Kinetic Modeling of Carbon Mass Loss in Nuclear Thermal Propulsion

Nuclear Thermal Propulsion (NTP) is a low-readiness-level technology that enables human space exploration with reduced travel times and costs. However, current solid-core NTP systems, which utilize hydrogen as a propellant, suffer from mass loss due to the interaction between hot hydrogen and the fuel element, particularly its carbon content. This corrosion process significantly reduces the performance and lifespan of NTP systems, impacting overall mission safety, reliability, and cost. The underlying cause of carbon mass loss involves phase transition and chemical reactions between gases and surfaces under NTP-relevant flow conditions. Unfortunately, our current understanding of this process remains largely empirical, limiting our ability to make accurate predictions and optimize designs. To address this, I propose developing a finite-rate chemical kinetic model for gas-surface reacting flow systems relevant to NTP conditions. The model will build on existing research in carbon particulate formation during combustion and carbon ablation in reentry scenarios. While the current focus is carbon, the model framework can be extended to other species. First, I will compile historical experimental data and identify kinetic pathways to create a baseline model that incorporates reactions of both gaseous and surface carbon. Carbon mass loss will be estimated by considering both sublimation and surface reactions. Next, I will test the model using plug flow reactors to evaluate the sensitivity of key reaction pathways and optimize rate parameters using additional experimental data. A detailed rate parameter uncertainty analysis will be performed to identify opportunities for future experiments. Lastly, I will integrate the model into a computational fluid dynamics framework to study the influence of multi-dimensional flow characteristics on mass loss. Specifically, I will explore methane doping as a strategy to reduce carbon loss, potentially offering a viable solution for future NTP systems. This project is within the scopes of the Go: Space Nuclear Propulsion and the GO: Advanced Propulsion NASA Envisioned Futures, as well as the NASA Technology Area1.4.3: Nuclear Thermal Propulsion.

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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