Simulation of a Direct-Current Microdischarge for the Micro Plasma Thruster

We present computational modeling results for discharge phenomena in a microdischarge plasma thruster device. The model provides self-consistent, multispecies, and multitemperature description of the direct-current microdischarge in an expanding gas stream. Results include the potential profiles as well as the number density profiles of the different species inside the microdischarge. Strong coupling between plasma and gas dynamics is observed, resulting in a small fraction of ions escaping the device that can contribute to an electrostatic component of thrust from microthruster.