U.S.A. as Represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Banks, Daniel W
Heineck, James T
Abstract
An air-to-air background-oriented schlieren system in which reference frames are acquired concurrently with the image frames, recording a target aircraft from a sensor aircraft flying in formation, while concurrently recording reference frames of underlying terrain to provide a visually textured background as a reference. This auto-referencing method improves the original AirBOS method by allowing a much more flexible and useful measurement, reducing the flight planning and piloting burden, and broadening the possible camera choices to acquire imaging of visible density changes in air that cause a refractive index change by an airborne vehicle.
U.S.A, as Represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Strutner, Scott Michael
Barra, Anthony
Carman, Gregory Paul
Richards, William Lance
Peña, Francisco
Abstract
A system for measuring magnetic field gradients comprising a multi-bay support structure with a series of raised contact shoulders separated from each other by voids. An optical fiber is spaced along the length of the multi-cell support structure and traverses all the raised contact points and voids. The optical fiber has a plurality of Fiber Bragg gratings (FBGs) spaced lengthwise, each FBG suspended in a void. In addition, a plurality of ferromagnetic members are strung onto the optical fiber, each suspended in a void. Magnetic field gradients act on the ferromagnetic member to create localized tension in the optical fiber. The FBG's refractive indices are monitored, tension is calculated therefrom, and the tension is correlated to the magnetic field gradient. This greatly simplifies mechanical, optical, electronic and computational complexity and is bay suited for any FOSS array for measuring magnetic fields using many dense measurement points.
U.S.A. as Represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Chan, Hon Man
Parker, Jr., Allen R.
Abstract
A method and system for using a wavelength tunable semiconductor laser as an excitation source of a fiber optics sensing system (FOSS) based on a thermoelectric control of a laser sweep. A device can include an optical fiber; a set of fiber Bragg gratings disposed within the optical fiber; a single-frequency laser (SFL) operatively connected to the optical fiber; a thermoelectric cooler operatively connected to the SFL; a controller comprising a processor in communication with the thermoelectric cooler; and a nontransitory, computer-readable storage medium in communication with the processor. The nontransitory, computer-readable storage medium can store instructions that, when executed by the processor, cause the processor to perform operations including determining a strain value at a first fiber Bragg grating of the set of fiber Bragg gratings based on a second laser signal received at the device that is reflected from an interaction of a first laser signal with the first fiber Bragg grating.
H01S 3/10 - Controlling the intensity, frequency, phase, polarisation or direction of the emitted radiation, e.g. switching, gating, modulating or demodulating
H01S 5/06 - Arrangements for controlling the laser output parameters, e.g. by operating on the active medium
H01S 5/062 - Arrangements for controlling the laser output parameters, e.g. by operating on the active medium by varying the potential of the electrodes
U.S.A, as Represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
West, William C.
Abstract
An electrocaloric-based cooling system includes a solid electrolyte, which includes a silver conducting electrolyte sandwiched between a first electrode and a second electrode. The solid electrolyte when biased shows an electrocaloric effect.
USA as Represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Fang, Xiaomei
Hertel, Christopher J.
Riehl, John D.
Connell, John W.
Palmieri, Frank L.
Hopkins, John W.
Abstract
2 and a laser speed between 25.4 cm/s and 127 cm/s. The laser may generate an open pore oxide layer on the contact surface of the substrate with a thickness of 0.1-1 μm, an open pore distance of 0.05-1 μm. The open pore oxide layer may have a topography corresponding to the predefined geometric pattern. The topography may contain open pore structures and promote adhesive bond performance.
B23K 26/359 - Working by laser beam, e.g. welding, cutting or boring for surface treatment by providing a line or line pattern, e.g. a dotted break initiation line
B23K 26/0622 - Shaping the laser beam, e.g. by masks or multi-focusing by direct control of the laser beam by shaping pulses
U.S.A. as Represented by the Administration of the National Aeronautics and Space Administration (USA)
Inventor
Ko, William L
Fleischer, Van T
Lung, Shun-Fat
Abstract
The invention is a method for obtaining the curved displacement of a flexible structure by using strain measurements obtained by strain sensors. By obtaining the displacement of structures in this manner, one may accurately construct the deformed shape of the structure under large geometric nonlinear deformations and display said deformed shape in real-time, enabling active control of the structure shape if desired.
G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
G01B 7/16 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring the deformation in a solid, e.g. by resistance strain gauge
USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Mogford, Richard Hugh
Evans, Cody Allan
Abstract
A software tool assists airline dispatchers and other professionals in management of winter weather events at airports. The flight awareness collaboration tool (FACT) may gather pertinent weather information, air traffic information, airport information, and any other suitable information onto one display screen. FACT can be used by airline dispatchers to manage the airline fleet prior to during the day of a winter weather event, and may have built-in automation tools that can predict the impact of winter weather on airport capacity. FACT may be designed to support collaboration between the airline dispatcher, the air traffic control tower, the airport authority, and de-icing operators on the ground.
