Acoustic emission analysis of full-scale honeycomb sandwich composite curved fuselage panels

Frank A. Leone Jr.; Didem Ozevin; Valery Godinez; Bao Mosinyi; John G. Bakuckas Jr.; Jonathan Awerbuch; Alan Lau; Tein-Min Tan

doi:10.1117/12.776146

28 April 2008 Acoustic emission analysis of full-scale honeycomb sandwich composite curved fuselage panels

Frank A. Leone Jr., Didem Ozevin, Valery Godinez, 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; 69340E (2008) https://doi.org/10.1117/12.776146
Event: SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring, 2008, San Diego, California, United States

Abstract

Acoustic emission (AE) was monitored in notched full-scale honeycomb sandwich composite curved fuselage panels during loading. The purpose of the study was to evaluate the AE technique as a tool for detecting notch tip damage initiation and evaluating damage severity in such structures. This evaluation was a part of a more general study on the damage tolerance of six honeycomb sandwich composite curved panels, each containing a different damage scenario. The overall program objective was to investigate the effects of holes and notches on residual strength. The investigation was conducted using the Full-Scale Aircraft Structural Test Evaluation and Research (FASTER) facility located at the Federal Aviation Administration William J. Hughes Technical Center, Atlantic City International Airport, NJ. This paper reports on the AE results recorded during the loading to failure of two selected panels. The results show that damage initiation at the tips of the notches, and its progression along the panel, could be detected and located. These AE results were correlated with the deformation and strain fields measured through strain photogrammetry, throughout loading, at the vicinity of these notches. This correlation aided in interpreting the AE results. While the fretting among the newly created fracture surfaces generated a large number of low-intensity AE signals, the high-intensity signals generated at high load levels provided a good measure for anticipating incipient fracture. Further, the AE results located internal disbonding caused during panel fabrication. The large number of low-intensity AE signals generated from the disbonded regions was associated with the fretting among the disbonded surfaces.

Citation Download Citation

Frank A. Leone Jr., Didem Ozevin, Valery Godinez, Bao Mosinyi, John G. Bakuckas Jr., Jonathan Awerbuch, Alan Lau, and Tein-Min Tan "Acoustic emission analysis of full-scale honeycomb sandwich composite curved fuselage panels", Proc. SPIE 6934, Nondestructive Characterization for Composite Materials, Aerospace Engineering, Civil Infrastructure, and Homeland Security 2008, 69340E (28 April 2008); https://doi.org/10.1117/12.776146

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