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Detecting damage in full-scale honeycomb sandwich composite curved fuselage panels through frequency response
Conference proceeding

Detecting damage in full-scale honeycomb sandwich composite curved fuselage panels through frequency response

Frank A Leone, Jr, Didem Ozevin, Bao Mosinyi, John G Bakuckas, Jr, Jonathan Awerbuch, Alan Lau and Tein-Min Tan
Proceedings of SPIE, v 6934(1), pp 693405-6934010
27 Mar 2008

Abstract

Preliminary tests were conducted using frequency response (FR) characteristics to determine damage initiation and growth in a honeycomb sandwich graphite/epoxy curved panel. This investigation was part of a more general study investigating the damage tolerance characteristics of several such panels subjected to quasi-static internal pressurization combined with hoop and axial loading. The panels were tested at the Full-Scale Aircraft Structural Test Evaluation and Research (FASTER) facility located at the Federal Aviation Administration William J. Hughes Technical Center in Atlantic City, NJ. The overall program objective was to investigate the damage tolerance characteristics of full-scale composite curved aircraft fuselage panels and the evolution of damage under quasi-static loading up to failure. This paper focuses on one aspect of this comprehensive investigation: the effect of state-of-damage on the characteristics of the frequency response of the subject material. The results presented herein show that recording the frequency response could be used for real-time monitoring of damage growth and in determining damage severity in full-scale composites fuselage aircraft structures.

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Web of Science research areas
Acoustics
Engineering, Civil
Engineering, Environmental
Materials Science, Characterization & Testing
Materials Science, Multidisciplinary
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