Due to the advances in miniaturization Cubesats are becoming more versatile, with projected mission capabilities that are traditionally reserved for larger satellites. However they are still limited by a lack of efficient propulsive means. A novel electric thruster based on Electron Cyclotron Resonance heating and Magnetic Nozzle acceleration may provide a suitable yet simple solution. This device, while currently providing 1000 s Isp and 1 mN of thrust at 30W of power, may enable Lunar CubeSat missions from GEO using on-board propulsion. An example mission to provide GPS on the Lunar surface using 3U CubeSats in a 60°:28/4/6 Walker constellation with a semi-major axis of 4000 km is proposed; a preliminary assessment of this mission, together with the satellite architecture and cost, is performed. Concurrent trajectory design for very-low-energy transfers is used to demonstrate the feasibility of the mission and its impact on the space-craft design.