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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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Optical charge transfer transitions in N-alkyl iodide salts, examining transient absorptions due to flash photolysis
Predicting crater size and impact flash for S-4B stage lunar impact on Apollo 13 flight
Compilation of optical properties data of xenon flash tubes for pilot warning indicator systems
Exposure of human subjects to fast neutron beam to determine cause of light flashes observed by astronauts on lunar missions
Feasibility of spraying flash evaporator as heat rejection device for space shuttle environmental control system
Visual flash duration discrimination and analysis of temporal and energy cue models, and memory effects
Determination of correlation between impact flash radiative properties and impacting meteoroid projectile characteristics
High frequency sudden deviations caused by extreme ultraviolet flashes from solar flares in ionosphere
Liquid spray flash evaporator for space shuttle thermal control
Flash points, fire points and impact sensitivity of materials under gaseous oxygen pneumatic and mechanical impact
Martian blue haze clearings and flash phenomena meteorological mechanism, considering atmospheric clearing due to water precipitation
Array of photodetectors and associated circuitry continuously monitors entire horizon to measure distance and direction of lightning flashes.
A functional description of the flash evaporator that is being developed as a candidate for the Space Shuttle Environmental Control System thermal control is presented. A single evaporator configuration uses water as an evaporant to accommodate on-orbit peak heat loads and Freon 22 for terrestrial flight phases below 120,000 ft altitude. Development history, test plans, and operational characteristics are described. Detailed information is included to show: design features, fabrication techniques used for a prototype unit, redundancy considerations, and the control arrangement.
A laboratory prototype flash evaporator that is being developed as a candidate for the space shuttle environmental control system expendable heat sink is described. The single evaporator configuration uses water as an evaporant to accommodate reentry and on-orbit peak heat loads, and Freon 22 for terrestrial flight phases below 120,000 feet altitude. The design features, fabrication techniques used for the prototype unit, redundancy considerations, and the fluid temperature control arrangement are reported in detail. The results of an extensive test program to determine the evaporator operational characteristics under a wide variety of conditions are presented.
Center-of-mass coordinates for 28 NASA MOTS and SAO Baker-Nunn camera sites have been obtained from optical flash data from Geos 1 (1965 89A) and Geos 2 (1968 002A). More than 25,000 observations in about 100 two-day arcs were used in dynamical solutions (SAO 1969 AGU gravity model). Comparison of results with local survey solutions and with solutions from deep-space vehicle tracking suggests accuracy of about 2 meters in longitude and height and 5 meters in latitude. The relatively larger error in latitude arose from propagation of gravity-model error largely along the track of these high-inclination satellites. The results have also been compared with the solutions of the SAO 1969 standard earth for station coordinates on the North American datum. The solution obtained in the present work is much closer to the survey results in chord length between stations.
The energy spectrum and temporal behavior of the 10 to 100 keV solar flare electrons observed at 1 AU are interpreted in terms of: (1) the location of the acceleration region, (2) the time of acceleration and duration of the injection into the interplanetary medium, and (3) type 3 radio burst origin at the sun and at 1 AU. For at least some and possibly the majority of electron flare events the density of the acceleration region is approximately 2 X 10 to the 9th power cu/cm, the time of acceleration and release coincides to within minutes of the flash phase as indicated by the type 3 radio burst, and the duration of the release less than or approximately 3 minutes. Evidence for the origin of type 3 radio bursts in 10 to 100 keV electron streams is shown and discussed.
The crew members on the last seven Apollo flights observed light flashes that are tentatively attributed to cosmic ray nuclei (atomic number equal to or greater than 6) penetrating the head and eyes of the observers. Analyses of the event rates for all missions has revealed an anomalously low rate for transearth coast observations with respect to translunar coast observations.
Using the technique of flash photolysis-resonance fluorescence, the reaction of ground-state atomic sulfur with carbonyl sulfide has been investigated over the temperature range from 233 to 445 K. Over this temperature range, the experimental data were fitted to an Arrhenius equation of the form k sub 1 = (1.52 plus or minus 0.20) x 10 to the minus 12th power exp(-3.63 plus or minus 0.12 kcal/mol/RT) cu cm/molecule/sec. A comparison of these results with previous investigations on this reaction system is presented.