Biaxial Flexural Testing of a Carbon Fiber Reinforced Epoxy Composite

Abstract

The response of a 3501-6 resin composite to biaxial flexural loading was assessed using disk specimens. The composite was cross-ply reinforced with continuous carbon fibers with a volume content of 60%. Under monotonic flexural loading, the formation of delaminations limited the useful range of the composite's deformation to a biaxial tensile strain of 0.0067. Under cyclic flexural loading and for a fatigue life of 10(6) cycles, the useful strain range was limited to 0.003. The latter strain is only 19% of the composite's uniaxial tensile strain to failure. Fatigue failure mechanisms included delaminations, matrix cracking, fiber, and possible fiber bundle debonds. Some delaminations were identified with ultrasonic C-scanning.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1993
Accession Number
ADA271956

Entities

People

  • Barmac K. Taleghani
  • Nikos Tsangarakis

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Ground and Sea Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Carbon Fibers
  • Composite Materials
  • Delamination
  • Engineering
  • Failure Mode And Effect Analysis
  • Fatigue Life
  • Graphitic Materials
  • Laminates
  • Materials
  • Materials Science
  • Materials Testing
  • Mechanical Properties
  • Metal Matrix Composites
  • Military Research
  • Tensile Strain
  • Tensile Strength

Fields of Study

  • Materials science

Readers

  • Structural Health Monitoring of Composite Structures.