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A higher-order theory
for crack growth in fiber-metal laminates under generalized
plane-stress conditions
Xijia Wu, Zhong Zhang and J. Laliberté |
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Vol. 1 (2006), No. 3, 431–445
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Abstract |
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Fiber-metal laminates (FML) are hybrid materials that consist of alternating layers of metal and fiber-reinforced prepreg. The classical plane-stress theory has difficulty in dealing with the fatigue fracture of such materials where the crack only grows in the metal layers, while the prepreg layers remain intact. In this paper, a new theoretical treatment is given to FML under generalized plane-stress conditions. The new theory introduces a harmonic anti-plane-stress potential to describe the interlaminar stresses near the crack tips and the “bridging” effect of the unbroken fibers along the crack wakes. An analytical solution is derived for GLARE-3 containing collinear cracks with length (the initial crack length) in the prepreg and length in the aluminum layer. The effective stress intensity factor is obtained in a closed form, and the theoretical prediction is compared with the experimental behavior obtained from fatigue crack growth testing of center-notched specimens. |
Keywords
fiber-metal laminate, stress intensity factor
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Milestones
Received: 10 October 2005
Revised: 16 December 2005
Accepted: 6 January 2006
Published: 1 July 2006
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Authors |
| Xijia Wu | |
| Structures and Materials Performance
Laboratory Institute for Aerospace Research National Research Council of Canada 1200 Montreal Road, M-13 Ottawa, ON K1A OR6 Canada |
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| Zhong Zhang | |
| Department of Mechanical and
Aerospace Engineering Carleton University 1125 Coloniel By Drive Ottawa, ON K1S 5B6 Canada |
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| J. Laliberté | |
| Structures and Materials Performance
Laboratory Institute for Aerospace Research National Research Council of Canada 1200 Montreal Road, M-13 Ottawa, ON K1A OR6 Canada |
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