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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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High capacity nonaqueous secondary battery development - lithium deposition and cycling, ionic solvation, cathode construction and discharge efficiency, and solvent purification
Development of membrane separators for sterilizable silver-zinc battery
Development of battery with lithium-magnesium alloy anode, molten cuprous chloride cathode, and zeolite separator cells and cupric oxide cathode and porous glass separator cells
High energy density primary battery development - electrochemical half-cell screening of anode- electrolyte combinations, cell discharge, and potential studies
Cell discharge measurements for dry tape battery couple - anode and cathode development in aqueous and nonaqueous electrolytes
X-ray diffraction patterns of nickel-cadmium battery electrodes and stabilization of nickel oxides and hydroxides
Lightweight, rugged, inexpensive satellite battery for producing electrical power from ionosphere using electrodes with different contact potentials
Inorganic separator for high temperature silver- zinc battery
Radiation effects on silver and zinc battery electrodes
High capacity nonaqueous secondary battery - synthesis and electrochemical studies of dialkyl and diary beryllium compounds, organoberyllium complex salts, and other complex salt solutions
High energy density primary battery development - anode-electrolyte, cupric fluoride cathode, and chemical stability tests
The generalized Newton-Raphson method, an iterative procedure for solving nonlinear operator equations, has been extended in application to variational problems with bounded control variables. A minimum fuel interplanetary low thrust orbital transfer problem is worked out in detail to demonstrate the practical aspects of the algorithm as well as its computational effectiveness. The control variables are the thrust magnitude, limited from zero to some prescribed maximum value, and the thrust steering angle.
Battery charger for Atmosphere Explorer B spacecraft - packaging in aluminum frame rectangular configuration with three separate compartments
Automatic battery formation cycler and controller to determine charge capacity and to perform charge-discharge operations for electrochemical cells intended for satellite power sources
Active compound formation on battery nickel oxide electrode during charge, overcharge, and discharge
Test of electrochemical cell and local action mechanisms of wet cell battery for space probe applications
The Lunar and Planetary X-Ray Diffraction Program consists of three concurrent efforts aimed at rapid development of a first-generation flight-instrument system, evaluation of potential advances in diffractometer components for a possible second-generation instrument, and full investigation of the capabilities and limitations of rock analysis by X-ray diffraction. More complete descriptions of each of these studies are given below; the papers which follow are grouped according to these subjects in Sections II through V.