Currently, an urgent problem is the use of an electric propulsion system for interorbital flights.

During the flight, various perturbing forces and moments act on the spacecraft, which will lead to significant deviations of the actual flight path from the nominal. Therefore, it is necessary to periodically adjust the motion control program in order to ensure a given accuracy of launching into the target orbit.

In general, the solution to the control problem is built in two stages. At the first stage, algorithms are formed that make it possible to transfer the deviation vector of the final state to a certain region in which one or more components of the deviation vector of the final state satisfy a given accuracy. At the second stage, control laws and algorithms for narrowing the region of deviations of the final trajectory parameters to the region where all the components of the deviation vector of the final state satisfy the given accuracy are formed. In this paper, we consider the solution to the control problem at the first stage.

The calculation results show that during an interorbital flight using an electric propulsion system, actions of various kinds of perturbations on the spacecraft, primarily from inaccurate implementation of the thrust magnitude, lead to significant deviations of the final trajectory parameters. In this paper, we propose an algorithm for refining the thrust of a propulsion system by measuring the actual period of circulation. To measure the actual period of circulation on the trajectory, passive sections are introduced. After specifying the thrust value, the control program is adjusted.

The results of modeling the trajectory motion of a spacecraft with an electric propulsion system during a flight into a geostationary orbit showed that the algorithm for refining the thrust and correction of the control program allows us to narrow the deviation range of the final trajectory parameters, reducing the error along the major semiaxis by an order of magnitude and transferring the spacecraft to near equatorial orbit.