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Research Papers

Predictions of Delamination Growth for Quasi-Static Loading of Composite Laminates

[+] Author and Article Information
Jiawen Xie

Department of Aerospace Engineering,
University of Michigan,
Ann Arbor, MI 48109-2140
e-mail: jwxie@umich.edu

Anthony M. Waas

Felix Pawlowski Collegiate Professor, Emeritus
University of Michigan,
Ann Arbor, MI 48109-2140
Boeing Egtvedt Endowed Chair & Chair
William E. Boeing Department of Aeronautics
and Astronautics,
University of Washington,
Seattle, WA 98195-2400
e-mail: awaas@aa.washington.edu

1Corresponding author.

Contributed by the Applied Mechanics Division of ASME for publication in the JOURNAL OF APPLIED MECHANICS. Manuscript received March 13, 2015; final manuscript received May 14, 2015; published online June 9, 2015. Assoc. Editor: Daining Fang.

J. Appl. Mech 82(8), 081004 (Aug 01, 2015) (12 pages) Paper No: JAM-15-1134; doi: 10.1115/1.4030684 History: Received March 13, 2015; Revised May 14, 2015; Online June 09, 2015

This paper presents an exact, two-dimensional (2D) quasi-static elastic analysis of predelaminated composite panels subject to arbitrary transverse pressure loads. The piecewise linear spring model and the shear bridging model are, respectively, used to simulate the normal contact and shear frictional behavior between the interfaces of the existing delamination. This general contact model can be further reduced to the “friction-free model” and the “constrained model” by assigning extreme values to the spring stiffnesses. The analysis yields a closed-form solution for the 2D displacement and stress fields. To predict the delamination propagation, different propagation criteria as suggested in the literature are used. Calculated load–displacement responses and delamination threshold loads are in good agreement with existing experimental data. The results are further compared against simple fracture models and a model that uses a modified classical laminated plate theory for the predelaminated composite with fracture criteria, showing an overestimation of the delamination threshold loads. The 2D elasticity theory that is formulated can be used with confidence to study other multilayered structures with multiple delaminations and subject to arbitrary loading profiles.

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References

Figures

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Fig. 1

Two-dimensional illustration of the predelaminated composite panel. The panel is assumed in a state of plane strain in the xz plane and simply supported at its left and right ends.

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Fig. 2

The piecewise linear spring model, which is a slightly modified version of Ref. [16]

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Fig. 3

Three-point bend test setup

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Fig. 5

Free body diagrams of modified CLT

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Fig. 6

Simple fracture models. The model only considers the potential energy change of the center delaminated region form pristine to delaminated configuration.

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Fig. 4

The four-section partition of a predelaminated composite panel in modified CLT

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Fig. 14

The load–displacement response variation with delamination length for 12-ply and 32-ply specimen with midplane delamination

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Fig. 7

Transverse stress distributions at delaminated interface of specimens with midplane delamination length 0.3L. The dashed line represents the location of crack tip.

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Fig. 8

Transverse shear stress distribution near the crack tip at delaminated interface of specimens with midplane delamination length of 0.3L. The dashed line represents the location of crack tip.

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Fig. 9

The convergence study on average transverse stresses of 32-ply specimen with midplane delamination length. d/L is the relative delamination length.

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Fig. 10

The variation of delamination threshold load versus existing center delamination length of 12-ply orthotropic laminated panel. The delamination is located at: (a) upper-quarter-plane; (b) mid-plane; and (c) lower-quarter-plane. Two-dimensional elastic solutions use the combination of three contact models (M1: general model, M2: friction-free model, and M3: constrained model) and two delamination criteria (stress: quadratic stress criterion and energy: fracture mechanics based criterion).

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Fig. 11

The variation of delamination threshold load versus existing center delamination length of 32-ply cross-ply laminated panel

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Fig. 12

The errors between simple fracture models and 2D elasticity theory using general contact model and fracture mechanics based failure criterion

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Fig. 13

The load–displacement response for 12-ply specimen with delamination length of 0.5L. The delamination is located at: (a) upper-quarter-plane; (b) lower-quarter-plane; and (c) mid-plane.

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