Terminal control of the spatial orientation of a manipulative spacecraft in the program rotation mode

An algorithm has been developed for calculating the moments of inertia of the «manipulation spacecraft-sunscreen» system, depending on the time and angular position of the manipulation spacecraft relative to the mobile orbital coordinate system. The results of modeling the process of terminal orientation control of a manipulative spacecraft, taking into account changes in the components of its inertia tensor, are presented. The influence of changes in the moments of inertia of the spacecraft on the accuracy of its spatial orientation has been studied. The program for controlling the orientation of the manipulating spacecraft in the program rotation mode is calculated using a modified method of an approximate correction operator for constant control moments of orientation engines.