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; Tein-Min Tan

doi:10.1117/12.776166

28 April 2008 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, Tein-Min Tan

Author Affiliations +

Proceedings Volume 6934, Nondestructive Characterization for Composite Materials, Aerospace Engineering, Civil Infrastructure, and Homeland Security 2008; 693405 (2008) https://doi.org/10.1117/12.776166
Event: SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring, 2008, San Diego, California, United States

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.

Citation Download Citation

Frank A. Leone Jr., Didem Ozevin, Bao Mosinyi, John G. Bakuckas Jr., Jonathan Awerbuch, Alan Lau, and Tein-Min Tan "Detecting damage in full-scale honeycomb sandwich composite curved fuselage panels through frequency response", Proc. SPIE 6934, Nondestructive Characterization for Composite Materials, Aerospace Engineering, Civil Infrastructure, and Homeland Security 2008, 693405 (28 April 2008); https://doi.org/10.1117/12.776166

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