FIELD: space.
SUBSTANCE: invention relates to controling spacecraft around its centre of gravity. Method includes turning spacecraft around its axis of minimum moment of inertia (longitudinal). Before turning, longitudinal axis of spacecraft is aligned with plane formed by normal to orbital plane and radius vector of spacecraft. Turning is performed until angle between longitudinal axis of spacecraft and orbital plane reaches a certain value depending on speed of turning and ratio of minimum moment of inertia of spacecraft to average value of transverse moments of inertia. Turning speed (order of orbital) is selected depending on specified angle and ratio of moments of inertia of spacecraft. Angle between radius-vector of spacecraft and vector directed from spacecraft centre of gravity towards centre of aerodynamic pressure of solar panels of spacecraft must not be more than 90°.
EFFECT: technical result of invention consists in implementing long-term mode of gravity orientation with spinning, with evolution of spacecraft rotation towards acceleration.
1 cl
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|
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