Comparative Design and Ballistic Analysis of Using Chemical and Electric Propulsion Systems in the Solar Probe Project

The possibility of implementing the solar probe project by launching a research satellite into the system of heliocentric orbits with a relatively small perihelion radius and a sufficiently large inclination to the solar equator (the inclination of the last heliocentric orbit to the plane of the solar equator should be at least 30°) is analyzed. A comparative design and ballistic analysis of the possibility of using chemical and electric propulsion systems (EP) when launching a spacecraft into the considered system of heliocentric orbits is conducted. The transport systems being analyzed assume the use of the Soyuz-2-1b launch vehicle and the chemical upper stage Fregat when launching the spacecraft from Earth. The propulsion systems of the spacecraft itself are different. In one case, a chemical propulsion system is used, in the other, a solar EP based on one stationary plasma thruster of the SPT-140 type. The time of launching the spacecraft into the last heliocentric orbit of the considered orbit system is limited to 5 years from above. It was shown that using EP can significantly increase the spacecraft mass in operational orbits (from 910 to 1600 kg).

Authors
Journal
Publisher
Maik Nauka Publishing / Springer SBM
Number of issue
5
Language
English
Pages
325-338
Status
Published
Volume
57
Year
2019
Organizations
  • 1 Российский университет дружбы народов
  • 2 ФГБОУ ВПО «Московский авиационный институт (национальный исследовательский университет)»
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Константинов М.С.
НЕКОТОРЫЕ АСПЕКТЫ СОВРЕМЕННЫХ ПРОБЛЕМ МЕХАНИКИ И ИНФОРМАТИКИ. Институт космических исследований Российской академии наук. 2018. P. 153-165