Deformation and failure of angle-ply composite laminates

B. T. Werner*, J. D. Schaefer, Isaac M Daniel

*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference contribution

8 Scopus citations

Abstract

Angle-ply carbon/epoxy composite laminates were tested under uniaxial compression at two strain rates (10-4 and 1 s-1). In this study, failure is defined as maximum ply damage. This is determined by noting where the stress-strain curve of the laminate reaches a characteristic damage state and the stress-strain behavior reaches a terminal modulus. The characteristic damage state stress is compared to predictions from the recently introduced Northwestern (NU) theory at each strain rate. Residual and interlaminar stresses were considered in the analysis and experiment design. Most classical theories fail to predict the exact failure behavior of the laminates. The NU theory is in good agreement in most cases with the exception of cases where the state of stress includes a non negligible stress component in the fiber direction. However, for determining lamina failure due to matrix dominated failure modes, the NU theory is in excellent agreement with experimental results.

Original languageEnglish (US)
Title of host publicationExperimental Mechanics of Composite, Hybrid, and Multifunctional Materials - Proceedings of the 2013 Annual Conference on Experimental and Applied Mechanics
Pages167-171
Number of pages5
DOIs
StatePublished - Jan 1 2014
Event2013 Annual Conference on Experimental and Applied Mechanics - Lombard, IL, United States
Duration: Jun 3 2013Jun 5 2013

Publication series

NameConference Proceedings of the Society for Experimental Mechanics Series
Volume6
ISSN (Print)2191-5644
ISSN (Electronic)2191-5652

Other

Other2013 Annual Conference on Experimental and Applied Mechanics
CountryUnited States
CityLombard, IL
Period6/3/136/5/13

ASJC Scopus subject areas

  • Engineering(all)
  • Computational Mechanics
  • Mechanical Engineering

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