scholarly journals Structural health monitoring of adhesively bonded composite joints

2012 ◽  
Author(s):  
Fady Habib
Keyword(s):  
Structural Health Monitoring ◽  
Health Monitoring ◽  
Composite Joints ◽  
Adhesively Bonded ◽  
Structural Health ◽  
Bonded Composite

A review of structural health monitoring of bonded structures using electromechanical impedance spectroscopy

2021 ◽  
pp. 147592172199341
Author(s):  
A Francisco G Tenreiro ◽  
António M Lopes ◽  
Lucas FM da Silva
Keyword(s):  
Structural Health Monitoring ◽  
Impedance Spectroscopy ◽  
Health Monitoring ◽  
Mechanical Impedance ◽  
Local Area ◽  
Electric Response ◽  
Adhesively Bonded ◽  
Adhesively Bonded Joints ◽  
Electromechanical Impedance ◽  
Structural Health

The article presents a literature review of electromechanical impedance spectroscopy for structural health monitoring, with emphasis in adhesively bonded joints. The concept behind electromechanical impedance spectroscopy is to use variable high-frequency structural vibrations with piezoelectric elements to monitor the local area of a structure for changes in mechanical impedance that may indicate imminent damage. Various mathematical models that correlate the structural impedance with the electric response of the piezoelectric sensors are presented. Several algorithms and metrics are introduced to detect, localize, and characterize damage when using electromechanical impedance spectroscopy. Applications of electromechanical impedance spectroscopy to study adhesive joints are described. Research and development of alternative hardware for electromechanical impedance spectroscopy is presented. The article ends by presenting future prospects and research of electromechanical impedance spectroscopy–based structural health monitoring, and, while advances have been made in algorithms for damage detection, localization, and characterization, this technology is not mature enough for real-world applications.

Structural health monitoring of an adhesively bonded CFRP aircraft fuselage by ultrasonic Lamb Waves

2020 ◽  
Vol 234 (13) ◽  
pp. 2000-2010
Author(s):  
J Weiland ◽  
DF Hesser ◽  
W Xiong ◽  
A Schiebahn ◽  
B Markert ◽  
...  
Keyword(s):  
Structural Health Monitoring ◽  
Health Monitoring ◽  
Adhesive Bonding ◽  
Lamb Waves ◽  
Reconstruction Algorithm ◽  
Aviation Industry ◽  
Adhesively Bonded ◽  
Structural Health ◽  
Aircraft Fuselage ◽  
Future Work

The aviation industry faces the challenge of offering aircraft that are lighter, more economical, and safer. One of the solutions is to increase the use of composites. For these materials, adhesive bonding has proven to be the appropriate joining technology. To check these adhesive joints, costly and time-consuming maintenance measures are carried out. An intelligent Structural Health Monitoring (SHM) system can extend these intervals and allow the use of a predictive maintenance system. This paper describes the method of Ultrasonic Lamb Waves for monitoring a adhesively bonded Carbon Fiber Reinforced Polymer (CFRP) aircraft fuselage. Prior to this, the production of a segment of a fuselage and the characterization of the materials (CFRP and adhesive) is shown. Afterwards the method of Ultrasonic Lamb Waves with the use of piezoelectric transducers and signal processing based on the Reconstruction Algorithm for Probabilistic Inspection of Damage (RAPID) algorithm are explained. At the end, the experimental evaluation of an undamaged and a damaged fuselage structure is done. The results have shown the possibility of RAPID algorithm for damage detection on adhesive. An outlook on future work is given.

scholarly journals Structural Health Monitoring of Bonded Composite Joints Using Embedded Chirped Fibre Bragg Gratings

2005 ◽  
Vol 14 (6) ◽  
pp. 096369350501400 ◽  
Author(s):  
J Palaniappan ◽  
H Wang ◽  
S L Ogin ◽  
A Thorne ◽  
G T Reed ◽  
...  
Keyword(s):  
Structural Health Monitoring ◽  
Health Monitoring ◽  
Bragg Gratings ◽  
Composite Joints ◽  
Bonded Joints ◽  
Load Redistribution ◽  
Gfrp Composite ◽  
Bonded Composite ◽  
Fibre Bragg Gratings ◽  
The Relationship

Chirped fibre Bragg gratings (CFBGs) have been used to monitor disbond initiation and disbond growth in composite bonded joints. The CFBGs have been embedded within, but near the surface of, a transparent GFRP composite adherend that has been bonded to a second transparent adherend. The low wavelength end of the CFBGs has been arranged to be adjacent to the end of the first adherend. Disbond initiation is readily detected as a modification to the reflected spectrum of the CFBG, consisting of the low wavelength part of the reflected spectrum being shifted to lower wavelengths; this is due to the unloading of the adherend resulting from the disbond. Disbond growth is detected by the movement of a dip in the reflected spectrum of the CFBG (as a consequence of the load redistribution at the disbond front); this dip moves to higher wavelengths as the disbond propagates. The relationship between the shift of the dip in the reflected spectrum with the position of the disbond front has been determined directly through the use of transparent GFRP joints.

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