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The strain in laminate under maximum applied stress is.
A potential problem in the DRA is the restriction of maximum applied stress.
A linear line in a maximum applied stress versus logarithm of life coordinate system appears to be a good fit to the experimental data.
The results show that, the fatigue life of the SiCf/Ti 6Al 4V composite decreases substantially in proportion to the increase in maximum applied stress.
Damage was observed to initiate as shear bands or mixed-mode cracks propagating at ∼49° to the maximum applied stress axis after only a few stress cycles.
The tests explored the influence of the applied stress, the ratio of the minimum to the maximum applied stress, R, and crack closure.
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The fatigue S N behavior was recorded for maximum applied stresses between 300 and 500 MPa (R = 0.1, 5 Hz).
In addition, tensile fatigue loading up to 5000 cycles evidenced a limited amount of degradation for maximum applied stresses up to 70% of composite tensile strength.
This work investigated the effect of nominal boron (B) additions of 0.1 wt.% and 1.0 wt.% on the elevated-temperature (455 °C) fatigue deformation behavior of Ti 6Al 4V (wt.%) for maximum applied stresses between 250 and 550 MPa (R = 0.1, 5 Hz).
For these reasons an alternative technique has been developed, which requires calculating the stress intensity factors at both the maximum and minimum applied stresses for each crack length.
It was found that in specimens with bedding planes aligned perpendicularly to the maximum applied compressive stress, the effects of the flaw angle and flaw pair bridging angle on the cracking processes were similar to those observed in previously tested rocks without bedding planes.
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