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Onboard Iterative Algorithm of Defining the Parameters of Keplerian Orbits Based on Solving the Orbital Motion Equations in Velocity Reference Frame

  • FLIGHT DYNAMICS AND CONTROL OF FLIGHT VEHICLES
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Abstract

We suggest a determined iterative algorithm of defining the planar parameters of a spacecraft Keplerian orbit in the velocity reference frame. Analytical relations for creating the iterative algorithm and the numeric example of defining parameters of a spacecraft Keplerian orbit are given.

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Authors and Affiliations

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

    N. E. Zubov, V. N. Ryabchenko & A. V. Lapin

  2. S.P. Korolev Rocket and Space Corporation Energiya, ul. Lenina 4A, 141070, Korolev, Moscow oblast, Russia

    N. E. Zubov & A. V. Lapin

Authors
  1. N. E. Zubov
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  2. V. N. Ryabchenko
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  3. A. V. Lapin
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Corresponding author

Correspondence to N. E. Zubov.

Additional information

Translated from Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2021, No. 3, pp. 67 - 74.

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Zubov, N.E., Ryabchenko, V.N. & Lapin, A.V. Onboard Iterative Algorithm of Defining the Parameters of Keplerian Orbits Based on Solving the Orbital Motion Equations in Velocity Reference Frame. Russ. Aeronaut. 64, 432–440 (2021). https://doi.org/10.3103/S1068799821030090

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  • DOI: https://doi.org/10.3103/S1068799821030090

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