FIELD: transport.
SUBSTANCE: invention relates to spacecraft control with the help of jet engines and can be used in placing spacecraft into orbit by boost unit. Method comprises determining power functional via fixed times after cutting off sustainer assigned for aftereffect pulse termination. Then difference between preset power functional and reached power functional is determined. This difference being positive, time required for compensation of said difference is calculated with pulse correction engine cut in. Said time is limited by tolerable level which, is exceeded, is reset. If specified time does not exceed its minimum tolerable duration, pulse correction engines are cut in for this time. Note here that in calculating time required for compensation of power functional deviation from preset value, angular mismatch between speed vector and boost unit lengthwise axis is allowed for that defines pulse correction engine thrust direction.
EFFECT: higher accuracy of compensation, hence, accuracy of control over spacecraft preset orbit.
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