Forming design layout of a technological purpose small spacecraft based on other class of technological spacecraft design and operation experience

DOI: 10.34759/vst-2020-3-84-93

Аuthors

Sedel'nikov A. V.^*, Taneeva A. S.^**, Orlov D. I.^***

Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia

*e-mail: axe_backdraft@inbox.ru
**e-mail: nastya-gorozhankina@yandex.ru
***e-mail: grand_99v@mail.ru

Abstract

The article analyzes a possible design layout of a promising small spacecraft for technological purposes. Specific requirements for such devices are requirements for micro-accelerations, which, on the one hand, determine the possibility and feasibility of implementing a particular gravity-sensitive technological process onboard the spacecraft, and, on the other hand, impose requirements for the orientation and motion control system of the spacecraft.

Since there are no fully implemented projects of small spacecraft for technological purposes at this stage of space technology development, the experience of designing and operating medium-class spacecraft and orbiting space stations is under discussion. However, small spacecraft have their own specifics in terms of the super-dense layout. Thus, while designing small spacecraft this experience should be significantly reworked with account for this feature.

The design requirements for the small spacecraft and its orientation and motion control system are formed in view of meeting the requirements for micro-accelerations that contribute to the favorable implementation of gravitationally sensitive processes, and with account for other features of small spacecraft. This feature consists in a significantly higher ratio of the mass of elastic elements to the spacecraft total mass for a small spacecraft than for spacecraft of other classes. This feature affects the actuating devices selection of the orientation and motion control system of a small spacecraft, as well as the characteristics of these actuating devices.

The results of this work can be used in the development of small spacecraft for technological purposes.

Keywords:

small spacecraft of technological purpose, gravity-sensitive processes, design layout, micro-accelerations

References

1. Belousov A.I., Sedel’nikov A.V., Molyavko D.P., Potienko K.I. Nauchnoe obozrenie, 2016, no. 17, pp. 186–194.

2. Lobykin A.A. Poverkhnost’. Rentgenovskie, sinkhrotronnye i neitronnye issledovaniya, 2009, no. 2, pp. 84–91.

3. Lukiashchenko V., Borisov V., Semenchenko V. et al. “MAKOS–T” A New Spacecraft for Conducting Experiments in Microgravity. Russian Space Bulletin, 1996, vol. 1, no. 4, pp. 13–15.

4. Kiselev A.I., Medvedev A.A., Men’shikov V.A. Kosmonavtika na rubezhe tysyacheletii: itogi i perspektivy (Cosmonautics on the frontier of millenia), Moscow, Mashinostroenie, 2001, 672 p.

5. Elkin K.S., Mel’nikov E.K., Mironov V.I. et al. Kosmonavtika i raketostroenie, 2009, no. 4(57), pp. 109–121.

6. Abrashkin V.I., Voronov K.E., Piyakov I.V. et al. Kosmicheskie issledovaniya, 2016, vol. 54, no. 4, pp. 315–322.

7. Abrashkin V.I., Voronov K.E., Piyakov I.V. et al. Kosmicheskie issledovaniya, 2015, vol. 53, no. 4, pp. 306. DOI: 10.7868/S0023420615040019

8. Hu W.R., Zhao J.F., Long M. et al. Space Program SJ–10 of Microgravity Research. Microgravity Scienсe and Technology, 2014, vol. 26, no. 3, pp. 159–169. DOI: 10.1007/s12217-014-9390-0

9. Ushakov I.B., Ilyin E.A. Advances of space medicine and biology research in Russia. 47th session of the STS of the Committee on the Peaceful Uses of Outer Space (February 2010, Vienna, Austria). URL: http:// www.unoosa.org/pdf/pres/stsc2010/tech-13.pdf

10. Sedel’nikov A.V., Podlesnova D.P. Izvestiya vysshikh uchebnykh zavedenii. Severo-Kavkazskii region. Seriya “Estestvennye nauki”, 2007, no. 4, pp. 44–46.

11. Kirilin A.N., Akhmetov R.N., Anshakov G.P. et al. Polet. Obshcherossiiskii nauchno-tekhnicheskii zhurnal, 2015, no. 2, pp. 3–9.

12. Kirilin A.N., Akhmetov R.N., Shakhmatov E.V. et al. Opytno-tekhnologicheskii malyi kosmicheskii apparat “Aist–2D” (Experimental and technological small spacecraft “AIST-2D”), Samara, SamNTsRAN, 2017,324 p.

13. Sedelnikov A.V., Kireeva A.A. Alternative solution to increase the duration of microgravity calm period on board the space laboratory. Acta Astronautica, 2011, vol. 69, no. 7-8, pp. 480–484. DOI: 10.1016/j.actaastro.2011.05.009

14. Belousov A.I., Sedelnikov A.V., Potienko K.I. Study of Effective Application of Electric Jet Engine as a Mean to Reduce Microacceleration Level. International Review of Aerospace Engineering, 2015, vol. 8, no. 4, pp. 157–160. DOI: 10.15866/irease.v8i4.7578

15. Belousov A.I., Sedelnikov A.V. Selecting the parameters of the orientation engine for a technological spacecraft. IOP Conference Series: Materials Science and Engineering, 2018, vol. 302, 012019.

16. Anshakov G.P., Belousov A.I., Sedel’nikov A.V., Gorozhankina A.S. Efficiency Estimation of Electrothermal Thrusters Use in the Control System of the Technological Spacecraft Motion. Russian Aeronautics, 2018, vol. 61, no. 3, pp. 347-354. DOI: 10.3103/S1068799818030054

17. Abrashkin V.I., Voronov K.E., Piyakov I.V. et al. Kosmicheskie issledovaniya, 2017, vol. 55, no. 2, pp. 135–149.

18. Belew L.F., Stuhlinger E. Skylab. Periscope Film LLC, 2012, 264 p.

19. Rambaut P.C., Leach C.S., Whedon G.D. A study of metabolic balance in crewmembers of SKYLAB IV. Acta Astronautica, 1979, vol. 6, no. 10, pp. 1313–1322.

20. Blinov V.N., Shalai V.V., Zubarev S.I. et al. Issledovaniya elektrotermicheskikh mikrodvigatelei korrektiruyushchikh dvigatel’nykh ustanovok manevriruyushchikh malykh kosmicheskikh apparatov (Studies of electro-thermal micro-motors for corrective propulsion systems of maneuverable small spacecraft), Omsk, OmGTU, 2014, 264 p.

21. Blinov V.N., Vavilov I.S., Kositsyn V.V. et al. Dinamika sistem, mekhanizmov i mashin, 2016, no. 4, pp. 18–29.

22. Blinov V.N., Shalai V.V., Charushina E.B. Informatsiya i kosmos, 2015, no. 3, pp. 158–168.

23. Blinov V.N., Vavilov I.S., Kositsin V.V. et all. The studies of small space vehicles ammoniac electrothermal engine units design and structural layout. Modern Applied Science, 2015, vol. 9, no. 5, pp. 337–357. DOI: 10.5539/mas.v9n5p337

24. Oleynikov I.I., Pavlov V.P., Kovaleva M.V. Methods of identifying and estimating the parameters of dangerous situations, while ensuring the security of spacecraft flight security in the near earth space. Aerospace MAI Journal, 2012, vol. 19, no. 5, pp. 32-37.

25. Donskov A.V. Analysis of modern evaluation and modeling methods of contingencies occurrence risks onboard a spacecraft. Aerospace MAI Journal, 2018, vol. 25, no. 4, pp. 163-169.