A Detailed Global Model for Modeling and Optical Diagnostics of Low Power Propulsion Devices Fed by CO 2 IEPC-2019-682 Presented at the 36th International Electric Propulsion Conference University of Vienna • Vienna, Austria September 15-20, 2019 Chloe Berenguer 1 and Konstantinos Katsonis 2 DEDALOS Ltd., Thessaloniki, 54645, Greece Georg Herdrich 3 and Hendrik Burghaus 4 Institute of Space Systems (IRS), Stuttgart, Germany Abstract: A Detailed Global Model developed by DEDALOS Ltd for CO 2 plasma study in space and laboratory is used here for electric thruster characterization and optical emission spectroscopy diagnostics based on the obtained plasma components composition diagrams, on the functioning diagrams and on the concomitant theoretical first and second oxygen and carbon spectra. Comparison of our theoretical results including theoretical spectra with experimental ones obtained in IRS, is addressed in particular, taking into consideration that the experimental spectra do not come from a thruster but from a IPG run with CO2 for Mars entry investigation. Nomenclature x TOT = total ionization percentage ABET = Air Breathing Electric Thruster CO2DGM = CO 2 Detailed Global Model DEDALOS = Data Evaluation and Diagnostics ALgorithms Of Systems Ltd DGM = Detailed Global Model ET = Electric Thruster FD = Functioning Diagram GM = Global Model HelT = Helicon type Thruster HMO = High Mars Orbit IPG = Inductively heated Plasma Generator IRS = Institut für RaumfahrtSysteme, university of Stuttgart ISRU = in situ Resource Utilization L = cylinder lenght LMO = Low Mars Orbit MATM = Mars ATMosphere n e = electron density 1 Project Manager, berenguer.dedalos@gmail.com. 2 Director, katsonis.dedalos@gmail.com. 3 Head, Plasma Wind Tunnels and Electric Space Propulsion, herdrich@irs.uni-stuttgart.de. 4 PhD student, hburghaus@irs.uni-stuttgart.de. The 36th International Electric Propulsion Conference, University of Vienna, Austria September 15-20, 2019 1