| タイトル | Proof test and fatigue crack growth modeling on 2024-T3 aluminum alloy |
| 著者（英） | Dawicke, D. S.; Newman, J. C., Jr.; Poe, C. C., Jr. |
| 著者所属（英） | Analytical Services and Materials, Inc.|NASA Langley Research Center |
| 発行日 | 1990-01-01 |
| 言語 | eng |
| 内容記述 | Pressure proof testing of aircraft fuselage structures has been suggested as a means of screening critical crack sizes and of extending their useful life. The objective of this paper is to study the proof-test concept and to model the crack-growth process on a ductile material. Simulated proof and operational fatigue life tests have been conducted on cracked panels made of 2024-T3 aluminum alloy sheet material. A fatigue crack-closure model was modified to simulate the proof test and operational fatigue cycling. Using crack-growth rate and resistance-curve data, the model was able to predict crack growth during and after the proof load. These tests and analyses indicate that the proof test increases fatigue life; but the beneficial life, after a 1.33 or 1.5 proof, was less than a few hundred cycles. |
| NASA分類 | METALLIC MATERIALS |
| レポートNO | 92A19828 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/330256 |
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