Abstract
An analytical model based on an oscillatory circuit equation and dynamic equation for a uniform plasma slug has been developed in order to provide a design tool which is able to predict the dependence of µPPT performance on electrode configuration and circuit paramters. The results of the model show good aggrement with experimental results and have been implemented to improve µPPT performance. Thruster performance has been experimentally characterised for a capacitance range of 2 to 31 µF and propellant surface areas of 0.25 to 1.5 cm2 for low energy operation. Results indicate that the impulse bits required for picosatellite missions are achievable with the application of miniaturised thruster heads and energy densities of approximatley 5 to 10 Jcm2.