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Analytical Synthesis of Stabilization Laws for Spacecraft Orbit Attitude Using Information on an Angle and the Full Vector of Angular Velocity

  • Flight Dynamics and Control of Flight Vehicles
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Abstract

The problem of stabilizing the spacecraft orbit attitude was solved analytically for the sixth order model of its rotary motion with the use of the output feedback control synthesis that is based on decomposition of a control object. Numerical simulation data are presented.

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Authors and Affiliations

  1. Bauman Moscow State Technical University, ul. 2-ya Baumanskaya 5, Moscow, 105005, Russia

    N. E. Zubov & V. N. Ryabchenko

  2. Korolev Rocket and Space Corporation Energiya, ul. Lenina 4a, Korolev, Moskow region, 141070, Russia

    E. A. Mikrin & I. V. Sorokin

Authors
  1. N. E. Zubov
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  2. E. A. Mikrin
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  3. V. N. Ryabchenko
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  4. I. V. Sorokin
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Corresponding author

Correspondence to N. E. Zubov.

Additional information

Original Russian Text © N.E. Zubov, E.A. Mikrin, V.N. Ryabchenko, I.V. Sorokin, 2018, published in Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2018, No. 2, pp. 53–63.

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Zubov, N.E., Mikrin, E.A., Ryabchenko, V.N. et al. Analytical Synthesis of Stabilization Laws for Spacecraft Orbit Attitude Using Information on an Angle and the Full Vector of Angular Velocity. Russ. Aeronaut. 61, 201–211 (2018). https://doi.org/10.3103/S1068799818020083

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  • DOI: https://doi.org/10.3103/S1068799818020083

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