Patents Assigned to Space
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Patent number: 6387781Abstract: Silicon and metal are coevaporated onto a silicon substrate in a molecular beam epitaxy system with a larger than stoichiometric amount of silicon so as to epitaxially grow columns of metal silicide embedded in a matrix of single crystal, epitaxially grown silicon. Higher substrate temperatures and lower deposition rates yield larger columns that are farther apart while more silicon produces smaller columns. Column shapes and locations are selected by seeding the substrate with metal silicide starting regions. A variety of 3-dimensional, exemplary electronic devices are disclosed.Type: GrantFiled: May 18, 1990Date of Patent: May 14, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Robert W. Fathauer
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Patent number: 6385973Abstract: A microscalable thermal control module consists of a Stirling cycle cooler that can be manipulated to operate at a selected temperature within the heating and cooling range of the module. The microscalable thermal control module is particularly suited for controlling the temperature of devices that must be maintained at precise temperatures. It is particularly suited for controlling the temperature of devices that need to be alternately heated or cooled. The module contains upper and lower opposing diaphragms, with a regenerator region containing a plurality of regenerators interposed between the diaphragms. Gaps exist on each side of each diaphragm to permit it to oscillate freely. The gap on the interior side one diaphragm is in fluid connection with the gap on the interior side of the other diaphragm through regenerators. As the diaphragms oscillate working gas is forced through the regenerators.Type: GrantFiled: July 12, 2001Date of Patent: May 14, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Matthew E. Moran
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Patent number: 6387456Abstract: A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a barium-strontium alumino silicate.Type: GrantFiled: September 5, 2000Date of Patent: May 14, 2002Assignees: General Electric Company, United Technologies Corporation, The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Harry Edwin Eaton, Jr., William Patrick Allen, Nathan S. Jacobson, Narottam P. Bansal, Elizabeth J. Opila, James L. Smialek, Kang N. Lee, Irene T. Spitsberg, Hongyu Wang, Peter Joel Meschter, Krishan Lal Luthra
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Patent number: 6387399Abstract: Microcapsules prepared by encapsulating an aqueous solution of a protein, drug or other bioactive substance inside a semi-permeable membrane by are disclosed. The microcapsules are formed by interfacial coacervation under conditions where the shear forces are limited to 0-100 dynes/cm2 at the interface. By placing the microcapsules in a high osmotic dewatering solution, the protein solution is gradually made saturated and then supersaturated, and the controlled nucleation and crystallization of the protein is achieved. The crystal-filled microcapsules prepared by this method can be conveniently harvested and stored while keeping the encapsulated crystals in essentially pristine condition due to the rugged, protective membrane. Because the membrane components themselves are x-ray transparent, large crystal-containing microcapsules can be individually selected, mounted in x-ray capillary tubes and subjected to high energy x-ray diffraction studies to determine the 3-D structure of the protein molecules.Type: GrantFiled: May 15, 1998Date of Patent: May 14, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Dennis R. Morrison, Benjamin Mosier
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Patent number: 6383679Abstract: After discharge, a rechargeable battery having a nickel hydroxide positive electrode is charged at a temperature T1 between a proximately −10° C. and −30° C., lower than a temperature T2, in the range of approximately −15° C. to +5° C., at which discharge begins, automatically determining the total charge to be returned to the battery for establishing the ideal charge for the battery leading into the next discharge cycle, and applying charge energy to the battery having the magnitude as automatically determined. After discharge, the battery is cooled into the T1 range, then heated to stabilize the temperature to that in the T1 range. Then the battery is charged according to a nominal profile of charge power as a function of time, the accumulated charge imparted to the battery sensed as cooling proceeds, the nominal power profile adjusted according to the accumulated charge obtained, and the remainder of the nominal charge profile adjusted accordingly.Type: GrantFiled: November 10, 1999Date of Patent: May 7, 2002Assignee: Space Systems/Loral, Inc.Inventor: Aaron J. Rulison
