The interest in low-power electric thrusters stimulated our research on a small stationary plasma thruster. The first results on the dependence of the thrust, the discharge current, the ion current, and the axial electron current on gas flow are reported. It was also shown that the drop of the discharge current with magnetic field is strongly affected by the emission current of the filament neutralizer. (C) 1996 American Institute of Physics. References: 4
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