COMPLETE COMPUTATIONAL MODEL OF A HALL THRUSTER FROM THE ACCELERATION CHANNFL THROUGH THE PLUME

Abstract Two-and mnsional computational models describing both the internal' and extema12 physics of Hall thrusters have been developed at the Massachusetts Institute of Technology. Integration of these models would result in a single, stand-alone application characterizing thruster physics from the thruster interior through the plume region. The application would enhance the spacecraft design process by providing engineers with the ability to predict thruster performance and damage to the craft from plumeqcecmft interactions. This paper represents the first attempt at consolidation of the intemal and external computational models, exploring the issues critical to integration. 'Ihe key issue in integration is the compatibility between the source model produced by the acceleration channel code and the source model used by the threG dimensional plume code. Sensitivity analysis has been performed to de&mine the extent to which the source model affects the plume and the surrounding spgcecraft surface. Results on a realistic spacecraft geometry suggest that differences between the original source model and the model genemted by the acceleration channel code significantly affect satellite surface erosion rates. Enhancements have also been made to the source and sputtering models in the plume code. Results utilizing the improved source model have been validated against experimental data and suggest that the source axial ion temperature assumed in previous woe was over predicted. In addition, the sputtering model now includes the effect of the sputtering yield dependence upon particle angle of incidence. Future work includes a graphical user interface on Xwindows platforms, automatic source model generation, and code stream-lining and optimization