G06F 3/0481 - Interaction techniques based on graphical user interfaces [GUI] based on specific properties of the displayed interaction object or a metaphor-based environment, e.g. interaction with desktop elements like windows or icons, or assisted by a cursor's changing behaviour or appearance
G06F 3/0482 - Interaction with lists of selectable items, e.g. menus
8.
Robotic gripper for autonomous rendezvous and capture of satellites
U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Ashmore, Matthew S.
Abstract
A robotic gripper for rigidly grasping a section of a Marman ring of a satellite, the robotic gripper having an outboard jaw which interfaces to an outer diameter side of the Marman ring, a inboard jaw which interfaces to an inner diameter side of the Marman ring, and a palm which interfaces to a separation surface of the Marman ring. The jaws, when grasping the section of the Marman ring, execute a two-stage motion comprising a first movement toward the opposing jaw in a direction parallel to the palm, and a second movement of drawing the Marman ring down against the palm or other suitable surface in order to fully rigidize the grasp.
U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Burt, Irving Joseph
Abstract
A capsulation satellite module for transferring a payload by an earth-launch vehicle to an outer space. The capsulation satellite module comprises a casing defining a hermetically sealed inner cavity therewithin. The casing includes a continuous sidewall and first and second cover assemblies mounted to axially opposite sides of the sidewall so as to delimit the hermetically sealed inner cavity within the casing. The first cover assembly defines a first gas chamber therein extending over the inner cavity of the casing. The second cover assembly defines a second gas chamber therein extending over the inner cavity of the casing. Each of the first gas chamber and the second gas chamber are fluidly connected to the sealed inner cavity and to each other through the sealed inner cavity to maintain predetermined pressure and temperature within the cavity.
B65D 81/18 - Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents providing specific environment for contents, e.g. temperature above or below ambient
B64G 1/50 - Arrangements or adaptations of devices for control of environment or living conditions for temperature control
B64G 1/48 - Arrangements or adaptations of devices for control of environment or living conditions for treatment of the atmosphere
B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Hocker, John-Andrew S.
Park, Cheol
Chu, Sang-Hyon
Kang, Jin Ho
Fay, Catharine C.
Abstract
A lightweight flexible BNNT mat or fabric provides improved thermal stability and shielding capabilities under a hypersonic thermal flux. The BNNT mat reduces the stagnation temperature and maintains a low regression rate. An in-situ passivation layer may be formed on the BNNT mat or fabric under high thermal flux. The passivation layer minimizes or prevents penetration of the atmosphere (air or gas) as well as heat and radiation through the thickness of the BNNT material, and it effectively diffuses heat throughout the mat or fabric laterally and radially to minimize localized excessive heat. A BNNT mat according to the present disclosure may also efficiently transfer heat from the BNNT material via radiation due to the high thermal emissivity (0.92) of the BNNT material.
U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Raven, Hans
Ashmore, Matthew
Schulze, Erich
Abstract
A Cooperative Service Valve includes a fitting connected to a valve body via a tube, a stem configured to fit within the valve body. The stem includes a stem first end having a first seal and configured to movably fit within a tube first end, a sealing portion connected to the stem first end and configured, in a first position, to provide a second seal between the sealing portion and an inner surface of the stem body, a fluid flow portion comprising openings for allowing liquid or gaseous media to pass through the Cooperative Service Valve when the stem is in a second position and a stem second end configured to secure a poppet guide, a poppet and a spring associated with the poppet that biases the poppet against a seal to yield a third seal. The first, second and third seals open and close in a particular order to allow or prevent fluid from flowing through the stem.
U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Bly, Vincent T.
Abstract
The present invention relates to a high resolution additive manufacturing method, including: creating a rigid shell of a stable material on all surfaces except for a sprue of a three dimensional (3D) polymer part using a chemical vapor deposition (CVD) process which includes: depositing the stable material at a process temperature of 100° C. or less, and operating at, or near, atmospheric pressure; and removing the 3D polymer part by accessing the inside of the rigid shell through the sprue to allow dissolution of the 3D polymer part, thereby leaving a replicated rigid shell of the stable material.
C23C 16/01 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes on temporary substrates, e.g. on substrates subsequently removed by etching
C23C 16/16 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of metallic material from metal carbonyl compounds
C23C 16/44 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating
C23C 16/452 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for generating reactive gas streams, e.g. by evaporation or sublimation of precursor materials by activating reactive gas streams before introduction into the reaction chamber, e.g. by ionization or by addition of reactive species
B33Y 80/00 - Products made by additive manufacturing
B29C 64/135 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using layers of liquid which are selectively solidified characterised by the energy source therefor, e.g. by global irradiation combined with a mask the energy source being concentrated, e.g. scanning lasers or focused light sources
13.
