Propulsion systems and low-thrust rocket engines based on various physical principles for control systems of small and micro-spacecraft


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Abstract

The article presents an analysis of the possibility of using propulsion systems and rocket thrusters based on various physical principles and used as part of small and very small spacecraft. The parameters of efficient propulsion systems and low-thrust rocket engines are examined from the standpoint of being used as  components of spacecraft fueled by various kinds of propellant: gaseous fuel, mono-fuel, including advanced compositions based on hydroxyl-ammonium nitrate, bipropellant fuel; xenon electric rocket systems, as well as special propulsion systems and low-thrust rocket engines operating on nitrous oxide, ammonia, gaseous hydrogen and oxygen; electric-powered systems based on pulsed plasma thrusters, ion and steady-state plasma engines. Taking into account the data analyzed, an attempt was made to categorize the propulsion systems and low-thrust rocket engines. Their use in small spacecraft, spacecraft of the “Mini”, “Micro”, “Nano” classes in various propulsion systems and low-thrust rocket engines was found to be preferable.

About the authors

V. V. Ryzhkov

Samara National Research University

Author for correspondence.
Email: ke_src@ssau.ru

Candidate of Science (Engineering)
Head of the Research Center of Space Power

Russian Federation

A. V. Sulinov

Samara National Research University

Email: ke_src@ssau.ru

Candidate of Science (Engineering)
Senior Researcher of the Research Center of Space Power

Russian Federation

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