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TECHNICAL PAPERS

Stress Relaxation in Prestressed Composite Laminates

[+] Author and Article Information
A. P. Suvorov, G. J. Dvorak

Department of Mechanical Engineering, Aeronautical Engineering and Mechanics, Rensselaer Polytechnic Institute, Troy, NY 12180-3590

J. Appl. Mech 69(4), 459-469 (Jun 20, 2002) (11 pages) doi:10.1115/1.1460909 History: Received February 28, 2001; Revised October 23, 2001; Online June 20, 2002
Copyright © 2002 by ASME
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References

Dvorak,  G. J., and Suvorov,  A. P., 2000, “Effect of Fiber Prestress on Residual Stresses and Onset of Damage in Symmetric Laminates,” Compos. Sci. Technol., 60, (8), pp. 1129–1139.
Suvorov,  A. P., and Dvorak,  G. J., 2001, “Optimized Fiber Prestress for Reduction of Free Edge Stresses in Composite Laminates,” Int. J. Solids Struct., 38, pp. 6751–6786.
Dvorak,  G. J., Prochazka,  P., and Srinivas,  M. V., 1999, “Design and Fabrication of Submerged Cylindrical Laminates I,” Int. J. Solids Struct., 36, pp. 3917–3943.
Srinivas,  M. V., Dvorak,  G. J., and Prochazka,  P., 1999, “Design and Fabrication of Submerged Cylindrical Laminates II. Effect of Fiber Prestress,” Int. J. Solids Struct., 36, pp. 3945–3976.
Schapery,  R. A., 1967, “Stress Analysis of Viscoelastic Composite Materials,” J. Compos. Mater., 1, pp. 228–267.
Lou,  Y. C., and Schapery,  R. A., 1971, “Viscoelastic Characterization of a Nonlinear Fiber-Reinforced Plastic,” J. Compos. Mater., 5, pp. 208–234.
Mignery,  L. A., and Schapery,  R. A., 1991, “Viscoelastic and Nonlinear Adherent Effects in Bonded Composite Joints,” J. Adhes., 34, pp. 17–40.
Schapery,  R. A., 1993, “Compressive Strength and Failure Time Based on Local Buckling in Viscoelastic Composites,” Appl. Mech. Rev., 46, pp. 221–228.
Sims, D. F., and Halpin, J. C., 1974, “Methods for Determining the Elastic and Viscoelastic Response of Composite Materials,” Composite Materials: Testing and Design (Third Conference), ASTM STP, Philadelphia, PA, 546 , pp. 46–66.
Wang,  T. M., and Daniel,  I. M., 1992, “Thermoviscoelastic Analysis of Residual Stresses and Warpage in Composite Laminates,” J. Compos. Mater., 26, pp. 883–899.
Skudra,  A. M., and Auzukalns,  Y. V., 1973, “Creep and Long-Term Strength of Unidirectional Reinforced Plastics in Compression,” Polym. Mech., 6, pp. 718–722.
Ferry, J. D., 1980, Viscoelastic Properties of Polymers, John Wiley and Sons, New York.
Xia,  Z., and Ellyin,  F., 1998, “Time-Dependent Behavior and Viscoelastic Constitutive Modelling of an Epoxy Polymer,” Polymer and Polymer Comp., 6, pp. 75–83.
Hi,  Y., Xia,  Z., and Ellyin,  F., 2000, “Mechanical Behavior of an Epoxy Resin Under Multiaxial Loadings. Part I: Experimental Study,” Polym. Polym. Comp., 8, pp. 11–18.
Hi,  Y., Xia,  Z., and Ellyin,  F., 2000, “Mechanical Behavior of an Epoxy Resin Under Multiaxial Loadings. Part II: Comparison of Viscoelastic Constitutive Model Prediction,” Polym. Polym. Comp., 8, pp. 157–166.
Ellyin, F., Hu, Y., and Xia, Z., 2000, “Multiaxial Behavior and Viscoelastic Constitutive Modeling of Epoxy Polymers,” Recent Trends in Constitutive Modeling of Advanced Materials, AMD Vol. 239 , pp. 13–25.
Dvorak,  G. J., 1992, “Transformation Field Analysis of Inelastic Composite Materials,” Proc. R. Soc. London, Ser. A, 437, pp. 311–327.
Dvorak,  G. J., and Benveniste,  Y., 1992, “On Transformation Strains and Uniform Fields in Multiphase Elastic Media,” Proc. R. Soc. London, Ser. A, A437, pp. 291–310.
Dvorak,  G. J., Bahei-El-Din,  Y. A., and Wafa,  A. M., 1994, “Implementation of the Transformation Field Analysis for Inelastic Composite Materials,” Comput. Mech., 14, pp. 201–228.
Levin,  V. M., 1967, “Thermal Expansion Coefficients of Heterogeneous Materials,” Izv. AN SSSR, Mekhanika Tverdogo Tela, 2, pp. 88–94 (English Translation, Mechanics of Solids, 11, pp. 58–61).
Mori,  T., and Tanaka,  K., 1973, “Average Stress in Matrix and Average Elastic Energy of Materials With Misfitting Inclusions,” Acta Metall., 21, pp. 571–574.
Dvorak,  G. J., and Srinivas,  M. V., 1999, “New Estimates of Overall Properties of Heterogeneous Solids,” J. Mech. Phys. Solids, 47, pp. 899–920.
Blackketter,  D. M., and Upadhyaya,  D., 1993, “Micromechanics Predictions of the Transverse Tensile Strength of Carbon Fiber/Epoxy Composites: the Influence of the Matrix and Interface,” Polym. Compos., 14, pp. 437–446.
Adams,  D. F., King,  T. R., and Blackketter,  D. M., 1990, “Evaluation of the Transverse Flexure Test Method for Composite Materials,” Compos. Sci. Technol., 39, pp. 341–353.

