Accuracy of estimating an orbiting object center of mass motion parameters on the base of star-spacecraft angle measuring results

Abstract

Using mathematical modeling, the accuracy of estimating motion parameters of the center of mass of a nonoperated spacecraft located in the vicinity of established standing point of the geostationary orbit, is investigated. The simulation is performed on the basis of measurements of the orbital object angular position relative to the stars, carried out with the use of on-board optoelectronic devices of a service space robot. The estimation of the motion parameters of the non–operated spacecraft center of mass is obtained using the recurrent least squares method when processing measurements of the star-spacecraft angles performed by the space robot optoelectronic devices. It is established that the problem of determining the parameters of spacecraft motion can be solved with errors of less than ± 0.6 m in coordinates and ± 0.2 mm/s in the velocity vector components. To achieve these characteristics, the on–board control system of the space robot must contain optoelectronic equipment that provides a standard error of measuring the starspacecraft angles, not exceeding 1”.