Научная электронная библиотека ULRICH'S Periodicals Directory

Сибирский государственный университет
науки и технологий имени академика М.Ф. Решетнева

Сибирский аэрокосмический журнал
ISSN 2712-8970 (Print) ISSN 2782-5760 (on-line)

Сведения об образовательной организации

UDK 629.783.525 Doi: 10.31772/2712-8970-2021-22-1-137-150
Experimental investigations of a plasma thrusters and its power processing units performances like an electric load of a spacecraft’s power condition system
Ermoshkin Yu. M., Kochev Yu. V., Nikihelov A. V., Pervukhin A. V., Simanov R. S.
JSC Academician M. F. Reshetnev “Information Satellite Systems”; 52, Lenin Str., Zheleznogorsk, Krasnoyarsk region, 662972, Russian Federation
Electro-jet (plasma or ion) thrusters are becoming increasingly common to correct a satellite orbit and perform orbit raising maneuvers to achieve the geostationary orbit. This is due to the greater efficiency of plasma thrusters compared to chemical ones. When developing a satellite platform, an important place is the matching up of the electrical character-istics of the electric power subsystem (EPS) and on-board consumers. Intrinsically, this issue is an intersys-tem problem. The lack of proper attention paid to find the timely and correct solution of this problem can complicate the operation of the satellite electric power subsystem. The most important subsystem, which has a significant impact on the operation of the satellite EPS, is the electric-jet propulsion subsystem, since among on-board consumers, this one is the most powerful consumer being switched simultaneously. Tran-sients occurred in the power supply circuits following thruster firing and shut down processes can reach significant values. An electric jet thruster only runs in conjunction with a complex electronic unit – a power processing unit (PPU), which converts the voltage of the on-board power supply into a set of voltages nec-essary for thruster components to run. Therefore, in the preliminary design of the propulsion subsystem, it is necessary to know the electrical characteristics of transients and ripples in the power supply circuits of the thruster / PPU combination being an electrical load of the Electric power subsystem. It is difficult to obtain the characteristics of such processes by the calculation method. Therefore, an experimental method is the most common and objective method to obtain this information. JSC ISS carried out tests allowing to measure characteristics of transients and ripples under firing, running and shut down of plasma thrusters of different types powered by corresponding PPU’s. These tests were conducted using a vacuum chamber GVU-60. A test power supply was used to simulate EPS operation. This paper presents the results of meas-urements and analysis of parameters of transients and ripples on PPU power buses used for thrusters and devices of three types. These results are considered to be preliminary. It is shown that the greatest difficul-ties can arise when operating high-power thrusters. It is concluded that for each new type of thrusters and PPU’s it is advisable to conduct interface tests of the propulsion subsystem and the satellite electric power subsystem.
Keywords: plasma thruster, propulsion subsystem, power processing unit, transient processes, current, voltage, rippling.
References

