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TECHNICAL PAPERS

Refined First-Order Shear Deformation Theory Models for Composite Laminates

[+] Author and Article Information
F. Auricchio

Dipartimento di Meccanica Strutturale, Università di Pavia, Via Ferrata 1, 27100 Pavia, Italye-mail: auricchio@unipv.it

E. Sacco

Dipartimento di Meccanica, Stuutture, A. & T., Università di Cassino, Via Di Biasio 43, 03043 Cassino, Italye-mail: sacco@unicas.it

J. Appl. Mech 70(3), 381-390 (Jun 11, 2003) (10 pages) doi:10.1115/1.1572901 History: Received March 03, 2002; Revised October 04, 2002; Online June 11, 2003
Copyright © 2003 by ASME
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References

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Figures

Grahic Jump Location
Dimensionless shear stress τ1z/p0 at x1=0 for homogeneous plate in cylindrical bending; comparison between the different solutions
Grahic Jump Location
Dimensionless shear stress τ1z/p0 at x1=0 for homogeneous plate in cylindrical bending; comparison between the different solutions computed considering one, three, and ten equal layers
Grahic Jump Location
Dimensionless shear stress τ1z/p0 at x1=0 for the [0/90] laminate in cylindrical bending; comparison between the different solutions
Grahic Jump Location
Dimensionless shear stress τ1z/p0 at x1=0 for the [0/90] laminate in cylindrical bending; comparison between the different solutions
Grahic Jump Location
Dimensionless shear stress τ1z/p0 for the [0/90] laminate computed at x1=0,x2=a/2; comparison with the three-dimensional analytical solution
Grahic Jump Location
Dimensionless shear stress τ2z/p0 for the [0/90] laminate computed at x1=a/2,x2=0; comparison with the three-dimensional analytical solution
Grahic Jump Location
Dimensionless shear stress τ1z/p0 for the [0/90/0] laminate computed at x1=0,x2=a/2; comparison with the three-dimensional analytical solution
Grahic Jump Location
Dimensionless shear stress τ2z/p0 for the [0/90/0] laminate computed at x1=a/2,x2=0; comparison with the three-dimensional analytical solution
Grahic Jump Location
Dimensionless displacement wmax versus the thickness to side ratio
Grahic Jump Location
Dimensionless shear stress τ1z/p0 for the [−45/45] laminate computed at x1=0,x2=a/2; comparison with first-order shear deformation theory (χ=5/6) analytical solution

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