FIELD: transport.
SUBSTANCE: method includes choice of certain groups of jet engines (JE) for correction of spacecraft (SC) and intervals for JE actuation. JE performance is correlated with work of powered gyroscopes supporting desired orientation of SC in process of orbit correction. The said choice is made from current and anticipated values of angular momentum sum vector of SC with regard to external disturbing moments and JE thrust moments. At that anticipated momentum value of actuated group of JE is maximised with correction continued until difference between anticipated and current value remains admissible. Maximisation is effected on a number of JE available and a number of possible intervals of actuating such and such JE groups.
EFFECT: increase of spacecraft orbit correction efficiency by available set of jet engines.
4 dwg
