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Research Papers

Failure Theory/Failure Criteria for Fiber Composite Laminates

[+] Author and Article Information
Richard M. Christensen

Professor Research Emeritus,
Aeronautics and Astronautics Department,
Stanford University,
Stanford, CA 94305
e-mail: christensen@stanford.edu

Kuldeep Lonkar

Aeronautics and Astronautics Department,
Stanford University,
Stanford, CA 94305
e-mail: kuldeep@alumni.stanford.edu

1Corresponding Author.

Contributed by the Applied Mechanics Division of ASME for publication in the JOURNAL OF APPLIED MECHANICS. Manuscript received October 24, 2016; final manuscript received October 29, 2016; published online November 21, 2016. Editor: Yonggang Huang.

J. Appl. Mech 84(2), 021009 (Nov 21, 2016) (8 pages) Paper No: JAM-16-1522; doi: 10.1115/1.4035119 History: Received October 24, 2016; Revised October 29, 2016

Failure criteria are derived for the case of a quasi-isotropic laminate and for the more general case of orthotropic laminates. The former requires two calibrating failure properties obtained directly from laminate testing and the latter requires five standard experimental measurements for its calibration. Then the quasi-isotropic failure theory is taken much further, also admitting full calibration by only the two composites tow failure properties, the associated unidirectional tensile, and compressive strengths. The theoretically predicted failure envelope for the quasi-isotropic laminate is favorably compared with some comprehensive testing data. As a related matter, the general failure criteria for unidirectional fiber composites are also reviewed.

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References

Figures

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Fig. 1

Lamina orientations giving quasi-isotropy

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Fig. 2

Comparison between quasi-isotropic polynomial invariants failure theory, Eqs. (21) and (43), and first ply fiber failure

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Fig. 3

Quasi-isotropic failure data, Welsh et al. [6], versus the theoretical predictions from Eqs.(21) and (43)

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Fig. 4

Orthotropic failure envelope (48) for properties (50) with σ12=0

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