Designing the Configuration and Selecting the Design Parameters of Drag Systems for Deorbiting Spacecraft Created by Pivdenne Design Office

Authors

DOI:

https://doi.org/10.15407/scine18.04.055

Keywords:

space debris, aerodynamic deorbit system, deorbit time, design parameters of the deorbit system

Abstract

Introduction. To stabilize the space debris environment, defunct spacecraft and mission-related debris shall be deorbited.
Problem Statement. The analysis of drag sail systems for deorbiting spacecraft has shown that they are effective for spacecraft deorbiting from orbits having an altitude of up to 800 km, but have some disadvantages: vulnerability of the shell material to space debris fragments that may damage it and electrostatic breakdown.
Purpose. The purpose of this research is to design the configuration and to select the design parameters of drag systems for deorbiting spacecraft created by Pivdenne Design Office.
Materials and Methods. Methods of space flight mechanics, mathematical modeling of design problems have been used in this research.
Results. The calculations have shown that the time of deorbiting Sich-2-1 spacecraft from the design orbit is about 6.5 years for a mass of the drag deorbit system of 9 kg that is 5% of the mass of Sich-2-1 spacecraft. It has been determined that in the case of increasing the deorbit time from the design orbit after the end of operational life to 25 years, the mass of the drag system may be reduced to 4.5 kg. With a mass of the drag deorbit system of 9 kg, the effective use of this DAD system is limited to an altitude from 730 to 750 km, in the case of close to circular orbits of different dislocations, and to an altitude of at most 700 km in perigee and 842 km in apogee in the case of low-elliptical orbits.
Conclusions. Based on the requirements of Pivdenne Design Office for the mass and dimensions of the drag augmentation device, the configuration and design view of the drag augmentation device (DAD) have been developed. This design is notable for its compactness that is due to the use of spring mechanisms and low-cost micro-motors, which deploy drag elements. In this design, the device occupies a little space on Sich-2-1 spacecraft.

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References

The Orbital Debris Quarterly News. (2019). NASA JSC Houston, 23(1, 2).

Alpatov, A. P., Goldstein, Yu. M. (2017). Ballistic Analysis of Orbits Distribution of Spacecraft for Different Functional Missions. Technical mechanics, 2, 33-40. [in Russian]. https://doi.org/10.15407/itm2017.02.033

Alpatov, A. P., Holdshtein, Yu. M. (2019). On the choice of the ballistic parameters of an on-orbit service spacecraft. Technical mechanics, 1, 25-37. https://doi.org/10.15407/itm2019.01.025

Lovell, T. A., Tragesser, S. (2004, August). Guidance for Relative Motion of Low Earth Orbit Spacecraft Based on Relative Orbit Elements. AIAA Paper 2004-4988, presented at the AAS/AIAA Astrodynamics Specialist Conference, Providence, RI. https://doi.org/10.2514/6.2004-4988

. Paliy, A. S. (2012). Methods and means of spacecraft deorbiting from operating orbits (state of the problem). Technical mechanics, 1, 94-102 [in Russian]

Dron, N. M., Horolsky, P. G., Dubovik, L. G. (2014). Ways of reduction of technogenic pollution of the near-earth space. Scientific Bulletin of NMU, 3 (141), 125-130 [in Russian].

. Lapkhanov, Е. О. (2019). Features of the development of means for spacecraft removal from near-Earth operational orbits. Technical mechanics, 2, 16-30. [in Ukrainian] https://doi.org/10.15407/itm2019.02.016

Golovko, M. G., Bezugly, V. A., Bondarenko, S. G., Rubakha, Yu. A., Pokrovsky, R. O. (2012). Technical aspects of space debris control. Ecology and noosphereology, 23(1-2), 110-120.

Patent of Russian Federation No. 2014115630/11. Sergeev, V. E, Burdaev, M. N., Golovko, A. V. Method for removing nonfunctioning spacecraft from geostationary orbit [In Russian].

Alpatov, А. P., Gorbulin, V. P. (2013). Orbital space platforms for industrial complex: problems and prospects. Bulletin of the NAS of Ukraine, 12, 26-38 [in Russian]. https://doi.org/10.15407/visn2013.12.026

Alpatov, A. P. (2018). Information models and technologies for combating anthropogenic pollution of near space. System technologies, 3(116), 3-14 [in Russian].

