TY - JOUR
T1 - Simulation of the stagnation region microcrack growth during space shuttle reentry
AU - Titov, E. V.
AU - Levin, D. A.
AU - Anderson, Brian P.
AU - Rodriguez, Alvaro
AU - Picetti, Donald J.
N1 - Funding Information:
E. V. Titov and D. A. Levin would like to acknowledge support from NASA Grant NNX08AD84G from NASA/Johnson Space Flight Center. We would especially like to thank the AeroSoft Corporation, Blacksburg, Virginia, for their technical support and assistance in incorporating the gas wall oxidation boundary condition.
Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2011
Y1 - 2011
N2 - The newly developed reinforced-carbon-carbon damage assessment model is applied to a micrometeoroid crack at the stagnation point of a sphere for a space shuttle reentry trajectory. The model, which has been validated against arcjet tests (Titov, E., Zhong, J., Levin, D., and Picetti, D., "Simulation of Carbon-Carbon Crack Growth due to Carbon Oxidation in High Temperatures," Journal of Thermophysics and Heat Transfer, Vol. 23, No. 3, July- Sept. 2009, pp. 489-501.) (Titov, E., Levin, D., Picetti, D., and Anderson, B. P., "Thermal Protection System Crack Growth Simulation Using Advanced Grid Morphing Techniques," Journal of Thermophysics and Heat Transfer, Vol. 24, No. 4, 2010, pp. 708-720.), predicts the microhole wall material response to the high-energy, atomic oxygen rich flow to simulate a micrometeoroid impact of the space shuttle nose cap shield during the STS-5 mission reentry. The extent of the crack damage site hole diameter was found to grow by a factor of 2.7, which agrees within about 30%of the NASAJohnson Space Center reinforced-carbon-carbon damage growth tool, version 2, a semi-empirical approach developed through extensive arcjet testing.
AB - The newly developed reinforced-carbon-carbon damage assessment model is applied to a micrometeoroid crack at the stagnation point of a sphere for a space shuttle reentry trajectory. The model, which has been validated against arcjet tests (Titov, E., Zhong, J., Levin, D., and Picetti, D., "Simulation of Carbon-Carbon Crack Growth due to Carbon Oxidation in High Temperatures," Journal of Thermophysics and Heat Transfer, Vol. 23, No. 3, July- Sept. 2009, pp. 489-501.) (Titov, E., Levin, D., Picetti, D., and Anderson, B. P., "Thermal Protection System Crack Growth Simulation Using Advanced Grid Morphing Techniques," Journal of Thermophysics and Heat Transfer, Vol. 24, No. 4, 2010, pp. 708-720.), predicts the microhole wall material response to the high-energy, atomic oxygen rich flow to simulate a micrometeoroid impact of the space shuttle nose cap shield during the STS-5 mission reentry. The extent of the crack damage site hole diameter was found to grow by a factor of 2.7, which agrees within about 30%of the NASAJohnson Space Center reinforced-carbon-carbon damage growth tool, version 2, a semi-empirical approach developed through extensive arcjet testing.
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U2 - 10.2514/1.49993
DO - 10.2514/1.49993
M3 - Article
AN - SCOPUS:79251549235
VL - 25
SP - 48
EP - 54
JO - Journal of Thermophysics and Heat Transfer
JF - Journal of Thermophysics and Heat Transfer
SN - 0887-8722
IS - 1
ER -