Abstract: A system for propelling a nanosatellite, including a pair of separated electrodes defining an ignition space therebetween a power source operationally connected to the pair of separated electrodes. Also included is a liquid propellant reservoir a pump reconnected in fluidic communication with reservoir and the ignition space and an electronic controller operationally corrected to the power source and to the pump.

Abstract: A system for propelling a nanosatellite, including a pair of separated electrodes defining an ignition space therebetween a power source operationally connected to the pair of separated electrodes. Also included is a liquid propellant reservoir a pump reconnected in fluidic communication with reservoir and the ignition space and an electronic controller operationally corrected to the power source and to the pump.

Abstract: An ignitor subsystem for use in an electric propulsion system is disclosed. The igniter subsystem includes an igniter, which includes a first electrically conducting electrode, a second electrically conducting electrode, and an electrically insulating layer sandwiched between the first and the second electrically conducting electrodes, and a voltage pulse generator electrically coupled to the first and the second electrically conducting electrodes and is adapted to generate a plurality of pulses each with sufficient voltage to cause a breakdown of the electrically insulating layer, thus causing an avalanche of electrons from one of the first and the second electrically conducting electrodes to the other, the voltage pulse generator is further adapted to limit energy transferred to the igniter in each of the plurality of pulses so as to minimize damage to the igniter.