In the new space paradigm, CubeSats have become the go-to platform for researchers and industry devel- opers across the world for gaining access to space. As CubeSat technologies are maturing, many developers are planning intricate and utilitarian missions for CubeSats. Many of these concepts involve formation fly- ing or swarm dynamics, debris removal, and even deep space exploration. However in order for any of these missions to be realized in a long-term and sustainable way, the spacecraft will require propulsion systems. This thesis describes the design, construction and testing of a miniature iodine-fed Advanced Cusped Field Thruster (μACFT) engineering model (EM) for the 3U+ CubeSat platform. With a dry mass of 280 g and a volume of 180 cm3, the iodine μACFT EM is designed to fit inside of the tuna can extension of the 3U+ CubeSat structure. This form factor makes it incredibly small relative to other iodine thrusters. The measured thrust of the iodine μACFT is 227 - 254 μN, with a total system power consumption of 8.3 - 11.6 W. The small size and low power consumption make the μACFT the best suited iodine thruster candidate for the small 3U+ CubeSat platform.

Multiple distinct topics related to development of the μACFT engineering model are also explored in this the thesis. The fluidics of the two-stage iodine feed system are studied to create a thermodynamic model which can be used to predict the mass flow rate of the propellant as a function of temperature. A resonant DC/DC converter is designed and tested as a candidate for the power processing unit of the engineering model. The converter demonstrated inadequate performance, with respect to the power output and conver- sion efficiency which is linked to the simultaneous requirements on for a high voltage gain and low power consumption in the thruster. Lastly, a tungsten thermionic emitter cathode is verified as an effective option for neutralization of the exhaust plume.