Spacecraft Attitude Control Using a Control Moment Gyro with Multiple Degrees of Freedom

Abstract

In this study, the performance of rate damping control from a control moment gyro is investigated. Two types of wheel angular momentum (variable and constant) and two quantities of gimbal axes (one or two) are considered. When the angular momentum of the spacecraft body is fully absorbed by the wheel, the rate damping of the spacecraft can be achieved. In contrast, for cases of with constant wheel speed, the rate damping of the spacecraft body cannot be achieved. The steady state analysis of the rate damping control in these cases shows the stationary value of the angular velocity of the spacecraft. Numerical simulations verify the analytical results.