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Optimization of the trajectory of the spacecraft insertion into the system of heliocentric orbits

Cosmic Research volume 55, pages 214–223 (2017)Cite this article

Abstract

The possibility of the spacecraft insertion into the system of operational heliocentric orbits has been analyzed. It has been proposed to use a system of several operational heliocentric orbits. On each orbit, the spacecraft makes one or more revolutions around the Sun. These orbits are characterized by a relatively small perihelion radius and relatively high inclination, which allows one to investigate the polar regions of the Sun. The transition of the spacecraft from one orbit to another has been performed using an unpowered gravity assist maneuver near Venus and does not require the cruise propulsion operation. Each maneuver transfers the spacecraft into the sequence of operational heliocentric orbits. We have analyzed several systems of operational heliocentric orbits into which the spacecraft can be inserted by means of the considered transportation system with electric propulsion (EP). The mass of the spacecraft delivered to these systems of operational orbits has been estimated.

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Authors and Affiliations

  1. Moscow Aviation Institute, Moscow, 125993, Russia

    M. S. Konstantinov & Min Thein

Authors
  1. M. S. Konstantinov
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  2. Min Thein
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Correspondence to M. S. Konstantinov.

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Original Russian Text © M.S. Konstantinov, Min Thein, 2017, published in Kosmicheskie Issledovaniya, 2017, Vol. 55, No. 3, pp. 226–235.

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Konstantinov, M.S., Thein, M. Optimization of the trajectory of the spacecraft insertion into the system of heliocentric orbits. Cosmic Res 55, 214–223 (2017). https://doi.org/10.1134/S0010952517020034

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  • DOI: https://doi.org/10.1134/S0010952517020034