Mechanism of formation of the disturbing moment by the mobile mass of a spacecraft

The functional efficiency of a spacecraft depends largely on the accuracy of its attitude control and stabilization systems, which compensate for external and internal disturbances. The operating algorithms of these systems are based on dynamic equations describing the rotational motion of the spacecraft under the influence of control torques, internal and external disturbances from moving masses, and gravitational, magnetic, and aerodynamic effects. However, spacecraft attitude control algorithms pay insufficient attention to internal uncontrolled disturbance factors due to their relatively small magnitude. This reduces the accuracy of the spacecraft’s attitude control and stabilization. As the mass and service life of spacecraft increase, the total energy consumption for compensating for internal disturbance torques increases significantly. Therefore, this article analyzes the dynamic equations for the influence of internal disturbances from moving masses in a spacecraft on its angular destabilization. The mechanisms for generating kinetic momentum and Coriolis momentum are considered in a fixed coordinate system. The Coriolis moment is initiated by the rotation of the spacecraft, with translational motion superimposed on the relative motion of the mass. Conditions for mass movement in the spacecraft that reduce the level of internal disturbances are specified.
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