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NASA-TN-D-960
Effects of changing stress amplitude on the rate of fatigue-crack propagation in two aluminum alloys
Year: 1961
Abstract: A series of fatigue tests with specimens subjected to constant amplitude and two-step axial loads were conducted on 12-inch-wide sheet specimens of 2024-T3 and 7075-T6 aluminum alloy to study the effects of a change in stress level on fatigue-crack propagation. Comparison of the results of the tests in which the specimens were tested at first a high and then a low stress level with those of the constant-stress- amplitude tests indicated that crack propagation was generally delayed after the transition to the lower stress level. In the tests in which the specimens were tested at first a low and then a high stress level, crack propagation continued at the expected rate after the change in stress levels.
Subject: ALUMINUM ALLOYS
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:07:33Z | |
| date available | 2017-09-04T18:07:33Z | |
| date copyright | 01/01/1961 | |
| date issued | 1961 | |
| identifier other | GPBBFEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/190430 | |
| description abstract | A series of fatigue tests with specimens subjected to constant amplitude and two-step axial loads were conducted on 12-inch-wide sheet specimens of 2024-T3 and 7075-T6 aluminum alloy to study the effects of a change in stress level on fatigue-crack propagation. Comparison of the results of the tests in which the specimens were tested at first a high and then a low stress level with those of the constant-stress- amplitude tests indicated that crack propagation was generally delayed after the transition to the lower stress level. In the tests in which the specimens were tested at first a low and then a high stress level, crack propagation continued at the expected rate after the change in stress levels. | |
| language | English | |
| title | NASA-TN-D-960 | num |
| title | Effects of changing stress amplitude on the rate of fatigue-crack propagation in two aluminum alloys | en |
| type | standard | |
| page | 24 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1961 | |
| contenttype | fulltext | |
| subject keywords | ALUMINUM ALLOYS | |
| subject keywords | AXIAL LOADS | |
| subject keywords | CRACK INITIATION | |
| subject keywords | CRACK PROPAGATION | |
| subject keywords | FATIGUE TESTS | |
| subject keywords | PERFORMANCE TESTS | |
| subject keywords | STRESS ANALYSIS | |
| subject keywords | STRESS PROPAGATION |