Skip to main content

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

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.

This is a preview of subscription content, access via your institution.

References

  1. Solar Probe Plus, NASA Goddard Space Flight Center. http://solarprobe.gsfc.nasa.gov/spp_mission.htm.

  2. Solar Probe+ Mission Engineering Study Report, Prepared for NASA’s Heliophysics Division by the Johns Hopkins University Applied Physics Laboratory, 2008.

  3. Kuznetsov, V., The Russian InterhelioProbe Mission, in Fourth Solar Orbiter Workshop, Telluride, Colorado. USA, 2011, pp. 27–31.

    Google Scholar 

  4. InterhelioProbe Project: Workshop Proceedings, Tarusa, May, 11–13, 2011, Kuznetsov, V., Ed., 2011.

  5. Konstantinov, M.S., Petukhov, V.G., and Loeb, H.W., Application of RIT-22 thruster for InterhelioProbe Mission, Elektron. Zh. Tr. MAI, 2012, no. 60.

    Google Scholar 

  6. Konstantinov, M.S. and Petukhov, V.G., One version of a space transport system for research of the Sun, in The 62-nd International Astronautical Congress, Paper IAC-11.C4.6.10. Cape Town, South Africa, 2011.

    Google Scholar 

  7. Konstantinov, M.S., Petukhov, V.G., and Min, T., The one mission for Sun exploration, in Proceeding of the 63-th International Astronautical Congress, Paper IAC-12-A3.5.5, Naples, Italy, 2012.

    Google Scholar 

  8. Konstantinov, M.S. and Thein, M., Optimization of the trajectory of space vehicle insertion into a working heliocentric orbit, Elektron. Zh. Tr. MAI, 2013, no. 67.

    Google Scholar 

  9. Petukhov, V.G. and Popov G.A., Heliocentric trajectories of a space vehicle with ion propulsion for Sun exploration, Elektron. Zh. Tr. MAI, 2011, no. 42.

    Google Scholar 

  10. Konstantinov, M.S. and Thein, M., Analysis of a spacecraft flight scheme for Sun exploration, Elektronnyi zhurnal, Elektron. Zh. Tr. MAI, 2013, no. 71.

    Google Scholar 

  11. Konstantinov, M.S., Petukhov, V.G., and Thein, M., Optimization of the spacecraft insertion into the system of heliocentric orbits for Sun exploration, in Proceeding of the 65th International Astronautical Congress, Paper IAC-14.C1.9.4. Toronto, Canada, 2014.

    Google Scholar 

  12. Asyushkin, V.A, Vikulenkov, V.P., and Ishin, S.V., Results of the creation of initial stages for the operation of Fregat inter-orbital space transfer facilities, Vestn. NPO im. S. A. Lavochkina, 2014, no. 1.

    Google Scholar 

Download references

Author information

Authors and Affiliations

Authors

Corresponding author

Correspondence to M. S. Konstantinov.

Additional information

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

Rights and permissions

Reprints and Permissions

About this article

Verify currency and authenticity via CrossMark

Cite this article

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

Download citation

  • Received:

  • Published:

  • Issue Date:

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