Abstract
Structural health monitoring of cracked aircraft structural panels repaired with bonded FRP composite patches has received wide attention to extend service life of aging aircraft. In this paper is presented the method to identify the location and shape of a fatigue crack front in aircraft structural panels repaired with a bonded FRP composite patch by use of a tunneling method. As measured values, strains on a measurement plane in the FRP composite patch are utilized. Several numerical examples of the identification of location and shape of fatigue crack fronts are examined, and the effects of number of strain measurement points, position of a strain measurement plane and measurement errors of strains on the identification results are discussed. The validity of the present identification method is verified by comparing the identification results with the exact ones.
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