ST-40 HALL TRUSTER TESTING WITH LaB6 HOLLOW CATHODE

  • O. Petrenko Space Electric Thruster Systems, Oles Honchar Dnipro National University
  • A. Kashaba Kharkiv National University named V.Karazin
  • V. Maslov Space Electric Thruster Systems
  • S. Oslavsky Space Electric Thruster Systems
Keywords: HALL-EFFECT THRUSTER, LaB6 HOLLOW CATHODE, HALL THRUSTER START SEQUENCE DIAGRAMS, LABORATORY TESTING, HALL THRUSTER’S OPTIMAL PARAMETERS

Abstract

The results of experimental investigation of the ST-40 Hall thruster operating with a heating hexaboride cathode are presented. The readiness of the heating hollow cathode to the thruster start was assessed by reducing the cathode keeper voltage from the start value of 100 V to 15 ... 17 V, when an internal discharge in the hollow cathode occurred. Various cyclograms of the thruster start are considered with the definition of the purpose of the cyclogram, which ensures reliable thruster start. Three cyclograms of the thruster start are investigated: with the thruster’s electromagnet coils switched on; with the coils off; without switching off the voltage at the hollow cathode keeper, which made it possible to restart the thruster without preheating the hollow cathode. The obtained cyclograms make it possible to ensure a reliable start of the ST-40 thruster when operating with a heating hexaboride hollow cathode. In the course of laboratory research, the PPU-300 power processing unit was used. It ensured the stabilization of the discharge power in the thruster’s accelerating channel and stabilization of the currents supplied to the central and external coils of the thruster. The main operating characteristics and parameters of the ST-40 thruster were obtained for three fixed values of the discharge power: 265, 281, 300 W and a change in the mass flow rate of the working substance (Xenon) through the anode unit of the thruster 0.7 ... 1.3 mg/sec. Experimental investigation of the ST-40 thruster in a wide range of parameters made it possible to determine the optimal thruster’s parameters that provide the maximum values of thrust and specific impulse for the given values of the discharge power in the accelerating channel of the thruster and the minimum discharge current. The process of the thruster’s parameters optimizing was carried out by changing the currents flowing through the internal and external coils of the thruster. In the course of experimental research, it was found that the inner coil and the serially connected outer coils can be connected in parallel and powered by a single power supply. Experimental studies have confirmed the correctness of the adopted technical solutions in the development of the ST-40 Hall thruster and the heating hexaboride hollow cathode.

Author Biographies

O. Petrenko, Space Electric Thruster Systems, Oles Honchar Dnipro National University

Petrenko Olexandr. Ukraine. Space Electric Thruster Systems (SETS), Dnipro. Scientific chief. Dniprovsky National University named Oles Honchar. Doctor of science, Professor.

Interests sphere – design, testing and investigation of the electric propulsion systems.

A. Kashaba, Kharkiv National University named V.Karazin

Kashaba Andrey. Ukraine. Space Electric Thruster Systems (SETS). Dnipro. Researcher - developer. Kharkiv National University named Karazin. Senior researcher. PhD. Interests sphere – Plasma physics, the working processes optimizing in Hall thrusters and hollow cathodes.

V. Maslov, Space Electric Thruster Systems

Maslov Viktor. Ukraine. Space Electric Thruster Systems (SETS). Dnipro. Engineer-researcher. Interests sphere – design, testing and investigation of the Hall thrusters and hollow cathodes.

S. Oslavsky, Space Electric Thruster Systems

Oslavsky Sergey. Ukraine, Space Electric Thruster Systems (SETS). Dnipro.
Инженер-конструктор. Engineer-researcher.

Interests sphere – design, testing and investigation of the Hall thrusters and hollow cathodes.

References

Petrenko, O., Serbim, V., Perepechkin A., Tolok, S., Alekseenko, A. Hall-effect thruster ST-40 // Proc. of 70th International Astrounautical Congress, 2019.

Petrenko, O., Tolok, S., Perepechkin, A., Shcherbak, D. Development status of the ST-40 Hall Thruster // Space propulsion SP2020+1_00056, March 17 – 19, 2021.

Pedrini, D., Cannelli, F., Ducci C., Misuri, T., Paganucci, F., Andrenucci, M. Hollow cathodes development at SITAEL // Space propulsion SP2016_3124925, May 2 – 6, 2016.

Frollani, D., Coletti, M. & Gabriel, S. B. (2015). Flexible LaB6 Hollow Cathode for Lab Tests. IEPC-2015-46, 34th International Electric Propulsion Conference, Hyogo-Kobe, Japan.

Pedrini, D., Albertoni, R., Paganucci, F. & Andrenucci, M. (2015). Modeling of LaB6 Hollow Cathode Performance and Lifetime. Acta Astron., 106 (2015), 170–178.

Received by Editorial Board on 31.10.2022 г.

Published
2023-02-23
How to Cite
Petrenko, O., Kashaba, A., Maslov, V., & Oslavsky, S. (2023). ST-40 HALL TRUSTER TESTING WITH LaB6 HOLLOW CATHODE. Journal of Rocket-Space Technology, 30(4), 15-22. https://doi.org/10.15421/452203
Section
Engines and power plants

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