Chapter 7. Design and Fabrication of Stabilized Organic Matrix Composites

  1. William J. Smothers
  1. J. A. Suarez

Published Online: 26 MAR 2008

DOI: 10.1002/9780470291030.ch7

Proceedings of the 2nd and 3rd Annual Conference on Composites and Advanced Materials: Ceramic and Engineering Science Proceedings, Volume 1, Issue 7/8

Proceedings of the 2nd and 3rd Annual Conference on Composites and Advanced Materials: Ceramic and Engineering Science Proceedings, Volume 1, Issue 7/8

How to Cite

Suarez, J. A. (1980) Design and Fabrication of Stabilized Organic Matrix Composites, in Proceedings of the 2nd and 3rd Annual Conference on Composites and Advanced Materials: Ceramic and Engineering Science Proceedings, Volume 1, Issue 7/8 (ed W. J. Smothers), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470291030.ch7

Author Information

  1. Grumman Aerospace Corp. Bethpage, N.Y. 11714

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 1980

ISBN Information

Print ISBN: 9780470373842

Online ISBN: 9780470291030

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Keywords:

  • graphite/epoxy;
  • thermal pressure;
  • manufacture;
  • baseline sandwich;
  • aluminum honeycomb cores

Summary

Integrally-stiffened graphite/epoxy compression panels representative of secondary aircraft structure were designed and fabricated. A thermal pressure forming process was developed to manufacture various panels which were designed for compression loading and analyzed using existing analytical techniques. A structural efficiency comparison of the integrally-stiffened graphite/epoxy compression panels and a baseline sandwich panel with graphite/epoxy skins and aluminum honeycomb core was performed.