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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 37 records · Page 2
All sourcesNASA NTRSDOE OSTI
NASA NTRS1984

Phenomenology of plasma engine cathodes at high current rates and low pressures

The effects of low surrounding pressures on cathodes of arc jet engines with electromagnetic acceleration are investigated for pressure and current energies of 20 to 100 Torr. and 400 to 1000 A. Experiments with 50 mm long and 8 mm diameter tungsten-thorium cathode in a coaxial gas flow show that pre-heating of the cathode reduces the duration of the instable arc discharge and thus material loss. The use of lighter gases also reduces instability effects, as well as the use of increased pressures and a massive gas influx.

Huegel, H.↗
NASA NTRS1964

The plasma separator ion engine.

Plasma separator ion engine allowing optimization of ion source and accelerator system independently, showing gains in thrust and less propellant consumption

PLASMA ENGINE↗
NASA NTRS1978

Operations of the ATS-6 ion engine and plasma bridge neutralizer at geosynchronous altitude

The ion engine on ATS-6 has been operated in daylight and eclipse. The effect on particle fluxes to the spacecraft was monitored. This data provides information on the potential of the spacecraft with respect to the ambient plasma and the local electric fields caused by the charge distribution on the spacecraft. Operation of the ion engine and/or the neutralizer clamps the spacecraft within a few volts of the ambient plasma potential. Operation of only the neutralizer tends to reduce the differential charge on the satellite, whereas operation of the ion engine reduces it below the sensitivity limit of the detectors.

Olsen, R. C.↗
NASA NTRS1990

Magnetic insulation for plasma propulsion

The design parameters of effective magnetic insulation for plasma engines are discussed. An experimental model used to demonstrate the process of plasma acceleration and magnetic insulation is considered which consists of a copper strap that is wound around a glass tube and connected to a capacitor. In order to adequately model the magnetic insulation mechanisms, a computer algorithm is developed. Plasma engines, with their efficient utilization of the propellant mass, are expected to provide the next-generation advanced propulsion systems.

Gonzalez, Dora E.↗
NASA NTRS1999

MEMS Micropropulsion Activities at JPL

A status of MEMS-based micropropulsion activities conducted at JPL will be given. These activities include work conducted on the so called Vaporizing Liquid Micro-Thruster (VLM) which recently underwent proof-of-concept testing, demonstrating the ability to vaporize water propellant at 2 W and 2 V. Micro-ion engine technologies, such m field emitter arrays and micro-grids are being studied. Focus in the field emitter area is on arrays able to survive in thruster plumes and micro-ion engine plasmas to serve as neutralizers aW engine cathodes. Integrated, batch-fabricated Ion repeller grid structures are being studied as well as different emitter tip materials are being investigated to meet these goals. A micro-isolation valve is being studied to isolate microspacecraft feed system during long interplanetary cruises, avoiding leakage and prolonging lifetime and reliability of such systems. This concept relies on the melting of a thin silicon barrier. Burst pressure values as high as 2,900 psig were obtained for these valves and power requirements to melt barriers ranging between 10 - 50 microns in thickness, as determined through thermal finite element calculations, varied between 10 - 30 W to be applied over a duration of merely 0.5 ms.

Mueller, Juergen↗