scholarly journals Monitoring of fatigue crack growth in composite adhesively bonded joints using Fiber Bragg Gratings

2011 ◽  
Vol 10 ◽  
pp. 207-212 ◽  
Author(s):  
Andrea Bernasconi ◽  
Michele Carboni ◽  
Lorenzo Comolli
Keyword(s):  
Fatigue Crack ◽  
Fatigue Crack Growth ◽  
Crack Growth ◽  
Fiber Bragg Gratings ◽  
Bragg Gratings ◽  
Bonded Joints ◽  
Adhesively Bonded ◽  
Adhesively Bonded Joints

Fatigue crack growth monitoring at elevated temperatures using multiplexed Fiber Bragg Gratings

2009 ◽  
Author(s):  
Richard J. Black ◽  
David J. Zare ◽  
Levy Oblea ◽  
Behzad M. Moslehi ◽  
Shamachary Sathish ◽  
...  
Keyword(s):  
Fatigue Crack ◽  
Fatigue Crack Growth ◽  
Crack Growth ◽  
Elevated Temperatures ◽  
Fiber Bragg Gratings ◽  
Bragg Gratings ◽  
Growth Monitoring

scholarly journals Requirements and Variability Affecting the Durability of Bonded Joints

Materials ◽  
2020 ◽  
Vol 13 (6) ◽  
pp. 1468 ◽  
Author(s):  
Rhys Jones ◽  
Daren Peng ◽  
John G. Michopoulos ◽  
Anthony J. Kinloch
Keyword(s):  
Fatigue Crack ◽  
Fatigue Crack Growth ◽  
Crack Growth ◽  
Upper Bound ◽  
The United States ◽  
Fatigue Threshold ◽  
Growth Equation ◽  
Bonded Joints ◽  
Cohesive Failure ◽  
Structural Adhesives

This paper firstly reveals that when assessing if a bonded joint meets the certification requirements inherent in MIL-STD-1530D and the US Joint Services Standard JSSG2006 it is necessary to ensure that: (a) There is no yielding at all in the adhesive layer at 115% of design limit load (DLL), and (b) that the joint must be able to withstand design ultimate load (DUL). Secondly, it is revealed that fatigue crack growth in both nano-reinforced epoxies, and structural adhesives can be captured using the Hartman–Schijve crack growth equation, and that the scatter in crack growth in adhesives can be modelled by allowing for variability in the fatigue threshold. Thirdly, a methodology was established for estimating a valid upper-bound curve, for cohesive failure in the adhesive, which encompasses all the experimental data and provides a conservative fatigue crack growth curve. Finally, it is shown that this upper-bound curve can be used to (a) compare and characterise structural adhesives, (b) determine/assess a “no growth” design (if required), (c) assess if a disbond in an in-service aircraft will grow and (d) to design and life in-service adhesively-bonded joints in accordance with the slow-growth approach contained in the United States Air Force (USAF) certification standard MIL-STD-1530D.

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