FIELD: astronautics.
SUBSTANCE: invention relates to control of movement of spacecraft (SC) on geostationary orbit (GSO) by means of engines of mainly ultra-low thrust (~ 0.1 N). Deviations of orbital parameters from specified initial values are considered to be high. Method consists in changing GSO rotation period and eccentricity with systematic maximum corrections possible for a given spacecraft during a day. At the same time dependence of deviation of the period optimal for the fastest moving of the spacecraft to the specified longitude of standing, from its current deviation is used.
EFFECT: technical result is bringing SC into preset longitude of standing at GSO for minimum time, taking into account of characteristic limitations, at that calculation of reduction can be made on-board of spacecraft.
1 cl, 1 dwg
