METHOD OF LIGHT-SAIL SPACECRAFT REORIENTATION AND THRUST CONTROL Russian patent published in 2013 - IPC B64G1/28 G05D1/08 

FIELD: transport.

SUBSTANCE: invention relates to propulsion systems of spacecraft, particularly, to control over light-sail spacecraft thrust. Proposed method consists in varying angle of spacecraft orientation in space by varying its spinning parameters. Orientation through required angle is carried out by temporary loss of stability of spacecraft instantaneous axis and its recovery in reorientation of instantaneous axis through required angle relative to initial position. Loss of stability occurs owing to controlled change of the relationship between magnitudes of three main moments of inertia of spacecraft relative to its three main orthogonal axes. Moment of inertia relative to the axis of spacecraft stable spinning, initially maximum among three main moments of inertia, is rendered, temporarily and in controlled way, the mean moment of inertia. In spacecraft reorientation through required angle, said main moment of inertia is, again, rendered the maximum value. Moments of inertia are varied by redistributing spacecraft masses relative to appropriate axes in radial direction.

EFFECT: reorientation irrespective of solar light effects.

3 cl, 6 dwg