Thermal absorption coating on sapphire for epitaxial process
U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Choi, Sang H.
Duzik, Adam J.
Abstract
A method of forming an epitaxial layer on a substrate such as a sapphire wafer that does not readily absorb thermal radiation. The method includes coating a first side surface of the substrate with an energy-absorbing opaque material. The opaque material forms a thermally absorptive coating on the substrate. The coated substrate may be heated to remove contaminants from the thermally absorptive coating. The coated substrate is positioned in a vacuum deposition chamber and heated by directing radiative energy onto the thermally absorptive coating. An epitaxial layer such as GaN or SiGe is formed on a second side surface of the substrate opposite the thermally absorptive coating.
U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Gendreau, Keith C.
Arzoumanian, Zaven
Baker, Robert G.
Dobson, Norman
Koenecke, Richard
Abstract
A multiplexing x-ray fluorescence (MXRF) system and method are provided. The system can include a simple detector that counts x-rays with time resolution. A time-variable applied radiation source is used. The MXRF applied radiation source can produce an excitation spectrum with a peak average energy that grows with time and then recycles. Elemental identification can be achieved by time-correlating x-ray counts detected by the detector, with the time-variable applied radiation field. The system and method provide design flexibility for both commercial and NASA applications.
G01N 23/223 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by measuring secondary emission from the material by irradiating the sample with X-rays or gamma-rays and by measuring X-ray fluorescence
15.
SYNTHESIS OF COPOLYIMIDES CONTAINING FLUORINE AND SILICON SURFACE MODIFYING AGENTS
USA, AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Connell, John, W.
Wohl, Christopher, J.
Doss, Jereme, R.
Crow, Allison, M.
Kim, William, T.
Abstract
Various embodiments provide random copolyimides that may possess the mechanical, thermal, chemical and optical properties associated with polyimides yet achieve a low energy surface. In various embodiments, the copolyimides may be prepared using a minor amounts of a diamino terminated fluorinated alkyl ether oligomer and a diamino terminated siloxane oligomer. The various embodiments include processes for making the copolyimides containing fluorine and silicon surface modifying agents and anisotropic coatings and articles of manufacture from them. Thus the coatings and articles of manufacture made with the copolyimides of the various embodiments may be characterized as having an anisotropic fluorine and silicon composition and low surface energy.
C08G 73/10 - PolyimidesPolyester-imidesPolyamide-imidesPolyamide acids or similar polyimide precursors
C08G 77/24 - Polysiloxanes containing silicon bound to organic groups containing atoms other than carbon, hydrogen, and oxygen halogen-containing groups
B05D 7/24 - Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials for applying particular liquids or other fluent materials
U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Smith, Jr., Joseph G.
Wohl, Jr., Christopher J.
Abstract
Various embodiments provide ice mitigating surface coatings and methods for applying ice mitigating surface coatings. Various embodiment ice mitigating surface coatings may be formed by hydrolysis of one or more substituted n-alkyldimethylalkoxysilanes terminated with functionalities having the following characteristics with respect to water: 1) non-polar interactions; 2) hydrogen bonding through donor and acceptor interactions; or 3) hydrogen bonding through acceptor interactions only. The substituted n-alkyldimethylalkoxysilanes of the various embodiments may include methyl terminated species, hydroxyl terminated species, ethylene glycol terminated species, and methoxyethylene glycol terminated species. Various embodiment ice mitigating surface coatings may be applied to metal surfaces, such as aluminum surfaces. Various embodiment substituted n-alkyldimethylalkoxysilanes may have an aliphatic chain that is saturated and liner or branched or that is partially unsaturated and liner or branched.
B64D 15/00 - De-icing or preventing icing on exterior surfaces of aircraft
C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
U.S.A., AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Zuckerwar, Allan, J.
Shams, Qamar, A.
Dimarcantonio, Albert, L.
Abstract
An infrasonic stethoscope for monitoring physiological processes of a patient includes a microphone capable of detecting acoustic signals in the audible frequency bandwidth and in the infrasonic bandwidth (0.03 to 1000 Hertz), a body coupler attached to the body at a first opening in the microphone, a flexible tube attached to the body at a second opening in the microphone, and an earpiece attached to the flexible tube. The body coupler is capable of engagement with a patient to transmit sounds from the person, to the microphone and then to the earpiece.
U.S.A., AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Dimarcantonio, Albert L.
Shams, Qamar A.
Zuckerwar, Allan J. (deceased)
Abstract
An infrasonic stethoscope for monitoring physiological processes of a patient includes a microphone capable of detecting acoustic signals in the audible frequency bandwidth and in the infrasonic bandwidth (0.03 to 1000 Hertz), a body coupler attached to the body at a first opening in the microphone, a flexible tube attached to the body at a second opening in the microphone, and an earpiece attached to the flexible tube. The body coupler is capable of engagement with a patient to transmit sounds from the person, to the microphone and then to the earpiece.
USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Kang, Jin, Ho
Sauti, Godfrey
Park, Cheol
Gibbons, Luke
Thibeault, Sheila, A.
Lowther, Sharon, E.
Bryant, Robert, G.
Abstract
A novel radiation hardened chip package technology protects microelectronic chips and systems in aviation/space or terrestrial devices against high energy radiation. The proposed technology of a radiation hardened chip package using rare earth elements and multilayered structure provides protection against radiation bombardment from alpha and beta particles to neutrons and high energy electromagnetic radiation.
U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration (USA)
Inventor
Palmieri, Frank L.
Cruz, Vincent B.
Wohl, Jr., Christopher J.
Abstract
A soft lithography template or stamp is made by casting a polydimethysiloxane (PDMS) or other suitable elastomeric precursor onto a master pattern. The master pattern may be formed utilizing known micro-fabrication techniques. The PDMS template includes an inverse copy of the micro-structures on the master pattern, and can be placed into a mold used to prepare a carbon-fiber reinforced polymer composite part or other polymer molding systems where a matrix material passes through a fluid state during the cure process. The liquid resin material flows into the structures on the surface of the PDMS template and hardens during the curing cycle. After the part is released from the mold, the PDMS template can be peeled from the surface of the part to reveal the free standing micro structures which are a replica of the master pattern.
U.S.A., AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Jansen, Ralph, H.
Storozuk, Ronald, J.
Abstract
A touchdown bearing system is provided to safely spin down a magnetically suspended flywheel rotor from full speed when the magnetic suspension system fails. In one embodiment, a plurality of touchdown wheels are mounted on a rigid support ring in a planetary arrangement. The support ring is mounted to a stationary structure of a flywheel system.
F16C 17/20 - Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with emergency supports or bearings
U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Kang, Jin Ho
Bryant, Robert G.
Park, Cheol
Sauti, Godfrey
Gibbons, Luke
Lowther, Sharon
Thibeault, Sheila A.
Fay, Catharine C.
Abstract
Multifunctional Boron Nitride nanotube-Boron Nitride (BN-BN) nanocomposites for energy transducers, thermal conductors, anti-penetrator/wear resistance coatings, and radiation hardened materials for harsh environments. An all boron-nitride structured BN-BN composite is synthesized. A boron nitride containing precursor is synthesized, then mixed with boron nitride nanotubes (BNNTs) to produce a composite solution which is used to make green bodies of different forms including, for example, fibers, mats, films, and plates. The green bodies are pyrolized to facilitate transformation into BN-BN composite ceramics. The pyrolysis temperature, pressure, atmosphere and time are controlled to produce a desired BN crystalline structure. The wholly BN structured materials exhibit excellent thermal stability, high thermal conductivity, piezoelectricity as well as enhanced toughness, hardness, and radiation shielding properties. By substituting with other elements into the original structure of the nanotubes and/or matrix, new nanocomposites (i.e., BCN, BCSiN ceramics) which possess excellent hardness, tailored photonic bandgap and photoluminescence, result.
U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Kang, Jin Ho
Bryant, Robert, G.
Park, Cheol
Sauti, Godfrey
Gibbons, Luke
Lowther, Sharon
Thibeault, Sheila, A.
Fay, Catharine, C.
Abstract
Multifunctional Boron Nitride nanotube-Boron Nitride (BN-BN) nanocomposites for energy transducers, thermal conductors, anti-penetrator/wear resistance coatings, and radiation hardened materials for harsh environments. An all boron-nitride structured BN-BN composite is synthesized. A boron nitride containing precursor is synthesized, then mixed with boron nitride nanotubes (BNNTs) to produce a composite solution which is used to make green bodies of different forms including, for example, fibers, mats, films, and plates. The green bodies are pyrolized to facilitate transformation into BN-BN composite ceramics. The pyrolysis temperature, pressure, atmosphere and time are controlled to produce a desired BN crystalline structure. The wholly BN structured materials exhibit excellent thermal stability, high thermal conductivity, piezoelectricity as well as enhanced toughness, hardness, and radiation shielding properties. By substituting with other elements into the original structure of the nanotubes and/or matrix, new nanocomposites (i.e., BCN, BCSiN ceramics) which possess excellent hardness, tailored photonic bandgap and photoluminescence, result.
U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Quinn, Jacqueline W.
Clausen, Christian A.
Yestrebsky, Cherie L.
Captain, James G.
Devor, Robert W.
Maloney, Phillip R.
Abstract
A treatment system and a method for removal of at least one halogenated compound, such as PCBs, found in contaminated systems are provided. The treatment system includes a polymer blanket for receiving at least one non-polar solvent. The halogenated compound permeates into or through a wall of the polymer blanket where it is solubilized with at least one non-polar solvent received by said polymer blanket forming a halogenated solvent mixture. This treatment system and method provides for the in situ removal of halogenated compounds from the contaminated system. In one embodiment, the halogenated solvent mixture is subjected to subsequent processes which destroy and/or degrade the halogenated compound.
