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

Newman, James C.; Ramakrishnan, Ramesh

doi:10.1016/j.ijfatigue.2015.04.010

Cited by 29 publications

(13 citation statements)

References 7 publications

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“…However, fatigue life and crack length estimates have been found to be wrong by a factor of as much as tenfold (Haile, 2012 andVasudevan, 2016). The main contributing factor of such large errors is the use of equivalent initial flaw size (EIFS) (Newman, 2016). EIFS is commonly calculated through back extrapolation from a long fatigue crack using the Paris crack growth law (Paris, 1963).…”

Section: Background and Motivationmentioning

confidence: 99%

Machine Learning Based Prognostics of Fatigue Crack Growth in Notch Pre-cracked Aluminum 7075-T6 Rivet Hole

2018

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Constant stress amplitude fatigue tests were conducted on the notch pre-cracked Aluminum 7075-T6 rivet hole dog-bone coupons. Monitoring of visible surface crack length by special surface engraving using digital microscope images and by ultrasonic sensors signals was carried out to yield fatigue crack length measurements in relation to number of fatigue cycles applied. The experimental results provide ultrasonic sensor validation for fatigue crack length measurements. Fracto-graphic examination of failed fatigue surfaces has provided further confirmation of notch pre-crack length, crack initiation process, and crack growth marker bands. These experimental inputs were used in NASGRO and AFGROW software fatigue crack growth simulations. The simulation results did not match the crack initiation fatigue life measured by experiments. However, there was good agreement with crack growth simulations of larger cracks. Hence, we plan to develop a machine learning application that will learn the fatigue crack initiation and crack growth processes from data obtained from our own experiments and other fatigue data available from AFGROW databases. Nonlinear AutoRegressive models with eXogenous input (NARX) artificial neural network were used to predict crack growth longer than 5.0-mm. Particle filtering modeling with Bayesian updating was applied to these experimental data for prognostics of fatigue crack growth. A concept design and preliminary implementation results will be presented.

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Section: Background and Motivationmentioning

confidence: 99%

Machine Learning Based Prognostics of Fatigue Crack Growth in Notch Pre-cracked Aluminum 7075-T6 Rivet Hole

2018

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“…The stress intensity factor range is calculated as [21]. The SIF due to opening stress can be calculated from the closure model as a function of constraint ( ), stress ratio ( R ) and ratio of the maximum applied stress to flow stress ( max 0 /  ) [23].…”

Section: Experimental Data and Numerical Resultsmentioning

confidence: 99%

“…The MSD problems are usually analyzed by using numerical methods rather than the theoretical ones because of the complicated interactions between multiple cracks [2]. Newman Jr. and Ramakrishnan demonstrated that the fatigue life prediction methods based on the fatigue crack growth alone can be used adequately to calculating the life of the fuselage riveted lap joints [21].…”

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confidence: 99%

Study on life and path of fatigue cracks in multiple site damage plates

Seifi

Ghadimian

Ranjbaran

2015

International Journal of Fatigue

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“…Although extensive research and testing has been performed to improve the durability of mechanical connections, certain configurations have been investigated more thoroughly than others. For example, a large canon of research exists (e.g., Li et al, 1 Newman et al, 2 Skorupa et al 3 ) describing the fatigue characteristics of lap splice connections due to their extensive use in the manufacture of commercial aircraft fuselage.…”

Section: Introductionmentioning

confidence: 99%

Clamped member fatigue characteristics of bolted connections subject to out‐of‐plane loading

Zambino

Ural

2021

Engineering Reports

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In the presence of significant cyclic loading, the design of safe and efficient structural connections requires accurate determination of the clamped member stresses, amongst other considerations. Connections with pretensioned bolts and loading applied parallel to the bolt axis constitute a challenging analysis task that is underrepresented in the literature. To address this, parametric finite element analysis was performed on a representative bolted connection subject to out-of-plane loading and comprised of an aluminum member and a pretensioned steel bolt -a typical configuration in the aerospace industry. Of particular interest were the flexural stresses and their contribution to fatigue damage along the member faying surface. The analysis results demonstrated that both the location and magnitude of the stress extrema varied greatly with the geometric and loading parameters considered. To quantify regions most susceptible to fatigue damage, an equivalent stress formulation in conjunction with a critical plane approach was implemented. Contour plots were generated illustrating these regions and regression analysis was performed relating the parametric geometry and load quantities to the maximum equivalent and principal stresses. Regions of greatest fatigue susceptibility were shown to vary both radially and tangentially about the fastener. The data presented are intended to improve both the efficiency and safety of bolted connections.

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

Cited by 29 publications

References 7 publications

Machine Learning Based Prognostics of Fatigue Crack Growth in Notch Pre-cracked Aluminum 7075-T6 Rivet Hole

Machine Learning Based Prognostics of Fatigue Crack Growth in Notch Pre-cracked Aluminum 7075-T6 Rivet Hole

Study on life and path of fatigue cracks in multiple site damage plates

Clamped member fatigue characteristics of bolted connections subject to out‐of‐plane loading

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