Patents Assigned to The United States of America represented by the Administrator of the National Aeronautics Space Administration
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Patent number: 9549467Abstract: An electronic assembly for use in space missions that includes a PCB and one or more multi-pin CGA devices coupled to the PCB. The PCB has one or more via-in-pad features and each via-in-pad feature comprises a land pad configured to couple a pin of the one or more multi-pin CGA devices to the via. The PCB also includes a plurality of layers arranged symmetrically in a two-halves configuration above and below a central plane of the PCB.Type: GrantFiled: September 30, 2013Date of Patent: January 17, 2017Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: David J. Petrick, Luan Vo, Dennis Albaijes
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Patent number: 9541148Abstract: A process for forming a high temperature single crystal canted spring is provided. In one embodiment, the process includes fabricating configurations of a rapid prototype spring to fabricate a sacrificial mold pattern to create a ceramic mold and casting a canted coiled spring to form at least one canted coil spring configuration based on the ceramic mold. The high temperature single crystal canted spring is formed from a nickel-based alloy containing rhenium using the at least one coil spring configuration.Type: GrantFiled: August 15, 2013Date of Patent: January 10, 2017Assignee: The United States of America as Represented by the Administrator of National Aeronautics and Space AdministrationInventors: Jeffrey J DeMange, Frank J Ritzert, Michael V Nathal, Patrick H Dunlap, Bruce M Steinetz
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Patent number: 9531077Abstract: A flexible microwave antenna having a “fish-scale” ground plane is provided. The approach represents a significant advance in the combined thickness and flexibility that can be achieved, especially when using relatively thick substrates which are important for optimum antenna performance. An increase in gain was observed when bent in a positive radius of curvature and further reduction of back radiation.Type: GrantFiled: April 20, 2015Date of Patent: December 27, 2016Assignees: University of South Florida, Raytheon Company, The United States of America, as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Thomas Weller, David Cure, Paul A. Herzig, Felix Miranda
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Patent number: 9528192Abstract: Methods and devices for reducing CO2 to produce hydrocarbons are disclosed. A device comprises a photoanode capable of splitting H2O into electrons, protons, and oxygen; an electrochemical cell cathode comprising an electro-catalyst capable of reducing CO2; H2O in contact with the surface of the photoanode; CO2 in contact with the surface of the cathode; and a proton-conducting medium positioned between the photoanode and the cathode. Electrical charges associated with the protons and the electrons move from the photoanode to the cathode, driven in part by a chemical potential difference sufficient to drive the electrochemical reduction of CO2 at the cathode. A light beam is the sole source of energy used to drive chemical reactions. The photoanode can comprise TiO2 nanowires or nanotubes, and can also include WO3 nanowires or nanotubes, quantum dots of CdS or PbS, and Ag or Au nanostructures.Type: GrantFiled: July 31, 2013Date of Patent: December 27, 2016Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Bin Chen
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Patent number: 9523577Abstract: A vibrating gyroscope includes a piezoelectric strip having length and width dimensions. The piezoelectric strip includes a piezoelectric material and carbon nanotubes (CNTs) substantially aligned and polled along the strip's length dimension. A spindle having an axis of rotation is coupled to the piezoelectric strip. The axis of rotation is parallel to the strip's width dimension. A first capacitance sensor is mechanically coupled to the spindle for rotation therewith. The first capacitance sensor is positioned at one of the strip's opposing ends and is spaced apart from one of the strip's opposing faces. A second capacitance sensor is mechanically coupled to the spindle for rotation therewith. The second capacitance sensor is positioned at another of the strip's opposing ends and is spaced apart from another of the strip's opposing faces. A voltage source applies an AC voltage to the piezoelectric strip.Type: GrantFiled: February 27, 2014Date of Patent: December 20, 2016Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Dennis Stephen Tucker
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Patent number: 9523768Abstract: A method according to an illustrative embodiment includes generating first, second, third, and fourth signals. The method also includes transmitting from an antenna, the first signal, and transmitting the antenna, the second signal. The first and second signals are configured such that when the signals are transmitted simultaneously the signals constructively interact to form a first beam signal. The first beam signal has a first look angle. The method also includes transmitting from the antenna the third signal and from the antenna the fourth signal. The third and fourth signals are configured such that when the signals are transmitted simultaneously the signals constructively interact to form a second beam signal. The second beam signal has a second look angle. The method also includes receiving a first and second reflected signals and generating an interferogram utilizing information in the first and second reflected signals.Type: GrantFiled: September 30, 2014Date of Patent: December 20, 2016Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Rafael F. Rincon
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Patent number: 9521753Abstract: A vibration damping circuit card assembly includes a populated circuit card having a mass M. A closed metal container is coupled to a surface of the populated circuit card at approximately a geometric center of the populated circuit card. Tungsten balls fill approximately 90% of the metal container with a collective mass of the tungsten balls being approximately (0.07) M.Type: GrantFiled: March 4, 2014Date of Patent: December 13, 2016Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Ronald Allen Hunt
