On the Control of Angular Motion and Correction of the Satellite Orbit Using a Limited Set of Rocket Thrusters

The control of the motion of an automatic spacecraft (SC) is considered. For maneuvering and angular stabilization, a propulsion system with a small number of liquid rocket thrusters is used as an actuator. In order to ensure the simultaneous control of the motion of the center of mass of the SC and its stabilization using thrusters, at each moment of time, it is necessary to solve the problems of determining the required change in the speed of the SC, as well as the problem of choosing the optimal configuration of the thrusters for controlling the angular motion of the SC and correcting its orbit. Methods for solving these problems, which can be applied in the control system of the considered SC, are presented. The operability of the described algorithms is confirmed by the results of mathematical modeling on a ground-based test bench for the onboard software.