Abstract
Recent experimental results obtained with a laboratory model of the space-charge-sheath thruster are reported. The principal feature of this thruster is tlie electrostatic acceleration of ions in a space-charge sheath that is formed on the ionizer. The range of operating conditions tested was as follows: specific impulse = 2700-5500 sec; magnetic field strength = 800-2500 gauss; accelerating gap = 1-3 mm; ionizer surface — 13.8 cm2; cesium vapor pressure — 5-38 mm Hg; ion-beam current density = 4-14 ma/cm2. The resulting ion-beam has been found to be surprisingly well collimated, with an estimated half angle of 1.5°. Under best operating conditions, the electron drain current to the anode (ionizer) was 31% of the total current.
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