Aircraft designers, manufacturers and operators face many challenges related to maintenance in the near future. Existing ageing aircraft structures already require a significant maintenance effort. The application of new materials and wider use of damage-tolerant concepts in new aircraft will also require reliable damage monitoring for quality control, with regular periodic inspections to maintain the safe life. Over recent years, a number of new technologies have evolved with the potential for health monitoring of aerospace structures. Lamb wave inspection is the most widely used damage detection technique based on guided ultrasonic waves, i.e. ultrasonic waves propagating in bounded media. The majority of current signal processing techniques used for the analysis of Lamb wave responses rely on amplitudes and/or mode conversion. The paper explores the correlation characteristics of Lamb waves at progressing damage stages. Signal parameters used for damage detection are applied to Lamb wave data obtained from an aerospace riveted panel to detect fatigue cracks. The results demonstrate good sensitivity of the method to small fatigue cracks.


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    Title :

    Fatigue crack detection in aircraft riveted panels using frequency/phase analysis of Lamb waves


    Contributors:
    Stolze, F. (author) / Staszewski, W.J. (author) / Manson, G. (author) / Worden, K. (author)


    Publication date :

    2008


    Size :

    10 Seiten, 11 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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