Computation of Hall thruster performance

A quasi-neutral one-dimensional hybrid model of a stationary plasma thruste r has been used tu predict the performance of a laboratory model thruster t ested in the Propulsion Ionique pour Vols Orbitaux, Interpretation et Nouve lles Experiences, facility. In this model ions are treated as particles and electrons as a fluid and quasi neutrality is assumed. We describe the calc ulated efficiencies, thrust, and specific impulse using xenon and krypton a s propellant and their variations as a function of applied voltage and mass Row rate, Typically, for a voltage of 350 V and an anode mass Row rate of 5 mg/s, the thrust is on the order of 75 mN fur xenon and krypton, and the global efficiency is 40 and 30%, respectively, for xenon and krypton, Altho ugh the model is rather simple, the predicted trends are in reasonable agre ement with the experimental measurements, The question of doubly charged io ns is also examined, and results show that they do not strongly contribute to performance in a stationary plasma thruster-100 Hall thruster.