Compression behavior of ultra-high modulus carbon/epoxy composites using ASTM D6641 and SACMA SRM 1R-94

Michael Charles Glath, Kevin L. Koudela, Eric Strauch

Research output: Contribution to journalArticle

1 Citation (Scopus)

Abstract

The compression modulus and compression strength of a proprietary ultra-high modulus carbon/epoxy composite are experimentally determined using SACMA SRM 1R-94 and ASTM D6641 for laminates with stacking sequences of [(0/ ± 60)s]2 and [(+60/0/-60)s]2. The moduli of both laminates are experimentally shown to be statistically equivalent; the strength of the [(0/ ± 60)s]2 laminate is shown to be significantly less than the [(+60/0/-60)s]2 laminate. A finite element model is developed for each compression test to predict the compression modulus and compression strength using the built-in damage progression algorithm in Abaqus. Premature end crushing is predicted in the modulus specimen of SACMA SRM 1R-94 for the [(+60/0/60)s]2 laminate. End crushing in the modeled SACMA SRM 1R-94 strength specimen is predicted to occur immediately after ultimate laminate failure for the [(+60/0/60)s]2 laminate. Fiber misalignment is found to significantly affect the predicted compression modulus and compression strength of the ultra-high modulus carbon/epoxy composite analyzed.

Original languageEnglish (US)
Pages (from-to)701-712
Number of pages12
JournalJournal of Composite Materials
Volume50
Issue number5
DOIs
StatePublished - Mar 1 2016

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Laminates
Compaction
Carbon
Composite materials
Crushing
Fibers

All Science Journal Classification (ASJC) codes

  • Ceramics and Composites
  • Mechanics of Materials
  • Mechanical Engineering
  • Materials Chemistry

Cite this

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title = "Compression behavior of ultra-high modulus carbon/epoxy composites using ASTM D6641 and SACMA SRM 1R-94",
abstract = "The compression modulus and compression strength of a proprietary ultra-high modulus carbon/epoxy composite are experimentally determined using SACMA SRM 1R-94 and ASTM D6641 for laminates with stacking sequences of [(0/ ± 60)s]2 and [(+60/0/-60)s]2. The moduli of both laminates are experimentally shown to be statistically equivalent; the strength of the [(0/ ± 60)s]2 laminate is shown to be significantly less than the [(+60/0/-60)s]2 laminate. A finite element model is developed for each compression test to predict the compression modulus and compression strength using the built-in damage progression algorithm in Abaqus. Premature end crushing is predicted in the modulus specimen of SACMA SRM 1R-94 for the [(+60/0/60)s]2 laminate. End crushing in the modeled SACMA SRM 1R-94 strength specimen is predicted to occur immediately after ultimate laminate failure for the [(+60/0/60)s]2 laminate. Fiber misalignment is found to significantly affect the predicted compression modulus and compression strength of the ultra-high modulus carbon/epoxy composite analyzed.",
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Compression behavior of ultra-high modulus carbon/epoxy composites using ASTM D6641 and SACMA SRM 1R-94. / Charles Glath, Michael; Koudela, Kevin L.; Strauch, Eric.

In: Journal of Composite Materials, Vol. 50, No. 5, 01.03.2016, p. 701-712.

Research output: Contribution to journalArticle

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