Patents Assigned to Space
  • Patent number: 6353498
    Abstract: The present invention provides an optical function device which is capable of inverting and amplifying an optical signal of the optical communication wavelength band, and executing operation of an image optical signal, and is operable in a wide temperature range, said optical function device composed of a light transmitting medium containing a rare earth element, comprising a portion thereof doped with 1×1023 per 1 m3 or more of the rare earth element for inverting an optical signal and a portion thereof doped with 1×1021 per 1 m3 or more of the rare earth element for amplifying the optical signal with an excitation light superposed thereto.
    Type: Grant
    Filed: March 17, 2000
    Date of Patent: March 5, 2002
    Assignees: National Space Development Agency of Japan, The Japan Space Forum, Toyota School Foundation, Toyota Jidosha Kabushiki Kaisha
    Inventor: Yoshinobu Maeda
  • Patent number: 6352220
    Abstract: In at least one embodiment, the apparatus of the invention is a flight vehicle tail assembly having an exterior surface, at least one first vent in the exterior surface, at least one second vent in the exterior surface, and an air passage connecting the at least one first vent to the at least one second vent allowing air to flow therebetween. Where the at least one first vent is located near a high air pressure area acting on the exterior surface during a range of predefined flight conditions. Further, the at least one second vent is located near a low air pressure area acting on the exterior surface during the predefined flight conditions. So that at the predefined flight conditions adverse loads on the tail assembly are reduced by venting air from the high pressure area, through the tail assembly, to the low pressure area.
    Type: Grant
    Filed: June 2, 2000
    Date of Patent: March 5, 2002
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Daniel W. Banks, Henry L. Kelley
  • Publication number: 20020023450
    Abstract: A solar powered vapor compression refrigeration system is made practicable with thermal storage and novel control techniques. In one embodiment, the refrigeration system includes a photovoltaic panel, a variable speed compressor, an insulated enclosure, and a thermal reservoir. The photovoltaic (PV) panel converts sunlight into DC (direct current) electrical power. The DC electrical power drives a compressor that circulates refrigerant through a vapor compression refrigeration loop to extract heat from the insulated enclosure. The thermal reservoir is situated inside the insulated enclosure and includes a phase change material. As heat is extracted from the insulated enclosure, the phase change material is frozen, and thereafter is able to act as a heat sink to maintain the temperature of the insulated enclosure in the absence of sunlight. The conversion of solar power into stored thermal energy is optimized by a compressor control method that effectively maximizes the compressor's usage of available energy.
    Type: Application
    Filed: April 19, 2001
    Publication date: February 28, 2002
    Applicant: Government of the United States of America, National Aeronautics & Space Administration
    Inventors: Michael K. Ewert, David J. Bergeron
  • Patent number: 6350185
    Abstract: The invention resides in a method and apparatus for conditioning an inner surface of a tube. A pressurized mixture of air and grit and is supplied to a nozzle having an opening with a given diameter through which diameter the pressurized grit and air pass. An elongated nozzle adapter is connected to said nozzle. The nozzle adapter has a passage having a diameter substantially equal to the diameter of said nozzle and said nozzle adapter is connected to said nozzle such that the opening in said nozzle and said passage are aligned with one another. The nozzle adapter is inserted into a tube and is axially moved and rotated in order to condition the inner surface thereof with a pressurized mixture of air and grit.
    Type: Grant
    Filed: February 9, 2000
    Date of Patent: February 26, 2002
    Assignee: Space Systems/Loral, INc.
    Inventors: Brian Gregory Robins, Pierre Duden
  • Patent number: 6350817
    Abstract: Phenylethynyl containing reactive additives were prepared from aromatic diamines containing phenylethynyl groups and various ratios of phthalic anhydride and 4-phenylethynylphthalic anhydride in glacial acetic acid to form the imide in one step or in N-methyl-2-pyrrolidinone to form the amide acid intermediate. The reactive additives were mixed in various amounts (10% to 90%) with oligomers containing either terminal or pendent phenylethynyl groups (or both) to reduce the melt viscosity and thereby enhance processability. Upon thermal cure, the additives react and become chemically incorporated into the matrix and effect an increase in crosslink density relative to that of the host resin. This resultant increase in crosslink density has advantageous consequences on the cured resin properties such as higher glass transition temperature and higher modulus as compared to that of the host resin.
