The real attitude motion of a spacecraft based on indirect measurement data, i.e. the data of the electric current generated by its solar arrays, is reconstructed. The statistical technique for solving this problem is described. According to the technique, the measurements of the current, collected during a time interval about a few tens minutes, were processed simultaneously by means of the least squares method and integration of the spacecraft attitude motion equations. The estimates of the mathematical model parameters and initial conditions of an attitude motion were obtained as a result of such processing. The results of this reconstruction for low earth orbit and geostationary earth orbit satellite are given
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