Abstract
The paper describes a zero-dimensional balance mathematical model of a radio-frequency ion thruster with a ramjet discharge chamber and considers the case when the propellant is fed into the ionization chamber but is able to outflow through the ion-extraction system as well as through the inlet channel of the atmosphere gases intake device. Nitrogen was considered as the propellant. The mathematical model is distinctive as it takes into account the propellant dissociation and the influence of atmosphere gases intake device. The paper also gives the results of the first experiments with a laboratory model of the thruster. The comparison between the calculated and experimental data made it possible to obtain the discrepancies of less than 15 percent, which indicates the applicability of the developed mathematical model for a qualitative analysis of the processes occurring in the thruster.
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