Modification of the exact pole placement method and its application for the control of spacecraft motion

For linear stationary models of the spacecraft motion, a modification of the exact pole placement method is developed that makes it possible to design a modal control for any class of linear stationary systems. In the case of circular orbits, the modified method is used to obtain an analytical solution of the problem of gravitational angular momentum unload problem for inertial actuators of a spacecraft in the gyroscopically coupled roll-yaw channels.