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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).
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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.
The tests explored the influence of the applied stress, the ratio of the minimum to the maximum applied stress, R, and crack closure.
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.
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.
Our major conclusion is that over a wide range of frequencies, the maximum propagating stress is always small compared with the maximum applied stress; hence Saint-Venant's principle may be said to apply in this problem.
Results indicated that the system could maintain 80% of the recovery stress, after up to 2 million load cycles, so long as the maximum applied stress was below the debonding onset level.
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