The recent developments have shown the advantages of the thermographic technique for the detection of corrosion and disbonds in aircraft structures [1-3]. These have typically involved the application of heat with an infrared source and imaging the induced temperature change with an infrared imager. This offers a rapid method for detecting corrosion and quantifying its extent in single layer structures. In these application, the heating and imaging components of the system remain stationary during the measurement cycle. Two disadvantages of this technique are the expense of the infrared imager and the large power requirement for the infrared heater.
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