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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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Low frequency oscillation measurements on spherical magnetized cold cathode direct current discharge by plasma probes
Cathode insulator modifications of radiation cooled MPD arc thrustor tested in power range of 9.8 to 46.4 kW using ammonia as principal propellant
Color television system utilizing single gun current sensitive color cathode ray tube
Cold cathode gage for measuring amount of gas present in lunar atmosphere
Survey of various cathodes used in Kaufman ion thruster
Mercury vapor fed hollow cathodes for electron bombardment ion thrusters
Development and characteristics of display system for space shuttle and cost effectiveness analysis of cathode ray tube system
Parameters influence on mercury hollow cathode neutralizers for Kaufman ion thrustor
Low power MPD arc thrustor performance with downstream cathode, using Xe propellant
Hollow cathode ion thrustor and lightweight power conditioner of solar-electric propulsion system for unmanned deep space probes
Cold cathode ionization gages dynamic pressure response as function of gas pulse mean speed and gas type, using magnetron test measurements
Porous structure effects in oxygen consuming cathode, discussing electrode thickness, effective pore diameter, pressure difference and electrode performance
A layer of material is described, which contains fine grains of phosphor material stimulated by electrons to produce visible radiation. The layer, which also contains fine grains of cobalt oxide, is deposited on the glass screen of a cathode ray tube to provide high contrast, by absorbing most of the visible radiation which is directed to the layer through the screen, while not materially affecting the visible light which the phosphor material produces in response to the electron stimulation.
A preliminary evaluation of the cold cathode gage experiment which was included in the ALSEP to determine the amount of gas present on the lunar surface is reported. The instrument, electronic circuitry, and deployment are described. The preliminary results are summarized and include temperature history, and variations in gas concentration detected after deployment.
Thrust measurements of a hollow cathode mercury discharge were made with a synthetic mica target on a torsion pendulum. Thrust measurements were made for various target angles, tip temperatures, flow rates, keeper discharge powers, and accelerator electrode voltages. The experimental thrust data are compared with theoretical values for the case where no discharge power was employed.
Operating and maintenance instructions for cathodic protection of communication cables at the Cape Kennedy Launch Complex are presented. The system is designed to prevent or arrest corrosion of communication cables buried in soil or submerged in water by impressing sufficient direct current from the rectifier through the anodes to the cable. This process neutralizes or counteracts current flowing from the cable into the soil or water, thus preventing or arresting corrosion of the cable sheath material.
Four hot-cathode ionization vacuum gages were calibrated in 12 gases. The relative sensitivities of these gages were compared to several gas properties. Ionization cross section was the physical property which correlated best with gage sensitivity. The effects of gage accelerating voltage and ionization-cross-section energy level were analyzed. Recommendations for predicting gage sensitivity according to gage type were made.
Methods have been developed and applied to the determination of iron, titanium, and nickel in Apollo 14 fine soil and rock by differential cathode ray polarography on the same sample. A 5 mg sample was sufficient for the determination of all 3 elements. Iron and titanium were determined either directly or after cupferron separation. Nickel was determined after dimethylglyoxime separation.