Semi-empirical electromechanical model for pulsed plasma thrusters using two different approaches and comparison with experimental results

Space engines are used for missions such as altitude change, position control, position maintenance, landing, and orbit change. In recent decades, the use of plasma thrusters as a space propulsion system has been considered, one of which is the pulsed plasma thrusters. In this paper, a quasi-experimental electromechanical model for rectangular flat plate electrodes has been developed using two different approaches: slug and snowplow. By equating the whole physical process as a one-dimensional electrical circuit and in the next step, coupling it with the force equation as well as using some experimental parameters, the electromechanical model is obtained. The results of this semi-empirical model are compared and evaluated with the basic experimental parameters for pulsed plasma thrusters used in two satellites. According to the positive results of the evaluations, using this semi-empirical model, the basic parameters of a pulsed plasma thruster such as impulse bit and plasma exhaust velocity can be calculated and some geometric parameters and capacitor parameters of this thruster can be optimized and controlled. The two approaches of slug and snowplow in this model are also compared with experimental results.