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Patent number: 9515531Abstract: Flywheel systems are disclosed that provide increased energy density and operational effectiveness. A first bearingless motor and a second bearingless motor may be configured to simultaneously suspend the central rotor in a radial direction and to rotate the central rotor. However, certain implementations may have one motor or more than two motors, depending on the design. A plurality of the flywheel systems may be collectively controlled to perform community energy storage with higher storage capacities than individual flywheel systems.Type: GrantFiled: December 21, 2012Date of Patent: December 6, 2016Assignee: The United States of America as Represented by the Administrator of National Aeronautics and Space AdministrationInventors: Ralph H Jansen, Larry M Trase, Timothy P Dever, Peter E Kascak, Thomas G Kraft
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Patent number: 9514734Abstract: An improved acoustic liner for turbine engines is disclosed. The acoustic liner may include a straight cell section including a plurality of cells with straight chambers. The acoustic liner may also include a bent cell section including one or more cells that are bent to extend chamber length without increasing the overall height of the acoustic liner by the entire chamber length. In some cases, holes are placed between cell chambers in addition to bending the cells, or instead of bending the cells.Type: GrantFiled: June 29, 2012Date of Patent: December 6, 2016Assignee: The United States of America as Represented by the Administrator of National Aeronautics and Space AdministrationInventors: Michael G Jones, Joseph E Grady, James D. Kiser, Christopher Miller, James D. Heidmann
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Patent number: 9505134Abstract: A lower robotic arm includes a base structure, a plurality of digits, and a plurality of tendons. The digits each include first, second, third, and fourth phalanges. Each digit is operatively attached to the base structure at the respective first phalange. A first joint operatively connects the first and second phalange to define a first axis, a second operatively connects the second and third phalange to define a second axis, and a third joint operatively connects the third and fourth phalange to define a third axis, such that the phalanges are selectively rotatable relative to the adjacent phalange, about the respective axis. The tendons are operatively connected to a respective one of the fourth phalanges. Each tendon selectively applies a first torque to the respective fourth phalange to urge the respective phalanges to rotate in a first direction about the respective axes.Type: GrantFiled: April 17, 2015Date of Patent: November 29, 2016Assignees: GM Global Technology Operations LLC, The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Raymond Guo, Lyndon Bridgwater, Vienny Nguyen, Nicolaus A. Radford
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Patent number: 9506571Abstract: A cryogenic cam butterfly valve has a body that includes an axially extending fluid conduit formed there through. A disc lug is connected to a back side of a valve disc and has a circular bore that receives and is larger than a cam of a cam shaft. The valve disc is rotatable for a quarter turn within the body about a lug axis that is offset from the shaft axis. Actuating the cam shaft in the closing rotational direction first causes the camming side of the cam of the cam shaft to rotate the disc lug and the valve disc a quarter turn from the open position to the closed position. Further actuating causes the camming side of the cam shaft to translate the valve disc into sealed contact with the valve seat. Opening rotational direction of the cam shaft reverses these motions.Type: GrantFiled: August 19, 2014Date of Patent: November 29, 2016Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Kenneth J. McCormack
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Patent number: 9508885Abstract: The present invention relates to a graphene field effect transistor-based radiation sensor for use in a variety of radiation detection applications, including manned spaceflight missions. The sensing mechanism of the radiation sensor is based on the high sensitivity of graphene in the local change of electric field that can result from the interaction of ionizing radiation with a gated undoped silicon absorber serving as the supporting substrate in the graphene field effect transistor. The radiation sensor has low power and high sensitivity, a flexible structure, and a wide temperature range, and can be used in a variety of applications, particularly in space missions for human exploration.Type: GrantFiled: September 2, 2015Date of Patent: November 29, 2016Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Mary J. Li, Zhihong Chen
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Patent number: 9499882Abstract: A composite material includes a structural material and a shape-memory alloy embedded in the structural material. The shape-memory alloy changes crystallographic phase from austenite to martensite in response to a predefined critical macroscopic average strain of the composite material. In a second embodiment, the composite material includes a plurality of particles of a ferromagnetic shape-memory alloy embedded in the structural material. The ferromagnetic shape-memory alloy changes crystallographic phase from austenite to martensite and changes magnetic phase in response to the predefined critical macroscopic average strain of the composite material.Type: GrantFiled: January 11, 2010Date of Patent: November 22, 2016Assignee: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONInventors: Terryl A. Wallace, Stephen W. Smith, Robert S. Piascik, Michael R. Horne, Peter L. Messick, Joel A. Alexa, Edward H. Glaessgen, Benjamin T. Hailer
