Measurements are reported of the thrust and exhaust characteristics of a pulsed plasma rail thruster engerized by a 1.0 or 1.3 microfarads capacitor charged to up to 4.5 kV. This device, intended for satellite attitude control, uses mercury propellant injected by an auxiliary discharge between a trigger pin and a small mercury pool. Measurements using a beam-type thrust balance indicate that the thrust at 20 pulses/second rises from 5 dynes at 2 kV to 90 dynes at 4.5 kV. Plasma velocities derived from Langmuir probe data (8 cm/microseconds at 2.5 kV) are broadly in agreement with those deduced from image converter photographs of the acceleration process, but the detailed structure expected in the exhaust from these photographs is not detected by the probe. (Modified author abstract)
Measurements of the Thrust and Exhaust Characteristics of a Pulsed Rail Thruster Using Mercury Propellant
1973
24 pages
Report
Keine Angabe
Englisch
Performance Characteristics of Liquid Propellant Pulsed Plasma Thruster
British Library Conference Proceedings | 2004
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