HEALTH MONITORING OF AIRCRAFT FUSELAGE STRUCTURES USING ULTRASONIC WAVES

摘要

A series of numerical and experimental investigations were conducted into the use of acousto-ultrasonic stress waves for the detection of defects in a typical aluminium (Al) aircraft fuselage structure. This structure consists of a skin, stringer and frame. PZT actuator/sensor pairs placed on the stringer were able to detect stringer cracks but not frame cracks. Actuators on the stringer and sensors on the frame were able to detect both stringer and frame cracks however the signal intensity was very low.