Design of an Attitude Controller for Large-Angle Maneuvers of a Satellite considering of Reaction Wheels Constraints with High Fidelity Model

In this paper، a proportional-derivative attitude control system will be designed for large- angle maneuvers of a three-axis stabilized satellite using four reaction wheels and its stability is proven using Lyapanov theory. In this method، the nonlinear terms of satellite dynamic model are effective because of large angle rotational maneuvers and will be considered in designing the control law. Since the complex structure of the reaction wheels and their performance are effective on the stability and accuracy of satellite، therefore، in order to evaluate the effectiveness of the designed control system، the control accuracy and stability of the satellite will be evaluated using simulation in presence of Reaction Wheels Constraints with High Fidelity Model.