Health monitoring of aircraft fuselage structures using ultrasonic waves

Z. Q. Zhou, W. K. Chiu, M. K. Bannister

Research output: Chapter in Book/Report/Conference proceedingConference PaperResearchpeer-review

3 Citations (Scopus)


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.

Original languageEnglish
Title of host publicationICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006
Number of pages8
Publication statusPublished - 1 Dec 2006
EventCongress of the International Council of Aeronautical Sciences 2006 - Hamburg, Germany
Duration: 3 Sep 20068 Sep 2006
Conference number: 25th


ConferenceCongress of the International Council of Aeronautical Sciences 2006
Abbreviated titleICAS 2006

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