Analysis of characteristics of electric propulsion systems intended for carrying out maneuvers of maintenance of low Earth working orbit of small satellites


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Abstract

An analysis of the mass of the working fluid and motor operating time of electric propulsion systems applied as a part of small spacecraft to carry out maneuvers of maintenance of the low Earth working orbit is carried out. The analysis is carried out for the small spacecraft with the weight in the range from 300 to 1000 kg functioning in working orbits with the height in the range from 400 to 600 km. When carrying out the analysis the values of the specific impulse of the propulsion system in the range from 800 to 1600 sec were accepted. Procedural guidelines for assessing the value of the required characteristic speed depending on the aerodynamic drag force, as well as for assessing the value of mass of the working fluid with account for the value of the specific impulse and defining the motor operating time of the propulsion system depending on the exhaust speed of the working fluid were used. The results of calculations given in the article show that the mass of the working fluid and the motor operating time vary depending on the height of the orbit and the mass of the small spacecraft and allow making quick preliminary assessment of the main design characteristics of the electric propulsion engines used to carry out maneuvers of maintenance of the low Earth working orbit of small spacecraft with different weight dimension characteristics during the prescribed term of active existence.

About the authors

V. V. Salmin

Samara National Research University

Author for correspondence.
Email: sputnik@ssau.ru

Doctor of Science (Engineering), Professor, Director of Scientific Research Institute of Space Mechanical Engineering

Russian Federation

V. V. Volotsuev

Samara National Research University

Email: volotsuev@mail.ru

Candidate of Science (Engineering), Associate Professor of Space Mechanical Engineering named after General Designer D.I. Kozlov

Russian Federation

A. V. Nikitin

Joint Stock Company Space Rocket Centre Progress; Samara National Research University

Email: alex.nik.job@gmail.com

Leading Design Engineer; Postgraduate Student

Russian Federation

References

  1. Holste K., Dietz P., Scharmann S., Keil K., Henning T., Zschätzsch D., Reitemeyer M., Nauschütt B., Kiefer F., Kunze F., Zorn J., Heiliger C. Ion thrusters for electric propulsion: Scientific issues developing a niche technology into a game changer. Review of Scientific Instruments. 2020. V. 91, Iss. 6. doi: 10.1063/5.0010134
  2. Tsentsura K. Revolyutsiya v kosmose. Vse, chto nuzhno znat' o pervom korable s ionnym dvigatelem, kotoryy otpravilsya k Merkuriyu [Revolution in space]. Available at: https://nv.ua/techno/popscience/2512340.html
  3. Lesnevskiy V.A., Makhova L.I., Mikhaylov M.V., Khodnenko V.P., Khromov A.V. Electric propulsion system of the «Kanоpus-V» spacecraft and its firing tests. Bulletin of the Tomsk Polytechnic University. 2011. V. 319, no 4. P. 144-147. (In Russ.)
  4. Eutelsat 172B zapushchen [Eutelsat 172B is started]. Available at: https://www.comnews.ru/content/ eutelsat-172B-zapushen
  5. Sputnik FKI. Venµs [Satellite for basic space research. Venµs]. Available at: https://ecoruspace.me/VEN%C2%B5S.html
  6. Kulkov V.M., Obukhov V.A., Yegorov Y.G., Belik A.A., Krainov A.M. Comparative evaluation of the effectiveness of the application of perspective types of electric propulsion thrusters in the small spacecraft. Vestnik of the Samara State Aerospace University. 2012. No. 3 (34), part 1. P. 187-195. (In Russ.). doi: 10.18287/2541-7533-2012-0-3-1(34)-187-195
  7. GOST P 25645.166-2004. Earth upper atmosphere. Density model for ballistic support of flights of artificial Earth satellites. Moscow: Izdatel'stvo Standartov Publ., 2004. 23 p. (In Russ.)
  8. Raschet zapravki i ostatkov topliva v BKhP dvigatel'noy ustanovki kosmicheskogo apparata «Luch-5A» pri ekspluatatsii [Calculation of fuel filling and remaining fuel in the fuel storage and delivery system of the propulsion system of «Luch-5A» spacecraft in operation]. Kaliningrad: Experimental Design Bureau «Fakel» Publ., 2006.
  9. Abramovich G.N. Prikladnaya gazovaya dinamika. Ch. 2 [Applied fluid dynamics]. Moscow: Nauka Publ., 1991. 304 p.
  10. Vlasov S.A., Mamon P.A. Teoriya poleta kosmicheskikh apparatov: ucheb. posobie [Theory of spacecraft flights: manual]. SPb: Mozhaisky Military Space Academy Publ., 2007. 435 p.
  11. Salmin V.V., Chetverikov. A.S., Gogolev M.Yu. Raschet proektno-ballisticheskikh kharakteristik i formirovanie proektnogo oblika mezhorbital'nykh transportnykh apparatov s elektroreaktivnoy dvigatel'noy ustanovkoy s ispol'zovaniem informatsionnykh tekhnologiy: ucheb. posobie [Calculation of design ballistic data and conceptual design of orbital transfer vehicles with electric propulsion systems using information technologies]. Samara: Samara University Publ., 2019. 196 p.
  12. Makridenko L.A., Volkov S.N., Gorbunov A.V., Salikhov R.S., Khodnenko V.P. The first Russian next generation high resolution Earth remote sensing small satellite Canopus-V No. 1. Electromechanical Matters. VNIIEM Studies. 2017. V. 156, no. 1. P. 10-20. (In Russ.)
  13. Vlasov S.A., Kubasov I.Y., Selin V.A. Choice of ballistic structure of a system of Earth remote sensing satellites. Proceedings of the Mozhaisky Military Space Academy. 2009. Iss. 625. P. 76-80. (In Russ.)
  14. Tkachenko I.S., Salmin V.V. The analysis of efficiency of satellte inspectors with electrojet impellent modules. Izvestiya Samarskogo Nauchnogo Tsentra RAN. 2011. V. 13, no. 6. P. 106-115. (In Russ.)
  15. Volotsuev V.V., Salmin V.V. Analysis of the cyclogram of maintaining a low working orbit of a spacecraft of the AIST-2 class using an electric jet engine. Spacecrafts and Technologies. 2020. V. 4, no. 2 (32). P. 61-71. (In Russ.). doi: 10.26732/j.st.2020.2.01
  16. Anshakov G.P., Salmin V.V., Volotsyev V.V. Mathematical models for maintaining a low orbit of a spacecraft with the help of electrically reactive engines with allowance for power limitations. Proceedings of the 4th International Conference on Information Technology and Nanotechnology, ITNT 2018 (April, 24-27, 2018, Samara). Samara: Novaya Tekhnika Publ., 2018. P. 2813-2820. (In Russ.)

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