The proposed work will demonstrate a TRL5 electrospray thruster for primary propulsion of a 12U Smallsat, and design a CubeSat-class power system for operation of the propulsion system. Efforts will include substantial lab tests on thrust, Isp, and efficieny, and build a CDR package for CubeSat-like platform using the propulsion system.

The proposed electrospray thruster is an enabling technology for Smallsat-based lunar missions, and will offer significant improvements on efficiency, operational flexibility (variable Isp operation), and spacecraft scalability over existing technologies. This enables operation at very different Isp points, flexibility that makes it possible to optimally execute, at constant power, maneuvers such as orbit insertion or S/C pointing prioritizing a short maneuver time (high thrust), as well as station-keeping which requires low thrust and can be done at high Isp to reduce propellant consumption.