Plasma simulation of a two-stage electric propulsion system for spacecraft

Space-based technology is allowing for smaller and more cost-effective satellites to be produced. By working in large swarms, many small satellites can provide additional capabilities while reducing risk. The high exhaust velocity and propellant efficiency of plasma-based electric propulsion makes it ideally suited for low thrust missions. The two dominant types of electric propulsion, namely ion thrusters and Hall thrusters, excel in different mission types. In this work, an electric hybrid propulsion design is modelled to enhance understanding of key plasma phenomena and evaluate performance. Specifically, the modelled hybrid thruster seeks to overcome issues with existing Ion and Hall thruster designs. A two-stage Hall thruster is investigated and the potential feasibility of coupling the two stages to produce the ion-beam is evaluated. The ionization and acceleration events are investigated via multiphysics simulations. The key trends ranging from the discharge inception, amplification and drift to formation of the ion beam are discussed and characterized.