Figures

Grahic Jump Location
Initial damage envelope for the (0/45/−45/90/0̄)s carbon/epoxy viscoelastic laminate before and after 12,000 sec stress relaxation. Overall stress is applied at the rate 1 MPa/sec. Optimized fiber prestress is 1950 MPa in the 0-deg plies, 77.9 MPa in the 90-deg plies, 62.7 MPa in the 45-deg plies and 62.7 MPa in the −45-deg plies. Thermal change of Δθ=−45°C is applied at t≥0.
Grahic Jump Location
Stress relaxation of the EPON 828 matrix material. The matrix is first subjected to constant axial strain ε11m=−0.005. After 12,000 sec of stress relaxation strain is applied at a rate either 0.007 * 10−3 or −0.007 * 10−3/sec, so that at time t=13,000  sec, the magnitude of axial strain is 0.002 or −0.012, respectively.
Grahic Jump Location
Initial damage envelope for the ((0/90)2/0̄)s carbon/epoxy viscoelastic laminate before and after 12,000 sec stress relaxation. Thermal change of Δθ=100°C is applied at t≥0.
Grahic Jump Location
Geometry of an element of a symmetric laminated plate
Grahic Jump Location
Initial damage envelope for the ((0/90)2/0̄)s carbon/epoxy viscoelastic laminate before and after 12,000 sec stress relaxation. Initial fiber prestress is 2100 MPa in the 0-deg plies and 470.8 MPa in the 90-deg plies. Thermal change of Δθ=−45°C is applied at t≥0.
Grahic Jump Location
Initial damage envelope for the (0/45/−45/90/0̄)s carbon/epoxy viscoelastic laminate before and after 12,000 sec stress relaxation. Optimized fiber prestress is 1950 MPa in the 0-deg plies, 77.9 MPa in the 90-deg plies, 62.7 MPa in the 45-deg plies and 62.7 MPa in the −45-deg plies. Thermal change of Δθ=−45°C is applied at t≥0.
Grahic Jump Location
Initial damage envelope for the ((0/90)2/0̄)s carbon/epoxy viscoelastic laminate before and after 12,000 sec stress relaxation. The overall stress is applied at the rate 1 MPa/sec. Optimized fiber prestress is 2100 MPa in the 0-deg plies and 470.8 MPa in the 90-deg plies. Thermal change of Δθ=−45°C is applied at t≥0.
Grahic Jump Location
Initial damage envelope for the (0/45/−45/90/0̄)s carbon/epoxy viscoelastic laminate before and after 12,000 sec stress relaxation. Thermal change of Δθ=100°C is applied at t≥0.

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