Satellite Attitude Control by using Back Steeping and Feedback Linearization Methods

In this paper, a combination of step-back theories and linear feedback is used to control the status of a satellite. Dynamic equations govern the status of nonlinear and multi-input-multi-output satellites. The angles of rotation, the direction and top of the outputs of this system and the torques around the three axes of the satellite are its inputs. In the proposed algorithm, which uses the step-back theory, in the first step, the linear input-output feedback method is used for multi-inputmulti-output systems, and the desired angular velocities around the three axes of the satellite are determined. Using this method, in the second step, we will face three single-input-single-output subsystems. Then, in the second step, in order for the angular velocities to reach the desired values, the linear feedback theory is once again used to generate torques around three axes. Finally, computer simulation is performed to evaluate the efficiency of the proposed method.