Plasma flow and plasma-wall transition in Hall thruster channel

In this paper a model of the quasineutral plasma and the transition between the plasma and the dielectric wall in a Hall thruster channel is developed . The plasma is considered using a two-dimensional hydrodynamic approximati on while the sheath in front of the dielectric surface is considered to be one dimensional and collisionless. The dielectric wall effect is taken into account by introducing an effective coefficient of the secondary electron emission (SEE), s. In order to develop a self-consistent model, the boundar y parameters at the sheath edge (ion velocity and electric field) are obtai ned from the two-dimensional plasma bulk model. In the considered condition , i.e., ion temperature much smaller than that of electrons and significant ion acceleration in the axial direction, the presheath scale length become s comparable to the channel width so that the plasma channel becomes an eff ective presheath. It is found that the radial ion velocity component at the plasma-sheath interface varies along the thruster channel from about 0.5C( s) (C-s is the Bohm velocity) near the anode up to the Bohm velocity near t he exit plane dependent on the SEE coefficient. In addition, the secondary electron emission significantly affects the electron temperature distributi on along the channel. For instance in the case of s=0.95, the electron temp erature peaks at about 16 eV, while in the case of s=0.8 it peaks at about 30 eV. The predicted electron temperature is close to that measured experim entally. The model predictions of the dependence of the current-voltage cha racteristic of the ExB discharge on the SEE coefficient are found to be con sistent with experiment. (C) 2001 American Institute of Physics.