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Patent number: 6382024Abstract: Apparatus and method for providing a velocity flow profile near a reference surface. A measuring device utilizes a plurality of thermojunction pairs to provide the velocity flow profile in accordance with behavior of a gas relative to a constant thickness strut which stands vertically from the reference surface such that the span is normal to the surface, and the chord is parallel to the surface along the initial flow direction. Each thermojunction is carried on either side of a heater formed on a measuring surface in a constant thickness portion of a strut. Additionally, each thermojunction of a given pair is located at a predetermined height from the reference surface. Gas velocity data obtained from temperature differentials from one side of the heater to the other at each successive height is utilized to generate the velocity and turbulence level profiles.Type: GrantFiled: June 28, 2000Date of Patent: May 7, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Danny P. Hwang, Herbert A. Will, Gustave C. Fralick
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Publication number: 20020050908Abstract: A device to protect electronic circuitry from high voltage transients is constructed from a relatively thin piece of conductive composite sandwiched between two conductors so that conduction is through the thickness of the composite piece. The device is based on the discovery that conduction through conductive composite materials in this configuration switches to a high resistance mode when exposed to voltages above a threshold voltage.Type: ApplicationFiled: December 28, 2000Publication date: May 2, 2002Applicant: U.S. Goverment, National Aeronautics and Space AdministrationInventor: Hamid Javadi
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Patent number: 6381081Abstract: A flexure-ring is provided for centering a lens in a bore of a housing with 3N lens contacting stubs, where N is an integer equal to or greater than one. The stubs are formed by increasing the inside diameter of the ring made to fit tightly around a lens except at 3N locations for the aforesaid stubs, and said ring having an outside diameter made to fit tightly inside the housing bore locations. Behind each stub, a segment of the ring is removed down to a chord perpendicular to a ring diameter passing through the center of each stub. That chord is selected to have a length greater than the lens contacting surface of the stub, thereby to produce a reduced cross section of the ring on both sides of the stub to serve as flexures in relieving stresses due to different coefficients of thermal expansion of the three parts involved due to changes in temperature while in use.Type: GrantFiled: January 19, 2001Date of Patent: April 30, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Virginia G. Ford
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Patent number: 6380685Abstract: The design and manufacturing processes for Hollow Cathode Assemblies (HCA's) that operate over a broad range of emission currents up to 30 Amperes, at low potentials, with lifetimes in excess of 17,500 hours. The processes include contamination control procedures which cover hollow cathode component cleaning procedures, gas feed system designs and specifications, and hollow cathode activation and operating procedures to thereby produce cathode assemblies that have demonstrated stable and repeatable operating conditions, for both the discharge current and voltage. The HCA of this invention provides lifetimes of greater than 10,000 hours, and expected lifetimes of greater than 17,500 hours, whereas the present state-of-the-art is less than 500 hours at emission currents in excess of 1 Ampere.Type: GrantFiled: December 28, 2000Date of Patent: April 30, 2002Assignee: United States of America as represented by the Administrator of National Aeronautics and Space AdministrationInventors: Michael J. Patterson, Timothy R. Verhey, George C. Soulas
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Patent number: 6381559Abstract: A computer implemented physical signal analysis method includes four basic steps and the associated presentation techniques of the results. The first step is a computer implemented Empirical Mode Decomposition that extracts a collection of Intrinsic Mode Functions (IMF) from nonlinear, nonstationary physical signals. The decomposition is based on the direct extraction of the energy associated with various intrinsic time scales in the physical signal. Expressed in the IMF's, they have well-behaved Hilbert Transforms from which instantaneous frequencies can be calculated. The second step is the Hilbert Transform which produces a Hilbert Spectrum. Thus, the invention can localize any event on the time as well as the frequency axis. The decomposition can also be viewed as an expansion of the data in terms of the IMF's. Then, these IMF's, based on and derived from the data, can serve as the basis of that expansion.Type: GrantFiled: March 31, 1999Date of Patent: April 30, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Norden E. Huang
