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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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Design of liquid metal magnetohydrodynamic power system for nuclear propulsion spacecraft
Rechargeable, high energy density battery using molten salt electrolyte and aluminum and chlorine electrodes
Cubical complex theory with applications to diagnosis and algorithmic description
Breadboard model tests for 20 CM electric thruster power conditioner and support equipment
Fabrication and testing of peak wind speed recording device
Maxometers for peak wind speed anemometry for Saturn 5 launch umbilical tower and normal meteorological environment
Nuclear magnetic resonance, solubility, stability, and resistance of electrolytes for lithium batteries
Reactions between liquid dinitrogen tetraoxide and titanium alloy that result in stress corrosion cracking
Intake system design, fabrication, and testing in two phase hydrogen
The charge composition of solar cosmic rays were measured during two flares occurring in April and September 1971. The results were derived from a solid state dE/dx vs E telescope which was part of the cosmic ray experiment on the IMP 6 spacecraft. The data suggest that the helium to medium ratio may be varying from one flare to the next. The abundance ratios (normalized to oxygen) are compared with measurements of other investigators and significant disagreements are found. In particular, the data do not exhibit any systematic enhancement of heavy nuclei with respect to the spectroscopic abundances such as previously reported. Finally, the results are compared with the spectroscopically determined coronal and photospheric values, and again several important differences between the two sets of data are found.
This special bibliography lists 448 reports, articles, and other documents introduced into the NASA scientific and technical information system in December 1972.
The results of the analysis conducted on the telemetry data from the prelaunch, launch, and flight activation phases of the ERTS-1 spacecraft are presented. It is presented by sub system sections and provides for inter-relationships as they exist between the several subsystems. A brief statement of subsystem characteristics precedes flight evaluation statements. The appendix contains a total list of components flow on ERTS-1 and a complete listing of commands and telemetry functions for reference.
Various methods used in the organic analysis of lunar samples are reviewed. The scope, advantages, and limitations of these methods are discussed, with particular emphasis on possible sources of contamination and experimental artifacts inherent in their use. A broad survey of the organogenic elements and compounds found in lunar samples covers the search for biogenic structures and viable organisms; the abundance and isotopic composition of various elements and compounds; the search for porphyrins, amino acids, or amino acid precursors; and the presence of heterocylics, aromatic hydrocarbons, and other organic compounds. The sources of the organogenic elements and compounds detected in lunar samples are discussed. The significance of the lunar organic analysis for exobiology is discussed in terms of its relevance to and implications for the studies of chemical evolution and terrestrial organic geochemistry. Individual items are announced in this issue.
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Results obtained from a high altitude balloon flight from Thompson, Canada in August, 1973 are reported. The instrument consisted of a spark chamber, a Lucite Gerenkov counter and thirteen layers of scintillators. For heavy particles the Cerenkov-range method of analysis was used to determine the mass of particles energetic enough to produce a Cerenkov signal and then stop in the layered scintillators. The data appear to be consistent with current cosmic-ray propagation models. Using a simple exponential path length propagation model this data is extrapolated to the cosmic-ray source and some implications of the data are discussed as to the nature of the source.
The results of wind tunnel tests conducted on a 0.010-scale version of the Vehicle 3 Space Shuttle Configuration were presented. Pressure measurements were made on the launch configuration, orbiter alone, external tank alone, and solid rocket booster alone, to provide heat transfer pressure data. The tests were conducted for a Mach number range from 2.36 to 4.6 and Reynolds number range from 1.2 to 5 million per foot. The model was tested at angles of attack from -10 deg to 20 deg for a sideslip angle range from -5 deg to +5 deg and at sideslip angles from -5 deg to 48 deg for 0 deg angle of attack.
Results of wind tunnel tests, conducted at the Langley Research Center Unitary Plan Wind Tunnel, are presented. The model tested was an 0.010-scale version of the Vehicle 3 Space Shuttle Configuration. Pressure measurements were made on the launch configuration, Orbiter alone, external tank alone, and solid rocket booster alone, to provide heat transfer pressure data. The tests were conducted for a Mach number range from 2.36 to 4.6 and Reynolds number range from 1.2 to 5 million per foot. The model was tested at angles of attack from -10 to 20 deg for a sideslip angle range from -5 to +5 deg, and at sideslip angles from -5 to 48 deg for 0 deg angle of attack. Tabulated data are given and photographs of the test configuration are shown.