The complex problem of constructing the return trajectories of a spacecraft (SC) from a circumlunar orbit before entering the Earth's atmosphere for subsequent landing on the southern territory of the Russian Federation is considered. The problem includes two components: the choice of the conditions for the optimal impulse maneuver for the Moon-Earth flight and the determination of the descent distance from the point of entry into the Earth's atmosphere to the given landing point. The magnitude of the impulse required and the sufficient descent distance to return on any date are estimated.
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