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Acoustic Emission Structure-Borne Noise Measurements on Aircraft During Flight

  • C. M. Breevoort
  • C. D. Bailey
  • W. M. Pless
Part of the Acoustical Imaging book series (ACIM, volume 14)

Abstract

The assurance of structural integrity is a major requirement of service-life maintenance procedures for large commercial and military aircraft. This generates requirements for reliable and cost effective techniques for detecting small fatigue cracks and for following their growth. Research conducted at Lockheed-Georgia and elsewhere demonstrates that the acoustic emission from a fatigue crack can be detected in a noisy environment. This paper summarizes the results of acoustic emission work performed on-board an aircraft. The characteristics of the acoustic emission signal as the crack progresses from crack initiation and the on-board system requirements will be presented.

Keywords

Fatigue Crack Acoustic Emission Acoustic Emission Signal Flight Test Landing Gear 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. [1]
    Bailey, C. D. and Pless, W. M., “Acoustic Emission Used to Nondestructively Determine Crack Locations in Aircraft Structural Fatigue Specimens”, Proceedings of 9th Symposium on Nondestructive Evaluation, April 1973, p.224f. Also, IDEP no. 556.45-FH-n1.Google Scholar
  2. [2]
    Bell, R. L., “Acoustic Emission Transducer Calibration-Transient Pulse Method”, Technical Report DE-73-2, Dunegan/Endevco, San Juan Capistrano, California, Feb. 1973.Google Scholar

Copyright information

© Plenum Press, New York 1985

Authors and Affiliations

  • C. M. Breevoort
    • 1
  • C. D. Bailey
    • 1
  • W. M. Pless
    • 1
  1. 1.Lockheed-Georgia CompanyMariettaUSA

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