Equivalent Initial Flaw Size Testing and Analysis

Fawaz, Scott A.

doi:10.21236/ada387280

Cited by 15 publications

(20 citation statements)

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“…The two levels of bending were estimated from lap-joints with and without a bonded doubler [3,27,28].…”

Section: Curved Fuselage Test Panelsmentioning

confidence: 99%

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Fatigue and crack-growth analyses of riveted lap-joints in a retired aircraft

Newman

Ramakrishnan

2016

International Journal of Fatigue

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“…The two levels of bending were estimated from lap-joints with and without a bonded doubler [3,27,28].…”

Section: Curved Fuselage Test Panelsmentioning

confidence: 99%

“…The high bending level (0.85) was obtained from reference 3, which was based on results from reference 23. However, Fawaz [28] had tested 4 joints and measured secondary bending factors from 0.2 to 0.34. None of these joints, however, were exactly the same as the retired fuselage joints, but Joint I was the closest.…”

Section: Curved Fuselage Test Panelsmentioning

confidence: 99%

Fatigue and crack-growth analyses of riveted lap-joints in a retired aircraft

Newman

Ramakrishnan

2016

International Journal of Fatigue

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“…A digital computer was used to control the closed loop, servo hydraulic load frames. [10]. Each frame is equipped with a 20 Â travelling optical microscope (TOM) mounted to a stage that can translate along the length and across the width of the specimen.…”

Section: E X P E R I M E N T a L I N V E S T I G A T I O Nmentioning

confidence: 99%

“…[10]. Depending on the joint type, edge treatments in the joint overlap area were applied to decrease the likelihood of edge cracking.…”

Section: Test Proceduresmentioning

confidence: 99%

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Equivalent initial flaw size testing and analysis of transport aircraft skin splices

Fawaz

2003

Fatigue Fract Eng Mat Struct

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The equivalent initial flaw size (EIFS) concept was developed nearly 30 years ago in an attempt to account for the initial quality, both manufacturing and material properties, of a structural detail prone to fatigue cracking. Widespread use of this concept has been limited due to the large amount of test data required to develop a reliable EIFS distribution. In this effort, an EIFS distribution was determined for four types of flat, production like transport aircraft fuselage skin joints loaded by remote tension. Two crack growth prediction codes, AFGROW and FASTRAN, were used to not only develop the EIFS but also to compare the crack growth algorithms in each code. The EIFS calculations are prone to compounding errors in the crack growth analysis due to the changing stress intensity factor solutions and stress fields as the crack gets longer. Thus, only including EIFS calculations for mechanically small cracks, crack lengths less than 1.27 mm, results in a mean EIFS of 18.0 μm with a standard deviation of 3.78 μm.

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