Simulation of the stagnation region microcrack growth during space shuttle reentry

E. V. Titov, D. A. Levin, Brian P. Anderson, Alvaro Rodriguez, Donald J. Picetti

Research output: Contribution to journalArticlepeer-review

Abstract

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.

Original languageEnglish (US)
Pages (from-to)48-54
Number of pages7
JournalJournal of thermophysics and heat transfer
Volume25
Issue number1
DOIs
StatePublished - 2011
Externally publishedYes

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Aerospace Engineering
  • Mechanical Engineering
  • Fluid Flow and Transfer Processes
  • Space and Planetary Science

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