Development of PIC simulations and plume diagnostics for a magnetoplasmadynamic thruster

With the increasing number of satellite launches, the use of electric propulsion systems in space has expanded rapidly in recent years. There is significant interest in electric propulsion technologies offering high specific impulse and thrust for deep space and manned missions, and as a result, devices with different thrust ranges are currently under research and development. These devices include the magnetoplasmadynamic thruster (MPDT). This device, while promising for high thrust applications and known to be efficient at powers in the hundreds of kW range, has significant limitations, such as erosion and unstable operating regimes. The operation of an MPDT involves a substantial mass flow and typically high back pressure, resulting in more facility effects compared to other electric propulsion devices. Specifically, in the plume region, interactions such as charge exchanges with neutral particles in the vacuum chamber can lead to erroneous performance assessments during diagnostics investigations. This study aims to construct a plume simulation for a kW-scale MPDT using particle-in-cell methods to evaluate the facility effects present in experimental settings.