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Patent number: 6380834Abstract: A magnetic assembly is constructed comprising a first core portion, a second core portion, and a winding assembly. The first and second core portions each include a base portion and a plurality of projections extending from the base portion. The winding includes a plurality of stacked layers having conductive paths applied to their surfaces. The winding is constructed with a bore, wherein each conductive path encircles the bore. A number of the stacked conductive layers form a primary winding, and a number of the stacked conductive layers form a secondary winding. The winding is disposed over the first core portion in a manner so that a projection engages the opening of the winding to provide magnetic coupling of winding and core. The second core portion is disposed over the first core portion to form a closed magnetic circuit through and around the winding.Type: GrantFiled: March 1, 2000Date of Patent: April 30, 2002Assignee: Space Systems/Loral, Inc.Inventors: Steven M. Canzano, Howard Webber, Michael McVey
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Patent number: 6381520Abstract: A control system and method that keeps solar arrays on a satellite pointing toward the sun. Exemplary control systems and methods are implemented as follows. An orbit propagator computes satellite orbital location data and computes a sun vector referenced to an inertial reference frame. A coordinate transformation processor processes the sun vector in the inertial reference frame and a sensed satellite attitude signal to generate a sun vector referenced to a satellite body reference frame. A solar array position processor processes a step count derived from a solar array pointing control system and sensed solar array position to generate an estimate of the position of the solar array. A summing device sums the solar array position estimate output, the body frame gun vector, and a bias signal derived from a ground command, to produce a solar array position error signal. A filter filters the solar array position error signal.Type: GrantFiled: July 10, 2000Date of Patent: April 30, 2002Assignee: Space Systems/Loral, Inc.Inventors: John S. Higham, Lee Rotlisberger
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Patent number: 6378809Abstract: In a presently preferred embodiment of this invention a spacecraft includes at least four thermal radiator panels, with a first pair of said panels being initially stowed along a North facing surface of said spacecraft and a second pair of said panels being initially stowed along a South facing surface of said spacecraft. Each of said panels is coupled to a hinge mechanism at an anti-Earth facing end of said spacecraft and is rotatable by said hinge mechanism from a stowed position to a deployed position. The deployed position is a position that is off of the anti-Earth facing end of the spacecraft. In the presently preferred embodiment of this invention, when in the deployed position a longitudinal axis of each of said panels forms a non-zero angle with an Earth-pointing axis of said spacecraft.Type: GrantFiled: September 16, 1998Date of Patent: April 30, 2002Assignees: Space Systems, Loral, Inc.Inventor: Randy Pon
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Patent number: 6378291Abstract: A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the reduced toxicity propellant to the ACS decomposing element (26) of an ACS thruster. The ACS decomposing element is operative to decompose the reduced toxicity propellant into hot propulsive gases. In addition the system includes suitable valves and conduits (18) for supplying the reduced toxicity propellant to an axial decomposing element (24) of the axial thruster. The axial decomposing element is operative to decompose the reduced toxicity propellant into hot gases. The system further includes suitable valves and conduits (20) for supplying a second propellant (12) to a combustion chamber (28) of the axial thruster, whereby the hot gases and the second propellant auto-ignite and begin the combustion process for producing thrust.Type: GrantFiled: April 17, 2001Date of Patent: April 30, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronatics and Space AdministrationInventor: Steven J. Schneider
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Patent number: 6378810Abstract: A satellite has a platform of elongated shape in a direction parallel to a roll axis of the satellite. A deployable arm is pivotally carried by a longitudinally extending face of the platform. A solar generator is carried at the end of the arm by a first motor for aiming the generator through a range of 360° about a pitch axis orthogonal to the direction of elongation of the platform. A second motor rotates the solar generator through a limited angular range about an axis that is orthogonal to the pitch axis and parallel to the plane of the generator. The arm, when deployed, moves the solar generator away from on a stored position in contact with the platform in a direction of a yaw axis.Type: GrantFiled: February 14, 2000Date of Patent: April 30, 2002Assignee: Matra Marconi Space FranceInventors: Philippe Pham, Bernard Polle
