Development of a Direct Drive Vacuum Arc Thruster Passively Ignited for Nanosatellite

摘要: Active attitude control systems require a non-negligible amount of space to be mounted on board satellites. For the nanosatellite case, it becomes even more difficult accommodate an active system due size and mass constraints, choices are therefore limited. In this paper, small lightweight realized by direct drive passive ignition thruster. The is power supply without booster circuit. using microdischarge generated interaction with plasma environment propellant surface. Availability these two was verified. As result, when thruster placed into high-density ( $10^{12}~\text{m}^{-3})$ , confirmed that can operate normally. Moreover, expected performance vacuum arc measured. results show impulse bit micronewtons order, ion velocity measured approximately 12 km/s. found changes applied voltage capacitance value discharge