FIELD: aerospace navigation.
SUBSTANCE: in compliance with proposed method, required angle of engine thrust vector departure from normal to orbit in yawing plane is determined. This angle ensures preset accuracy of correcting spacecraft period and necessary changes per correction of transversal and orthogonal components of spacecraft speed. Departure of engine thrust vector directions are set and engine operating duration is computed by special formulae. A pair of engines arranged on opposite sides from normal effects correction. For this engines are sequentially switched on for computed time intervals.
EFFECT: accurate pulse processing, reduced power consumption, shorter breaks in use of spacecraft for its designated purpose.
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