| 摘要 |
FIELD: transport.SUBSTANCE: invention relates to aerospace engineering, particularly, to spacecraft orientation. Proposed method comprises the steps that follow. Generation of angle estimate signal and signal of spacecraft spin rate. Generation of control estimate signal. Determination of difference in angle signal and angle estimate signal. Determination of difference in spin rate and spin rate estimate signal. Determination of difference in control signal and control estimate signal and determination of corrected angle estimate signal, corrected spin rate estimate signal and outer interference estimate signal. Then, generated are control signal with corrected angle estimate signal, corrected spin rate estimate signal and external interference estimate signal. Proposed device to this end comprises five normally-closed switches, two normally-open switches, seven adders, model of engine-flywheel, two amplifiers and five integrators.EFFECT: higher accuracy and reliability.2 cl, 1 dwg |
