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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 1,783 records · Page 99
All sourcesNASA NTRSDOE OSTI
NASA NTRS2011

The Track Imaging Cerenkov Experiment

We describe a. dedicated cosmic-ray telescope that explores a new method for detecting Cerenkov radiation from high-energy primary cosmic rays and the large particle air shower they induce upon entering the atmosphere. Using a camera comprising 16 multi-anode photomultiplier tubes for a total of 256 pixels, the Track Imaging Cerenkov Experiment (TrICE) resolves substructures in particle air showers with 0,086 deg resolution. Cerenkov radiation is imaged using a novel two-part optical system in which a Fresnel lens provides a wide-field optical trigger and a mirror system collects delayed light with four times the magnification. TrICE records well-resolved cosmic-ray air showers at rates ranging between 0.01-0.1 Hz.

Wissel, S. A.↗
NASA NTRS2004

Miniature Robotic Spacecraft for Inspecting Other Spacecraft

A report discusses the Miniature Autonomous Extravehicular Robotic Camera (Mini AERCam)-- a compact robotic spacecraft intended to be released from a larger spacecraft for exterior visual inspection of the larger spacecraft. The Mini AERCam is a successor to the AERCam Sprint -- a prior miniature robotic inspection spacecraft that was demonstrated in a space-shuttle flight experiment in 1997. The prototype of the Mini AERCam is a demonstration unit having approximately the form and function of a flight system. The Mini AERCam is approximately spherical with a diameter of about 7.5 in. (.19 cm) and a weight of about 10 lb (.4.5 kg), yet it has significant additional capabilities, relative to the 14-in. (36-cm), 35-lb (16-kg) AERCam Sprint. The Mini AERCam includes miniaturized avionics, instrumentation, communications, navigation, imaging, power, and propulsion subsystems, including two digital video cameras and a high-resolution still camera. The Mini AERCam is designed for either remote piloting or supervised autonomous operations, including station keeping and point-to-point maneuvering. The prototype has been tested on an air-bearing table and in a hardware-in-the-loop orbital simulation of the dynamics of maneuvering in proximity to the International Space Station.

Fredrickson, Steven↗
DOE OSTI2013

Low Dimensional System Hybrids for Advanced Electronics/Optoelectronics [Slides]

Interacting quantum wells: Type II InAs/GaSb superlattice for high performance infrared detection and imaging – CQD, Northwestern University 2005-2011: – Physics of interacting quantum wells: InAs/GaSb superlattice; – M-structure superlattice; – Materials growth and characterization; – Infrared detector operation and optimization strategies; – Infrared Focal Plane Array (aka. infrared camera). Cylindrical quantum Well In a Nanowire (CWIN): Heterostructuring core/multi-shell nanowires for advanced electronic/optoelectronic devices – CINT,LANL 2012-present: – Si-based Nanowire research overview; – Device physics of NWFETs: Diameter dependence performance; – CWIN design for high performance FET; – Growth and characterization of Si/Ge/Si core/multi-shell NWs; – Towards ultra-short channel length NWFETs.

36 MATERIALS SCIENCE↗
DOE OSTI2012

A new compact, high sensitivity neutron imaging system

We have developed a new small neutron imaging system (SNIS) diagnostic for the OMEGA laser facility. The SNIS uses a penumbral coded aperture and has been designed to record images from low yield (10{sup 9}-10{sup 10} neutrons) implosions such as those using deuterium as the fuel. This camera was tested at OMEGA in 2009 on a rugby hohlraum energetics experiment where it recorded an image at a yield of 1.4 Multiplication-Sign 10{sup 10}. The resolution of this image was 54 {mu}m and the camera was located only 4 meters from target chamber centre. We recently improved the instrument by adding a cooled CCD camera. The sensitivity of the new camera has been fully characterized using a linear accelerator and a {sup 60}Co {gamma}-ray source. The calibration showed that the signal-to-noise ratio could be improved by using raw binning detection.

46 INSTRUMENTATION RELATED TO NUCLEAR SCIENCE AND ↗
DOE OSTI2025

Planar laser-induced fluorescence system for spatiotemporal ion velocity distribution function measurements

