Investigation of a radio-frequency ion thruster with a ramjet discharge chamber
Authors: Gordeev S.V., Kanev S.V., Melnikov A.V., Nazarenko I.P., Khartov S.A.
Published in issue: #5(125)/2022
DOI: 10.18698/2308-6033-2022-5-2179
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts
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.
References
[1] Erofeev A.I., Suvorov M.O., Nikiforov A.P., Syrin S.A., Popov G.A., Khartov S.A. Vestnik NPO imeni S.A. Lavochkina, 2016, no. 3, pp. 104–110.
[2] Corbett M.H., Edwards C.H. Thrust control algorithms for the GOCE ion propulsion assembly. 30th International Electric Propulsion Conference, Florence, Italy, 2007, September 17–20. IEPC-2007-21.
[3] Nishiyama K. Air breathing ion engine concept. 54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law, Bremen, Germany, 29 September – 3 October 2003. IAC-03-S4-02.
[4] Erofeev A.I., Filatyev A.S., Golikov A.A., Khartov S.A., Nikiforov A.P., Popov G.A., Suvorov M.O., Yanova O.V. Pryamotochnye vozdushnye elektroreaktivnye dvigateli dlya dlitelnykh poletov aerokosmicheskikh apparatov na sverkhnizkikh orbitahh [Air-Breathing Electric Propulsion for Long-Term Flights in Very Low Earth Orbits]. Mezhdunarodnaa konferentsia po fundamentalnym issledovaniyam “Nauka i tekhnologii vysokoskorostnykh letatelnykh apparatov” — HiSST-2018. Moskva, 26–29 noyabrya 2018 g. [International Conference on Fundamental Research “High-Speed Vehicle Science and Technology”, Moscow, November 26–29, 2018].
[5] Gordeev S.V., Filatyev A.S., Khartov S.A., Popov G.A., Suvorov M.O. The concept of ramjet electric propulsion for a low-orbit spacecraft. IAA/AAS Scitech Forum 2019 on Space Flight Mechanics and Space Structures and Materials, Advances in the Astranautical Sciences, 2019, vol. 174, pp. 245–256, IAA-AAS-SciTech2019-027 AAS 19-967.
[6] Erofeev A.I., Nikiforov A.P., Plugin V.V. Uchenye zapiski TSAGI — TsAGI Science Journal, 2017, vol. XLVIII, no. 3, pp. 56–69.
[7] Goebel D.M. Analytical Discharge Model for RF Ion Thrusters. IEEE Transactions on Plasma Science, October 2008, vol. 36, no. 5, pp. 2111–2121. https://doi.org/10.1109/tps.2008.2004232
[8] Gordeev S.V., Kanev S.V., Suvorov M.O., Khartov S.A. Trudy MAI, 2017, no. 96. Available at: http://trudymai.ru/published.php?ID=85709 (accessed March 18, 2022).
[9] Kanev S.V., Kozhevnikov V.V., Khartov S.A. Izvestiya Rossiyskoy akademii nauk. Energetika — Thermal Engineering, 2017, no. 3, pp. 21–30.
[10] Gordeev S.V., Kanev S.V., Melnikov A.V., Nazarenko I.P., Khartov S.A. Mode-ling of processes in plasma of radio-frequency ion injector with an antenna placed inside the volume of discharge chamber. Aerospace, 2021, vol. 8, paper no. 209. https://doi.org/10.3390/aerospace8080209
[11] Chen F. Introduction to Plasma Physics. Springer; 1974 ed., 2012, 34 p. [In Russ.: Chen F. Vvedenie v fiziku plazmy. Moscow, Mir Publ., 1987, 282 p.].