Mission analysis using experimental results from an 8-cm ion thruster

Ion thrusters are a type of electric propulsion device in which positively charged particles are electrostatically accelerated to create thrust. Ion thrusters are currently used for station keeping and deep space missions because of their high efficiency and specific impulse. This efficiency is a function of its beam voltage.;The effects of beam voltage on thrust, efficiency, and beam divergence were studied using experimental data from an 8-cm ion thruster. The beam voltage was varied between 600 V and 1400 V. Using these data, a mission analysis was performed for Lower Earth Orbit (LEO) to Mars and LEO to Jupiter.;Upper and lower bounds on beam divergence efficiency were calculated using experimental measurements of the plume expansion. Overall thruster efficiency increased monotonically with beam voltage. These performance data were input into CHEBYTOP to calculate trip time and propellant fraction for both the Mars and Jupiter missions. Trip time decreased with beam voltage while propellant fraction increased. Beam divergence was found to have a negligible effect on mission performance.