Crack-Closure Behavior of 7050 Aluminum Alloy Near Threshold Conditions for Wide Range in Load Ratios and Constant Kmax Tests PDF Download
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Author: J. C. Newman
Publisher:
ISBN:
Category : Crack closure
Languages : en
Pages : 16
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Author: J. C. Newman
Publisher:
ISBN:
Category : Crack closure
Languages : en
Pages : 16
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Author: Talal Mehdi Senhaji
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
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Book Description
Fatigue-crack-growth-rate tests were conducted on compact tension specimens made of 7050-T7451 aluminum alloy and 9310 steel. Compact tension specimens were tested over a wide range of load ratios (0.1 ≤ R ≤ 0.9) to generate crack-growth-rate data from threshold to near fracture. Three methods were used to generate near threshold data. A crack-closure analysis was performed on both materials using the FASTRAN crack-closure model. The crack-growth-rate data for each material correlated very well and each collapsed onto a nearly unique curve in the low- and mid-rate regimes using the strip-yield model in the FASTRAN life-prediction code. For the 7050 alloy, a constraint factor of a = 1.8 was required, while for the 9310 steel a = 2.5 worked very well in correlating the test data over a very wide range in R values and rates from threshold to near fracture.
Author: Jerzy Komorowski
Publisher: Springer Science & Business Media
ISBN: 9400716648
Category : Technology & Engineering
Languages : en
Pages : 950
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Proceedings of the 26th Symposium of the International Committee on Aeronautical Fatigue are a widely referenced summary of advances in aeronautical design against fatigue. This is a bi-annual event and the proceedings have been published in book form for over 35 years.
Author:
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages :
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Fatigue and crack-growth tests were conducted on 7050-T7451 aluminum alloy under a wide range of loading conditions. Crack-growth tests were conducted on compact, C(T), specimens under constant-amplitude loading, single-spike overloads, and a simulated aircraft spectrum loading. Fatigue tests were also conducted on single-edgenotch bend, SEN(B), specimens under constant-amplitude loading and three aircraft load spectra. The FASTRAN, life-prediction code, was used to make crack-growth predictions on the C(T) specimens; and to make fatigue-life calculations using a 12- micrometer initial flaw size at the center of the edge-notch on the SEN(B) specimens. The predictions agreed fairly well with most of the tests, except the model was unconservative on the single-spike overload tests and the severe spectrum Mini-TWIST+ Level 1 tests. The discrepancy was suspected to be caused by a low constraint factor and/or crack paths meandering around overload plastic zones. A roughness- and plasticity-induced crack-closure model would be needed to improve the model.
Author: EP. Phillips
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 11
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Crack opening loads were determined in load-shedding fatigue crack growth threshold tests on 2024-T3 aluminum alloy at stress ratios R of -2, -1, 0, 0.33, 0.5, and 0.7. The effects of load-shedding procedure and rate were investigated. Values of threshold ?K were found to vary significantly with R, whereas values of threshold effective ?K did not. That is, the variation of threshold ?K with R was almost completely explained by accounting for the measured variation in crack opening load behavior with R. The load-shedding guidelines of ASTM Test Method for Measurement of Fatigue Crack Growth (E 647) produced a threshold ?K value for R = 0.7 that was in agreement with the value determined using a procedure that should minimize closure effects (constant-Kmax, increasing-Kmin test). At both R = 0 and R = 0.7, high load-shedding rates produced high values of threshold ?K caused by large closure effects.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
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Author: William T. Riddell
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 24
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Author: John J. Ruschau
Publisher:
ISBN:
Category : Aluminum
Languages : en
Pages : 15
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The scope of this paper is to determine the fatigue-crack growth rates in the near-threshold regime for both an aluminum and titanium alloy using the compression precracking constant-amplitude (CPCA) test method on compact specimens. Tests were conducted over a wide range of stress ratios (R=Pmin/Pmax=0.1 to 0.9). Results were compared with threshold and near-threshold data generated on the same materials using the ASTM E647, "Standard Test Method for Measurement of Fatigue Crack Growth Rates," load-shedding test procedure. On the 7075-T651 alloy, very little difference was observed in threshold values between the load-shedding and CPCA test methods. In contrast, the titanium alloy (Ti-6Al-4V) showed very large differences between the CPCA and load-shedding test results in the near-threshold and threshold regimes for the low stress ratios. Results under high R conditions (R>=0.7) agreed well between the two-threshold test methods for both materials. On the titanium alloy, the load-shedding test method also produced a specimen width effect on near-threshold behavior, whereas the CPCA test method produced results that were independent of specimen width and produced "steady-state" constant-amplitude data in the near-threshold regime, after the crack had grown several compressive plastic-zone sizes.
Author: R. Craig McClung
Publisher: ASTM International
ISBN: 0803126115
Category : Fracture mechanics
Languages : en
Pages : 487
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