Determining the regions for efficient use of electro­jet low­thrust engines




flight dynamics, low orbits, electro-jet engine, mono-component engine, maintaining the orbit.


This work addresses the issues on determining the optimal regions for using propulsion system for spacecraft at low near-Earth orbits. An analysis of spacecraft launches over the past 5 years has been performed. The result of analyzing the launches is the type of spacecraft, selected for subsequent calculations, specifically a remote sensing satellite at low near-Earth orbit. We have solved the problem on determining parameters for the trajectory of a spacecraft motion, exposed to external non-permanent forces. Based on an analysis of the external influence, the scope of possible future application of spacecraft propulsion systems has been defined. A comparative analysis has been performed for the mass criterion of efficiency of using propulsion systems based on the chemical mono-component and electro-jet engines in order to solve tasks on maintaining the circular orbit parameters over a long time.

For orbit altitudes below 300 km, as was established based on the calculation results, the application of a propulsion system proved to be inefficient due to the need for a large reserve of fuel aboard and a large required engine thrust. For satellites at circular orbits from 350 to 450 km, a propulsion system that includes the Hall-effect- based engine ST-25, manufactured by SETS, proved to be more effective than the chemical propulsion unit. Application of chemical engines to maintain the orbit parameters at altitude above 500 km would be preferable to electro-jet ones due to a relatively small mass of the chemical propulsion system and a sufficient resource of engines operation in order to maintain the orbit.

We have obtained parameters for the propulsion system that uses the Hall-effect-based engine ST-25 in order to maintain orbital parameters within different ranges of altitudes, solar activity, and geometrical parameters for a satellite. The result of calculation is the determined necessary resource of operation and the fuel stock to maintain parameters of the orbit.

The calculation results obtained could be used to design new satellites and to modify satellite platforms.

Author Biographies

Aleksey Sidorov, Oles Honchar Dnipro National University Gagarina ave., 72, Dnipro, Ukraine, 49010

Senior Lecturer

Department of Construction and Design

Viktor Pererva, Oles Honchar Dnipro National University Gagarina ave., 72, Dnipro, Ukraine, 49010

Senior Lecturer

Department of Manufacturing Technology


  1. UCS Satellite Database. Available at:
  2. NASA Space Science Data Coordinated Archive, NASA's archive for space science mission data. Available at:
  3. Salmin, V. V., Volotsuev, V. V., Shikhanov, S. V. (2013). Spacecraft preset orbital parameters control by means of thrusters. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta, 4 (42), 248–254. Available at:
  4. BGT-X5 Green Monopropellant Thruster. Busek. Available at:
  5. Krejci, D., Lozano, P. (2018). Space Propulsion Technology for Small Spacecraft. Proceedings of the IEEE, 106 (3), 362–378. doi:
  6. SPS25 propulsion system. Available at:
  7. Mammarella, M., Fusaro, R., Andreussi, T., Paissoni, C. A., Viola, N. et. al. (2018). Mission Scenarios for High-Power Electric Propulsion Space Propulsion 2018. Conference: Space Propulsion 2018. Available at:
  8. Pererva, V. A., Karpovich, E. V., Fedosov, A. V. (2016). Development of penetration zone size prediction technique for hollow-cathode welding technology of spherical titanium tanks. Eastern-European Journal of Enterprise Technologies, 1 (5 (79)), 47–52. doi:
  9. Zakharenkov, L. E., Kim, V., Lovtsov, A. S., Semenkin, A., Solodukhin, A. E. (2018). Modern trends and development prospects of thrusters with closed electron drift. Conference: Space Propulsion 2018. Available at:
  10. Peter, T., Dyer, A., Ryan, E., Garcia, C. et. al. (2018). Initial investigation of alternative propellants for use with a low-power cylindrical hall thruster. In Space Propulsion 2018, 12. Available at:
  11. Andreussi, T., Cifali, G., Giannetti, V., Piragino, A., Ferrato, E., Rossodivita, A., Andrenucci, M. (2017). Development and experimental validation of a hall effect thruster RAM-EP concept. 35th International Electric Propulsion Conference Georgia Institute of Technology. Available at:
  12. Yermoshkin, Yu. M. (2011). Electric propulsions rational application range on the applied spacecrafts. Sibirskiy zhurnal nauki i tekhnologiy, 2 (35), 109–113. Available at:
  13. Maslova, A. I., Pirozhenko, A. V. (2009). Izmeneniya plotnosti atmosfery pri dvizhenii kosmicheskih apparatov na nizkih okolozemnyh orbitah. Kosmichna nauka i tekhnolohiya, 1, 13–18.
  14. Ishkov, S. A. (2016). Efficiency of using electric propulsion engines for the task of keeping in a near-circular orbit. VESTNIK of the Samara State Aerospace University, 15 (1), 55–63. doi:
  15. Ishkov, S. A. (2017). Optimization of Design Parameters of Spacecraft Equipped with Electro Rocket Low-thrust Engine and Calculation its Applying Area at Low Earth Orbit. Procedia Engineering, 185, 239–245. doi:
  16. Dron', N. M., Kondrat'ev, A. I., Hit'ko, A. V., Horol'skiy, P. G. (2008). Kontseptsiya ispol'zovaniya elektroraketnyh dvigateley na mikrosputnikah. Aviatsionno-kosmicheskaya tekhnika i tekhnologiya, 9, 39–43.
  17. Alpatov, A. P. (2016). Dinamika kosmicheskih letatel'nyh apparatov. Kyiv: Naukova dumka, 487.
  18. Montenbruck, O., Gill, E. (2005). Satellite Orbits: Models, Methods and Applications. Springer, 369.
  19. Curtis, H. D. (2014). Orbital Mechanics for Engineering Students. Butterworth-Heinemann, 768. doi:




How to Cite

Sidorov, A., & Pererva, V. (2019). Determining the regions for efficient use of electro­jet low­thrust engines. Eastern-European Journal of Enterprise Technologies, 3(5 (99), 43–50.



Applied physics