Micro-scale modeling of ablative thermal protection systems during atmospheric entry

When spacecraft enter an atmosphere, they require the use of a thermal protection system (TPS) to mitigate the harsh aerothermal environment. NASA relies heavily on computational modeling to design and size TPS for planetary missions. However, post-flight analysis of NASA missions often reveals discrepancies between predicted and actual behavior, and highlights the need for improved first-principles modeling. High-fidelity modeling of ablation poses significant challenges due to the multi-physics and multi-scale nature of the phenomena, and the difficulty in conducting experiments representative of atmospheric entry conditions. One area of potential improvement is in better understanding the micro-scale behavior and decomposition of heat shield materials, and upscaling the micro-scale behavior to macro-scale modeling. In this proposed work, a multi-physics computational framework will be developed to study the micro-scale decomposition behavior of ablative thermal protection systems. The proposed research will include modeling high-temperature flow though porous media using Direct Simulation Monte Carlo (DSMC) methods, given the non-continuum conditions that exist during an atmospheric entry. Within the DSMC framework, oxidation at the fiber scale, including pitting dynamics (the non-uniform way in which carbon fibers oxidize), as well as solid and radiative heat transfer, will be simulated. Oxidation modeling will be coupled with mechanical failure modeling of the carbon fibers, including thermal stresses and fluid-structure interactions. The computational framework will be used to model the thermochemical and mechanical erosion that occurs when a spacecraft enters an atmosphere, including those with atmospheric dust, such as Mars. The proposed work aims to improve NASA’s understanding of micro-scale material response of TPS, and use that understanding to improve macro-scale modeling and help NASA prepare for the entry systems challenges of future missions. In particular, this work hopes address fundamental questions in the mechanical erosion of heat shield materials, a critical source of uncertainty in atmospheric modeling.

The proposed work aims to improve NASA’s understanding of micro-scale material response of TPS, and use that understanding to improve macro-scale modeling and help NASA prepare for the entry systems challenges of future missions. In particular, this work hopes address fundamental questions in the mechanical erosion of heat shield materials, a critical source of uncertainty in atmospheric modeling.

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