    Type: Grant
    Filed: April 13, 1999
    Date of Patent: February 26, 2002
    Assignee: The United States of America as represented by the United States National Aeronautics and Space Administration
    Inventors: John W. Connell, Joseph G. Smith, Jr., Paul M. Hergenrother
  • Patent number: 6350176
    Abstract: A new technical advancement in the field of precision aluminum optics permits high quality optical polishing of aluminum monolith, which, in the field of optics, offers numerous benefits because of its machinability, lightweight, and low cost. This invention combines diamond turning and conventional polishing along with india ink, a newly adopted material, for the polishing to accomplish a significant improvement in surface precision of aluminum monolith for optical purposes. This invention guarantees the precise optical polishing of typical bare aluminum monolith to surface roughness of less than about 30 angstroms rms and preferably about 5 angstroms rms while maintaining a surface figure accuracy in terms of surface figure error of not more than one-fifteenth of wave peak-to-valley.
    Type: Grant
    Filed: January 27, 2000
    Date of Patent: February 26, 2002
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: James J. Lyons, III, John J. Zaniewski
  • Publication number: 20020020181
    Abstract: A solar powered vapor compression refrigeration system is made practicable with thermal storage and novel control techniques. In one embodiment, the refrigeration system includes a photovoltaic panel, a variable speed compressor, an insulated enclosure, and a thermal reservoir. The photovoltaic (PV) panel converts sunlight into DC (direct current) electrical power. The DC electrical power drives a compressor that circulates refrigerant through a vapor compression refrigeration loop to extract heat from the insulated enclosure. The thermal reservoir is situated inside the insulated enclosure and includes a phase change material. As heat is extracted from the insulated enclosure, the phase change material is frozen, and thereafter is able to act as a heat sink to maintain the temperature of the insulated enclosure in the absence of sunlight. The conversion of solar power into stored thermal energy is optimized by a compressor control method that effectively maximizes the compressor's usage of available energy.
    Type: Application
    Filed: April 19, 2001
    Publication date: February 21, 2002
    Applicant: Government of the United States of America, National Aeronautics & Space Administration
    Inventors: Michael K. Ewert, David J. Bergeron
  • Patent number: 6343513
    Abstract: An acoustic non-linearity parameter (&bgr;) measurement method and system for Non-Destructive Evaluation (NDE) of materials and structural members obviates the need for electronic calibration of the measuring equipment. Unlike known substitutional measuring techniques requiring elaborate calibration procedures, the electrical outputs of the capacitive detector of a sample with known &bgr; and the test sample of unknown &bgr; are compared to determine the unknown &bgr;. In order to provide the necessary stability of the present-inventive reference-based approach, the bandpass filters of the measurement system are maintained in a temperature-controlled environment, and the line voltage supplied to said amplifiers is well-regulated.
    Type: Grant
    Filed: July 14, 2000
    Date of Patent: February 5, 2002
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: William T. Yost, John H. Cantrell
  • Publication number: 20020012221
    Abstract: An asymmetrical capacitor module for generating thrust includes two conductive elements of similar but different geometries separated by a dielectric member. Improved embodiments provided in the construction of conductive elements of smaller axial extent include those where the element is formed by an annular wire or a dielectric supported ring. Other embodiments concern the dielectric member and involve changes in the extent and shape thereof.
    Type: Application
    Filed: September 20, 2001
    Publication date: January 31, 2002
    Applicant: United States of America, National Aeronautics and Space Administration
    Inventor: Jonathan W. Campbell
  • Patent number: 6341750
    Abstract: A method for estimating motion of a dual-spin spacecraft having a gimballed momentum wheel. The method disengages the gimbal from its drive train in anticipation of a short disturbance. Then, the gimbal slip resulting from the disturbance is measured. The method may be used to stabilize any dual-spin spacecraft that uses a gimballed momentum wheel. To stabilize the dual-spin spacecraft, the gimbal angle and gimbal rate are measured during and after the disturbance to provide an indication of the inertial spacecraft motion along gimbal axes. The magnitude and direction of the disturbance are determined by comparing motion of the gimbal before and after the disturbance. Then, torques are applied to the gimbal to counteract the spacecraft motion resulting from the disturbance.
