Modeling of Stationary Plasma Thruster-100 Thruster Plumes and Implications for Satellite Design

A computational model of a stationary plasma thruster (SPT) has been developed using a quasineutral particle-in-cell/direct simulation Monte Carlo (PIC-DSMC) model. This model is based on theoretical work showing that the plume consists of a quasineutral plasma with collisionless electrons in which the magnetic field can be neglected. Details of the PIC DSMC method are presented as well as axisymmetric and three-dimensional results. Comparisons are made to new and previously reported experimental data. The model is shown to produce results similar to laboratory measurements of the ion current density and plume-induced sputter erosion rates. The model does not compare as well with retarding potential analyzer measurements of the ion energy distribution. The results confirm previous observations that measurements made in some ground facilities may substantially overpredict the amount of backflow current that will be experienced under operational conditions. A surface-sputtering model is used to predict the impact the plume has on solar array interconnects and to show the impact an SPT thruster could have on a communications satellite. The results show that the thruster should be canted with respect to the solar array, lowering its effective thrust and specific impulse.

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