Acoustic Emission Monitoring of Crack Propagation on the Expedited Wing Fatigue Test Article (X993).
Abstract
This final report describes work accomplished, under USAF contract, whose objective was to evaluate the ability of acoustic emission techniques to detect crack growth in a large full-production aircraft wing fatigue test article subjected to simulated flight spectra. Fatigue cracks were propagated at seventeen selected pre-damaged fastener holes in eight test areas on the test article. The flight load spectra consisted of fifty variable tension-tension gust cycles followed by 1/2 of a compressive ground cycle. Sixteen of the fastener holes were monitored with a 32-channel acoustic emission flaw locator system containing a computer, CRT monitor, input/output teleprinter console and tape recorder. Linear and triangular sensor arrays were used to detect and locate cracks. Twelve fatigue cracks were detected at fifteen fastener holes monitored where crack growth occurred. Acoustic emission data were correlated to crack growth data, determined through fractographic analysis, for several of the test cracks. Complex structural features which were accommodated successfully for detection of AE across joints are described. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1976
- Accession Number
- ADA041107
Entities
People
- Cliff D. Bailey
- James M. Hamilton
- William M. Pless
Organizations
- Lockheed Martin