Abstract: This invention relates generally to poly(aryl ether ketones) bearing alkylated side chains. It relates particularly to soluble, thermally stable, low dielectric poly(aryl ether ketones) with alkylated side chains and especially to films and coatings thereof. These poly(aryl ether ketones) have the following structural formula: wherein Y is selected from the group consisting of CF3 and CH3; and wherein R is CnH(2n+1) and n=11-18.Type: GrantFiled: June 1, 2000Date of Patent: April 16, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Patrick E. Cassidy, John W. Fitch, III, Scott D. Gronewald, Anne K. St. Clair, Diane M. Stoakley
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Patent number: 6367844Abstract: This invention provides sealed access to the interior of a pressure vessel and consists of a tube, a collar, redundant seals, and a port. The port allows the seals to be pressurized and seated before the pressure vessel becomes pressurized.Type: GrantFiled: June 22, 1999Date of Patent: April 9, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Stanley S. Smeltzer, III, Robert W. Carrigan
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Patent number: 6367509Abstract: An improved thermal harness or thermal heat strap that comprises carbon based (graphite) fiber heat conducting elements coupled to graphite, composite, polymer, or metal end attachment brackets. An outer casing comprising a tubular braided sleeve surrounds the heat conducting elements and eliminates possible contamination caused by the graphite fibers. The thermal harness may be advantageously used in electronic applications to dissipate heat from high temperature components.Type: GrantFiled: April 27, 2001Date of Patent: April 9, 2002Assignee: Space Systems/Loral, Inc.Inventors: W. Scott Bonneville, Roger A. Stonier
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Patent number: 6368662Abstract: Polymer encapsulated metal oxide particles are prepared by combining a polyamide acid in a polar aprotic solvent with a metal alkoxide solution. The polymer was imidized and the metal oxide formed simultaneously in a refluxing organic solvent. The resulting polymer-metal oxide is an intimately mixed commingled blend, possessing synergistic properties of both the polymer and preceramic metal oxide. The encapsulated metal oxide particles have multiple uses including, being useful in the production of skin lubricating creams, weather resistant paints, as a filler for paper, making ultraviolet light stable filled printing ink, being extruded into fibers or ribbons, and coatings for fibers used in the production of composite structural panels.Type: GrantFiled: February 1, 2000Date of Patent: April 9, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Patricia R. McDaniel, Terry L. St. Clair
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Patent number: 6367243Abstract: A method and system are provided for propelling an aerodynamic vehicle into space. The aerodynamic vehicle uses a nuclear-based thermal rocket (NTR) propulsion system capable of producing a hydrogen exhaust. A flow of air is introduced into the hydrogen exhaust to augment the thrust force at speeds of the vehicle up to approximately Mach 6. When the speed of the vehicle is approximately Mach 6 and the altitude of the vehicle is approximately 40 kilometers, the flow of air is stopped and the vehicle is propelled into space using only the NTR.Type: GrantFiled: April 10, 2000Date of Patent: April 9, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: George R. Schmidt
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Patent number: 6367250Abstract: The present invention discloses and teaches a unique, remote optically controlled micro actuator particularly suitable for aerospace vehicle applications wherein hot gas, or in the alternative optical energy, is employed as the medium by which shape memory alloy elements are activated. In gas turbine powered aircraft the source of the hot gas may be the turbine engine compressor or turbine sections.Type: GrantFiled: September 1, 2000Date of Patent: April 9, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Robert J. Baumbick
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Patent number: 6368482Abstract: A system and a method for selective plating processes are disclosed which use directed beams of high intensity acoustic waves to create non-linear effects that alter and improve the plating process. The directed beams are focused on the surface of an object, which in one embodiment is immersed in a plating solution, and in another embodiment is suspended above a plating solution. The plating processes provide precise control of the thickness of the layers of the plating, while at the same time, in at least some incidents, eliminates the need for masking.Type: GrantFiled: September 19, 2000Date of Patent: April 9, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration, Washington, DC (US)Inventors: Richard C. Oeftering, Charles Denofrio
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Publication number: 20020038990Abstract: The present invention includes a method of fabricating a piezoelectric composite device comprising steps of (a) disposing a first layer of electrically non-conductive film over the first layer of tape; (b) disposing a first electrically conductive lead over the first layer of electrically non-conductive film; (c) disposing a piezoelectric wafer over the first electrically conductive lead and the first layer of electrically non-conductive film; (d) disposing a second electrically conductive lead over the piezoelectric wafer; (e) disposing a second electrically non-conductive film over the second electrically conductive lead and the wafer, wherein the layers of electrically non-conductive film, the electrically conductive leads, and the wafer form a laminate assembly; and (f) consolidating the laminate assembly at a predetermined temperature and pressure.Type: ApplicationFiled: August 17, 2001Publication date: April 4, 2002Applicant: National Aeronautics and Space AdministrationInventors: Garnett C. Horner, John Edward Teter, William Eugene Robbins, Benjamin M. Copeland
