Hybrid Plasma Thruster for Small Spacecraft

Аuthors

Gopanchuk V. V.^*, Kozubski K. N.^*, Potapenko M. Y.^*

Experimental Design Bureau “Fakel”, 181, Moskovsky av, Kaliningrad, 236001, Russia

*e-mail: fakel@gazinter.net

Abstract

The results of the development of highly efficient electric propulsion of low power for small spacecraft are presented. The parameters and performance of the new scheme thruster PlaS-40 (average diameter of acceleration channel is equal to 40 mm) with small power consumption 200…650 W are investigated at discharge voltage from the following range 100…500 V.

Keywords:

electric propulsion; small spacecraft; hybrid plasma thruster

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