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TECHNICAL PAPERS

Damage of Short-Fiber-Reinforced Metal Matrix Composites Considering Cooling and Thermal Cycling

[+] Author and Article Information
Chuwei Zhou, Wei Yang, Daining Fang

FML, Department of Engineering Mechanics, Tsinghua University, Beijing 100084, China

J. Eng. Mater. Technol 122(2), 203-208 (Nov 04, 1999) (6 pages) doi:10.1115/1.482788 History: Received March 24, 1999; Revised November 04, 1999
Copyright © 2000 by ASME
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References

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Figures

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Cohesive force curve during normal separation
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Aligned short fibers arranged in a transverse hexagon array. (a) A longitudinal section shows the fiber alignments; (b) a transverse section shows the hexagon array; (c) finite element mesh with indication of boundary conditions.
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Stress and damage fields during two thermal cycles of ±200°C. (a) Maximum radial stress distribution in matrix; (b) maximum longitudinal stress distribution; (c) maximum shear stress distribution; (d) distribution of the interface damage λmax with matrix damage; (e) distribution of λmax without matrix damage; (f ) distribution of the matrix damage f with interface damage; (g) distribution of f without interface damage.
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Average tensile stress σ̄x versus average logarithmic strain ε̄x curves (ff=20 percent,σnt=2.5σ0f=5 and βR=4.3) after various thermal histories. A, without cooling and thermal cycling; B, with cooling from 525°C to 25°C but not thermal cycling; C, cooling followed by thermal cycling of ±100°C; D, cooling followed by thermal cycling of ±200°C.
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Average tensile stress σ̄x versus average logarithmic strain ε̄x curves after zero, one, two, and twenty thermal cycles
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The interface and matrix damage distributions at the failure stage after (a) thermal history A, (b) thermal history B, (c) thermal history D, preceding the uniaxial tension at the room temperature.
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Average debonding tensile stress and strain versus the relative interface thickness δ/rf curves under thermal histories B,C, and D. (a) σ̄d0 versus δ/rf curves; (b) ε̄d versus δ/rf curves.

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