Axisymmetric stress distribution in a transversely isotropic thick plate with a circular hole

1977 ◽  
Vol 28 (1-4) ◽  
pp. 65-76 ◽  
Author(s):  
K. Chandrashekhara ◽  
S. K. Muthanna
Keyword(s):  
Stress Distribution ◽  
Circular Hole ◽  
Thick Plate ◽  
Transversely Isotropic ◽  
Axisymmetric Stress

scholarly journals Approximate Biaxial Stress Solution for Orthotropic Open-Hole Composite Laminates

1996 ◽  
Vol 5 (4) ◽  
pp. 096369359600500
Author(s):  
C. Filiou ◽  
C. Soutis
Keyword(s):  
Approximate Solution ◽  
Stress Distribution ◽  
Circular Hole ◽  
Composite Laminates ◽  
Composite Laminate ◽  
Biaxial Loading ◽  
Biaxial Stress ◽  
Orthotropic Composite ◽  
Open Hole ◽  
Simple Approximate Solution

A simple approximate solution has been derived for the stress distribution near a circular hole applicable to any orthotropic composite laminate subjected to biaxial loading. The degree of accuracy of this solution was found to be overall acceptable, but strongly dependent upon the laminate lay-up and biaxiality ratio.

The Fatigue Crack and Delamination Behavior on the Fuselage-Wing Intersection Containing Variable Notches

2003 ◽  
Vol 17 (08n09) ◽  
pp. 1540-1546 ◽  
Author(s):  
Sam Hong Song ◽  
Cheol Woong Kim
Keyword(s):  
Fatigue Crack ◽  
Stress Distribution ◽  
Crack Propagation ◽  
Circular Hole ◽  
Fatigue Crack Propagation ◽  
Aluminum Layer ◽  
Fiber Layer ◽  
Stress Criterion ◽  
Fatigue Crack Propagation Behavior ◽  
Propagation Behavior

The delamination and the fatigue crack propagation behavior in aramid fiber reinforced metal laminates(AFRMLs) containing a saw-cut and circular hole such as the fuselage-wing intersection was investigated. The fatigue crack propagation in aluminum layer is accompanied with the delamination between aluminum layer and fiber layer. The delamination deteriorates the fiber bridging mechanism in the crack tip of AFRMLs. Therefore, this study evaluates the stress distribution of AFRMLs containing a saw-cut and circular hole using the Average Stress Criterion (ASC) model. The delamination zone was observed by ultrasonic C-scan images. As the result of this study, in case of AFRMLs containing a saw-cut specimen. the fatigue crack propagation always occurred in aluminum layer and the delamination zone formed along the fatigue crack. However, in case of AFRMLs containing a circular hole specimen, the delamination zone was formed in two types. First, delamination zone was formed along the fatigue crack in aluminum layer. Second, delamination zone was formed without any fatigue crack around the circular hole. Consequently, delamination zone was formed dependently on the notch shape and the stress distribution.

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