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The results of flight tests of an attitude control system for the Chibis-M microsatellite

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Abstract

The attitude control system of the Chibis-M microsatellite is described. Results of flight experiments on damping the initial angular velocity (made using magnetorquers) are considered, as well as stabilization in the orbital referece frame, and orientation of solar arrays toward the Sun using reaction wheels. The operation of algorithms of satellite attitude determination on sunlit and shadow segments of the orbit is also under study. The general logic of operation of the attitude control system in automatic mode is presented and discussed.

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Authors and Affiliations

  1. Keldysh Institute of Applied Mathematics, Russian Academy of Sciences, Miusskaya sq. 4, 125047, Moscow, Russia

    D. S. Ivanov, M. Yu. Ovchinnikov, D. S. Roldugin & S. S. Tkachev

  2. SputniX, Ltd, Berezhkovskaya nab., 20-6, 123995, Moscow, Russia

    N. A. Ivlev & S. O. Karpenko

Authors
  1. D. S. Ivanov
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  2. N. A. Ivlev
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  3. S. O. Karpenko
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  4. M. Yu. Ovchinnikov
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  5. D. S. Roldugin
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  6. S. S. Tkachev
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Corresponding author

Correspondence to D. S. Ivanov.

Additional information

Original Russian Text © D.S. Ivanov, N.A. Ivlev, S.O. Karpenko, M.Yu. Ovchinnikov, D.S. Roldugin, S.S. Tkachev, 2014, published in Kosmicheskie Issledovaniya, 2014, Vol. 52, No. 3, pp. 218–228.

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Ivanov, D.S., Ivlev, N.A., Karpenko, S.O. et al. The results of flight tests of an attitude control system for the Chibis-M microsatellite. Cosmic Res 52, 205–215 (2014). https://doi.org/10.1134/S0010952514020038

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  • DOI: https://doi.org/10.1134/S0010952514020038

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