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Proceedings Paper

Detection of surface breaking fatigue crack on a complex aircraft structure with Rayleigh surface waves
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Paper Abstract

As part of an on-going, multi-year effort focused on developing a practical structural health monitoring (SHM) sensor for critical structural components in aircraft, a miniature Rayleigh surface wave sensor has been developed and tested. The sensor was specifically designed to detect localized, deterministic cracking in targeted locations in critical locations where fatigue cracking is prevalent. A representative aircraft component was used in the present investigation. Miniature interdigital transducers (IDTs) operating in the low megahertz frequency range were designed, fabricated, and tested on compact tension (CT) fatigue specimens in the laboratory before they were strategically placed on the structure, where surface wave signals were monitored in both pitch-catch and pulse-echo detection modes simultaneously. Under a high-cycle fatigue loading to the structure, the IDT sensors performed well with three of the sensors successfully detecting the existence of a critical fatigue crack. Visual and eddy current inspection methods subsequently verified the presence of the crack and its location. In this paper, the entire effort from the design and characterization of the IDT sensors to the final fatigue test on an actual aircraft part is discussed.

Paper Details

Date Published: 8 April 2009
PDF: 9 pages
Proc. SPIE 7295, Health Monitoring of Structural and Biological Systems 2009, 72950G (8 April 2009); doi: 10.1117/12.815079
Show Author Affiliations
Jeong K. Na, Univ. of Dayton Research Institute (United States)
James L. Blackshire, Air Force Research Lab. (United States)
Samuel J. Kuhr, Univ. of Dayton Research Institute (United States)


Published in SPIE Proceedings Vol. 7295:
Health Monitoring of Structural and Biological Systems 2009
Tribikram Kundu, Editor(s)

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