FIELD: astronautics.
SUBSTANCE: invention relates to spacecraft orientation control, carried out in the solar-terrestrial coordinate system. Method includes orienting the first axis of spacecraft towards the Earth by turning around the second and third axes of the spacecraft using electromechanical actuators. In the absence of Earth's shadow, control actions around the second axis of the spacecraft are generated based on information from the instrument for orientation towards the Earth, and relative to the third axis of the spacecraft – based on information from the instrument for orientation towards the Sun.
EFFECT: technical result is reduced error of orientation of spacecraft towards the Earth.
1 cl, 3 dwg
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