2nd International Mars Sample Return 2018 (LPI Contrib. No. 2071) 6004.pdf THE DESIGNING OF THE MISSION TO MARS FOR THE SOIL DELIVERY BY THE ELECTRIC PROPULSION SPACECRAFT. O. L. Starinova1, Ch. Gao2, D. V. Kurochkin3 and H. Yudong4, 1Professor of Space Engineering Department, Samara National Research University, Russian Federation,
[email protected], 2Accosiate professor of Harbin University of Technology, People's Republic of China,
[email protected], 3Engineer of Space Engineering Department, Samara National Research University, Russian Federation, 4Master student , Sa- mara National Research University, Russian Federation. Introduction: Mission to return soil from Mars is choosing the design parameters corresponding to the a typical kind of transfer with the return to the source minimum spacecraft launching mass. orbit. The effectiveness of such a flight depends on The movement of the electric propulsion spacecraft many parameters describing the design scheme of is described by the system of the differential equations spacecraft and the features of the trajectory. It is well take into account the following assumptions. The known [1]-[4] that the electric propulsion spacecraft is spacecraft contemporaneously is subject to the gravita- the most useful for interplanetary flights at the present tion of the one-body (a planet or the Sun). The gravita- stage of space technology development. tional field of all bodies isn't central. The Earth and The problem of comprehensive optimization of the Mars atmospheres are standard. The planet orbits rela- trajectory and the ballistic parameters of a low-thrust tive to the Sun are known. mission Earth-Mars-Earth is formulated and solved in A design vector which uses to create the design this paper.