U.S.A AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Quinn, Jaqueline, W.
Clausen, Christian, A.
Yestrebsky, Cherie, L.
Abstract
A treatment system and a method for removal of at least one halogenated compound, such as PCBs, found in contaminated systems are provided. The treatment system includes a polymer blanket for receiving at least one non-polar solvent. The halogenated compound permeates into or through a wall of the polymer blanket where it is solubilized with at least one non-polar solvent received by said polymer blanket forming a halogenated solvent mixture. This treatment system and method provides for the in situ removal of halogenated compounds from the contaminated system. In one embodiment, the halogenated solvent mixture is subjected to subsequent processes which destroy and/or degrade the halogenated compound.
B01D 61/00 - Processes of separation using semi-permeable membranes, e.g. dialysis, osmosis or ultrafiltrationApparatus, accessories or auxiliary operations specially adapted therefor
A62D 3/34 - Dehalogenation using reactive chemical agents able to degrade
26.
EFFICIENT BORON NITRIDE NANOTUBE FORMATION VIA COMBINED LASER-GAS FLOW LEVITATION
USA as represented by THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Whitney, R., Roy
Jordan, Kevin
Smith, Michael, W.
Abstract
A process for producing boron nitride nanotubes and/or boron-carbon- nitrogen nanotubes of the general formula BxCyNz. The process utilizes a combination of laser light and nitrogen gas flow to support a boron ball target during heating of the boron ball target and production of a boron vapor plume which reacts with nitrogen or nitrogen and carbon to produce boron nitride nanotubes and/or boron-carbon-nitrogen nanotubes of the general formula BxCyNz.
USA as represented by the Administrator of the National, Aeronautics and Space Administration (USA)
Inventor
Smith, Michael, W.
Jordan, Kevin
Abstract
An integrated production apparatus for production of boron nitride nanotubes via the pressure vapor-condenser method. The apparatus comprises: a pressurized reaction chamber containing a continuously fed boron containing target having a boron target tip, a source of pressurized nitrogen and a moving belt condenser apparatus; a hutch chamber proximate the pressurized reaction chamber containing a target feed system and a laser beam and optics.
USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL, AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Jordan, Kevin
Whitney, R., Roy
Smith, Michael, W.
Kim, Jae-Woo
Park, Cheol
Abstract
Nanotube filaments comprising carbon, boron and nitrogen of the general formula BxCyNz, having high-aspect ratio and high-crystallinity produced by a pressurized vapor/ condenser method and a process of production. The process comprises thermally exciting a boron-containing target in a chamber containing a carbon source and nitrogen at a pressure which is elevated above atmospheric pressure.
B01J 19/12 - Processes employing the direct application of electric or wave energy, or particle radiationApparatus therefor employing electromagnetic waves
THE U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Linn, Douglas Martin
Ambrose, Robert, O.
Diftler, Myron A.
Askew, Scott R.
Platt, Robert
Mehl Ing, Joshua S.
Radford, Nicolaus A.
Strawser, Phillip A.
Bridgwater, Lyndon
Wampler Ii. Charles W.
Abdallah, Muhammad E.
Ihrke, Chris A.
Reiland, Matthew J.
Sanders, Adam M.
Reich, David M.
Hargrave, Brian
Parsons, Adam H.
Permenter, Frank Noble
Davis, Donald R.
Abstract
A humanoid robot includes a torso, a pair of arms, two hands, a neck, and a head. The torso extends along a primary axis and presents a pair of shoulders. The pair of arms movably extend from a respective one of the pair of shoulders. Each of the arms has a plurality of arm joints. The neck movably extends from the torso along the primary axis. The neck has at least one neck joint. The head movably extends from the neck along the primary axis. The head has at least one head joint. The shoulders are canted toward one another at a shrug angle that is defined between each of the shoulders such that a workspace is defined between the shoulders.
U.S.A AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Moore, Jason, P.
Abstract
A method of determining the shape of an unbound optical fiber includes collecting strain data along a length of the fiber, calculating curvature and bending direction data of the fiber using the strain dala. curve-fitting the curvature and bending direction data to derive curvature and bending direction functions, calculating a torsion function using the bending direction function, and determining the 3D shape from the curvature, bending direction, and torsion functions. An apparatus for determining the 3D shape of the fiber includes a fiber optic cable unbound with respect to a protective sieeve, strain sensors positioned along the cable, and a controller in communication with the sensors. The controller has an algorithm for determining a 3D shape and end position of the fiber by calculating a set of curvature and bending direction data, deriving curvature, bending, and torsion functions, and solving Frenet-Serret equations using these functions.
