It is proposed to develop a space propulsion concept based on the physics of pseudospark discharges. The device will be based on a multi-gap pseudospark device with a closed anode. The pseudospark is characterized by a transient phase, where high-intensity are created, and a "super-dense" glow discharge phase when the steady state is achieved. This phase produces very high plasma densities with minimal electrode erosion. In pulsed operation, a transient charged plasma can be used to generate a high density ion beam, which can then be accelerated to higher velocities. The physics of the concept will be investigated in detail to evaluate its efficiency for space propulsion, and scaling properties for micro-propulsion applications. The concept does not use an applied magnetic field and can therefore be very compact; micro-scale effects at the electrode surface may also facilitate the design of micro-thrusters for nano-satellites. Two operational modes will be considered; a steady-state operation, using the high-density plasma of the super-dense glow phase, and a pulsed operation, using the transient formation of a space-charged plasma for ion beam generation. The scaling properties will be determined through numerical simulations, and preliminary designs of a candidate propulsion system and an experiment will be accomplished. The proposed pseudospark-based propulsion system can be designed on various scales or assembled as an array of micro-devices, if it can be successfully scaled. This extends the range of applicability from nano-satellites to conventional satellites, and widens the commercial market for the technology. The commercial applications are therefore primarily aimed at satellite propulsion and station-keeping. Furthermore, the technology can be generalized to other applications, such as power processing and material fabrication and treatment, for which the pseudospark is currently being developed.
Keywords: Nano-Satellites, Electric Propulsion, Pseudospark, Micro-Discharge
