The results of the spatial accelerated ion flow density distribution and of the mean energy of ions exhausting thruster and moving in the different directions in the plume of the stationary plasma thruster operating with Krypton of the experimental SPT model of new scheme operating with Krypton are presented in the given paper. There are also presented the results of the directed radial and "back" ion flows in the vicinity of the mentioned SPT experimental model. Keywords: Stationary Plasma Thruster, gas discharge, crossed electric and magnetic fields, propellant flow ionization and accleration, plume divergence, radial and "back" ion flows.

Given paper presents the results of the propellant flow ionization peculiarities study in the discharge with crossed electric and magnetic fields burning in the different scale stationary plasma thruster (SPT) models with the ionization and acceleration layer shifted out of thruster, namely: there were determined the integral characteristics and dependences of the total current of the exhausting ions from thruster operating with Krypton under different operation modes. It is shown that the mentioned ion current and its ratio to the discharge current are typically reduced with increase of the discharge voltage and these trends are different from that ones for the standard SPT's. As result they cause the notable change of the thrust efficiency dependence on the discharge voltage. Keywords: Stationary Plasma Thruster, propellant flow ionization, gas discharge, crossed electric and magnetic fields.