FIELD: astronautics.
SUBSTANCE: invention relates to space engineering. In method of automatic orientation of spacecraft (SC) and solar battery (SB) in case of failure of solar battery rotation device SB angular position relative to the Sun is determined and connected with it coordinate system (FCS). To reduce mismatch between projection of vector of direction to Sun and normal to SB working surface command for rotation and SB rotation termination are given. When after issuing command nearest to current solar panel position is determined corresponding to position of the solar panel fixed position relative to FCS. Establishing fixed value of specified angle corresponding to nearest fixed value relative to FCS is controlled during preset time interval setting of solar panel in given fixed position.
EFFECT: technical result is increased resource of operation and increased durability of the spacecraft in case of device for turning solar panel failure.
1 cl, 4 dwg