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Patent number: 6379809Abstract: A thermally stable, piezoelectric and pyroelectric polymeric substrate was prepared. This thermally stable, piezoelectric and pyroelectric polymeric substrate may be used to prepare electromechanical transducers, thermomechanical transducers, accelerometers, acoustic sensors, infrared sensors, pressure sensors, vibration sensors, impact sensors, in-situ temperature sensors, in-situ stress/strain sensors, micro actuators, switches, adjustable fresnel lenses, speakers, tactile sensors, weather sensors, micro positioners, ultrasonic devices, power generators, tunable reflectors, microphones, and hydrophones. The process for preparing these polymeric substrates includes: providing a polymeric substrate having a softening temperature greater than 100° C.Type: GrantFiled: August 18, 1998Date of Patent: April 30, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Joycelyn O. Simpson, Terry L. St. Clair
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Publication number: 20020046820Abstract: A recording paper coated or impregnated with a sizing agent containing a water-soluble soybean polysaccharide as an indispensable component, and optionally a cationic polymer and a surfactant, preferably a nonionic surfactant having HLB of 5-15. The water-soluble soybean polysaccharide is a water-soluble polysaccharide extracted from soybean or soybean extraction residue and subjected to desalinating purification.Type: ApplicationFiled: October 22, 2001Publication date: April 25, 2002Applicant: SPACE ENVIRONMENTAL TECH. COMPANY, INC.Inventors: Toshikatsu Furunaga, Yoshiyuki Kondo
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Patent number: 6377097Abstract: A delay circuit includes a first network having an input and an output node, a second network having an input and an output, the input of the second network being coupled to the output node of the first network. The first network and the second network are configured such that: a glitch at the input to the first network having a length of approximately one-half of a standard glitch time or less does not cause the voltage at the output of the second network to cross a threshold, a glitch at the input to the first network having a length of between approximately one-half and two standard glitch times causes the voltage at the output of the second network to cross the threshold for less than the length of the glitch, and a glitch at the input to the first network having a length of greater than approximately two standard glitch times causes the voltage at the output of the second network to cross the threshold for approximately the time of the glitch.Type: GrantFiled: March 13, 2000Date of Patent: April 23, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Robert L. Shuler, Jr.
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Patent number: 6376830Abstract: A method/system are provided for measuring the N×N scalar transfer function elements for an N-port guided wave device. Optical energy of a selected wavelength is generated at a source and directed along N reference optical paths having N reference path lengths. Each reference optical path terminates in one of N detectors such that N reference signals are produced at the N detectors. The reference signals are indicative of amplitude, phase and frequency of the optical energy carried along the N reference optical paths. The optical energy from the source is also directed to the N-ports of the guided wave device and then on to each of the N detectors such that N measurement optical paths are defined between the source and each of the N detectors. A portion of the optical energy is modified in terms of at least one of the amplitude and phase to produce N modified signals at each of the N detectors.Type: GrantFiled: June 15, 2000Date of Patent: April 23, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Mark E. Froggatt, Turan Erdogan
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Patent number: 6374630Abstract: A carbon dioxide absorption heat pump cycle is disclosed using a high pressure stage and a super-critical cooling stage to provide a non-toxic system. Using carbon dioxide gas as the working fluid in the system, the present invention desorbs the CO2 from an absorbent and cools the gas in the super-critical state to deliver heat thereby. The cooled CO2 gas is then expanded thereby providing cooling and is returned to an absorber for further cycling. Strategic use of heat exchangers can increase the efficiency and performance of the system.Type: GrantFiled: May 9, 2001Date of Patent: April 23, 2002Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Jack A. Jones