Abstract
Hall thrusters are a common spacecraft propulsion device for orbit maintenance and north-south station keeping. One of the concerns about Hall thrusters is the effect of the thruster plume on the spacecraft life [1]. The sputtering of high energy ions, can cause erosion of sensitive surface coatings used for solar cell elements and thermal control. Although previously there has been ground-based facility tests, these could not replicate a space environment, due to the so called facility effects [2]. Thus, in order to understand the effect of CEX ions, Hall thruster plumes should be modeled.
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