FIELD: physics; control.
SUBSTANCE: invention relates to space engineering. A method of controlling orientation of a spacecraft with fixed solar panels when conducting experiments on orbits with maximum duration of the eclipse period includes gravitational orientation of the spacecraft by the longitudinal axis along the local vertical and spinning around its longitudinal axis, which corresponds to the minimum moment of inertia. Gravitational orientation of the spacecraft and its spinning are performed with the value of the angle between the direction towards the Sun and the orbital plane not greater than a given value. The time when the spacecraft passes the counter-sun point of the orbit pass is further determined and recorded.
EFFECT: maximum overall illumination of the working surface solar panels in one pass.
4 dwg
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