Chapter 15. Thermal Response of Integral Multicomponent Composites to a High-Energy Aerothermodynamic Heating Environment with Surface Temperature to 1800 K

  1. William Smothers
  1. David A. Stewart and
  2. Daniel B. Leiser

Published Online: 26 MAR 2008

DOI: 10.1002/9780470320402.ch15

11th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science Proceedings, Volume 8, Issue 7/8

11th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science Proceedings, Volume 8, Issue 7/8

How to Cite

Stewart, D. A. and Leiser, D. B. (2008) Thermal Response of Integral Multicomponent Composites to a High-Energy Aerothermodynamic Heating Environment with Surface Temperature to 1800 K, in 11th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science Proceedings, Volume 8, Issue 7/8 (ed W. Smothers), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470320402.ch15

Author Information

  1. NASA Ames Research Center Moffett Field, CA 94035

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 1987

ISBN Information

Print ISBN: 9780470374733

Online ISBN: 9780470320402

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Keywords:

  • aeroassisted orbital transfer vehicle(AOTV);
  • thermal protection system(TPS);
  • national aerospace plane(NASP);
  • outer mold line (OML);
  • inner mold line (IML)

Summary

Laminated composite insulations developed for potential use on advanced spacecraft operating between geosynchronous and low earth orbits were tested in an aerothermodynamic environment simulating an AOTV aerobraking maneuver (altitude 82.3 km and velocity = 9.0 km/s). Comparisons are discussed between these data and predictions of in-depth temperature response using dynamic thermal conductivity values to 2000K.