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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

Figures

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Geometry of an element of a symmetric laminated plate
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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. 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.
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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
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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