Hall thruster systems based on the SPT-50 and the TAL D-38 were evaluated and mission studies were performed. The 0.3 kilowatt SPT-50 operated with a specific impulse of 1160 seconds and an efficiency of 0.32. The 0.8 kilowatt D-38 provided a specific impulse above 1700 seconds at an efficiency of 0.5. The D-38 system was shown to offer a 56 kilogram propulsion system mass savings over a 101 kilogram hydrazine monopropellant system designed to perform North-South station keeping maneuvers on board a 430 kilogram geostationary satellite. The SPIT-50 system offered a greater than 50% propulsion system mass reduction in comparison to the chemical system on board a 200 kilogram low Earth orbit spacecraft performing two orbit raises and drag makeup over two years. The performance characteristics of the SPF-50 were experimentally evaluated at a number of operating conditions. The ion current density distribution of this engine was measured. The performance and system mass benefits of advanced systems based on both engines were considered.
Evaluation of Low Power Hall Thruster Propulsion
1996
18 pages
Report
Keine Angabe
Englisch
Electric & Ion Propulsion , Unmanned Spacecraft , Plasma engines , Ion currents , Current density , Plasma propulsion , Density measurement , Ion propulsion , Hall accelerators , Propulsion system performance , Specific impulse , Density distribution , Low earth orbits , Monopropellants , Data correlation , Synchronous satellites , Spacecraft orbits
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