Application of stretch broken carbon fiber materials to rotorcraft structures

Gregory P. Dillon, Donald H. Stiver

Research output: Contribution to journalConference articlepeer-review

2 Scopus citations

Abstract

Production costs for advanced composite aerospace components are directly related to part complexity. Touch labor content is substantial when parts with high levels of double curvature are fabricated by conventional hand lay up and autoclave cure. Automated forming processes have reduced the labor content of production parts with commensurate cost savings. However, such processes are also limited by the level of double curvature present, as the tendency toward laminate wrinkling increases with part complexity. New material systems, based on Stretch Broken Carbon Fibers, offer the potential to increase the part complexity spectrum available to these cost efficient automated forming processes. By offering additional deformation mechanisms, associated with fiber axis stretching, these materials alleviate in-plane and interply shearing requirements that constitute the principal process limitations of continuous fiber systems. This paper summarizes the results of a study aimed at determining the suitability of Stretch Broken Carbon Fiber material forms to a class of bead stiffened panels commonly used in rotorcraft cabin construction. These components are too geometrically complex to be formed with continuous fiber systems and incur a significant cost penalty in hand lay-up, again because of the high degree of local double curvature.

Original languageEnglish (US)
JournalInternational SAMPE Symposium and Exhibition (Proceedings)
Volume51
StatePublished - Dec 1 2006
EventSAMPE '06: Creating New Opportunities For The World Economy - Long Beach, CA, United States
Duration: Apr 30 2006May 4 2006

All Science Journal Classification (ASJC) codes

  • Materials Science(all)
  • Mechanics of Materials
  • Mechanical Engineering

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