FIELD: control systems.
SUBSTANCE: invention relates to spacecraft (SC) with self-colocation (SCSC) movement control near preset work position on geostationary orbit during its collocation with adjacent SC (ASC) located with SCSC in single holding area. Method includes correction of SCSC retention in accordance with dependence of sidereal period of revolution on SC current position on longitude. Beforehand according to trajectory measurements, the highest possible value of the eccentricity vector (EV) of the ASC orbits is detected. EV module of SCSC orbit makes larger than the specified maximum value and EV corrections are used to convert SCSC to solar-synchronous (with constant orientation of EV on Sun) orbit. When changing ASC retention strategy and its dangerous approach to SCSC, evasion maneuvers (EV orbit corrections) of SCSC are performed.
EFFECT: technical result is guaranteed removal of SCSC from ASC by height during maneuvers, which allows its autonomous collocation with unlimited number of ASC.
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