Chapter 16. Development of an Improved, Lightweight Insulation Material for the Space Shuttle Orbiter's Thermal-Protection System

  1. William J. Smothers
  1. R. S. Tomer and
  2. E. R. Cordia

Published Online: 26 MAR 2008

DOI: 10.1002/9780470318782.ch16

Proceedings of the 6th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science Proceedings, Volume 3, Issue 9/10

Proceedings of the 6th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science Proceedings, Volume 3, Issue 9/10

How to Cite

Tomer, R. S. and Cordia, E. R. (2008) Development of an Improved, Lightweight Insulation Material for the Space Shuttle Orbiter's Thermal-Protection System, in Proceedings of the 6th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science Proceedings, Volume 3, Issue 9/10 (ed W. J. Smothers), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470318782.ch16

Author Information

  1. Lockheed Missiles & Space Co., Inc. Box 504, Sunnyvale, CA 94086

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 1982

ISBN Information

Print ISBN: 9780470373972

Online ISBN: 9780470318782

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Keywords:

  • escalating energy;
  • enameling;
  • hydrocarbon;
  • installation;
  • deterioration

Summary

A laboratory procedure for making a lightweight (128 kg/m3 (8 lb/ft3) Fibrous Refractory Composite Insulation (FRCI) was scaled up to a pilot-plant process at Lockheed Missiles & Space Co., Inc., (LMSC) in 1979. Thermal performance of this material was unacceptable for the intended application on the Space Shuttle Orbiter. However, the mechanical properties were acceptable. An FRCl material at 136 kg/m3 (8.5 lb/ft3) with acceptable thermal performance was developed by varying processing and compositional factors.