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Research Papers

Experimental Investigation of Static Interfacial Fracture in Orthotropic Polymer Composite Bimaterials Using Photoelasticity

[+] Author and Article Information
Marius D. Ellingsen

Department of Mechanical and Aerospace Engineering, University of Missouri, Columbia, MO 65211

Sanjeev K. Khanna1

Department of Mechanical and Aerospace Engineering, University of Missouri, Columbia, MO 65211

1

Corresponding author

J. Eng. Mater. Technol 132(2), 021007 (Feb 18, 2010) (11 pages) doi:10.1115/1.4000223 History: Received March 06, 2009; Revised August 27, 2009; Published February 18, 2010; Online February 18, 2010

The effects of static Mode I (opening mode) loading on orthotropic-orthotropic bimaterial interface cracks have been investigated using the experimental technique of transmission photoelasticity. For successful implementation of this experimental technique transparent and birefringent glass fiber reinforced polyester composite materials were developed, enabling the direct observation and recording of photoelastic fringes in the vicinity of the interface crack in the orthotropic bimaterial. It is our belief that this is the first of such experimental investigation. Opening and shearing mode stress-intensity factors and the strain energy release rates have been calculated for various combinations of the bimaterial halves. Results have been verified by mathematically regenerating the observed isochromatic fringe patterns. This study has made it feasible to investigate interfacial fracture in orthotropic-orthotropic bimaterials and orthotropic-isotropic bimaterials using photoelasticity.

Copyright © 2010 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Uniaxial tension center cracked specimen with crack tip coordinate system

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Figure 2

Composite-composite bimaterial (a/w=0.33) under 2.4 kN (600 lbs) load, both halves have reinforcement directions of 0 deg/90 deg

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Figure 3

Composite-composite bimaterial (a/w=0.33) under 2.4 kN (600 lbs) load, upper half has reinforcement directions of 0 deg /90 deg, lower half has reinforcement directions of 30 deg /60 deg

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Figure 4

Data collected from annular region surrounding the crack tip, shown by solid square dots

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Figure 5

Specification of bimaterial quadrants

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Figure 6

Photograph of angled interface bimaterial halves about to be joined

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Figure 7

Close-up of original fringe pattern (left) and its false-color fringe multiplied counterpart (right)

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Figure 8

Effect of increasing the number of terms in stress-field equations

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Figure 9

Effect of incorrectly locating the crack tip

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Figure 10

Aluminum −30 deg/60 deg composite bimaterial, 2 kN (450 lbs) load, a/w=0.33, w=76 mm (3.0 in.)

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Figure 11

0 deg/90 deg composite −0 deg/90 deg composite bimaterial, 2.7 kN (600 lbs) load, a/w=0.17, w=76 mm (3.0 in.)

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Figure 12

0 deg/90 deg composite −0 deg/90 deg composite bimaterial, 2.7 kN (600 lbs) load, a/w=0.25, w=76 mm (3.0 in.)

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Figure 13

0 deg/90 deg composite −0 deg/90 deg composite bimaterial, 2.7 kN (600 lbs) load, a/w=0.5, w=121 mm (4.75 in.)

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Figure 14

0 deg/90 deg composite −15 deg/75 deg composite bimaterial, 2.7 kN (600 lbs) load, a/w=0.33, w=76 mm (3.0 in)

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Figure 15

0 deg/90 deg composite −30 deg/60 deg composite bimaterial, 2.7 kN (600 lbs) load, a/w=0.33, w=76 mm (3.0 in.)

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Figure 16

0 deg/90 deg composite −45 deg/45 deg composite bimaterial, 3.3 kN (750 lbs) load, a/w=0.33, w=152 mm (6.0 in.)

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Figure 17

Energy release rate versus a/w for specimens with reinforcement directions 0 deg/90 deg in both halves

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Figure 18

Mode mixity versus a/w ratio for specimens with reinforcement directions 0 deg/90 deg in both halves

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Figure 19

Mode mixity versus reinforcement angle in the bottom half of the bimaterial specimens

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