Control of the Earth remote sensing spacecraft using rotors

The method of reorientation of a satellite-gyrostat for remote sensing of the Earth using a flywheel engine is considered, at any location of the spacecraft relative to the object of observation. In the course of the study, geometric dependences of the angles of nutation and precession on time were derived, differential equations of motion of the spacecraft relative to the center of mass were constructed, their solutions were obtained and corresponding graphs were constructed. The obtained equations make it possible to determine the motion parameters (coordinates and velocities) depending on the inertial mass characteristics of the system, initial conditions and time, as well as to control the effect of these parameters on the system. The article presents the results of the conducted research showing the operability of the developed mathematical model, thanks to which it is possible to determine the control actions for the reorientation of the gyrostat satellite. A practical application may be the use of the results obtained when aiming spacecraft at an object of observation.