Comparison of a Field Effect Emission Propulsion System and a Hydrogen Peroxide Monopropellant Thruster for Small Satellites Orbital Control System

The disruptive emergence of the NewSpace economy is leading the space sector towards solutions based on small satellites, and specifically on CubeSats. These satellites, modest in size, but less and less in their potential and effective commercial spin-offs, require ever greater autonomy and ability to operate in complex mission scenarios. The range of possible operation is diversifying and the demand for flexible and adaptable systems is rising. In this regard, all on-board systems must underly the standardization paradigm, cardinal principle behind CubeSats. The possibilities opening are endless: starting from mega-constellations for Earth Observation and telecommunication, up to advanced small probes for the exploration of remote celestial bodies. The realization of these ambitious missions requires unprecedented high-tech know-how and versatility that could not be achieved without an innovative micropropulsion system. The key issue in the development of these systems dwells in miniaturization: the entire subsystem must fit into a restricted volume while satisfying compelling mass and power requirements. Two promising systems stand out for their groundbreaking capabilities and efficient scalability: a Field Emission Electric Propulsion and a "green" monopropellant thruster. In this Master Thesis, the potentialities of these two candidates are investigated through a simulation-based approach, aiming at individuating preliminary technical requirements for their development and future employment as Orbital Control System for small satellites.