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Research Papers

Mechanical Behavior of High Temperature Hybrid Carbon Fiber/Titanium Laminates

[+] Author and Article Information
Christos G. Papakonstantinou1

Department of Civil and Environmental Engineering, University of Massachusetts Dartmouth, 285 Old Westport Road, North Dartmouth, MA 02747cpapakonstan@umassd.edu

Konstantinos Katakalos

Department of Civil and Environmental Engineering, University of Massachusetts Dartmouth, 285 Old Westport Road, North Dartmouth, MA 02747

1

Corresponding author.

J. Eng. Mater. Technol 131(2), 021008 (Mar 09, 2009) (10 pages) doi:10.1115/1.3030879 History: Received November 10, 2007; Revised March 06, 2008; Published March 09, 2009

The aim of this paper was to investigate the tensile and flexural properties of hybrid laminates made with titanium sheets and high modulus carbon fiber composites. Grade II titanium was used, which exhibits great high-temperature performance and creep resistance, low weight, and high strength. An inorganic fireproof matrix, known as geopolymer, was used to fabricate the high modulus carbon fiber composites. Previous studies have shown that these composites are strong, durable, lightweight, and can exhibit excellent performance up to 400°C. In the present study, a number of specimens were tested in uniaxial tension and four-point bending after exposure at elevated temperatures. The results indicate that the addition of carbon fibers can reduce the weight and increase the stiffness of the pure titanium. Moreover, the hybrid laminates are stronger and stiffer than the sum of the individual strengths and stiffnesses of the parent materials. An important finding is that the interlaminar bond is strong, and as a result no delamination failures were observed.

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Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

(a) Type A laminate, (b) Type B laminate, (c) Type C laminate, and (d) Type D laminate

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Figure 2

Curing cycle details

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Figure 3

(a) Tensile setup and (b) bending setup

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Figure 4

Stress-stain curves for carbon fiber/polysialate composite (CFRP) and grade 2 titanium (Ti)

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Figure 5

Tensile stress-strain curves under different temperatures for type A and B laminates

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Figure 6

Tensile stress-stain curves (a) at room temperature and (b) after exposure at 400°C

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Figure 7

Load-displacement curves for type A, B, C, and D specimens

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Figure 8

Failure of fibers (a) in compressive face and (b) in tension face

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Figure 9

Load-displacement curves for different laminates (a) at room temperature and (b) after exposure at 400°C

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Figure 10

Theoretical versus experimental load-displacement curves for different laminates

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