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Research Papers

Generalized Free-Edge Stress Analysis Using Mechanics of Structure Genome

[+] Author and Article Information
Bo Peng

School of Aeronautics and Astronautics,
Purdue University,
West Lafayette, IN 47907
e-mail: peng69@purdue.edu

Johnathan Goodsell

Research Assistant Professor
School of Aeronautics and Astronautics,
Purdue University,
West Lafayette, IN 47907
e-mail: jgoodsell@purdue.edu

R. Byron Pipes

Fellow ASME
Professor
School of Aeronautics and Astronautics,
Purdue University,
West Lafayette, IN 47907-2045
e-mail: bpipes@purdue.edu

Wenbin Yu

Fellow ASME
Associate Professor
School of Aeronautics and Astronautics,
Purdue University,
West Lafayette, IN 47907-2045
e-mail: wenbinyu@purdue.edu

1Corresponding author.

Contributed by the Applied Mechanics Division of ASME for publication in the JOURNAL OF APPLIED MECHANICS. Manuscript received July 23, 2016; final manuscript received July 30, 2016; published online August 22, 2016. Editor: Yonggang Huang.

J. Appl. Mech 83(10), 101013 (Aug 22, 2016) (7 pages) Paper No: JAM-16-1371; doi: 10.1115/1.4034389 History: Received July 23, 2016; Revised July 30, 2016

This work reveals the potential of mechanics of structure genome (MSG) for the free-edge stress analysis of composite laminates. First, the cross-sectional analysis specialized from MSG is formulated for solving a generalized free-edge problem of composite laminates. Then, MSG and the companion code SwiftComp™ are applied to the free-edge stress analysis of several composite laminates with arbitrary layups and general loads including extension, torsion, in-plane and out-of-plane bending, and their combinations. The results of MSG are compared with various existing solutions for symmetric angle-ply laminates. New results are presented for the free-edge stress fields in general laminates for combined mechanical loads and compared with three-dimensional (3D) finite element analysis (FEA) results, which agree very well.

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References

Figures

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Fig. 1

The laminate geometry and coordinate system

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Fig. 9

Distribution of the interlaminar stresses along the width of the [30/60/−45/45] laminate under combined loads: extension, bending, and twisting

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Fig. 10

Distribution of the interlaminar stress at the free edge of the [30/60/−45/45] laminate under combined loads: extension, bending, and twisting

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Fig. 8

Convergence of interlaminar normal stress distribution of the [30/60/−45/45] laminate under combined loads: extension, bending, and twisting

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Fig. 7

Axial displacement term U at y = b of [45/−45]s laminate under anticlastic bending

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Fig. 6

Interlaminar shear stress at y = b of [45/−45]s laminate under anticlastic bending

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Fig. 5

In-plane shear stress and interlaminar shear stress approaching the free edge of the [45/−45]s laminate under anticlastic bending

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Fig. 4

Convergence study of the interlaminar shear stress distribution along z = h0 of the [45/−45]s laminate under tension

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Fig. 3

A typical mesh pattern (mesh 2) of the 2D cross section of the laminate

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Fig. 2

Comparison of interlaminar shear stress distribution for the [45/−45]s laminate under tension

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