22 July 2003 Structural integrity monitoring of aircraft panels using a distributed Bragg grating sensing technique
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Abstract
We report the use of a fiber-optic distributed sensing system to monitor crack growth on aircraft panels. The system utilizes optical frequency domain reflectometry to demodulate the reflected signals from up to thousands of weakly reflecting gratings photoetched along a single optical fiber. In our experiment, data from a regular array of sensors attached to an aircraft panel were recorded as the panel was subjected to increasing loads. Strain contour maps generated from these data enable clear visualization of the crack growth over time. A similar experiment was also performed using fiber-optic strain sensors embedded in aircraft composite repair patches. The results of these experiments demonstrate the viability of distributed fiber-optic sensing for crack growth monitoring.
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Dawn K. Gifford, Dawn K. Gifford, Brooks A. Childers, Brooks A. Childers, Roger G. Duncan, Roger G. Duncan, Anthony C. Jackson, Anthony C. Jackson, Surendra Shaw, Surendra Shaw, William Schwienberg, William Schwienberg, James Mazza, James Mazza, } "Structural integrity monitoring of aircraft panels using a distributed Bragg grating sensing technique", Proc. SPIE 5050, Smart Structures and Materials 2003: Smart Sensor Technology and Measurement Systems, (22 July 2003); doi: 10.1117/12.508072; https://doi.org/10.1117/12.508072
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