Benvenuto, R., Salvi, S., Lavagna, M. (2015). Dynamics analysis and GNC design of flexible systems for space debris active removal. Acta Astronautica, 110, 247-265. https://doi.org/10.1016/j.actaastro.2015.01.014

Alpatov, A. P., Khoroshylov, S. V., Maslova, A. I. (2019). Сontactless de-orbiting of space debris by the ion beam. Dynamics and control. Kyiv: Akademperiodyka, 150. https://doi.org/10.15407/akademperiodyka.383.170

Dudeck, M., Doveil, F., Arcis, N., Zurbach, S. (2011). Plasma propulsion for geostationary satellites and interplanetary spacecraft. Rom. Journ. Phys. Bucharest, 56, 3-14. URL: http://www.nipne.ro/rjp/2011_56_Suppl/0003_ 0014.pdf (Last accessed 30.10.2021).

Alby, F. (2004). SPOT-1 End of life disposal maneuvers. Advances in Space Research, 35, 1335-1342. https://doi.org/10.1016/j.asr.2004.12.013

Pikalov, R . S., Yudintsev, V. V. (2018). Review and selection of means for removing large-sized space debris. Proceedings of the MAI, 100. URL: http://trudymai.ru/upload/iblock/239/Pikalov_YUdintsev_rus.pdf?lang=ru&issue=100 (Last accessed 30.10.2021) [in Russian].

Alpatov, A. P., Paliy, O. S., Skorik, О. D. (2017). The Development of Structural Design and the Selection of Design Parameters of Aerodynamic Systems for De-orbiting Upper-stage Rocket Launcher. Nauka innov., 13(4), 33-45. https://doi.org/10.15407/scin13.03.033

Rasse, B., Damilano, P., Dupuy, C. (2014). Satellite inflatable deorbiting equipment for LEO spacecrafts. Journal of Space Safety Engineering, 1(2), 75-83. https://doi.org/10.1016/S2468-8967(16)30084-2

Anderson, J. L. NASA's Nanosail-D 'Sails' Home - Mission Complete. NASA.gov. URL: https://www.nasa.gov/mission_pages/smallsats/11-148.html (Last accessed 30.10.2021).

Mishchenko, O. V. (2017). On the determination of the tether length for an experimental electrodynamic system. Technical mechanics, 4, 55-63. [in Russian]. https://doi.org/10.15407/itm2017.04.055

Pirozhenko, A. V., Mischenko, A. V. (2018). Small Experimental Electrodynamic Space Tether System. Electrical model. Space Sci.&Technol, 24(3), 3-10. [in Russian]. https://doi.org/10.15407/knit2018.03.003

Kawashima, R., Bak, J., Matsuzawa, S. (2018). Inamori T. Particle Simulation of Plasma Drag Force Generation in the Magnetic Plasma Deorbit. Tokyo University. URL: www.al.t.utokyo.ac.jp/members/junhwib/docs/2018Kawashima_ JSR.pdf (Last accessed 30.10.2021).

Shuvalov, V. A., Gorev, N. B., Tokmak, N. A., Pis'menny, N. I., Kochubei, G. S. (2018). Control of the drag on a spacecraft in the earth's ionosphere using the spacecraft's magnetic field. Acta Astronautica, 151, 717-725. https://doi.org/10.1016/j.actaastro.2018.06.038

Fortescue, P., Stark, J., Swinerd, G. (2011). Spacecraft systems engineering. Chichester. 724 p. https://doi.org/10.1002/9781119971009

Maslova, A. I., Pirozhenko, A. V. (2016). Orbit changes under the small constant deceleration. Space Sci.&Technol, 22(6), 20-24. [in Russian]. https://doi.org/10.15407/knit2016.06.020

Pirozhenko, A. V., Maslova, A. I., Vasilyev, V. V. (2019). About the influence of second zonal harmonic on the motion of satellite in almost circular orbits. Space Sci. & Technol., 25(2), 3-11 [In Russian] https://doi.org/10.15407/knit2019.02.003

ECSS-E-ST-10-04C. Space engineering, Space environment (2008). Noordwijk: ECSS Secretariat, ESA-ESTEC, Requirements & Standards Division, 198.

Lapkhanov, E., Khoroshylov, S. (2019). Development of the aeromagnetic space debris deorbiting system. Eastern-European Journal of Enterprise Technologies, 5 (5(101)), 30-37. https://doi.org/10.15587/1729-4061.2019.179382

Trofimov, S. P. (2015). Taking small spacecraft from the upper segment of low orbits using a sail to increase the force of light pressure. Keldysh Institute preprints, 32, URL: http://library.keldysh.ru/preprint.asp?id=2015-32 (Last accessed 30.10.2021) [in Russian].

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Published

2022-08-14

How to Cite

Alpatov А., Lapkhanov Е., & Palii О. (2022). Designing the Configuration and Selecting the Design Parameters of Drag Systems for Deorbiting Spacecraft Created by Pivdenne Design Office. Science and Innovation, 18(4), 55–63. https://doi.org/10.15407/scine18.04.055

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Section

Scientific and Technical Innovation Projects of the National Academy of Sciences