Monitoring of a Full-Scale Wing Fatigue Test

Jaap Heida, Joong Sun Hwang

Research output: Chapter in Book/Report/Conference proceedingConference contributionAcademic

2 Citations (Scopus)
28 Downloads (Pure)


A wing of a decommissioned aircraft of the Royal Netherlands Air Force (RNLAF) was fatigue tested to more than two times the design life. Part of the test was the evaluation of load monitoring and Structural Health Monitoring (SHM) techniques. For load monitoring the data of conventional resistance strain gauges was compared with the response of optical Fibre Bragg Gratings (FBG). For SHM the Acoustic Emission (AE) and Comparative Vacuum Monitoring (CVM) techniques were employed to monitor fatigue crack initiation and growth. With the optical fibres a linear correlation between the FBG’s and the conventional strain gauges was obtained using a specific strain transfer factor. The SHM techniques, on the other hand, were less successful. For the CVM technique no cracks occurred at the locations under periodic monitoring (but also no false calls occurred during the complete test). Further, the AE system under continuous monitoring registered a lot of AE activity from different sources (also after drastic filtering of the AE data) but the AE data could not be reliably related to the initiation and growth of fatigue cracks in the areas monitored. Most of the AE activity was probably caused by mechanically induced noise such as frictional noise from the fastener locations and other surface rubbing areas.
Original languageEnglish
Title of host publication7th European Workshop on Structural Health Monitoring
Place of PublicationNantes, France
Publication statusPublished - 8 Jul 2014
Event7th European Workshop on Structural Health Monitoring, EWSHM 2014 - Nantes, France
Duration: 8 Jul 201411 Aug 2014
Conference number: 7

Publication series



Conference7th European Workshop on Structural Health Monitoring, EWSHM 2014
Abbreviated titleEWSHM


  • METIS-304488
  • IR-91441


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