This paper presents an overview of current world developments in the field of low-energy plasma propulsion systems for small micro - and nanoclass spacecraft. A promising direction of thrusters for devices of nanoclass are propulsion ion propulsion. The use of electrical energy and high-frequency electromagnetic radiation eliminates the problem of significant power losses, because at this level, the laws of optics (reflection and focusing of waves by metal surfaces and dielectrics) and electrical conductivity (energy transfer through metal conductors) work. This fact is an advantage of plasma installations over thermal ones.

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The paper presents the results of experimental studies of an arcjet thruster in pulsed mode of operation on nitrogen with a thrust value of up to 32 mN and energy consumption of up to 30 watts. The pulse mode of operation of the arcjet thruster is provided by the developed power source. At measured values of temperature at the nozzle and pressure in the arc chamber of the engine in a pulsed mode of operation define the basic characteristics of gas-dynamic functions of gas flow. The forecast of the achieved values of the specific impulse when using ammonia as a working fluid is carried out

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