Residual strength prediction for aircraft panels with Multiple Site Damage, using the ?EPFEAM? for stable crack growth analysis

1995 ◽  
Vol 16 (3) ◽  
pp. 190-196 ◽  
Author(s):  
C. R. Pyo ◽  
H. Okada ◽  
S. N. Atluri
Keyword(s):  
Crack Growth ◽  
Residual Strength ◽  
Growth Analysis ◽  
Stable Crack Growth ◽  
Strength Prediction ◽  
Multiple Site ◽  
Multiple Site Damage ◽  
Aircraft Panels

Residual strength of aircraft panels with multiple site damage

1994 ◽  
Vol 13 (4) ◽  
pp. 285-294 ◽  
Author(s):  
Pin Tong ◽  
Robert Greif ◽  
Li Chen
Keyword(s):  
Residual Strength ◽  
Multiple Site ◽  
Multiple Site Damage ◽  
Aircraft Panels

Modified Swift Criteria for Residual Strength of Multiple Site Damage Structure

2009 ◽  
Vol 417-418 ◽  
pp. 881-884 ◽  
Author(s):  
Jian Yu Zhang ◽  
Rui Bao ◽  
Bin Jun Fei
Keyword(s):  
Residual Strength ◽  
Yield Criterion ◽  
Fatigue Cracks ◽  
Tensile Load ◽  
Maximum Load ◽  
Alloy Sheet ◽  
Multiple Cracks ◽  
Multiple Site ◽  
Multiple Site Damage ◽  
Aluminum Panels

As more aircrafts reach or exceed their design life, it is becoming very important to research multiple cracks damage, especially the multiple site damage (MSD) in order to re-evaluate their service life and damage tolerance/durability performance. The existing of MSD may remarkably reduce the residual strength of an aerospace structural component than those with a singe lead crack. This study investigated the residual strength of aluminum alloy sheet with MSD through three types of aluminum specimens test. Aluminum panels with bare collinear constant diameter holes were chosen as specimens. After some constant amplitude tension-tension load cycles, the MSD were found in these specimens since there were multiple fatigue cracks emanating from the saw cuts of holes. The residual strength was recorded as the maximum load when every specimen was subjected to monotonically increasing tensile load until failure occurred. In different failure prediction criteria that were often used in engineering in order to evaluate the accuracy of these criteria, Swift criterion (ligament yield) criterion got more accurate prediction results than other criteria. Although Swift criterion was more accurate than some other criteria, its error was still big for some specimens. Two modified approaches were proposed in order to get more accurate and appropriate failure criterion for MSD structure.

scholarly journals Residual Strength Prediction of Aluminum Panels with Multiple Site Damage Using Artificial Neural Networks

Materials ◽  
2020 ◽  
Vol 13 (22) ◽  
pp. 5216 ◽  
Author(s):  
Ala Hijazi ◽  
Sameer Al-Dahidi ◽  
Safwan Altarazi
Keyword(s):  
Neural Networks ◽  
Artificial Neural Networks ◽  
Residual Strength ◽  
Lap Joints ◽  
Multiple Site ◽  
Ann Model ◽  
Model Predictions ◽  
Multiple Site Damage ◽  
Artificial Neural ◽  
Aluminum Panels

Multiple site damage (MSD) cracks are small fatigue cracks that may accumulate at the sides of highly loaded holes in aging aircraft structures. The presence of MSD cracks can drastically reduce the residual strength of fuselage panels. In this paper, artificial neural networks (ANN) modeling is used for predicting the residual strength of aluminum panels with MSD cracks. Experimental data that include 147 unique configurations of aluminum panels with MSD cracks are used. The experimental dataset includes three different aluminum alloys (2024-T3, 2524-T3, and 7075-T6), four different test panel configurations (unstiffened, stiffened, stiffened with a broken middle stiffener, and bolted lap-joints), many different panel widths and thicknesses, and the sizes of the lead and MSD cracks. The results presented in this paper demonstrate that a single ANN model can predict the residual strength for all materials and configurations with high accuracy. Specifically, the overall mean absolute error for the ANN model predictions is 3.82%. Furthermore, the ANN model residual strength predictions are compared to those obtained using the most accurate semi-analytical and computational approaches from the literature. The ANN model predictions are found to be at the same accuracy level of these approaches, and they even outperform the other approaches for many configurations.

Residual strength of aging aircraft with multiple site damage/multiple element damage

AIAA Journal ◽  
1998 ◽  
Vol 36 ◽  
pp. 840-847
Author(s):  
L. Wang ◽  
W. T. Chow ◽  
H. Kawai ◽  
S. N. Atluri
Keyword(s):  
Residual Strength ◽  
Multiple Site ◽  
Aging Aircraft ◽  
Multiple Site Damage
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