In response to the need for monitoring cracks around aircraft bolt and rivet holes, this study proposes and develops an electromagnetic induction sensor that combines load-bearing and structural crack monitoring capabilities. The sensor's layout is designed, and its working principle is explained. Using laser engraving and physical vapor deposition (PVD) processes, the sensor is fabricated. Experimental results demonstrate that the sensor can detect fatigue cracks of 0.8 mm in length around structural holes under bolt assembly and structural fatigue loads, confirming its effectiveness.

Electromagnetic induction sensor,Structural crack monitoring,Bolted connection structure