Designing Spacecraft Attitude Control Using Model-free Optimal Control Theory

The purpose of the present paper is to prove the model-free optimal control theory. This theory is derived from the principles of dynamic programming and it is produced for discrete-time systems. The design of the controller depends merely on the I/O data of the controlled planet; hence, the controller is independent of the model. In this paper, two actions have been performed in order to measure the value of the controller. In the first step, the control method was designed to control the attitude of spacecraft. The purpose of this theory was to create a model-free optimal control for the spatial model and to measure the efficiency of the spacecraft systems. Secondly, designing linear quadratic regulator (LQR) controller for attitude control of spacecraft was carried out. The reason for designing this controller was to compare it with model-free optimal control. If the differences between two controllers was proved to be small, then the theory would be proven. Finally, it has been concluded that controller is valuable and acceptable.