| タイトル | An evaluation of the pressure proof test concept for 2024-T3 aluminium alloy sheet |
| 著者（英） | Newman, J. C.; Harris, C. E.; Dawicke, D. S.; Poe, C. C., Jr. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1991-01-01
1991 |
| 言語 | eng |
| 内容記述 | The concept of pressure proof testing of fuselage structures with fatigue cracks to insure structural integrity was evaluated from a fracture mechanics viewpoint. A generic analytical and experimental investigation was conducted on uniaxially loaded flat panels with crack configurations and stress levels typical of longitudinal lap splice joints in commercial transport aircraft fuselages. The results revealed that the remaining fatigue life after a proof cycle was longer than that without the proof cycle because of crack growth retardation due to increased crack closure. However, based on a crack length that is slightly less than the critical value at the maximum proof stress, the minimum assured life or proof test interval must be no more than 550 pressure cycles for a 1.33 proof factor and 1530 pressure cycles for a 1.5 proof factor to prevent in-flight failures. |
| NASA分類 | STRUCTURAL MECHANICS |
| レポートNO | 93A45780 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/316135 |
|
