Alternate direct-drive option for electric propulsion

The goal of this research is to power a 1.5-kW Hall thruster with a power source based on chemical double layer capacitor technology and to access performance characteristics of this power/propulsion system. The thruster was operated in a long-pulse mode with decaying power input and exhibited similar performance characteristics to being operated under steady-state conditions. Over the tested power range of 450-1750 W, the thruster generated thrust of 30-100 mN at an efficiency of 30-55% and a specific impulse of 900-1950 s. These results formed the basis for a mission analysis considering extremes with regard to shading and atmospheric density. A near-Earth orbiting spacecraft served as an analysis platform to compare the mission performance of direct-drive electric propulsion options and a state-of-the-art hydrazine monopropellant system. Regardless of orbit conditions, electric propulsion options outperformed the conventional chemical system in terms of wet mass decrease (41-59%) and net mass increase (14-47%), while capacitor-powered electric propulsion options substantially reduced the onboard power requirement (66-91 %).