Modeling fatigue crack growth for a through thickness crack: An out-of-plane constraint-based approach considering thickness effect

2020 ◽  
Vol 178 ◽  
pp. 105625 ◽  
Author(s):  
He Liu ◽  
Xiaoguang Yang ◽  
Shaolin Li ◽  
Duoqi Shi ◽  
Hongyu Qi
Keyword(s):  
Fatigue Crack ◽  
Fatigue Crack Growth ◽  
Crack Growth ◽  
Thickness Effect ◽  
Out Of Plane

Reliability Assessment on Thickness Effect in Fatigue Crack Growth

2005 ◽  
Vol 297-300 ◽  
pp. 1913-1918
Author(s):  
Seon Jin Kim ◽  
Yu Sik Kong ◽  
Sang Woo Kwon
Keyword(s):  
Fatigue Crack ◽  
Fatigue Crack Growth ◽  
Crack Growth ◽  
Random Fields ◽  
Crack Surface ◽  
Simulation Method ◽  
Thickness Effect ◽  
Specimen Thickness ◽  
Fatigue Crack Growth Life ◽  
Non Gaussian

The evaluation of specimen thickness effect of fatigue crack growth life by the simulation of probabilistic fatigue crack growth is presented. In this paper, the material resistance to fatigue crack growth is treated as a spatial stochastic process, which varies randomly on the crack surface. Using the previous experimental data, the non-Gaussian (eventually Weibull, in this report) random fields simulation method is applied. This method is useful to estimate the probability distribution of fatigue crack growth life and the variability due to specimen thickness by simulating material resistance to fatigue crack growth along a crack path.

On the Characterization of Fatigue Crack Growth in a Plate With a Single-Sided Repair

2004 ◽  
Vol 126 (2) ◽  
pp. 192-198 ◽  
Author(s):  
C. N. Duong ◽  
C. H. Wang
Keyword(s):  
Fatigue Crack ◽  
Stress Intensity ◽  
Fatigue Crack Growth ◽  
Crack Growth ◽  
Stress Intensity Factors ◽  
Load Path ◽  
Intensity Factors ◽  
Analytical Work ◽  
Out Of Plane ◽  
Plane Bending

An unsupported cracked plate repaired with a reinforcement bonded on one side may experience considerable out-of-plane bending due to the load-path eccentricity. This out-of-plane bending causes the stress intensity factor at the crack tip to vary significantly through the plate’s thickness with a maximum value attained at the un-patched side of the crack. Even though significant analytical work has been done in the past to evaluate these thickness-varying stress intensity factors, however, to the authors’ knowledge, little work has been done to characterize the fatigue crack growth in a plate with a single-sided repair. The purposes of the present work are to (i) assess the accuracy of the available analytical methods for predicting the stress intensity factors of the panels with a single-sided repair and more importantly, and (ii) characterize the fatigue crack growth in these panels, using test results generated recently under the Composite Repair of Aircraft Structures (CRAS) program.

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