Some results for the study of the spacecraft (SC) flight from low-Earth orbit of the Earth artificial satellite (EAS) to low-Moon orbit of the Moon artificial satellite (MAS) are given. To decrease the energy consumption for the transfer, an intermediate geocentric orbit with the capture by the Moon is used in this trajectory. During a passive motion along this orbit, the SC comes in the Lunar sphere of influence near the libration point L₁ and goes to the Moon along a selenocentric elliptic orbit. The trajectory for the transfer between the EAS and MAS orbits is studied in frame of the four-body problem (SC, Earth with its oblateness, Moon and Sun). The control is performed by a low thrust. All the flight consists of three parts. At first, an active controlled geocentric flight from the initial orbit of the EAS to the intermediate geocentric orbit of the capture is performed. Then, a passive flight along an arc of the capture orbit and the SC coming in the Lunar sphere of influence is realized. At the final part of the trajectory, an active controlled selenocentric flight from the intermediate orbit to the final orbit of the MAS is performed. Some geometric, energy and time characteristics of the flight are given.

Earth-Moon flight, low thrust, capture orbit, optimal space trajectories

Theoretical and applied problems of mechanics