Abstract. Results of pilot studies of changing the characteristics of optical sensors of the spacecraft movement control system under the impact of external destructive influences of thermal and mechanical nature are presented. An analytical description is derived for dependencies of the sensor characteristics deter-mining the accuracy of the retention of the angular position of the spacecraft irrespective of the change in optical parameters of its elements, which allows to determine the maximum permissible levels of the influencing factors. The choice of the object of experimental research is substantiated and its constructive-functional scheme is presented. The problems of experimental research are formulated, the experimental procedure is presented, and the graphs of the output control signal versus the angular position are plotted based on the results of the experiments and simulations. 

Keywords: космический аппарат, система управления движением, оптические датчики, лазерное излучение

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