Carbon fiber reinforced plastic (CFRP) skin-stringer structures are expected to be widely employed in lightweight aircrafts. A suitable joining method between the CFRP stringers and skins is an adhesive bonding. However, the adhesive joint has a possibility to be degraded because of the appearance of debonding. Moreover, since the skin-stringer structures are usually located in inaccessible regions, the inability to reliably detect the weakening of adhesive bonding by conventional non-destructive evaluation (NDE) techniques remains a major barrier to widespread adoption of adhesive bonding. Hence, inspections with real-time structural health monitoring (SHM) technology are desired to ensure the structural integrity of the adhesively bonded structures.
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