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Patent number: 6366255Abstract: Deployable antenna systems for use on a spacecraft that is moveable from a stowed position to a deployed position. Two embodiments are disclosed that include one or two sets of main reflector assembly (and optional adjustment mechanism) and subreflectors. The antenna systems include a feed horn assembly fixedly attached to the spacecraft and a rotatable hinge attached to the spacecraft. A substantially rigid reflector support structure is attached to the hinge and rotates about a hinge axis. The main reflector assembly (and optional adjustment mechanism) is attached to a lower portion of the support structure and the subreflector is attached to an upper portion of the support structure. The subreflector has a fixed relation relative to the main reflector assembly and has a fixed relation relative to the feed horn assembly when the antenna system is in the deployed position so that the antenna systems generate predetermined beam coverage patterns.Type: GrantFiled: September 15, 2000Date of Patent: April 2, 2002Assignee: Space Systems/Loral, Inc.Inventor: Jason J. Chiang
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Patent number: 6366681Abstract: Analysis of multi-spectral data for extraction of chlorophyll content. Multi-spectral data is obtained from an imaging device. The multi-spectral data contains spectral response data for chlorophyll and background data. The background data is removed from the multi-spectral data to isolate the spectral response due only to chlorophyll. This is then presented as a chlorophyll absorption feature which may be analyzed by measuring the width of the feature, the surface area of the feature, or measuring various angular changes of the feature. These measurements may than be used for a variety of purposes including plant health analysis.Type: GrantFiled: April 7, 1999Date of Patent: April 2, 2002Assignee: Space Imaging, LPInventor: Kevin S. Hutchins
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Patent number: 6366403Abstract: An optical image enhancement system provides improved image contrast in imaging of a target in high temperature surroundings such as a furnace. The optical system includes a source of vertically polarized light such as laser and a beam splitter for receiving the light and directing the light toward the target. A retardation plate is affixed to a target-facing surface of the beam splitter and a vertical polarizer is disposed along a common optical path with the beam splitter between the retardation plate and the target. A horizontal polarizer, disposed in the common optical path, receives light passing through a surface of the beam splitter opposed to the target-facing surface. An image detector is disposed at one end of the optical path. A band pass filter having a band pass filter characteristic matching the frequency of the vertically polarized light source is disposed in the path between the horizontal polarizer and the image detector.Type: GrantFiled: February 12, 2001Date of Patent: April 2, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Robert L. Kurtz, Richard R. Holmes, William K. Witherow
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Patent number: 6360993Abstract: A system for supplying a space station or satellite comprises a low cost expendable single-stage to orbit launch vehicle having a moderate reliability in the range of about 0.5 to 0.8 for launching a payload of consumable items to low earth orbit. For propulsion, the launch vehicle includes a pressure-fed rocket engine, preferably with a nozzle for aiming products of combustion in a direction away from the launch vehicle and having a fixed orientation relative to the launch vehicle. A pressurant tank contains an inert pressurant gas under pressure. A conduit system serves to introduce the inert pressurant gas from the pressurant tank to a fuel tank and thence to the rocket engine and also to introduce the inert pressurant gas from the pressurant tank to an oxidizer tank and thence to the rocket engine for combustion with the fuel.Type: GrantFiled: April 9, 1999Date of Patent: March 26, 2002Assignee: Space Systems/ Loral, Inc.Inventor: Andrew E. Turner
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Patent number: 6361961Abstract: A method and apparatus for sensing gravity using an NADH oxidase of the plasma membrane which has been found to respond to unit gravity and low centrifugal g forces. The oxidation rate of NADH supplied to the NADH oxidase is measured and translated to represent the relative gravitational force exerted on the protein. The NADH oxidase of the plasma membrane may be obtained from plant or animal sources or may be produced recombinantly.Type: GrantFiled: April 25, 2000Date of Patent: March 26, 2002Assignee: The United States of America as represented by the National Aeronautics and Space AdministrationInventor: D. James Morreā²
