Surface properties on thermal protection system microstructure during hypersonic ablation

Ashwin Dev Achambath, Sahadeo Ramjatan, Thomas E Schwartzentruber

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Hypersonic boundary layer flow during Stardust entry is simulated over Thermal Protection System (TPS) microstructure using the Direct Simulation Monte Carlo (DSMC) method. During the ablation process, the thermal stresses and traction forces acting on the TPS microstructure, combined with its oxidation, could affect its structural integrity. Hence, the local surface properties, namely, heat flux and traction force acting on the microstructure are estimated, studied and compared to estimates from Computation Fluid Dynamics (CFD). Preliminary simulations have been performed on different microstructures varying in porosity, orientation and diameter of fibers to study its effect on the surface properties. The capability of DSMC to compute relevant surface properties required for thermo-structural material response studies of TPS structures is demonstrated.

Original languageEnglish (US)
Title of host publicationAIAA Scitech 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105784
DOIs
StatePublished - Jan 1 2019
EventAIAA Scitech Forum, 2019 - San Diego, United States
Duration: Jan 7 2019Jan 11 2019

Publication series

NameAIAA Scitech 2019 Forum

Conference

ConferenceAIAA Scitech Forum, 2019
CountryUnited States
CitySan Diego
Period1/7/191/11/19

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Achambath, A. D., Ramjatan, S., & Schwartzentruber, T. E. (2019). Surface properties on thermal protection system microstructure during hypersonic ablation. In AIAA Scitech 2019 Forum (AIAA Scitech 2019 Forum). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2019-1283