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AA-CP-20212-001
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ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
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AD-A175110 Assessment of Damage Tolerance Requirements and Analyses

AD-A175110 Assessment of Damage Tolerance Requirements and Analyses
  • Version
  • 196 Downloads
  • 1.77 MB File Size
  • 1 File Count
  • May 9, 2020 Create Date
  • May 9, 2020 Last Updated
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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.

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AD-A175110 Assessment of Damage Tolerance Requirements and Analyses

AD-A175110 Assessment of Damage Tolerance Requirements and Analyses
  • Version
  • 196 Downloads
  • 1.77 MB File Size
  • 1 File Count
  • May 9, 2020 Create Date
  • May 9, 2020 Last Updated
Scroll for Details

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.

FileAction
AD-A175110 Assessment of Damage Tolerance Requirements and Analyses.pdfDownload 
17,005 Documents in our Technical Library
3206925 Total Downloads

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Newest Additions

NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
AA-CP-20212-001
AA-CP-20212-001
ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...