FIELD: spacecraft attitude control systems. SUBSTANCE: prior to first internal of measurements, attitude is measured taking into account spacecraft configuration at which magnetic moment of solar batteries is equal to zero. Then, this attitude is plotted and maintained and moment of momentum of powered gyroscopes is measured at all intervals of measurements. Magnitude of total moment of momentum of spacecraft is calculated by measured moments of momentum and angular velocity. Then, magnitude of main moment of external forces at all intervals of measurements is determined. Magnetic moment of solar batteries is determined by results of change of main vector of external force moment and magnitudes of Earth magnetic field. EFFECT: possibility of determination of magnetic moment of solar batteries under any conditions and various modes of spacecraft attitude. 1 dwg, 1 tbl