1. Lev D., Myers R. V., Lemmer K. M. et al. The Technological and Commercial Expansion of Electric Propulsion in the Past 24 Years. 35th Electric Propulsion Conference. IEPC-2017-242. Geor-gia Institute of Technology. USA, October 8–12, 2017.
2. Vorontsov V. V., Kostin A. N., Lovtsov A. S. et al. Development of KM-60 Based Orbit Con-trol Propulsion Subsystem for Geostationary Satellite. Procedia Engineering. 2017, Vol. 185, P. 319–325.
3. Garcia V., Lamoureux E., Andersson B. et al. EP System Development and Functional Valida-tion Tests for Electra GEO Satellite. 36th International Electric Propulsion Conference. IEPC-2019-A288. Vienna, Austria. September 15–20, 2019. 14 p.
4. Ermoshkin Yu. M., Yakimov E. N. On the concepts of the station keeping and geostationary orbit injection thruster’s application. Proceedings of XVI International conf. “Aviation and Space”. Moscow, 2017, Nov. 20–24, P. 92–93.
5. Ermoshkin Yu. M., Kochev Yu. V., Volkov D. V. et al. Design of a multifunctional electric propulsion subsystem of the spacecraft. Siberian journal of science and technology. 2020, Vol. 21, No. 2, P. 233–243. Doi: 10.31772/2587-6066-2020-21-2-233-243.
6. Kryuchkov P. A., Ermoshkin Yu. M., Vavilov A. V. et al. [Agreement of electric interfaces of the electric power subsystem and the orbit raising propulsion subsystem]. Elektronnyye i elektromek-hanicheskiye sistemy i ustroystva. Tomsk, 2020, P. 52–54. (In Russ.)
7. Gladuchenko V. N., Galaiko V. N., Gordeev K. G. et al. Modern status and future directions of evolution of power processing units for electric plasma thrusters. Electronic and electromechanical systems and devices. Scientific papers, JSC “NPC “Polus”. Tomsk Polytechnic University Press, 2016, P. 59–65.
8. Eric Bourguignon, Stéphane Fraselle. Power Processing Unit activities at Thales Alenia Space in Belgium. Space prop. Conf. 2018, Seville, Spain, 14–18 May 2018, 8 p.
9. Mallmann A., Forrisi F., Mache E. et al.High Voltage Power Supply for T5 Gridded Ion Thrust-er. 36th International Electric Propulsion Conference, IEPC-2019A512. Vienna, Austria, September 15–20, 2019, 7 p.
10. Ermoshkin Yu. M., Galaiko V. N., Kim V. P. et al. [Specifics of transients in the discharge cir-cuit during the SPT-140D plasma engine starting]. Vestnik Moskovskogo Aviatsionnogo Instituta. 2017, Vol. 24, No. 4, P. 80–88. (In Russ.)
11. Yermoshkin Yu. M., Volkov D. V., Yakimov E. N. On the concept of “all electric propulsion spacecraft”. Siberian Journal of Science and Technology. 2018, Vol. 19, No. 3, P. 489–496. Doi: 10.31772/2587-6066-2018-19-3-489-496.
12. Kochev Yu. V., Ermoshkin Yu. M, Merkuryev D. V. et al. [The new technical solutions to be implemented to ground experimental development of an SC orbit raising and orbit correction elec-tric propulsion]. Aktualnyye voprosy proyektirovaniya avtomaticheskikh kosmicheskikh apparatov dlya fundamentalnykh i prikladnykh nauchnykh issledovany. 2017. Iss. 2, P. 300–306. (In Russ.)
13. Baranov S. V., Plokhikh A. P., Popov G. A. et al. Determination of Electromagnetic Emission from Electric Propulsion Thrusters under Ground Conditions. 35th International Electric Propulsion Conference. IEPC-2017-167. Georgia Institute of Technology, USA, Oct. 8–12, 2017, 8 p.
14. Nikipelov A. V., Simanov R. S., Ermoshkin Yu. M. et al. [Electric propulsion firing tests bench at JSC “ISS”]. Naukoyemkiye tekhnologii. 2016, Vol. 17, No. 8, P. 61–65. (In Russ.)
15. Jackson J., Miller S., Cassidy J. et al. 13 kW advanced electric propulsion flight system devel-opment and qualification. 36th International Electric Propulsion Conference, IEPC-2019-A692. Vien-na, Austria, September 15–20, 2019, 19 p.


Yuriy Ermoshkin – Dr. Sc. (tech.), head of propulsion department; JSC Academician M. F. Reshetnev “Infor-mation Satellite Systems”. E-mail: erm@iss-reshetnev.ru.
Yuriy Kochev – Сand. Sc., head of propulsion subsystem electric design group; JSC Academician M. F. Resh-etnev “Information Satellite Systems”. E-mail: koch@iss-reshetnev.ru.
Alexander Nikipelov – Cand. Sc. (tech.), head of propulsion firing tests group; JSC Academician M. F. Reshetnev “Information Satellite Systems”. E-mail:niki@iss-reshetnev.ru.
Artem Pervukhin – Сand. Sc., head of electromagnetic compatibility sector; JSC Academician M. F. Reshetnev “Information Satellite Systems”. E-mail: pervukhin@iss-reshetnev.ru.
Ruslan Simanov – leadig engineer; JSC Academician M. F. Reshetnev “Information Satellite Systems”. E-mail: simru@iss-reshetnev.ru.


  Experimental investigations of a plasma thrusters and its power processing units performances like an electric load of a spacecraft’s power condition system