Satellite Orbit correction using Model based Predictive Control

In this paper autonomous modification of satellite attitude in its orbit is implemented for low earth orbit satellites using Model Predictive Control. MPC minimizes force which applying on the thrusters subject to hard constraints on the control input and output of the system. Here Clohessy-Wilshire equations are utilized by consideration of main disturbance of low orbits such as Atmospheric Drag and Non-Spherical earth disturbance for the design of MPC. The result of simulation proves that this MPC can amend the difference between the linear and non-linear mathematical models of the satellite. In addition, not only orbital disturbances are compensated but also the satellite maintained in orbit with high accuracy. For performance evaluation of this MPC method, A Linear Quadratic Regulator is realized for Orbitchr('39')s autonomous control; the result of these two methods demonstrated that fuel consummation and control effort in MPC manner is considerably less than LQR method.