Abstract
This work focuses on an ultrasonic guided wave structural health monitoring (SHM) systemdevelopment for aircraft wing inspection. In part I of the study, a detailed description of areal aluminum wing specimen and some preliminary wave propagation tests on the wingpanel are presented. Unfortunately, strong attenuation and scattering impede guidedwaves for large-area inspection. Nevertheless, small, low-cost and light-weightpiezoelectric (PZT) discs were bonded to various parts of the aircraft wing, in a formof relatively sparse arrays, for simulated cracks and corrosion monitoring. ThePZT discs take turns generating and receiving ultrasonic guided waves. Pair-wisethrough-transmission waveforms collected at normal conditions served as baselines,and subsequent signals collected at defected conditions such as rivet cracks orcorrosion detected the presence of a defect and its location with a novel correlationanalysis based technique called RAPID (reconstruction algorithm for probabilisticinspection of defects). The effectiveness of the algorithm was tested with severalcase studies in a laboratory environment. It showed good performance for defectdetection, size estimation and localization in complex aircraft wing structures.
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