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TECHNICAL PAPERS

Higher-Order Zig-Zag Theory for Laminated Composites With Multiple Delaminations

[+] Author and Article Information
M. Cho

School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Korea   e-mail: mhcho@snu.ac.kr

J.-S. Kim

Department of Aerospace Engineering, Inha University, Inchon 402-751, Korea

J. Appl. Mech 68(6), 869-877 (Oct 19, 2000) (9 pages) doi:10.1115/1.1406959 History: Received July 12, 1999; Revised October 19, 2000
Copyright © 2001 by ASME
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References

Figures

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Geometry of laminated composite with multiple delaminations
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Laminate deformed configurations with multiple delaminations
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Configuration of a simply supported beam-plate with a single delamination
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Nondimensionalized buckling load versus delamination length
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Configuration of a clamped beam-plate with centrally located delaminations
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Normalized buckling load versus delamination length for [0//90/90/0] composite, symmetric mode
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Normalized buckling load versus delamination length for [0//90/90/0] composite, antisymmetric mode
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Normalized buckling load versus delamination length for [0//90/0/90] composite
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Normalized buckling load versus delamination length for [0/90/90/0] composite with S=20, symmetric mode
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Normalized buckling load versus delamination length for [0/90/90/0] composite with S=20, antisymmetric mode
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Configuration of cantilevered [0/90]2s composite beam with a single delamination
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Configuration of cantilevered [0/90/90/0] composite beam with multiple delaminations
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Normalized natural frequency versus normalized distance for [0/90/90/0] composite with S=400
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Normalized natural frequency versus normalized distance for [0/90/90/0] composite with S=50
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Normalized natural frequency versus normalized distance for [0/90/90/0] composite with S=10

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