    Type: Grant
    Filed: May 3, 2000
    Date of Patent: January 29, 2002
    Assignee: Space Systems/Loral, Inc.
    Inventors: Peter Y. Chu, John S. Higham
  • Patent number: 6343245
    Abstract: A microaltimeter measures altitude or range highly accurately from an orbiting vehicle. The microaltimeter has a low power solid state laser that is pulsed at a rate above 1 kilohertz. The pulses are delivered to a small telescope which sends them to a planetary surface and receives return reflections. A high efficiency photon detector measures received photons and supplies received photon signals to a process or which makes a time-based bin-wise comparison to find the time of flight and hence the range.
    Type: Grant
    Filed: April 6, 2000
    Date of Patent: January 29, 2002
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: John J Degnan
  • Patent number: 6341933
    Abstract: An end-effector comprises a circulating scoop that cooperates with a plate that lies in its arcuate path. The plate spans the arcuate gap present within the scoop and preferably may be contained within that gap. The plate may be positioned to provide a bucket-like cavity facing in either fore or aft directions. The scoop and/or plate can carry indentations whereby they grasp shaped articles for controlled manipulation.
    Type: Grant
    Filed: June 4, 1999
    Date of Patent: January 29, 2002
    Assignee: MacDonald Detwiler Space & Advanced Robotics Limited
    Inventors: Eric Gagnon, Bruno Rubinger
  • Publication number: 20020009797
    Abstract: The present invention provides systems for growing two or three dimensional mammalian cells within a culture medium facilitated by an electromagnetic field, and preferably, a time varying electromagnetic field. The cells and culture medium are contained within a fixed or rotating culture vessel, and the electromagnetic field is emitted from at least one electrode. In one embodiment, the electrode is spaced from the vessel. The invention further provides methods to promote neural tissue regeneration by means of culturing the neural cells in the claimed system. In one embodiment, neuronal cells are grown within longitudinally extending tissue strands extending axially along and within electrodes comprising electrically conductive channels or guides through which a time varying electrical current is conducted, the conductive channels being positioned within a culture medium.
    Type: Application
    Filed: February 28, 2001
    Publication date: January 24, 2002
    Applicant: National Aeronautics & Space Administration
    Inventors: David A. Wolf, Thomas J. Goodwin
  • Patent number: 6341181
    Abstract: A finite impulse response digital filter is designed for boosting mid-spatial frequencies as opposed to the frequencies near the sensor resolution limit. The digital filter's boost is centered on frequencies at about half the Nyquist frequency. To prevent over-boosting or enhancement of noise, the detail signal can be run through a coring filter to remove any low amplitude detail signal that resulted from noise.
    Type: Grant
    Filed: August 7, 1998
    Date of Patent: January 22, 2002
    Assignee: Canadian Space Agency
    Inventors: John E. Greivenkamp, Jr., Andrew E. Lowman
  • Publication number: 20020005866
    Abstract: A method and system that develops a presentation of an image with a plurality of web pages with capabilities of zoom in, URL linkage, media of various types that present content for one or more parts of the image when selected by an end user. The method enables a developer to create the presentation in an interactive session. Initially, the developer selects a file of an image, which may be any desired image, such as a floor plan of a building, a crime or scene, a map, a landscape, a human, animal, aquatic or other body. The image is stored as a digital background in a project folder. The developer is given the option to provide scaling data and to select one or more spatial parts of the image. The scaling data and the spatial part data is stored in the project folder. The developer can then select one or more elements for placement within one or more areas of the image. For example, furniture elements can be selected from a library of furniture elements for placement in a bedroom of a floor plan image.