U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Woodard, Stanley, E.
Taylor, Bryant, Douglas
Abstract
A wireless electrical device includes an electrically unconnected electrical conductor and at least one electrically unconnected electrode spaced apart from the electrical conductor. The electrical conductor is shaped for storage of an electric field and a magnetic field. In the presence of a time-varying magnetic field, the electrical conductor so- shaped resonates to generate harmonic electric and magnetic field responses. Each electrode is at a location lying within the magnetic field response so- generated and is constructed such that a linear movement of electric charges is generated in each electrode due to the magnetic field response so-generated.
U.S.A. as represented by THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Choi, Sang, H.
Park, Yeonjoon
King, Glen, C.
Elliott, James, R.
Abstract
An embodiment generally relates to an optical device suitable for use with an optical medium for the storage and retrieval of data. The optical device includes an illumination means for providing a beam of optical radiation of wavelength λ and an optical path that the beam of optical radiation follows. The optical device also includes a diffractive optical element defined by a plurality of annular sections. The plurality of annular sections having a first material alternately disposed with a plurality of annular sections comprising a second material. The diffractive optical element generates a plurality of focal points and densely accumulated ray points with phase contrast phenomena and the optical medium is positioned at a selected focal point or ray point of the diffractive optical element.
G11B 7/00 - Recording or reproducing by optical means, e.g. recording using a thermal beam of optical radiation, reproducing using an optical beam at lower powerRecord carriers therefor
33.
ARRAYED MICRO-RING SPECTROMETER SYSTEM AND METHOD OF USE
U.S.A AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Choi, Sang, H.
Park, Yeonjoon
King, Glen, C.
Elliott, James, R.
Abstract
A spectrometer system includes an array of micro-zone piates (MZP) each having coaxial ly-aligned ring gratings, a sample plate for supporting and illuminating a sample, and an array of photon detectors for measuring a spectral characteristic of the predetermined wavelength. The sample plate emits an evanescent wave in response to incident light, which excites molecules of the sample to thereby cause an emission of secondary photons. A method of detecting the intensity of a selected wavelength of incident iight includes directing the incident light onto an array of MZP. diffracting a selected wavelength of the incident light onto a target focal point using the array of MZP, and detecting the intensity of the selected portion using an array of photon detectors. An electro-optic layer positioned adjacent to the array of MZP may be excited via an applied voltage to select the wavelength of the incident light.
U.S.A. as represented by THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Quinn, Jaqueline, W.
Clausen, Christian, A.
Geiger, Cherie, L.
Abstract
PCBs are removed from contaminated media using a treatment system including zero-valent metal particles and an organic hydrogen donating solvent. The treatment system may include a weak acid in order to eliminate the need for a coating of catalytic noble metal on the zero-valent metal particles. If catalyzed zero-valent metal particles are used, the treatment system may include an organic hydrogen donating solvent that is a non- water solvent. The treatment system may be provided as a "paste-like" system that is preferably applied to natural media and ex-situ structures to eliminate PCBs.
A62D 3/30 - Processes for making harmful chemical substances harmless, or less harmful, by effecting a chemical change in the substances by reacting with chemical agents
C02F 1/68 - Treatment of water, waste water, or sewage by addition of specified substances, e.g. trace elements, for ameliorating potable water
U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Kim, Jae-Woo
Park, Cheol
Lillehei, Peter, T.
Choi, Sang, H.
Harrison, Joycelyn, S.
Abstract
Carbon nano tubes (CNTs) are dispersed in an aqueous buffer solution consisting of at least 50 weight percent water and a remainder weight percent that includes a buffer material. The buffer material has a molecular structure defined by a first end, a second end, and a middle disposed between the first and second ends. The first end is a cyclic ring with nitrogen and oxygen heteroatomes, the middle is a hydrophobic alkyl chain, and the second end is a charged group.
U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Wincheski, Russell, A.
Abstract
An electrospinning system using a spinneret and a counter electrode is first operated for a fixed amount of time at known system and operational parameters to generate a fiber mat having a measured fiber mat width associated therewith. Next, acceleration of the fiberizable material at the spinneret is modeled to determine values of mass, drag, and surface tension associated with the fiberizable material at the spinneret output. The model is then applied in an inversion process to generate predicted values of an electric charge at the spinneret output and an electric field between the spinneret and electrode required to fabricate a selected fiber mat design. The electric charge and electric field are indicative of design values for system and operational parameters needed to fabricate the selected fiber mat design.
U.S.A AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Buckley, John, D.
Edwards, William, C.
Kelliher, Warren, C.
Carlberg, Ingrid, A.
Abstract
A wave energy transmission apparatus has a conduit made from a refractory oxide. A transparent, refractory ceramic window is coupled to the conduit. Wave energy passing through the window enters the conduit.
U.S.A. AS REPRESENTATED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Choi, Sang, H.
