Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
  • Русский
  • Английский

Analysis of the design of the drag braking device for CubeSat satellites for withdrawal from low near-Earth orbits

Published: 11.05.2020

Authors: Pichkhadze K.M., Sysoev V.K., Firsyuk S.O., Yudin A.D.

Published in issue: #5(101)/2020

DOI: 10.18698/2308-6033-2020-5-1982

Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control

Clogging near-Earth outer space by spacecrafts that have failed is a threat of collision with functioning objects in space. To solve the problem of man-made debris, which may affect the development of cosmonautics in the future, a lot of collision avoidance maneuvers are proposed. The most feasible method is to use spherical braking devices providing a predictable descent of the satellite from the orbit, regardless of the orientation of its body, and the shortest time of departure from low earth orbits. Based on the results of the system analysis, the rational composition and configuration design of the device using spherical brake shells for deorbiting CubeSat nanosatellites from low Earth orbits were determined, taking into account the mass and size limitations of the standard 1U CubeSat module.

[1] Karchaev Kh.Zh., Pichkhadze K.M., Sysoev V.K., Firsyuk S.O., Yudin A.D. Obshcherossiyskiy nauchno-tekhnicheskiy zhurnal “Polyot” — All-Russian Scientific-Technical Journal “Flight”, 2019, no. 4, pp. 19–28.
[2] Trofimov S.P. Uvod malykh kosmicheskikh apparatov s nizkikh okolozemnykh orbit. Diss. cand. fiz.-mat. nauk [The withdrawal of a small spacecraft from low Earth orbits. Cand. phys. and math. sc. diss.]. Moscow, 2015, p. 93. Available at: (accessed January 20, 2020).
[3] Heaton A.F., Faller B.F., Katan C.K. NanoSail-D Orbital and Attitude Dynamics. In: Advances in Solar Sailing. Macdonald M., ed. Berlin, Heidelberg, Springer-Verlag Publ., 2014, pp. 95–113.
[4] Aalto-1: The Finnish Student Nanosatellite. eoPortal News. Available at: (accessed January 20, 2020).
[5] Kosmicheskiy sputnik “Mayak” [Space satellite “Mayak”]. Boomstarter. Available at: (accessed January 20, 2020).
[6] Finchenko V.S., Ivankov A.A., Shmatov S.I. Vestnik AO “NPO imeni S.A. Lavochkina” — Space Journal of FSUE “Lavochkin Association”. Cosmonautics and Rocket Engineering, 2018, no. 1, pp. 11–18.
[7] ESA “Requirements on Space Debris Mitigation for ESA projects”. ESA/ADMIN/IPOL (2008) 2, Annexes 1, Paris, April 2008.
[8] NASA. “Process for Limiting Orbital Debris”. NASA Technical Standard. Revision A with Change 1. NASA-STD-8719.14A. Dec. 8, 2011.
[9] GOST R 52925–2008. Izdeliya kosmicheskoy tekhniki. Obshchiye trebovaniya k kosmicheskim sredstvam po ogranicheniyu tekhnogennogo zasoreniya okolozemnogo kosmicheskogo prostranstva [State Standard R 52925–2008. Products of space technology. General requirements for space facilities on limiting technological clogging of near-Earth space]. Moscow, Standartinform Publ., 2008, 8 p.
[10] Nesterin I.M., Pichkhadze K.M., Sysoev V.K., Finchenko V.S. et al. Vestnik AO «NPO imeni S.A. Lavochkina» — Space Journal of FSUE “Lavochkin Association”. Cosmonautics and Rocket Engineering, 2017, no. 3, pp. 20–26.
[11] Koryukin A.V. Metallopolimernyye pokrytiya polimerov [Metal-polymer coatings of polymers]. Moscow, Khimiya Publ., 1983, 240 p.
[12] GOST R 25645.166–2004. Atmosfera Zemli verkhnyaya. Model plotnosti dlya ballisticheskogo obespecheniya poletov iskusstvennykh sputnikov Zemli [State Standard R 25645.166–2004. Earth upper atmosphere. Density model for ballistic support of flights of artificial earth satellites]. Moscow, IPK Izdatelstvo standartov Publ., 2004.