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Patent number: 9494044Abstract: The present invention is a turbojet design that integrates power generation into the turbojet itself, rather than use separate generators attached to the turbojet for power generation. By integrating the power generation within the jet engine, the weight of the overall system is significantly reduced, increasing system efficiency. Also, by integrating the power generating elements of the system within the air flow of the jet engine, the present invention can use the heat generated by the power generating elements (which is simply expelled waste heat in current designs) to increase the engine performance.Type: GrantFiled: April 2, 2014Date of Patent: November 15, 2016Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space AdministrationInventor: Kurt J Kloesel
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Patent number: 9493635Abstract: Stable dispersions of carbon nanotubes (CNTs) in polymeric matrices include CNTs dispersed in a host polymer or copolymer whose monomers have delocalized electron orbitals, so that a dispersion interaction results between the host polymer or copolymer and the CNTs dispersed therein. Nanocomposite products, which are presented in bulk, or when fabricated as a film, fiber, foam, coating, adhesive, paste, or molding, are prepared by standard means from the present stable dispersions of CNTs in polymeric matrices, employing dispersion interactions, as presented hereinabove.Type: GrantFiled: December 22, 2006Date of Patent: November 15, 2016Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Kristopher Eric Wise, Cheol Park, Jin Ho Kang, Emilie J. Siochi, Joycelyn S. Harrison
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Patent number: 9494143Abstract: Ion optics for use in a conventional or annular or other shaped ion thruster are disclosed including a plurality of planar, spaced apart ion optic electrode pairs sized to include a diameter smaller than the diameter of thruster exhaust and retained in, on or otherwise associated with a frame across the thruster exhaust. An electrical connection may be provided for establishing electrical connectivity among a set of first upstream electrodes and an electrical connection may be provided for establishing electrical connectivity among the second downstream electrodes.Type: GrantFiled: January 10, 2014Date of Patent: November 15, 2016Assignee: The United States of America as Represented by the Administrator of National Aeronautics and Space AdministrationInventor: Michael J. Patterson
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Patent number: 9497846Abstract: A plasma generator includes a pair of identical spiraled electrical conductors separated by dielectric material. Both spiraled conductors have inductance and capacitance wherein, in the presence of a time-varying electromagnetic field, the spiraled conductors resonate to generate a harmonic electromagnetic field response. The spiraled conductors lie in parallel planes and partially overlap one another in a direction perpendicular to the parallel planes. The geometric centers of the spiraled conductors define endpoints of a line that is non-perpendicular with respect to the parallel planes. A voltage source coupled across the spiraled conductors applies a voltage sufficient to generate a plasma in at least a portion of the dielectric material.Type: GrantFiled: October 22, 2014Date of Patent: November 15, 2016Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: George N. Szatkowski, Kenneth L. Dudley, Larry A. Ticatch, Laura J. Smith, Sandra V. Koppen, Truong X. Nguyen, Jay J. Ely
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Patent number: 9488312Abstract: Disclosed herein is a lubrication device comprising a solid lubricant disposed between and in contact with a first electrode and a second electrode dimensioned and arranged such that application of an electric potential between the first electrode and the second electrode sufficient to produce an electric arc between the first electrode and the second electrode to produce a plasma in an ambient atmosphere at an ambient pressure which vaporizes at least a portion of the solid lubricant to produce a vapor stream comprising the solid lubricant. Methods to lubricate a surface utilizing the lubrication device in-situ are also disclosed.Type: GrantFiled: January 9, 2014Date of Patent: November 8, 2016Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Richard R. Hofer, Donald B. Bickler, Saverio A. D'Agostino
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Patent number: 9488607Abstract: A multi-purpose, cylindrical thermal insulation test apparatus is used for testing insulation materials and systems of materials using a liquid boil-off calorimeter system for absolute measurement of the effective thermal conductivity (k-value) and heat flux of a specimen material at a fixed environmental condition (cold-side temperature, warm-side temperature, vacuum pressure level, and residual gas composition). An inner vessel receives liquid with a normal boiling point below ambient temperature, such as liquid nitrogen, enclosed within a vacuum chamber. A cold mass assembly, including upper and lower guard chambers and middle test vessel, is suspended from a lid of the vacuum canister. Each of the three chambers is filled and vented through a single feedthrough. All fluid and instrumentation feedthroughs are mounted and suspended from a top domed lid allowing easy removal of the cold mass. A lift mechanism allows manipulation of the cold mass assembly and insulation test article.Type: GrantFiled: November 26, 2013Date of Patent: November 8, 2016Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space AdministrationInventors: James E. Fesmire, Adam G. Dokos
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Patent number: 9491118Abstract: A nanoionic switch connected to one or more rectenna modules is disclosed. The rectenna module is configured to receive a wireless signal and apply a first bias to change a state of the nanoionic switch from a first state to a second state. The rectenna module can receive a second wireless signal and apply a second bias to change the nanoionic switch from the second state back to the first state. The first bias is generally opposite of the first bias. The rectenna module accordingly permits operation of the nanoionic switch without onboard power.Type: GrantFiled: October 5, 2012Date of Patent: November 8, 2016Assignee: The United States of America as Represented by the Administrator of National Aeronautics and Space AdministrationInventors: James A. Nessel, Felix A Miranda