In this work, we present a planar laser-induced fluorescence (PLIF) system for measuring two-dimensional (2D), spatiotemporally resolved ion velocity distribution functions (IVDFs). A continuous-wave tunable diode laser produces a laser sheet that irradiates the plasma, and the resulting fluorescence is captured by an intensified CCD (ICCD) camera. Fluorescence images recorded at varying laser wavelengths are converted into 2D IVDFs using the Doppler shift principle. The developed diagnostic is implemented in an electron beam generated E × B plasma with a bulk plasma density of $\sim\!\!{10^{10}}{\text{c}}{{\text{m}}^{ - 3}}$ . The developed diagnostic is validated against a conventional single-point LIF method using photomultiplier tube-based detection, while significantly reducing the total measurement time by the number of spatial positions measured. The time-resolving capability of this diagnostic is tested by oscillating the plasma between two nominal operating modes with different density profiles and triggering the ICCD camera by the externally driven plasma oscillation. The measured 2D IVDF maps reveal several signatures of ion dynamics in this plasma source, including radially outflowing ions across the electric field and anomalous ion heating at the periphery, consistent with recent kinetic simulations and theoretical studies. A possible correlation between these ion kinetic features and rotating spoke structures is discussed.

E×B plasma↗
DOE OSTI2014

Imaging of large-area microchannel plates using phosphor screens

A testing system was built, using UV illumination at 254 nm and a cathodoluminescent phosphor screen, to measure the gain uniformity of large area (20 x 20 cm(2)) microchannel plates. The phosphor screen image is captured with a wide-angle CMOS digital camera (4032 x 3024 pixels) and analyzed. First a reference MCP is illuminated and the generated phosphor screen image is captured with a CCD camera. In a second step, another image is captured with the MCP under test inserted between the reference MCP and the phosphor screen. The ratio of the two images is analyzed and provides a quantitative measure of the relative gain uniformity of the MCP under test.

46 INSTRUMENTATION RELATED TO NUCLEAR SCIENCE AND ↗
NASA NTRS1982

Plasma ignition for laser propulsion

For a specific optical system a pulsed carbon dioxide laser having an energy output of up to 15 joules was used to initiate a plasma in air at one atmosphere pressure. The spatial and temporal development of the plasma were measured using a multiframe image converter camera. In addition the time dependent velocity of the laser supported plasma front which moves opposite to the direction of the laser pulse was measured in order to characterize the type of wavefront developed. Reliable and reproducible spark initiation was achieved. The lifetime of the highly dense plasma at the initial focal spot was determined to be less than 100 nanoseconds. The plasma front propagates toward the laser at a variable speed ranging from zero to 1.6 x 1,000,000 m/sec. The plasma front propagates for a total distance of approximately five centimeters for the energy and laser pulse shape employed.

Askew, R. F.↗
NASA NTRS1992

Endoscopic measurements using a panoramic annular lens

The objective of this project was to design, build, demonstrate, and deliver a prototype system for making measurements within cavities. The system was to utilize structured lighting as the means for making measurements and was to rely on a stationary probe, equipped with a unique panoramic annular lens, to capture a cylindrical view of the illuminated cavity. Panoramic images, acquired with a digitizing camera and stored in a desk top computer, were to be linearized and analyzed by mouse-driven interactive software.

Gilbert, John A.↗
NASA NTRS1993

The Mars Observer Camera ground data system

The Mars Observer Camera (MOC), launched on board the Mars Observer spacecraft in September 1992, is to be operated by a small team using large amounts of computer assistance. Here, we describe the architecture of the MOC Ground Data System, which is capable of taking imaging requests, generating imaging command sequences, receiving the acquired images, archiving them, and delivering them in several processed forms to the MOC user community, all with the need for only a limited amount of human interaction.

Caplinger, Michael↗
NASA NTRS1995

PRISM Spectrograph Optical Design

The objective of this contract is to explore optical design concepts for the PRISM spectrograph and produce a preliminary optical design. An exciting optical configuration has been developed which will allow both wavelength bands to be imaged onto the same detector array. At present the optical design is only partially complete because PRISM will require a fairly elaborate optical system to meet its specification for throughput (area*solid angle). The most complex part of the design, the spectrograph camera, is complete, providing proof of principle that a feasible design is attainable. This camera requires 3 aspheric mirrors to fit inside the 20x60 cm cross-section package. A complete design with reduced throughput (1/9th) has been prepared. The design documents the optical configuration concept. A suitable dispersing prism material, CdTe, has been identified for the prism spectrograph, after a comparison of many materials.

Chipman, Russell A.↗
NASA NTRS1996

Adaptive Optics For Imaging Bright Objects Next To Dim Ones

Adaptive optics used in imaging optical systems, according to proposal, to enhance high-dynamic-range images (images of bright objects next to dim objects). Designed to alter wavefronts to correct for effects of scattering of light from small bumps on imaging optics. Original intended application of concept in advanced camera installed on Hubble Space Telescope for imaging of such phenomena as large planets near stars other than Sun. Also applicable to other high-quality telescopes and cameras.

