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| Title: |
Crack Turning and Arrest Mechanisms for Integral Structure
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| Author(s): |
Pettit, Richard; Ingraffea, Anthony
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| Abstract: |
In the course of several years of research efforts to predict crack turning and flapping in aircraft fuselage structures and other problems related to crack turning, the 2nd order maximum tangential stress theory has been identified as the theory most capable of predicting the observed test results. This theory requires knowledge of a material specific characteristic length, and also a computation of the stress intensity factors and the T-stress, or second order term in the asymptotic stress field in the vicinity of the crack tip. A characteristic length, r(sub c), is proposed for ductile materials pertaining to the onset of plastic instability, as opposed to the void spacing theories espoused by previous investigators. For the plane stress case, an approximate estimate of r(sub c), is obtained from the asymptotic field for strain hardening materials given by Hutchinson, Rice and Rosengren (HRR). A previous study using of high order finite element methods to calculate T-stresses by contour integrals resulted in extremely high accuracy values obtained for selected test specimen geometries, and a theoretical error estimation parameter was defined. In the present study, it is shown that a large portion of the error in finite element computations of both K and T are systematic, and can be corrected after the initial solution if the finite element implementation utilizes a similar crack tip discretization scheme for all problems. This scheme is applied for two-dimensional problems to a both a p-version finite element code, showing that sufficiently accurate values of both K(sub I) and T can be obtained with fairly low order elements if correction is used. T-stress correction coefficients are also developed for the singular crack tip rosette utilized in the adaptive mesh finite element code FRANC2D, and shown to reduce the error in the computed T-stress significantly. Stress intensity factor correction was not attempted for FRANC2D because it employs a highly accurate quarter-point scheme to obtain stress intensity factors.
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| NASA Center: |
Langley Research Center
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| Publication Date: |
Dec. 31, 1999
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| Document Source: |
CASI |
| Online Source: |
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| Document ID: |
20000058169
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| Publication Information: |
Number of Pages = 44 |
| Report Number: |
OSP-34049
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| Contract-Grant-Task Number: |
NAG1-2013 |
| Price Code: |
A03 |
| Keywords: |
STRESS DISTRIBUTION; CRACK ARREST; CRACKS; AIRCRAFT STRUCTURES; STRAIN HARDENING; SHEAR STRESS; FINITE ELEMENT METHOD; FUSELAGES; HARDENING (MATERIALS); ERROR ANALYSIS; DUCTILITY;
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| Accessibility: |
Unclassified; No Copyright; Unlimited; Publicly available; |
| Updated/Added to NTRS: |
2008-06-02 |
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