The thesis work aims at developing a liquid monopropellant injector for a high power electrodeless plasma thruster. The feasibility of using a chemical monopropellant for electric propulsion is investigated.
After a design phase, the injector is put to the test with a simulant to the real liquid monopropellant in a simulated environment. Theoretical models are created to predict the power needed to vaporize a mass flow of the monopropellant without decomposing the heavy molecules.
Testing has proved that the injector is able to vaporize the simulant of the real monopropellant. The properties of the propellant are compared to that of Xenon and Argon, showing good and promising results.
Author: Linde, Robin