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Residual Strength and Fatigue Lifetime of ... - Solid Mechanics

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is the elastic foundation modulus parameter defined as<br />

<br />

3<br />

hf bE f<br />

3K<br />

<strong>and</strong> Ddebpnded <strong>and</strong> Dintact are the bending stiffness <strong>of</strong> the debonded <strong>and</strong> intact parts <strong>of</strong> the MMB<br />

specimen (Quispitupa et al., 2009):<br />

45<br />

(3.10)<br />

<br />

2 B <br />

D <br />

<br />

debonded 1 D <br />

A <br />

(3.11)<br />

3 3<br />

E f hf<br />

2 E f hf<br />

Echc<br />

Dintact<br />

hchf <br />

2<br />

6 12<br />

(3.12)<br />

The energy release rate can be expressed as<br />

(3.13)<br />

<br />

When the expressions for the compliance <strong>and</strong> the energy release rate are known, it is possible to<br />

determine the crack length at a given load <strong>and</strong> deflection <strong>and</strong> fracture toughness as the crack<br />

grows. However, to fully characterise the face/core interface the mode-mixity must be evaluated<br />

as well. Since there is no analytical expression for the interface mode-mixity, it is usually<br />

determined by use <strong>of</strong> the finite element method. For static characterisation, the fracture<br />

toughness <strong>of</strong> the interface can be determined by Equation (3.13) <strong>and</strong> the mode-mixity is<br />

evaluated using finite element modelling <strong>and</strong> the CSDE method as explained before. For fatigue<br />

characterisation <strong>of</strong> the interface, Equation (3.1) is used to determine the crack length from the<br />

compliance <strong>of</strong> the MMB specimens evaluated from the actual applied load <strong>and</strong> displacement <strong>of</strong><br />

the test specimen. Fracture testing <strong>of</strong> the MMB specimens was performed at a cross-head rate <strong>of</strong><br />

1 mm/min. Figure 3.3. shows typical load vs. displacement curves for representative loading<br />

conditions <strong>and</strong> specimens. In Figure 3.3 the point where the crack starts to propagate is marked<br />

with an open circle (“”). The load vs. displacement curves are fairly linear up to the point <strong>of</strong><br />

crack propagation. It is seen that the load drops due to a change in the specimen stiffness as the<br />

crack propagates. The critical failure load was marked according to the ASTM D6671/D 6671M-<br />

06 recommendation (the load at which the compliance has increased by 5%) <strong>and</strong> complemented<br />

by visual inspection. These critical failure loads (Pc) were used in the determination <strong>of</strong> the<br />

face/core interface fracture toughness (Gc), according to the procedure outlined by Quispitupa et<br />

al., (2009).

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