The development of mode I, linear-elastic stress intensity factor solutions for cracks in mechanically fastened joints

Ball, Dale L.

doi:10.1016/0013-7944(87)90157-3

Cited by 20 publications

(15 citation statements)

References 10 publications

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“…3 and listed in Table 2. A theoretical result determined by the authors using the method of superposition of Ball [4] is also plotted. The stress intensity factor for a single edge crack at a hole is calculated from: …”

Section: Tensile Plate With a Free Holementioning

confidence: 99%

Stress Intensity Factors for Cracks at Fastener Holes

Nurse

O'BRmN

Patterson

1994

Fatigue Fract Eng Mat Struct

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Transmission and reflection photoelasticity has been used to determine the stress intensity factors for artificial cracks emanating from a hole in two-dimensional tensile plates. Three geometries were investigated, namely a free hole, a pin-loaded hole and a hole with an interference-fit pin. All these cases relate to situations commonly found in aircraft structures. The results have been compared where possible with analytical data and a good correlation was found for these cases.

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Section: Tensile Plate With a Free Holementioning

confidence: 99%

Stress Intensity Factors for Cracks at Fastener Holes

Nurse

O'BRmN

Patterson

1994

Fatigue Fract Eng Mat Struct

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“…This has been predicted by the finite element method in [8] and superposition of fundamental solutions in [10].Guidance from AFRL was to set a geometry factor intercept at the free edge to a very large value; a procedure used for other AFGROW geometry factor solutions. This guidance was taken into account when curve-fitting the StressCheck® solution as detailed below.…”

Section: Afgrow Implementationmentioning

confidence: 99%

“…Experimental geometry factors were modified using a correction factor based on a solution proposed by Ball [10]. The Ball solution was derived using the superposition method to determine the geometry factor for a point-loaded lug with either a single or double asymmetric through-crack.…”

Section: Accounting For Fretting Cracksmentioning

confidence: 99%

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Experimental Validation Of Stress Intensity Factor Solutions For The Pin Loaded Lug

Child¹,

Moyle²,

Grandt

2009

ICAF 2009, Bridging the Gap Between Theory and Operational Practice

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Predicting crack growth behaviour is an important element of managing the structural integrity of aircraft fleets. It is common for fleet managers to employ software packages, such as AFGROW, to automate the prediction of crack growth behaviour. Stress intensity factor solutions employed in these software packages must be appropriately verified in order for results to be utilised in structural integrity management. Two independent research programs were conducted at Purdue University to review stress intensity factor solutions for cracked, pin-loaded lugs. The purpose of the research was to experimentally validate stress intensity factor solutions derived from representative StressCheck® Finite Element Models (FEMs). Component fatigue tests were conducted on corner and through cracked, pin loaded aluminium lugs and non-dimensional stress intensity factor (geometry factor) solutions calculated utilising a backtracking method. For the through crack configuration, experimental and StressCheck® geometry factors closely correlated and were an improvement to the solutions provided in AFGROW at the time. Based on the results of this research, StressCheck® pin-loaded lug geometry factors have since been incorporated into the AFGROW software. In the case of the corner crack configuration, the correlation between experimental and StressCheck® results was dependant on the choice of pin-M. Bos (ed.), ICAF 2009, Bridging the Gap between Theory and Operational Practice, 871-898.

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“…Stress intensity factors for a pair of symmetric cracks at the edge of a fastener hole in an infinite isotropic strip were obtained by Cartwright and Ratcliffe [6]. Compounding individual solutions for various loading conditions, Ball [7] obtained the mode I stress intensity factors for isotropic finite-width plates, lugs, and multi-fastener joints. Using the principle of superposition, Grandt and Kullgren [8-101 transformed the problem to that of an edge crack with crack face pressure equal to the unflawed hoop stress surrounding the fastener.…”

Section: Introductionmentioning

confidence: 99%

Fracture Analysis for a Frictional Fastener Hole with Edge Cracks in an Anisotropic Plate∗

Kamel¹,

Liaw

1995

Mechanics of Structures and Machines

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Stress intensity factors are eva1uate:d for a singly or doubly cracked fastener hole with frictional traction in an anisotropic plate, using a special kernel boundary integral equation (BIE) approach. The integration kernel (Green's function) used in this BIE approach has already taken the presence of the crack (or cracks) into account, thus.avoiding the need for element discretization to model the stress singularity at the crack tip. The Green's function employed is that of an infinite anisotropic plate containing an elliptical hole or crack, and subjected to an arbitrarily positioned point force. Several types of normal and shear traction conditions at the pinhole interface are considered. Numerical results are obtained for var-'Communicated by C. A . Mota Soares 377

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The development of mode I, linear-elastic stress intensity factor solutions for cracks in mechanically fastened joints

Cited by 20 publications

References 10 publications

Stress Intensity Factors for Cracks at Fastener Holes

Stress Intensity Factors for Cracks at Fastener Holes

Experimental Validation Of Stress Intensity Factor Solutions For The Pin Loaded Lug

Fracture Analysis for a Frictional Fastener Hole with Edge Cracks in an Anisotropic Plate∗

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