Attitude control and momentum management for the spacecraft with inertial actuators on high-elliptical orbit

The article deals with the dynamics of the angular motion of the spacecraft on the high-elliptical orbit. The attitude control and momentum management algorithm is designed for the spacecraft with inertial actuators on the high-elliptical orbit using gravity gradient torque. Accurate pole placement method is used to develop attitude control and momentum management control laws. A numerical solution is derived for attitude control low and momentum management of the spacecraft on the high-elliptical orbit on all three control channels in the vicinity of the perigee of the orbit. Also, the stability analysis is performed for the linearized differential equations describing the dynamics of the spacecraft on the high-elliptical orbit.