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Patent number: 6359357Abstract: A combination radial and thrust magnetic bearing is disclosed that allows for both radial and thrust axes control of an associated shaft. The combination radial and thrust magnetic bearing comprises a rotor and a stator. The rotor comprises a shaft, and first and second rotor pairs each having respective rotor elements. The stator comprises first and second stator elements and a magnet-sensor disk. In one embodiment, each stator element has a plurality of split-poles and a corresponding plurality of radial force coils and, in another embodiment, each stator element does not require thrust force coils, and radial force coils are replaced by double the plurality of coils serving as an outer member of each split-pole half.Type: GrantFiled: August 18, 2000Date of Patent: March 19, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Kenneth A. Blumenstock
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Patent number: 6359107Abstract: A composition of and method for making high performance imide resins that are processable by resin transfer molding (RTM) and resin infusion (RI) techniques were developed. Materials with a combination of properties, making them particularly useful for the fabrication of composite parts via RTM and/or RI processes, were prepared, characterized and fabricated into moldings and carbon fiber reinforced composites and their mechanical properties were determined. These materials are particularly useful for the fabrication of structural composite components for aerospace applications. The method for making high performance resins for RTM and RI processes is a multi-faceted approach. It involves the preparation of a mixture of products from a combination of aromatic diamines and aromatic dianhydrides at relatively low calculated molecular weights (i.e. high stoichiometric offsets) and endcapping with latent reactive groups.Type: GrantFiled: May 18, 2000Date of Patent: March 19, 2002Assignee: The United States of America as represented by the Administrator, National Aeronautics and Space AdministrationInventors: John W. Connell, Joseph G. Smith, Paul M. Hergenrother
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Publication number: 20020031288Abstract: A gear bearing having a first gear and a second gear, each having a plurality of teeth. Each gear operates on two non-parallel surfaces of the opposing gear teeth to perform both gear and bearing functions simultaneously. The gears are moving at substantially the same speed at their contact points. The gears may be roller gear bearings or phase-shifted gear bearings, and may be arranged in a planet/sun system or used as a transmission.Type: ApplicationFiled: March 3, 2001Publication date: March 14, 2002Applicant: National Aeronautics and Space AdministrationInventor: John M. Vranish
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Patent number: 6356245Abstract: A novel method for producing improved RF transmission lines for satellite beamforming networks and printed circuit antenna(s) comprising the steps of (1) bonding together (a) a central conductor strip or trace comprising a dielectric layer or circuit board having on one or both surfaces thereof conductive strip circuitry; (b) upper and lower core layers of lightweight closed-cell plastic foam bonded to (a), and (c) upper and lower surface layers or faceskins of conductive metal foil or of dielectric material bonded to metal foil layers inside and/or outside, to form ground planes, bonded to the surfaces of the adjacent foam core layers.Type: GrantFiled: April 1, 1999Date of Patent: March 12, 2002Assignee: Space Systems/Loral, Inc.Inventors: Phillip Lee Metzen, Richmond Douglas Bruno
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Patent number: 6356171Abstract: An electromagnetic cavity filter is formed by at least two cavities having electrically conductive walls. Each cavity is the equivalent of two filter poles because two orthogonal modes of electromagnetic radiation can resonate within each cavity. Characterizing vector tuning elements are coupled to each of the cavities that are each aligned along respective axes. The tuning elements are used to provoke derivative orthogonal modes and determine the degree of coupling between orthogonal modes. One or more intercavity couplers interconnect the cavities and are rotated at arbitrary angles that are different from the axes of the characterizing vector tuning elements. Electrically adjacent and nonadjacent modes of proximate cavities can be coupled, permitting elliptic filter functions. Electrically nonadjacent modes are coupled by means of an iris interconnecting the two cavities. Electrically adjacent modes are coupled by means of an electrically conductive probe penetrating each of the cavities.Type: GrantFiled: March 27, 1999Date of Patent: March 12, 2002Assignee: Space Systems/Loral, Inc.Inventors: Slawomir J. Fiedziuszko, George A. Fiedziuszko
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Patent number: 6354540Abstract: The present invention relates to a fully androgynous, reconfigurable closed loop feedback controlled low impact docking system with load sensing electromagnetic capture ring. The docking system of the present invention preferably comprises two docking assemblies, each docking assembly comprising a load sensing ring having an outer face, one of more electromagnets, one or more load cells coupled to said load sensing ring. The docking assembly further comprises a plurality of actuator arms coupled to said load sensing ring and capable of dynamically adjusting the orientation of said load sensing ring and a reconfigurable closed loop control system capable of analyzing signals originating from said plurality of load cells and of outputting real time control for each of the actuators. The docking assembly of the present invention incorporates an active load sensing system to automatically dynamically adjust the load sensing ring during capture instead of requiring significant force to push and realign the ring.Type: GrantFiled: September 20, 1999Date of Patent: March 12, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: James L. Lewis, Monty B. Carroll, Ray H. Morales, Thang D. Le