MPD thrusters accelerate ionised plasma with electromagnetic fields to produce high specific impulse, but conventionally operate only in the vacuum of space. The project ran in two phases.
Phase one - design and analysis. I modelled the plasma chamber and converging diverging nozzle in CAD, then ran a full Ansys CFD study of the spacecraft configuration, analysing velocity flow, mass flow rate, static temperature, total pressure, turbulent kinetic energy and turbulent viscosity to evaluate thrust behaviour and keep component temperatures within safe structural limits. The results below are from this study, and were written up in the paper linked at the end of this section.
Phase two - atmospheric adaptation and hardware. After publication we revised the concept to work within the atmosphere, introducing a separate reaction chamber into the design. Butane was selected as the propellant, it ionises into a charged plasma and was the practical choice, since safely handling liquid hydrogen was beyond our university's facilities. I fabricated a physical demonstrator of the revised system from scratch and fired it.
Read the research paper →













