FIELD: astronautics.
SUBSTANCE: invention relates to reduction of spacecraft (SC) to rated parameters of its geostationary orbit at large initial deviations of these parameters from specified values. According to the method focused on the use of low-thrust engines, the actuation of the SC is performed through selectable and error-attenuated intermediate design longitude and period of revolution. Proposed selection of the latter and corresponding SC orbit correction plan provide sufficiently small deviations from nominal operating values of longitude and SC rotation period.
EFFECT: expansion of allowable initial deviations from nominal longitude and period of revolution of geostationary SC, at which specified reduction is feasible.
1 cl, 1 dwg
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