Electric propulsion is generally characterized by higher specific impulse than traditional chemical rockets, which gives them propellant saving benefits. These have been applied in deep-space missions and micro-satellites. A Pulsed Plasma Thruster consists of two electrodes around a block of teflon. A pulsed discharge ablates the teflon and ionizes the vapor. This plasma forms a current bridge between the electrodes which is accelerated outwards by the self-induced magnetic field, producing thrust.

The current research project has developed and used a 1D model to investigate the current bridge with a focus on the plasma electrode interaction. The influence of electron temperature and density, cathode temperature, voltage, geometry and propellant type on the current density and magnetic field has been explored. The influence of thermionic electron emissions on the current-voltage characteristic has been demonstrated.