Shao, Michael↗
NASA NTRS2004

Cloud-Aerosol LIDAR and Infrared Pathfinder Satellite Observation (CALIPSO) Spacecraft: Independent Technical Assessment

CALIPSO is a joint science mission between the CNES, LaRC and GSFC. It was selected as an Earth System Science Pathfinder satellite mission in December 1998 to address the role of clouds and aerosols in the Earth's radiation budget. The spacecraft includes a NASA light detecting and ranging (LIDAR) instrument, a NASA wide-field camera and a CNES imaging infrared radiometer. The scope of this effort was a review of the Proteus propulsion bus design and an assessment of the potential for personnel exposure to hydrazine propellant.

Gilbrech, Richard J.↗
NASA NTRS2005

Cloud-Aerosol LIDAR and Infrared Pathfinder Satellite Observation (CALIPSO) Spacecraft: Independent Technical Assessment

CALIPSO is a joint science mission between the CNES, LaRC and GSFC. It was selected as an Earth System Science Pathfinder satellite mission in December 1998 to address the role of clouds and aerosols in the Earth's radiation budget. The spacecraft includes a NASA light detecting and ranging (LIDAR) instrument, a NASA wide-field camera and a CNES imaging infrared radiometer. The scope of this effort was a review of the Proteus propulsion bus design and an assessment of the potential for personnel exposure to hydrazine propellant.

Gilbrech, Richard J.↗
NASA NTRS2016

High Precision Sunphotometer using Wide Dynamic Range (WDR) Camera Tracking

The NASA Ames Sun-photometer-Satellite Group, DOE, PNNL Atmospheric Sciences and Global Change Division, and NASA Goddards AERONET (AErosol RObotic NETwork) team recently collaborated on the development of a new airborne sunphotometry instrument that provides information on gases and aerosols extending far beyond what can be derived from discrete-channel direct-beam measurements, while preserving or enhancing many of the desirable AATS features (e.g., compactness, versatility, automation, reliability). The enhanced instrument combines the sun-tracking ability of the current 14-Channel NASA Ames AATS-14 with the sky-scanning ability of the ground-based AERONET Sunsky photometers, while extending both AATS-14 and AERONET capabilities by providing full spectral information from the UV (350 nm) to the SWIR (1,700 nm). Strengths of this measurement approach include many more wavelengths (isolated from gas absorption features) that may be used to characterize aerosols and detailed (oversampled) measurements of the absorption features of specific gas constituents. The Sky Scanning Sun Tracking Airborne Radiometer (3STAR) replicates the radiometer functionality of the AATS14 instrument but incorporates modern COTS technologies for all instruments subsystems. A 19-channel radiometer bundle design is borrowed from a commercial water column radiance instrument manufactured by Biospherical Instruments of San Diego California (ref, Morrow and Hooker)) and developed using NASA funds under the Small Business Innovative Research (SBIR) program. The 3STAR design also incorporates the latest in robotic motor technology embodied in Rotary actuators from Oriental motor Corp. having better than 15 arc seconds of positioning accuracy. Control system was designed, tested and simulated using a Hybrid-Dynamical modeling methodology. The design also replaces the classic quadrant detector tracking sensor with a wide dynamic range camera that provides a high precision solar position tracking signal as well as an image of the sky in the 45 field of view around the solar axis, which can be of great assistance in flagging data for cloud effects or other factors that might impact data quality.

aerosols↗
NASA NTRSDate not supplied

Mercury Lander: A Planetary Mission Concept Study for the 2023–2032 Decadal Survey

Mercury holds unique clues to the distribution of elements at the birth of the solar system and how planets form and evolve in close proximity to their host stars. The Mercury Lander mission concept returns in situ measurements to: understand Mercury’s unique mineralogy and geochemistry; characterize the massive core’s structure; measure the planet’s active and ancient magnetic fields at the surface; investigate the processes that alter the surface and produce the exosphere; and provide groundtruth for remote datasets. The mission concept achieves one Mercury year (~88 Earth days) of surface operations with an 11-instrument, high-heritage payload delivered to a landing site within Mercury’s widely distributed low-reflectance material, and addresses science goals encompassing geochemistry, geophysics, the Mercury space environment, and geology. The spacecraft launches on an expendable SpaceX Falcon Heavy in 2035. The four-stage flight system uses a solar-electric propulsion cruise stage to reach Mercury in2045. The orbital stage brings the spacecraft into a thermally safe orbit, then performs orbital maneuvers to prepare for descent. During the orbital phase, a narrow-angle camera acquires images for selecting a low-hazard landing zone within our region of interest. The descent stage begins the braking burn ~120 s before landing. The lander continues to touchdown, using continuous LIDAR operations to support hazard detection and safely deliver the payload to the surface. Landing is at dusk to meet thermal requirements, permitting ~30 hours of sunlight for initial observations. The radioisotope-powered lander continues operations through the Mercury night. Direct-to-Earth communication is possible for the initial three weeks of landed operations, drops out for six weeks, and resumes for the final month. Thermal conditions exceed lander operating temperatures shortly after sunrise, ending operations. A total of ~11 GB of data are returned to Earth. The Phase A–D mission cost estimate (50% unencumbered reserves, excluding launch vehicle) is $1.2 B(FY25$), comparing favorably with past New Frontiers missions and to the cost cap in the New Frontiers4 call(~$1.1B FY25$). This cost estimate shows that a Mercury Lander mission is feasible and compelling as a New Frontiers-class mission in the coming decade.

