Preliminary design of an iodine fluidic line for electric space propulsion system

Growing concern about space debris has imposed regulations that force SmallSats to be equipped with active disposal systems, making EP essential. However, meeting the difficult constraints on mass, volume, and cost remains challenging when including propulsion systems. Innovative thrusters may help to overcome these challenges and enable more ambitious missions. The work presented in this thesis, developed as part of the BOOST project of the University of Bologna, in collaboration with the aerospace company T4i S.p.A., Monselice (PD), Italy, presents the preliminary design of a fluidic line for iodine as a propellant for EP. An initial fluidic line model is proposed that contains the main components, including a possible use of SMA technology applied to the valves and an estimation of pressure drops, with the aim of identifying the most influential pressure loss elements between the reservoir and the thruster. The analysis includes a study on the design, in which the mass flow rate was varied, and in which the geometry was adapted in different case studies. In addition, preliminary indications for a second fluidic line between the reservoir and cathode were provided. In conclusion, the utilisation of AM for housing is proposed, with an evaluation of the compatibility of iodine with commercial materials. Results show that the proposed fluidic line model represents an initial point for future developments, although SMA technology applied to valves requires revision for maximum thermal operation. An analysis of pressure drops indicates higher losses in filters and variations in the outlet orifice with mass flow. Furthermore, AM technology could facilitate the acceleration of prototyping and support a circular economy by utilising recycled powders.