FIELD: cosmonautics.
SUBSTANCE: invention relates to interplanetary multipulse flights. In the disclosed method, the first launch is used to place a manned crew transfer vehicle (MCTV) into orbit of a near-earth space station (SS) and docked with it. Oxygen-hydrogen upper stage (OHUS) is brought to SS by the second launch. Heavy-duty RC is used for launches. OHUS coupled with MCTV generates an outbound impulse to the Moon and then separates. After the transition to the circular circumlunar orbit, the MCTV docks with the lunar SS (LSS), where lunar shuttle vehicle (LSV) with take-off module function is based. Fuelled landing stage (LS) and upper stage (US) are delivered to LSS beforehand. After docking of MCTV with LSS and separation from LSS of LSV-US-LS bundle, US transfers the bundle to low circumlunar orbit and then undocks. LSV uses LS to land on the lunar surface. After take-off, the LSV is placed in a circumlunar orbit where the US is located, which transfers the LSV to the LSS orbit and undocks (the LS remains on the Moon). Then LSV is docked with LSS, and MCTV is undocked from LSS and sent to Earth with further landing on it.
EFFECT: creation of an energetically rational competitive transport system with a stable flight pattern for regular flights, in particular, to a lunar base.
1 cl, 1 dwg, 2 tbl
