AD-A175110 Assessment of Damage Tolerance Requirements and Analyses
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- May 9, 2020 Create Date
- May 9, 2020 Last Updated
A structural test program of a typical aircraft structural configuration was conducted to assess the current Air Force damage tolerance design requirements defined in MIL-A-83444. The specimens, made of 2024-T3XX and 7075-T6XX, were subjected to randomized flight-byflgiht spectra, representative of fighter/trainer and bomber/cargo-type loading spectra, respectively, and to constant amplitude loading spectrum. A total of 72 specimens were tested. The test results were correlated with analytical predictions using the crack growth method and combined method. As a result of this study, a recommendation is provided to the validity of MIL-A-83444, to develop guidelines for selection of critical crack locations, and to assess the state-of-the-art analytical capabilities in predicting crack growth and crack initiaiton time.
| File | Action |
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| AD-A175110 Assessment of Damage Tolerance Requirements and Analyses.pdf | Download |

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