FIELD: astronautics.
SUBSTANCE: invention relates to spacecrafts (SC) orientation control by a solar sensor. Method consists in the Sun angular position measuring (two angles) in the SC own axes in successive time intervals. Angular velocity estimates are calculated on the basis of the measured angles from simplified (integer) formulas followed by their filtration (to reduce the effect of the solar sensor short-term false readings). Enabled estimation of all three components of the SC angular velocity without use (in case of failure) of angular velocity sensors.
EFFECT: increasing the SC reliability with a decrease in the load on the onboard computer.
1 cl, 2 dwg
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