Abstract
The article describes a method of reorienting of the Earth remote sensing gyrostat satellite using a flywheel engine, while located in the same vertical plane with the observation object. In the course of the study, a geometric dependence of the nutation angle on time was derived, differential equations of the motion of the spacecraft relative to the center of mass were generated and solutions were obtained. These obtained equations allows to determine motion parameters (coordinates and speeds) depending on the inertial mass characteristics of the system, initial conditions and time, as well as control the effect of these parameters on the system. The article presents the results of conducted studies that show the performance of the developed mathematical model. Thanks to the developed model, it is possible to determine the necessary control actions to target the gyrostat satellite to the observation object with high accuracy.
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