    Type: Application
    Filed: May 1, 2001
    Publication date: January 17, 2002
    Applicant: SPACE-WISE TECHNOLOGIES, INC.
    Inventors: Robert S. Gorham, Albert D. Hart, Richard D. Hart, Robert K. Gorham
  • Publication number: 20020000977
    Abstract: A three-dimensional (3-D) interactive display system, display and method of forming thereof. A transparent capaciflector (TC) camera is formed on a transparent shield layer on the screen surface. A first dielectric layer is formed on the shield layer. A first wire layer is formed on the first dielectric layer, wires on the first wire layer run in a first direction. A second dielectric layer is formed on the first wire layer. A second wire layer is formed on the second dielectric layer, wires on said second wire layer are orthogonal to wires on the first wire layer. The TC camera is protected by a surface dielectric layer. Wires on the first wire layer and second wire layer are grouped into groups of parallel wires with a turnaround at one end of each said group and a sensor pad at the opposite end. Each group of parallel wires includes five silver wires spaced a half a centimeter apart.
    Type: Application
    Filed: March 13, 2001
    Publication date: January 3, 2002
    Applicant: National Aeronautics and Space Administration
    Inventor: John M. Vranish
  • Patent number: 6335654
    Abstract: An inrush current control circuit having an input terminal connected to a DC power supply and an output terminal connected to a load capacitor limits the inrush current that charges up the load capacitor during power up of a system. When the DC power supply applies a DC voltage to the input terminal, the inrush current control circuit produces a voltage ramp at the load capacitor instead of an abrupt DC voltage. The voltage ramp results in a constant low level current to charge up the load capacitor, greatly reducing the current drain on the DC power supply.
    Type: Grant
    Filed: March 17, 2000
    Date of Patent: January 1, 2002
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Steven W. Cole
  • Patent number: 6334302
    Abstract: An engine is disclosed, including a controllable output plasma generator, a controllable heater for selectably raising a temperature of the plasma connected to an outlet of the plasma generator, and a nozzle connected to an outlet of the heater, through which heated plasma is discharged to provide thrust. In one embodiment, the source of plasma is a helicon generator. In one embodiment, the heater is an ion cyclotron resonator. In one embodiment, the nozzle is a radially diverging magnetic field disposed on a discharge side of the heater so that helically travelling particles in the heater exit the heater at high axial velocity. A particular embodiment includes control circuits for selectably directing a portion of radio frequency power from an RF generator to the helicon generator and to the cyclotron resonator so that the thrust output and the specific impulse of the engine can be selectively controlled. A method of propelling a vehicle is also disclosed.
    Type: Grant
    Filed: June 28, 1999
    Date of Patent: January 1, 2002
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Franklin R. Chang-Diaz
  • Patent number: 6332590
    Abstract: A charging sensor that uses photoemission to directly measure the electrical potential of a spacecraft in orbit relative to the space environment. The photoemission based charging sensor uses photoemission from a photoemitting conductive plate of a charge probe as a reference point for voltage readings and provides direct measurements of spacecraft charging.
    Type: Grant
    Filed: December 23, 1998
    Date of Patent: December 25, 2001
    Assignee: Space Systems/Loral, Inc.
    Inventor: David Oh
  • Patent number: 6330792
    Abstract: A thrust chamber assembly for liquid fueled rocket engines and the method of making it wherein a two-piece mandrel wrapped with a silica tape saturated with a phenolic resin, the tape extending along the mandrel and covering the combustion chamber portion of the mandrel to the throat portion. The phenolic in the tape is cured and the end of the wrap is machined. The remainder of the mandrel is wrapped with a third silica tape. The resin in the third tape is cured and the assembly is machined. The entire assembly is then wrapped with a tow of graphite fibers wetted with an epoxy resin and, after the epoxy resin is cured, the graphite is machined to final dimensions.
    Type: Grant
    Filed: December 22, 2000
    Date of Patent: December 18, 2001
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Charles S. Cornelius, Richard H. Counts, W. Neill Myers, Jeffrey D. Lackey, Warren Peters, Michael D. Shadoan, David L. Sparks, Timothy W. Lawrence