Summary
The main mission critical part of planned reusable re-entry vehicles is its thermal protection system. The surface material has to withstand high heat loads and a chemically aggressive environment in the upper atmosphere. In case of re-usability the candidate material has to withstand these loads several times. Therefore, the mass loss during one re-entry mission has to be as small as possible. In order to predict the mass loss, the material is investigated in plasma wind tunnels and meanwhile numerical simulation of surface processes is possible at Institut für Raumfahrtsysteme (IRS). This paper describes for the first time a quantitative comparison of the specific mass loss estimated on the one hand by plasma wind tunnel experiments and on the other hand by numerical simulation. Results for pressureless sintered silicon carbide (SSiC) and realistic C/C-SiC material are presented. Finally, an attempt is made to interpret the occurring differences.
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Löhle, S., Fertig, M., Auweter-Kurtz, M. (2006). Quantitative Comparison of Measured and Numerically Simulated Erosion Rates of SiC Based Heat Shield Materials. In: Rath, HJ., Holze, C., Heinemann, HJ., Henke, R., Hönlinger, H. (eds) New Results in Numerical and Experimental Fluid Mechanics V. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 92. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-33287-9_39
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DOI: https://doi.org/10.1007/978-3-540-33287-9_39
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