C M Ernst↗
NASA NTRSDate not supplied

EDS to the Moon!

The Electrostatics and Surface Physics Laboratory at NASA Kennedy Space Center is slated to send multiple Electrodynamic Dust Shields (EDS) to the surface of the moon. This paper discusses the EDS onboard a Commercial Lunar Payload System or CLPS mission slated to launch to the moon on July 27, 2023 on Firefly Aerospace’s Blue Ghost Lander to Mare Crisium. The EDS payload consists of a camera EDS, a separate glass EDS, a thermal radiator EDS as well as a Re-Duster system based on EDS technology. The EDS will be deposited on the ground by a deployable structure on the lunar lander shortly after touchdown and its operations will take precedence over the other 10 payloads on the lander. The camera will record images and videos of dust deposition and removal on both the Thermal Radiator EDS and the Glass EDS. Data handling will be done using a Data Storage Unit (DSU) developed by NASA Langley Research Center and downlinked to Earth in real time.

Charles R Buhler↗
DOE OSTI2017

How Useful Are Imaging and Remote Sensing Technologies in Decontamination and Decommissioning? - 17363

The examples of application of imaging and remote sensing technologies during decontamination and decommissioning works in nuclear environment at Kurchatov Institute site are presented. The systems which realized these technologies are: radiometric system installed on mechanical arm of Brokk remote controlled vehicle, collimated scanning spectrometric system and portable gamma cameras of different types. Objects of application: facilities of research reactors at characterization and under dismantling, temporal radwaste storages during discharge and remediation. (authors)

12 MANAGEMENT OF RADIOACTIVE AND NON-RADIOACTIVE W↗
DOE OSTI2014

Development of a Tender-Energy Microprobe for Geosciences at NSLS and NSLS-II

This funding is to develop a new Synchrotron user facility for microbeam X-ray absorption spectroscopy (XAS) and quantitative X-ray fluorescence (XRF) imaging, at the National Synchrotron Light Source (NSLS) and NSLS-II. It includes design, purchase of components, and construction of the microprobe endstation and controls. Initial development, commissioning, and application is ongoing at NSLS Beamline X15B, with planned transition in 2014-15 to the NSLS-II TES (Tender-Energy Spatially Resolved X-ray Absorption Spectroscopy) beamline. It is optimized for the “tender” energy range of 1-5 keV, reaching up to 8 keV. Thus it uniquely covers the K absorption edges of critical elements Mg, Al, Si, P, S, Cl, and Ca, and can reach up to Co. A stable, high-flux microbeam focus, user-tunable from ~50 to ~5 microns, has been achieved using two-stage achromatic focusing. Existing beamline optics collimate, monochromate, and macro-focus the X-ray beam to ~1 mm at a secondary source aperture (SSA). Beam from the SSA is then re-focused by a pair of mirrors in KB geometry to the microbeam scale. Size of the microbeam is tunable, at the expense of flux, by adjusting the size of the SSA as a virtual source. The new experimental endstation consists of 1) a sample chamber operable as a radiation enclosure with helium atmosphere to facilitate measurements in this energy range, 2) the KB microfocusing optics, 3) a sample-positioning stage for raster-scanning and positioning the sample, 4) X-ray fluorescence detectors, an existing Ge detector for low-signal sensitivity and a new Si detector for high count rates, 5) an optical camera for viewing samples and locating target locations, 6) beam intensity monitors and diagnostics, and 7) controls and data acquisition system. An important aspect of this project is the added capability for fast, on-the-fly scanning of the monochromator (energy), required for fast XAS and advanced XAS imaging. This instrument will be available for initial PI and Co-I measurements, and for General Users to apply for beamtime to use, at NSLS X15B for the remaining operation of NSLS, to September 30, 2014. Phase two of this project will transition this facility, both the primary optics and the endstation, to NSLS-II after NSLS ceases operation. While this transition itself is beyond the scope of the current grant, preparation and planning for it is included.

58 GEOSCIENCES↗