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Research Papers

Impact Damage Tolerance and Fatigue Durability of GLARE Laminates

[+] Author and Article Information
Hyoungseock Seo1

Mechanical and Aerospace Engineering Department, University of California Los Angeles, Los Angeles, CA 90095seohyung@ucla.edu

H. T. Hahn

Mechanical and Aerospace Engineering Department, University of California Los Angeles, Los Angeles, CA 90095; Materials Science and Engineering Department, University of California Los Angeles, Los Angeles, CA 90095

Jenn-Ming Yang

Materials Science and Engineering Department, University of California Los Angeles, Los Angeles, CA 90095

1

Corresponding author.

J. Eng. Mater. Technol 130(4), 041002 (Aug 26, 2008) (6 pages) doi:10.1115/1.2969253 History: Received August 14, 2007; Revised April 09, 2008; Published August 26, 2008

The fatigue behavior and residual strength of postimpacted GLARE 4-3/2, GLARE 5-2/1, and monolithic aluminum 2024-T3 alloy were investigated experimentally. Drop-weight impact was applied at a variety of energy levels to inflict a barely visible impact damage, a clearly visible impact damage, and a penetration damage. After the impact test, constant-amplitude tension-tension fatigue was done to delineate the modes of damage initiation and growth and the effect of damage on fatigue life and residual strength. The results showed that GLARE laminates exhibit superior postimpact fatigue durability when compared with the monolithic 2024-T3 aluminum alloy.

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 1

(a) Configuration of GLARE 5-2/1 and (b) GLARE 4-3/2

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Figure 2

(a) BVID (E=10.8 J) in GLARE 5-2/1, (b) CVID (E=18.1 J) in GLARE 5-2/1, (c) BVID (E=10.8 J) in GLARE 4-3/2, and (d) CVID (E=18.1 J) in GLARE 4-3/2

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Figure 3

Crack growth in GLARE 4-3/2 with CVID at a maximum fatigue stress of 81 MPa

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Figure 4

Crack growth in GLARE 5-2/1 with CVID at a maximum fatigue stress of 121.5 MPa

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Figure 5

Crack initiation life and fatigue life curves for aluminum 2024-T3, GLARE 5-2/1, and GLARE 4-3/2 with BVID

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Figure 6

Crack initiation life and fatigue life curves for aluminum 2024-T3, GLARE 5-2/1, and GLARE 4-3/2 with CVID

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Figure 7

Crack growth in GLARE 4-3/2 with BVID at various fatigue stresses

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Figure 8

Crack growth in GLARE 5-2/1 with BVID at various fatigue stresses

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Figure 9

Nuisance cracks in GLARE 4-3/2 with BVID; fatigue run-out at 232.4 MPa

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Figure 10

Change in residual strength in GLARE 4-3/2

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Figure 11

Change in residual strength in GLARE 5-2/1

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