Momentum transfer control of a spacecraft with two wheels by feedback linearization

The momentum transfer control of a rigid spacecraft with two momentum wheel actuators is investigated using feedback linearization technique focusing on very small nutation angle as a performance index. The equations of motion are transformed to a general linearized form by feedback linearization, including a guarantee of internal dynamics stability. It is known that the configuration of inertia properties plays a pivotal role by analyzing spacecraft energy level. The assistance of added wheel is also analyzed analytically and numerically. The effectiveness of the proposed control law is verified through simulation results.