METHOD OF FORMING CONTROL MOMENTS ON SPACECRAFT PROVIDED WITH POWERED GYROSCOPES AND SWIVEL SOLAR BATTERIES AND SYSTEM FOR REALIZATION OF THIS METHOD

摘要

FIELD: control systems; relief and compensation of disturbances acting on three-axis stabilization spacecraft. SUBSTANCE: method consists in determination of angular velocity of spacecraft and its kinetic moments: in powered gyroscope system and total moment The following data are found according to measured direction to Sun : time of application of control moment of light pressure forces to spacecraft which is formed through turning the solar battery. Selection is made on the condition of contrast of signs of projections and on axis preset by vector where ω_o is unit vector of orbital angular velocity and is average rate of change of vector according to magnitudes measured before. At initial and subsequent moments of time of forming , projections G₁ and M_cont1 of vectors and on said axis and on axis directed along projection of vector on plane of orbit G₂ and M_cont2 are determined. Angles of turn and correction of turn are found from comparison of present magnitude (G₁) and threshold magnitude (G_cr) of respective projections at unlike signs of projections G₂ and M_cont2. Discreteness of these angles and periodicity ((&Dgr;t)) of determination of required moment and preset minimum magnitude of relief during time &Dgr;t are taken into account. On-board system used for realization of proposed method includes functional units and their couplings. Proposed system ensures relief and continuous compensation of disturbing moment on spacecraft at any number of gyroscopes and effective use of solar batteries for forming control moments from light pressure forces. EFFECT: saving of working medium; increased service life of engine plants. 3 cl, 7 dwg