Design and Implementation of State Feedback Controllers for Spacecraft Attitude Stabilization

This paper presents a comprehensive approach to the design and implementation of state feedback controllers for the stabilization of spacecraft attitude. We begin by formulating the spacecraft’s dynamic and kinematic models, which describe the evolution of attitude angles (roll, pitch, yaw) and their corresponding angular velocities. The design of the state feedback controller is achieved using the pole placement method, where the gain matrix K is computed to position the closed-loop poles at desired locations in the complex plane. This approach ensures robust stability and precise control of the spacecraft’s attitude. The effectiveness of the proposed control strategy is demonstrated through simulations, which show that the attitude angles and angular velocities converge to desired values efficiently. Our results confirm that state feedback control is a powerful tool for achieving stable and controlled spacecraft orientation, highlighting its practical applicability in space missions.