Hybrid Plasma Thruster for Small Spacecraft
Аuthors*, *, *
Experimental Design Bureau “Fakel”, 181, Moskovsky av, Kaliningrad, 236001, Russia
AbstractThe 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