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Evaluation of Fiber Reinforced Aircraft Composites via Nondestructive Testing Techniques

[+] Author Affiliations
R. Asmatulu, V. Movva

Wichita State University, Wichita, KS

Paper No. IMECE2012-93466, pp. 257-265; 9 pages
doi:10.1115/IMECE2012-93466
From:
  • ASME 2012 International Mechanical Engineering Congress and Exposition
  • Volume 1: Advances in Aerospace Technology
  • Houston, Texas, USA, November 9–15, 2012
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4517-2
  • Copyright © 2012 by ASME

abstract

Nondestructive testing (NDT) techniques, such as ultrasonic C-scan and A-scan, time delay tap hammer and visual inspection were employed for advanced aircraft composite panels using standard procedures to achieve maximum possible error free data of voids, fiber volume, fiber wash, inter laminar and trans laminar cracks, miss-oriented fibers, lay-up orders and latent (or hidden) defects. The composite panels with different porosity levels (e.g., 0–2%, 3–6% and greater than 7%) were selected and examined in detail. Data obtained from C-scan images, attenuation (dB loss), time delay, fiber volume and void content was compared each other to determine the accuracy of the experimental results. Optimization of the parameters was conducted using design of experiments. Each technique was also used on a standard reference composite panel to establish the system parameters. We determined that each technique has some degree of variations on porosity and defects of the composites, which may be because of the operating skill, composite types, initial preparation, lack of standardized testing pattern and testing time. This also brings reliability and uncertainty issues for the NDT techniques on the composite panels.

Copyright © 2012 by ASME

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