Programmed load testing of a structural member from a MACCHI aircraft was undertaken in an attempt to determine the source of the acoustic emission previously recorded during in flight monitoring of the same component and to compare results obtained from different equipment. Although crack growth during laboratory testing appeared similar to in flight crack growth, the pattern of recorded AE was markedly different. The laboratory tests are described and an explanation of the test results sought.
Laboratory Studies Related to In-Flight Acoustic Emission Monitoring
1987
23 pages
Report
Keine Angabe
Englisch
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