Michael Kroells, Sahadeo Ramjatan, Thomas E. Schwartzentruber

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-0334

New planetary missions will require higher reliability ablative thermal protection systems to handle high heating rates and shear loads while providing the necessary protection for the interior of the vehicle. During the ablation process, thermal stresses and traction forces, combined with oxidation, could affect the structural integrity of individual fibers in the TPS, resulting in failure. This work consists of using the DSMC method to simulate boundary layer flows over resolved fiber microstructures at flight relevant conditions; the necessary boundary conditions for the DSMC simulation are provided using CFD per- formed on the Stardust capsule. Surface properties including heat flux, traction, and oxygen number flux will be determined on individual fibers, which can be used in a thermal-structural response.

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In Categories: High-Speed Aerodynamics and Aerothermodynamics, HiSST 2022
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