The oxidation of carbon-based ablative thermal protection systems is affected by the diffusion of gas from the boundary layer into the mesostructure and the reactivity of the gas with the microstructure (i.e. carbon fibers). To capture both of these effects, a DSMC approach is used and coupled to the ablating FiberGen code. FiberGen allows for movement of the triangles that make up the microstructure to account for gas surface reactions that remove carbon. A Thiele number analysis is performed based on the Stardust reentry trajectory to examine the diffusion of oxygen into the mesostructure at different trajectory points. In order to closely simulate the physics of a hypersonic boundary layer, a procedure for accurately imposing a CFD boundary layer onto a DSMC domain is presented. Subsequently, realistic boundary layer profiles from two Stardust reentry trajectory points are imposed over a mesostructure with and without ablation. This work provides insight on how in-depth oxidation occurs at flight relevant conditions.
|Original language||English (US)|
|Title of host publication||AIAA Scitech 2021 Forum|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|Number of pages||25|
|State||Published - 2021|
|Event||AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online|
Duration: Jan 11 2021 → Jan 15 2021
|Name||AIAA Scitech 2021 Forum|
|Conference||AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021|
|Period||1/11/21 → 1/15/21|
Bibliographical noteFunding Information:
The authors acknowledge funding from NASA grant 80NSSC18K0261 and the work of M. Kroells is supported by a NASA NSTRF award under grant 80NSSC19K1129.
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