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.

The paper studies the issues of design and structural layout of ammoniac corrective engine units (CEU) with electrothermal micromotors (ETMM) for manoeuvrable small space vehicles (SSV) using all-purpose approach. CEU and ETMM structural schemes are defined, adaptation questions of CEU to SSV are addressed, CEU mass analysis is carried out, and experimental study's findings are given.

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