Residual Strength and Fatigue Lifetime of ... - Solid Mechanics
Residual Strength and Fatigue Lifetime of ... - Solid Mechanics
Residual Strength and Fatigue Lifetime of ... - Solid Mechanics
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generated. Symmetry boundary conditions are imposed in the symmetry planes. The edges <strong>of</strong> the<br />
panels are clamped by imposing a zero displacement boundary condition. The finite element<br />
model <strong>of</strong> the debonded panel is shown in Figure 5.44. The accelerated fatigue crack growth<br />
simulation scheme (cycle jump method) developed in the previous chapter is used to simulate<br />
fatigue crack propagation in the s<strong>and</strong>wich panels. The energy release rate <strong>and</strong> mode-mixity phase<br />
angle are chosen as state variables in the cycle jump scheme. Figure 5.45 illustrates the<br />
distribution <strong>of</strong> the energy release rate <strong>and</strong> the related mode-mixity phase angle during the first<br />
cycle along the debond front using the maximum fatigue load amplitude. As expected the energy<br />
release rate <strong>and</strong> mode-mixity phase angle are evenly distributed along the debond front because<br />
<strong>of</strong> the circular shape <strong>of</strong> the debond <strong>and</strong> the large distance to the panel boundaries. Figure 5.46<br />
shows the energy release rate <strong>and</strong> mode-mixity phase angle vs. debond diameter using the<br />
maximum fatigue load amplitude.<br />
Debond<br />
Figure 5.44: Quarter finite element model <strong>of</strong> the debonded panels with a circular debond. The<br />
smallest element size is 10m.<br />
121<br />
Clamp B. C.<br />
Symmetry B. C.<br />
310 mm<br />
x<br />
y