FIELD: control of angular motion of spacecraft by means of powered gyroscopes and attitude-control jet engines. SUBSTANCE: proposed method includes creation of cycles for pulse relief of powered gyroscopes where parameters of attitude and angular motion of spacecraft are measured; changes of vector of angular momentum in powered gyroscope system are tracked; time of saturation of powered gyroscope is determined by axes of basic connected with spacecraft; time of optimal relief of powered gyroscope is determined; then axis of relief of powered gyroscopes corresponding to maximum difference of above-mentioned times is selected; after relief of powered gyroscopes, length of time from moment of optimal relief of powered gyroscopes till saturation of gyroscopes is compared with remaining interval of maintenance of spacecraft attitude control. If this interval is more than above-mentioned length of time, relief of powered gyroscopes is performed again, provided next predicted length of time of saturation of powered gyroscopes exceeds previous one, otherwise, preset attitude of space-craft is maintained without relief of powered gyroscopes till moment of optimal relief of gyroscopes is determined anew. EFFECT: reduced consumption of working medium required for maintenance of preset attitude of spacecraft. 3 cl, 6 dwg
