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Technical Brief

Interlaminar Stresses in Composite Laminates Subjected to Twisting Deformation

[+] Author and Article Information
Johnathan Goodsell, Bo Peng, Wenbin Yu

School of Aeronautics and Astronautics,
Purdue University,
West Lafayette, IN 47907

R. Byron Pipes

Schools of Aeronautics and Astronautics,
Materials Engineering and Chemical Engineering,
Purdue University,
West Lafayette, IN 47907

Contributed by the Applied Mechanics Division of ASME for publication in the JOURNAL OF APPLIED MECHANICS. Manuscript received April 27, 2017; final manuscript received July 18, 2017; published online August 7, 2017. Assoc. Editor: George Kardomateas.

J. Appl. Mech 84(10), 104503 (Aug 07, 2017) (4 pages) Paper No: JAM-17-1221; doi: 10.1115/1.4037317 History: Received April 27, 2017; Revised July 18, 2017

The interlaminar stress in angle-ply and cross-ply composite laminates subjected to twisting deformation are investigated. Two mechanisms of interlaminar load transfer have been developed by studying the angle-ply laminate and the cross-ply laminate subjected to uniform axial extension, thermoelastic deformation and anticlastic bending deformation. In the present, these mechanisms are investigated in laminates subjected to twisting deformation. It is shown that the mechanisms of interlaminar load transfer in twisting deformation are identical to those previously investigated, though they arise from different causes. Furthermore, a unified treatment of the mechanisms of interlaminar load transfer is presented for the angle-ply laminate and the cross-ply laminate subjected to the four aforementioned modes of deformation.

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Figures

Grahic Jump Location
Fig. 2

Stresses in angle-ply ([±45]s) laminate: (a) at center of laminate, y = 0; (b) transverse, through-thickness and interlaminar stresses approaching free-edge; (c) interlaminar stress, σzz at free-edge, y = b; (d) in-plane and interlaminar shearing stress approaching free-edge; and (e) interlaminar shearing stress at free-edge, y = b

Grahic Jump Location
Fig. 3

Stresses in cross-ply ([0/90]s) laminate: (a) at center of laminate, y = 0; (b) in-plane and interlaminar shearing stress approaching free-edge; and (c) interlaminar shearing stress at free-edge, y = b

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