Park, Yeonjoon
King, Glen, C.
Elliott, James, R.
Abstract
Growth conditions are developed, based on a temperature-dependent alignment model, to enable formation of cubic group IV, group II-V and group II-VI crystals in the [111] orientation on the basal (0001) plane of trigonal crystal substrates, controlled such that the volume percentage of primary twin crystal is reduced from about 40% to about 0.3%, compared to the majority single crystal. The control of stacking faults in this and other embodiments can yield single crystalline semiconductors based on these materials that are substantially without defects, or improved thermoelectric materials with twinned crystals for phonon scattering while maintaining electrical integrity. These methods can selectively yield a cubic-on-trigonal epitaxial semiconductor material in which the cubic layer is substantially either directly aligned, or 60 degrees-rotated from, the underlying trigonal material.
H01L 21/02 - Manufacture or treatment of semiconductor devices or of parts thereof
H01L 31/117 - Devices sensitive to very short wavelength, e.g. X-rays, gamma-rays or corpuscular radiation of the bulk effect radiation detector type, e.g. Ge-Li compensated PIN gamma-ray detectors
39.
EPITAXIAL GROWTH OF CUBIC CRYSTALLINE SEMICONDUCTOR ALLOYS ON BASAL PLANE OF TRIGONAL OR HEXAGONAL CRYSTAL
U.S.A AS REPRESENTATED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Park, Yeonjoon
Choi, Sang, H.
King, Glen, C.
Abstract
Hetero-epitaxial semiconductor materials comprising cubic crystalline semiconductor alloys grown on the basal plane of trigonal and hexagonal substrates, in which misfit dislocations are reduced by approximate lattice matching of the cubic crystal structure to underlying trigonal or hexagonal substrate structure, enabling the development of alloyed semiconductor layers of greater thickness, resulting in a new class of semiconductor materials and corresponding devices, including improved hetero-bipolar and high-electron mobility transistors, and high-mobility thermoelectric devices.
U.S.A. AS REPRESENTATED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Park, Yeonjoon
Choi, Sang, H.
King, Glen, C.
Elliott, James, R.
Talcott, Noel, A.
Abstract
New thermoelectric materials comprise highly [111] -oriented, twinned group IV alloys on the basal plane of trigonal substrates, which exhibit a high thermoelectric figure of merit and good material performance, and devices made with these materials.
U.S.A. AS REPRESENTATED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Park, Yeonjoon
Choi, Sang, H.
King, Glen, C.
Elliott, James, R.
Abstract
A method provides X-ray diffraction data suitable for integral detection of a twin defect in a strained or lattice-matched epitaxial material made from components having crystal structures having symmetry belonging to different space groups. The material is mounted in an X-ray diffraction (XRD) system. In one embodiment, the XRD system's goniometer angle Ω is set equal to {൘B - β) where ൘B is a Bragg angle for a designated crystal plane of the alloy that is disposed at a non-perpendicular orientation with respect to the (111) crystal plane, and β is the angle between the designated crystal plane and a (111) crystal plane of one of the epitaxial components. The XRD system's detector angle is set equal to (൘B ~ β). The material can be rotated through an angle of azimuthal rotation 섶 about the axis aligned with the material. Using the detector, the intensity of the X-ray diffraction is recorded at least at the angle at which the twin defect occurs.
G01N 23/20 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by using diffraction of the radiation by the materials, e.g. for investigating crystal structureInvestigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by using scattering of the radiation by the materials, e.g. for investigating non-crystalline materialsInvestigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by using reflection of the radiation by the materials
USA as represented by THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Haskin, Henry, H.
Vasquez, Peter
Abstract
A flame holder system includes a modified torch body and a ceramic flame holder. Catch pin(s) are coupled to and extend radially out from the torch body. The ceramic flame holder has groove (s) formed in its inner wall that correspond in number and positioning to the catch pin(s). Each groove starts at one end of the flame holder and can be shaped to define at least two 90° turns. Each groove is sized to receive one catch pin therein when the flame holder is fitted over the end of the torch body. The flame holder is then manipulated until the catch pin(s) butt up against the end of the groove (s).
U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Cantrell, John, H.
Cantrell, Sean, A.
Abstract
A scanning probe microscope and methodology, called resonant difference-frequency atomic force ultrasonic microscopy (RDF-AFUM)5 employs an ultrasonic wave launched from the bottom of a sample while the cantiJever of an atomic force microscope, driven at a frequency differing from the ultrasonic frequency by one of the contact resonance frequencies of the cantilever, engages the sample top surface. The nonlinear mixing of the oscillating cantilever and the ultrasonic wave in the region defined by the cantilever tip- sample surface interaction force generates difference-frequency oscillations at the cantilever contact resonance. The resonance-enhanced difference-frequency signals are used to create images of nanoscale near-surface and subsurface features.
