METHOD FOR UNIAXIAL ORIENTATION OF SPACECRAFT WITH ELONGATED SHAPE Russian patent published in 2016 - IPC B64G1/34 B64G1/28 

FIELD: astronautics.

SUBSTANCE: invention relates to control of a spacecraft (SC) motion around its centre of gravity. Method includes spinning of the SC around its axis of minimum moment of inertia (longitudinal). Before spinning, longitudinal axis of the SC is aligned with a plane formed by a normal to orbital plane and radius vector of the SC. Spinning is performed upon reaching by the angle between the longitudinal axis of the SC and the orbital plane of the maximum permissible deviation (β₀) of the longitudinal axis of the SC from a local vertical. At that, the angle between the SC radius-vector and the vector directed from the SC center of gravity to the centre of aerodynamic pressure of SC sun batteries, shall be less than 90°. Angular rate of spinning (of orbital order) is selected depending on the angle β₀ and ratio of the SC minimum moment of inertia to the average value of transverse moments of inertia.

EFFECT: implementation of a long-term mode of gravitational orientation of a SC with spinning at SC rotation evolution towards deceleration.

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