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 ωo 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 Mcont1 of vectors 
and 
on said axis 
and on axis directed along projection of vector 
on plane of orbit G2 and Mcont2 are determined. Angles of turn and correction of turn are found from comparison of present magnitude (G1) and threshold magnitude (Gcr) of respective projections at unlike signs of projections G2 and Mcont2. Discreteness of these angles and periodicity ((Δt)) of determination of required moment 
and preset minimum magnitude of relief during time Δt 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
