Operational process organization in very low-power plasma accelerators

Aeronautical and Space-Rocket Engineering


DOI: 10.34759/vst-2022-3-169-179

Аuthors

Kaplin M. A.1*, Mitrofanova O. A.1*, Markov A. S.1*, Rumyantsev А. V.2**

1. Experimental Design Bureau “Fakel”, 181, Moskovsky av, Kaliningrad, 236001, Russia
2. Immanuel Kant Baltic Federal University, IKBFU, 14, A. Nevskogo str., Kaliningrad, 236041, Russia

*e-mail: info@fakel-russia.com
**e-mail: albert37@list.ru

Abstract

An interest of the leading aerospace enterprises [1, 2, 3] in development and improvement of very low-power electric propulsion thrusters, which are characterized by a discharge power less than 100 W, for small spacecraft, including CubeSat standard small spacecraft, can be explained by a predicted possibility of getting new scientific knowledge and earning a commercial profit by using small spacecraft equipped with propulsion systems with high values of a generated total thrust impulse. Due to the interest of the world market in the availability of propulsion control systems for small spacecraft, the works on creation of very low-power plasma thrusters were initiated at EDB “Fakel”.

This paper gives the results of research work with experimental laboratory models of very low-power plasma accelerators U-M1 and U-M2 created with the purpose of searching and subsequent optimization of new technical solutions for very low-power plasma thrusters which are developed at EDB “Fakel”. The accelerators U-M1 and U-M2 are built on the basis of two principal schemes which differ by the configuration of their magnetic and discharge systems, what allows to expand the available range of magnetic field parameters and electric discharge parameters defining the studied operational processes’ organization in a discharge chamber. The accelerators’ models were created based on the principle of achievement of maximum simplified systems configurations at a minimum possible geometry enabling stability and sufficiency of the operational process.The results of the U-M1 and U-M2 accelerators performance research works are presented. A long-time functioning of two models of plasma accelerators has been demonstrated, which functioning is characterized by a stable operational process for a long (for this dimension type) time of a total firing and by the sufficiency of accelerators’ thrust parameters:

  • U-M1 accelerator: thrust is 0,77 mN, anode specific impulse is 523 s at the discharge power of 27 W;

  • U-M2 accelerator: thrust is 0,5 mN, anode specific impulse is 313 s at the discharge power of 20 W.

Specific features of the U-M1 and U-M2 accelerators’ operational process related to a very low geometry of systems and very low discharge power have been studied, and as a result, an assumption of a position of the ionization core and acceleration layer outside the spatial limits of the discharge chamber has been formulated. In case of an experimental confirmation of this assumption, the possibility of using the known assessment criteria of the ionization core and acceleration layer position for the conditions of very low geometry and very low discharge power is put in doubt.

Keywords:

very low power plasma accelerator, electric rocket plasma thruster, very low discharge chamber dimensions, small CubeSat spacecraft

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