Deformation and failure of angle-ply composite laminates

B. T. Werner; J. D. Schaefer; I. M. Daniel

doi:10.1007/978-3-319-00873-8_19

Deformation and failure of angle-ply composite laminates

B. T. Werner^*, J. D. Schaefer, I. M. Daniel

^*Corresponding author for this work

Civil and Environmental Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

9 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 language	English (US)
Title of host publication	Experimental Mechanics of Composite, Hybrid, and Multifunctional Materials - Proceedings of the 2013 Annual Conference on Experimental and Applied Mechanics
Pages	167-171
Number of pages	5
DOIs	https://doi.org/10.1007/978-3-319-00873-8_19
State	Published - 2014
Event	2013 Annual Conference on Experimental and Applied Mechanics - Lombard, IL, United States Duration: Jun 3 2013 → Jun 5 2013

Publication series

Name	Conference Proceedings of the Society for Experimental Mechanics Series
Volume	6
ISSN (Print)	2191-5644
ISSN (Electronic)	2191-5652

Other

Other	2013 Annual Conference on Experimental and Applied Mechanics
Country/Territory	United States
City	Lombard, IL
Period	6/3/13 → 6/5/13

Funding

The work described in this paper was sponsored by the Solid Mechanics Program of the Office of Naval Research (ONR). We are grateful to Dr. Y. D. S. Rajapakse of ONR for his encouragement and cooperation.

ASJC Scopus subject areas

General Engineering
Computational Mechanics
Mechanical Engineering

Access to Document

10.1007/978-3-319-00873-8_19

Cite this

Werner, B. T., Schaefer, J. D., & Daniel, I. M. (2014). Deformation and failure of angle-ply composite laminates. In Experimental Mechanics of Composite, Hybrid, and Multifunctional Materials - Proceedings of the 2013 Annual Conference on Experimental and Applied Mechanics (pp. 167-171). (Conference Proceedings of the Society for Experimental Mechanics Series; Vol. 6). https://doi.org/10.1007/978-3-319-00873-8_19

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title = "Deformation and failure of angle-ply composite laminates",

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.",

author = "Werner, {B. T.} and Schaefer, {J. D.} and Daniel, {I. M.}",

note = "Funding Information: The work described in this paper was sponsored by the Solid Mechanics Program of the Office of Naval Research (ONR). We are grateful to Dr. Y. D. S. Rajapakse of ONR for his encouragement and cooperation.; 2013 Annual Conference on Experimental and Applied Mechanics ; Conference date: 03-06-2013 Through 05-06-2013",

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doi = "10.1007/978-3-319-00873-8_19",

language = "English (US)",

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Werner, BT, Schaefer, JD & Daniel, IM 2014, Deformation and failure of angle-ply composite laminates. in Experimental Mechanics of Composite, Hybrid, and Multifunctional Materials - Proceedings of the 2013 Annual Conference on Experimental and Applied Mechanics. Conference Proceedings of the Society for Experimental Mechanics Series, vol. 6, pp. 167-171, 2013 Annual Conference on Experimental and Applied Mechanics, Lombard, IL, United States, 6/3/13. https://doi.org/10.1007/978-3-319-00873-8_19

Deformation and failure of angle-ply composite laminates. / Werner, B. T.; Schaefer, J. D.; Daniel, I. M.
Experimental Mechanics of Composite, Hybrid, and Multifunctional Materials - Proceedings of the 2013 Annual Conference on Experimental and Applied Mechanics. 2014. p. 167-171 (Conference Proceedings of the Society for Experimental Mechanics Series; Vol. 6).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

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PY - 2014

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N2 - 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.

AB - 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.

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Werner BT, Schaefer JD, Daniel IM. Deformation and failure of angle-ply composite laminates. In Experimental Mechanics of Composite, Hybrid, and Multifunctional Materials - Proceedings of the 2013 Annual Conference on Experimental and Applied Mechanics. 2014. p. 167-171. (Conference Proceedings of the Society for Experimental Mechanics Series). doi: 10.1007/978-3-319-00873-8_19

Deformation and failure of angle-ply composite laminates

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