FIELD: cosmonautics.
SUBSTANCE: invention relates to interplanetary multipulse flights with landing on the Moon, in which near-earth (SS) and lunar (LSS) space stations are used. Manned reusable spacecraft (MRS) based on SS is separated from it, transferred to LSS in circular circumlunar orbit and docked with it. A lunar shuttle vehicle (LSV) with a take-off module function is based on the LSS, which is docked with the pre-transferred to LSS fuelled landing stage (LS) and the upper stage (US). After undocking from the LSS, the US transfers LSV and LS to a low circumlunar orbit, separates itself, and the LSV lands on the lunar surface by means of the LS. After take-off of the LSV from the Moon and docking with the US in the waiting orbit, it is delivered to the LSS and docked with it. MRS is separated from LSS and transferred to return orbit with perigee in the Earth's atmosphere and apogee, after braking in atmosphere, at altitude of SS orbit. An apogee pulse is used to transfer the MRS to the SS orbit for subsequent docking with it.
EFFECT: creation, based on launch vehicle of heavy class, of competitive transport system for regular flights to the Lunar base, using braking in the Earth atmosphere for return of MRS to SS.
1 cl, 1 dwg, 3 tbl