U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Silva, Walter, A.
Abstract
Computational aeroeiastic analyses typically use a mathematical model for the structural modes of a flexible structure and a nonlinear aerodynamic model that can generate a plurality of unsteady aerodynamic responses based on the structural modes for conditions defining an aerodynamic condition of the flexible structure. In the present invention, a linear state-space model is generated using a single execution of the nonlinear aerodynamic model for all of the structural modes where a family of orthogonal functions is used as the inputs. Then, static and dynamic aeroeiastic solutions are generated using computational interaction between the mathematical model and the linear state-space model for a plurality of periodic points in time.
G06F 7/60 - Methods or arrangements for performing computations using a digital non-denominational number representation, i.e. number representation without radixComputing devices using combinations of denominational and non-denominational quantity representations
45.
METHOD OF CALIBRATING A FLUID-LEVEL MEASUREMENT SYSTEM
USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Woodard, Stanley, E.
Taylor, Bryant, Douglas
Abstract
A method of calibrating a fluid-level measurement system is provided. A first response of the system is recorded when the system's sensor (s) is (are) not in contact with a fluid of interest. A second response of the system is recorded when the system's sensor (s) is (are) fully immersed in the fluid of interest. Using the first and second responses, a plurality of expected responses of the system's sensor (s) is (are) generated for a corresponding plurality of levels of immersion of the sensor (s) in the fluid of interest.
USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Palumbo, Daniel, L.
Klos, Jacob
Grosveld, Ferdinand, W.
Castle, William, D.
Abstract
A composite panel has one or more recesses, or smoothly-contoured recesses formed in one or both opposing sides of a core. Reinforcement conforming to each recess is coupled to the core at the recess. First and second facing sneets are respectively coupled to the first and second opposing sides of the core.
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
47.
COMPOSITE MATERIAL HAVING A THERMALLY-REACTIVE-ENDCAPPED IMIDE OLIGOMER AND CARBON NANOFILLERS
U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Connell, John, W.
Siochi, Emilie, J.
Ghose, Sayata
Delozier, Donavon, M.
Watson, Kent, A.
Working, Dennis, C.
Abstract
Embodiments of the invention provide a composite material having sufficient strength to form structural components of an aerospace vehicle, while also having sufficient electrical conductivity to dissipate electrostatic charge. As such, a composite material comprises an imide oligomer having thermally reactive endcaps and carbon nanofillers. The imide oligomer may comprise a phenyl ethynyl terminated imide. The phenylethynyl terminated imide may have a molecular weight of less than about 5000, or may have a molecular weight in the range of about 250 to about 5000. In particular, the phenylethynyl terminated imide may have a molecular weight of about 1500. The carbon nanofillers may be selected from the group consisting of carbon nanotubes, carbon nanofibcrs, expanded graphite, exfoliated graphite and combinations thereof. The carbon nanotubes may be selected from the group consisting of single-walled carbon nanotubes, double-walled carbon nanotubes, multi-walled carbon nanotubes and combinations thereof.
USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Quinn, Jaqueline, W.
Clausen, Christian, A.
Geiger, Cherie, L.
Aitken, Brian, S.
Abstract
A hydrogenation catalyst including a base material coated with a catalytic metal is made using mechanical milling techniques. The hydrogenation catalysts are used as an excellent catalyst for the dehalogenation of contaminated compounds and the remediation of other industrial compounds. Preferably, the hydrogenation catalyst is a bimetallic particle including zero-valent metal particles coated with a catalytic material. The mechanical milling technique is simpler and cheaper than previously used methods for producing hydrogenation catalysts.
B22F 1/02 - Special treatment of metallic powder, e.g. to facilitate working, to improve properties; Metallic powders per se, e.g. mixtures of particles of different composition comprising coating of the powder
B22F 9/04 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from solid material, e.g. by crushing, grinding or milling
A62D 3/30 - Processes for making harmful chemical substances harmless, or less harmful, by effecting a chemical change in the substances by reacting with chemical agents
B01J 35/00 - Catalysts, in general, characterised by their form or physical properties
49.
THERMALLY DRIVEN PISTON ASSEMBLY AND POSITION CONTROL THEREFOR
USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (USA)
Inventor
Thomsen, Donald, L.
Bryant, Robert, G.
Abstract
A thermally driven piston assembly's housing has (i) a first material slidingly fitted therein, and (ii) at least one plug of a second material slidingly fitted therein and abutting the first material. The first material is one (e.g., a liquid crystal elastomer) that undergoes a stiffness change and/or a dimensional change when subjected to a temperature change in the temperature range of interest. When subjected to the temperature change while in the housing, the first material is restricted to changing dimensionally along a single dimension. The second material retains its shape and size throughout the temperature range of interest. As a result, the plug moves in the housing in correspondence with the dimensional change of the first material or the plug's movement is damped by the stiffness change of the first material.
patents
