Accurate stress intensity factor solutions for corner cracks at a hole

Fawaz, Scott A.; Andersson, B.

doi:10.1016/s0013-7944(03)00207-8

Cited by 38 publications

(15 citation statements)

References 3 publications

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“…3 in the same form as presented in Ref. 5, where the parameter ܳ is the shape factor for an ellipse, defined as 11 It is seen that the model presented in this paper is in very good agreement with the Fawaz-Andersson model for the considered configuration. The current model is able to calculate the stress intensity factor along the entire crack front, including the peaks close to the free surfaces, and was able to determine the effect of the two considered r/W values.…”

Section: Comparison With Other Solutionssupporting

confidence: 59%

“…For instance, the developed model was validated in part with results from Fawaz and Andersson (F-A), which have themselves been compared with results from a previous Round-Robin study problem of symmetric corner cracks at a hole. 5 The Round-Robin study included results from seven different calculation methods and analysis software. 11 To model symmetric cracks, half of the current model was deleted and symmetry boundary conditions were applied to the created face.…”

Section: Comparison With Other Solutionsmentioning

confidence: 99%

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Improved Stress Intensity Factor Solutions for Surface and Corner Cracks at a Hole

Renaud¹,

Liu²,

Bombardier³

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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Detailed three-dimensional finite element (FE) modeling and analysis of quarter-elliptical and semi-elliptical cracks at a hole were carried out. Comparison cases showed that the accuracy of the classical Newman-Raju closed-form stress intensity factor solutions can be improved, especially for the surface crack case and in the thickness direction for the corner crack case. Using the developed FE models, improved stress intensity factor solutions for quarter-circular and semi-circular cracks at a hole were obtained for uniaxial tensile loading. A simple correction approach is also proposed to improve the accuracy of the Newman-Raju solutions for more general cases of quarter-elliptical and semi-elliptical cracks at a hole. Nomenclature a = crack depth (surface length in the hole bore in the thickness direction) c = crack length (in-plane direction) K = stress intensity factor K t = stress concentration factor L = plate length Q = ellipse shape factor r = hole radius t = plate thickness W = plate width β = geometric stress intensity correction factor β cc , β ca = β factor for a corner crack in the c and a direction β sc , β sa = β factor for a surface crack in the c and a direction β s0 , β c0 = limiting β factor for a short surface and a short corner crack φ = angle along crack front σ = applied remote tensile stress ν = Poisson's ratio

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Section: Comparison With Other Solutionssupporting
confidence: 59%

Section: Comparison With Other Solutionsmentioning
confidence: 99%

Improved Stress Intensity Factor Solutions for Surface and Corner Cracks at a Hole
Renaud¹,
Liu²,
Bombardier³
2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
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“…Solutions for two symmetrical CCs were modified by a conversion factor developed by Shah, 9 based on area reduction, to estimate the SIF for a single CC at the hole. More recently Fawaz and Andersson 10 have reported an extensive database of SIF solutions generated using an hp‐version FE method. All of these solutions are limited to remote loading conditions such as uniform tension, in‐plane bending or pin loading.…”

Section: Introductionmentioning
confidence: 99%

An efficient stress intensity factor solution scheme for corner cracks at holes under bivariant stressing
Lee
¹
,
McClung
²
,
Chell
³

2008
Fatigue Fract Eng Mat Struct
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16
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A B S T R A C T This paper summarizes the development of an efficient stress intensity factor (SIF) solution scheme applicable to a corner crack (CC) in a rectangular section subjected to arbitrary stressing on the crack plane. A general bivariant weight function (WF) formulation developed previously for a CC in a plate was extended to address a CC at a hole. Two supplemental algorithms were developed to achieve a substantial reduction in the computational time necessary for practical application. The new SIF solution scheme was validated by comparison with more than 180 three-dimensional (3D) boundary element (BE) solutions.

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“…12 with the results predicted by NASGRO and by AFGROW, 14 a public domain fracture mechanic software for Damage Tolerance analysis developed by the U.S. Air Force. This software contains a recent and accurate solution for the stress intensity factor of a corner crack in a pin‐loaded hole 15 . Results obtained show that a crack propagates very slowly compared with predictions, particularly in the thickness direction; AFGROW predicts better the surface dimension of the crack, but in any case the result is very conservative.…”

Section: Wing To Fuselage Connection Specimenmentioning
confidence: 99%

Fatigue crack propagation in the wing to fuselage connection of the new trainer aircraft M346
Lanciotti
¹
,
Nigro
²
,
Polese
³

2006
Fatigue Fract Eng Mat Struct
7
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3
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A B S T R A C T The series version of the M346 military trainer aircraft is currently under construction atAermacchi (Venegono Superiore, Italy). The design target life of the aircraft, which will be certified for Damage Tolerance, is 12 000 flight hours (FH), with the possible extension to 16 000 FH after specific inspections. Fatigue tests were performed on critical elements at the Department of Aerospace Engineering at University of Pisa in order to verify crack propagation calculations. The wing to fuselage connection is one of the most interesting elements from the fatigue point of view. Spars and frames, both integrally machined, are connected by two lug-fork joints; the base material is aluminium alloy 7050-T7451 for both the elements. High interference bushings, ForceMate ® , produced by FTI (Fatigue Technology Inc., Seattle, WA) were used in the lug/fork connections.Experimental activity was carried out on two different specimens. The first, a Compact Tension specimen, was tested under constant amplitude loading to verify the fatigue crack growth rate data contained in NASGRO 4, the software used for Damage Tolerance evaluations. Experimental results were fully comparable with the NASGRO 4 material database. Additional variable amplitude loading tests were carried out in order to calibrate crack growth prediction models used in the analyses.The second specimen was a lug-fork joint designed as the actual joints present on the aircraft. Both constant and variable amplitude loading fatigue tests were carried out in this case too. Results obtained clearly indicated the beneficial effect of ForceMate bushings, compared to shrink fit bushings.

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Accurate stress intensity factor solutions for corner cracks at a hole

Cited by 38 publications

References 3 publications

Improved Stress Intensity Factor Solutions for Surface and Corner Cracks at a Hole

Improved Stress Intensity Factor Solutions for Surface and Corner Cracks at a Hole

An efficient stress intensity factor solution scheme for corner cracks at holes under bivariant stressing

Fatigue crack propagation in the wing to fuselage connection of the new trainer aircraft M346

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