A structural article representative of a large full-production military aircraft wing was subjected to flight-by-flight load spectra to initiate and propagate fatigue cracks in 17 selected fastener holes in eight test areas. One-hundred unit flights were applied to the wing to initiate crack growth at sharp notch sawcuts and existing cracks, followed by 2000 unit flights to propagate the cracks. Seven test areas were monitored for acoustic emission (AE) using a 32-channel AE flaw locator system and triangulated sensor arrays. AE was detected from 12 of the 15 test holes monitored which experienced crack growth. After the tests, the tes holes were removed from the structure fractographic analysis of crack growth.
Acoustic emission detection of fatigue crack growth in a production-size aircraft wing test article under simulated flight loads
Akustischer Nachweis des Ermuedungsrisswachstums in einem Flugzeugtragflaechenteil, der unter simulierter Fluglast geprueft wird
Materials Evaluation ; 36 , 5 ; 41-48
1978
8 Seiten, 10 Bilder, 1 Tabelle, 10 Quellen
Article (Journal)
English
In-flight fatigue crack monitoring using acoustic emission
Tema Archive | 1981
|British Library Online Contents | 1996
|