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A model of a two-stage thruster with anode layer is developed based on a two-dimensional hydrodynamic approach. Each stage is considered separately, while the solution of the first stage provides the boundary conditions forthesecondstage.Current-voltagecharacteristicofthedischargeinthe firststageiscalculatedandisfoundtobein agreement with experiment. In the acceleration channel the plasma-wall interactions are studied and expansion of the high-voltage sheath near the acceleration channel wall is investigated. It is predicted that under the typical conditions the sheath expands significantly and the quasi-neutral plasma region is confined in the middle of the channel.Forinstance,inthecaseofa3kVdischargevoltage,thesheaththicknessisabout1cm,whichisasignificant portionof thechannelwidth. Itisshownthatnear-wallsheathexpansionleadsto ashorteracceleration region.Wall erosion by the energetic ions is calculated. The erosion profiles and the total erosion rate generally agree well with available experimental data. Plasma flow analysis provides the boundary conditions for the plume expansion study. Theplumemodelispartiallyvalidatedbycomparisonoftheioncurrentdensitydistributionwithexperimentaldata.

Modeling a Two-Stage High-Power Anode Layer Thruster and its Plume