Computational Modeling of Lithium Magnetoplasmadynamic Thruster for Nuclear Electric Propulsion

This research aims to develop a novel simulation model for lithium Magnetoplasmadynamic (MPD) thrusters, promising candidates for high-power spacecraft propulsion, such as Nuclear Electric Propulsion (NEP) systems, which are essential for future Mars missions. Current models, like Magnetohydrodynamics (MHD), fail to accurately simulate critical phenomena like "onset" which leads to performance losses and significantly reduces thruster lifetime under high power and high current conditions. My research project proposes to create the first Full Fluid Moment (FFM) model for lithium MPD thrusters. The FFM model, unlike other fluid-based models, captures the inertia effect by solving the five moments of the kinetic equations for all species, including neutrals. It is also less computationally demanding than Particle-In-Cell (PIC) simulations. The model will address the unique challenges of MPD thrusters, particularly the need to solve Maxwell's equations without assuming plasma quasi-neutrality. To simplify these equations and make computations more efficient, the Darwin model will be used. The research will progress from a one-dimensional FFM model to a more advanced two-dimensional version, with the potential integration of PIC simulations to study microinstabilities. This work addresses the need for advanced simulation tools to optimize MPD thruster designs and extend their operational lifetimes for NEP systems, thus enabling the success of long-duration missions to Mars and advancing space exploration.

This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

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