Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Research of an oxide cathode as a cathode-neutralizer for EPSPS

Published: 19.06.2019

Authors: Benklyan A.S., Lyapin A.A., Klimenko G.K.

Published in issue: #6(90)/2019

DOI: 10.18698/2308-6033-2019-6-1888

Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts

In this research, a laboratory model of a thermionic oxide cathode was tested as part of  a diode circuit. The ultimate goal of this work was to obtain the thermionic characteristics of the emitter of the laboratory model and to study the processes of emitter activation. The relevance of the study is due to the increased interest in the possibility of using thermionic cathodes as cathode-neutralizers for electrically-powered spacecraft propulsion system (EPSPS). During the experiment, the following parameters were recorded: the pressure in the vacuum chamber and the emission current to the anode-collector. The current of the emitter and the voltage applied between the anode-collector and the emitter were regulated. The gap between the emitter and the anode-collector was set before the beginning of the experiment and was 2 mm. The emission current was measured in the emitter temperature range from 600 °C to 1260 °C. The temperature of the emitter was controlled by infrared and optical pyrometers. In the course of the work, three emitter activation processes were identified: temperature, time and voltage. The processes of activation by temperature and time are widely known, in contrast to the activation process by voltage, for which there is currently no unambiguous theoretical explanation

[1] Goebel D., Katz I. Fundamentals of Electric Propulsion: Ion and Hall Thrusters. Jet Propulsion Laboratory California Institute of Technology, 2008, 493 p.
[2] Holste K., Gärtner W., Köhler P., Dietz P., Konrad J., Schippers S., Peter J., Klar P., Müller A., Schreiner P. In Search of Alternative Propellants for Ion Thruster. 34th International Electric Propulsion Conference, At Kobe, Japan, 2015. Available at: (accessed November 4, 2018).
[3] Dankanich J., Szabo J., Pot B., Oleson S., Kamhawi H. Mission and System Advantages of Iodine Hall Thrusters. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, AIAA Propulsion and Energy Forum, 2014. Available at: DOI: 10.2514/6.2014-3905 (accessed November 4, 2018).
[4] Dankanich J. SmallSats, Iodine Propulsion Technology, Applications to Low-Cost Lunar Missions, and the Iodine Satellite (iSAT) Project. Annual Meeting of the Lunar Exploration Analysis Group (LEAG); 22–24 Oct. 2014. Available at: (accessed November 4, 2018).
[5] Polzin K., Iodine Hall Thruster Propellant Feed System for a CubeSat. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Cleveland, OH, 2014. Available at: DOI:10.2514/6.2014-3915 (accessed November 4, 2018).
[6] Ostrovskiy V.G., Smolentsev A.A., Shcherbina P.A. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta — Vestnik of Samara University. Aerospace and Mechanical Engineering, 2014, no. 5 (47), pp. 131–136.
[7] Lyapin A.A., Shcherbina P.A., Klimenko G.K., Konovalova A.I., Ostrovskiy V.G., Sishko I.B. Izvestiya Rossiyskoy akademii nauk. Energetika — Proceedings of RAS. Power Engineering, 2018, no. 2, pp. 93–97.
[8] Klimenko G.K., Konovalova A.I., Lyapin A.A. Inzhenernyy zhurnal: nauka i innovatsii — Engineering Journal: Science and Innovation, 2017, iss. 10. DOI: 10.18698/2308-6033-2017-10-1694
[9] Dyubua B.Yu., Korolev A.N. Elektronnaya tekhnika, ser. 1. SVCH-tekhnika. Nauchno-tekhnicheskiy sbornik — Electronic Engineering, ser. 1. Microwave Engineering, 2011, no. 1 (508), pp. 5–24.
[10] Evstigneev S.I., Tkachenko A.A. Katody i podogrevateli elektrovakuumnykh priborov [Electro-vacuum devices cathodes and heaters]. 2nd ed., rev. and corr. Moscow, Vysshaya shkola Publ., 1975, 196 p.