This thesis investigates the use of a dispatching system for the attitude control in space missions. Indeed, given the extended duration of these missions, conserving fuel for spacecraft attitude control while maintaining optimal performance is necessary. To address this challenge, magnetic torquers represent a promising addition to the actuation system, as they do not directly consume fuel and have been demonstrated success in previous space missions. In this context, the thesis outlines the development and simulation of a dispatching system, employing various optimization algorithms. The aim is to distribute the computed torque from the controller between the magnetic torquers and the cold gas thruster efficiently.