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  • 1
    Electronic Resource
    Electronic Resource
    Experimental Investigation of Typical Environmental Corrosion Influence on Fatigue Life in 2024-T3 Aluminium Alloy (2006)
    s.l. ; Stafa-Zurich, Switzerland
    Key engineering materials Vol. 324-325 (Nov. 2006), p. 363-366 
    Details
    ISSN: 1013-9826
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: The influence of environmental corrosion on fatigue life of 2024-T3 aluminum alloy isinvestigated in this paper. Experiments with center-hole specimens and CC(T) specimens areconducted and reported. The test result shows that the corrosion influence is becoming seriouswhile the environmental causticity is increasing, and the influence on crack initiation life is greaterthan that on crack propagation life. Analysis of the test data also indicates that the environmentalcausticity enlarges the dispersivity of fatigue life. Using the corrosion-modification-factor obtainedby eigenvalue or mean value to prediction the fatigue life with high reliability will cause anunconservative conclusion
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/52/transtech_doi~10.4028%252Fwww.scientific.net%252FKEM.324-325.363.pdf
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  • 2
    Electronic Resource
    Electronic Resource
    Crack Growth Life Estimating for MSD Panel (2008)
    s.l. ; Stafa-Zurich, Switzerland
    Advanced materials research Vol. 33-37 (Mar. 2008), p. 175-180 
    Details
    ISSN: 1662-8985
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: The problem of multiple site damage (MSD) has got more attention in ageing structures.Cumulative effects of interacting cracks may significantly degrade the damage tolerance capacity ofstructures. Cracks caused by MSD are extremely difficult to detect and greatly reduce the residualstrength, fatigue life and overall structural integrity of aircraft panels. This paper presents a simplenumerical method, which use the principles of fracture mechanics and the computation results, topredict the fatigue crack growth life of MSD structure. Comparing with calculating crack growth lifecycle by cycle, this method will save much time. To verify the validity of the proposed method,experiment was conducted and reported with simulation specimen of representative MSD structurewith 5 details. The comparison between the calculated a-N curves and the crack growth lives and thetest results shows that the prediction result with this fast method is acceptable. A discussion wascarried out by numerical analysis; in with typical MSD structures with different initial crack lengthwere adopted. Crack interaction effect was found obviously, but it occurred mainly in the last part ofthe crack growth lives. The relative size of MSD cracks depends significantly on the distribution ofthe initial cracks
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/40/transtech_doi~10.4028%252Fwww.scientific.net%252FAMR.33-37.175.pdf
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  • 3
    Electronic Resource
    Electronic Resource
    Residual Strength Research for Aluminum Alloy Sheet with Multiple Site Damage (2007)
    s.l. ; Stafa-Zurich, Switzerland
    Key engineering materials Vol. 348-349 (Sept. 2007), p. 489-492 
    Details
    ISSN: 1013-9826
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: This study investigated the residual strength of aluminum alloy sheet with multiple sitedamage (MSD) through three types of aluminum specimens test. Aluminum panels with barecollinear constant diameter holes were chosen as specimens. And there were saw cuts at both edgesof all the holes. After some constant amplitude tension-tension load cycles, the MSD were found inthese specimens since there were multiple fatigue cracks emanating from the saw cuts of holes. Theresidual strength was recorded as the maximum load when every specimen was subjected tomonotonically increasing tensile load until failure occurred. The test results were compared withpredicted residual strength results by five different failure prediction criteria that were often used inengineering in order to evaluate the accuracy of these criteria. The failure criteria included: fracturecriterion, net ligament loss criterion, ligament yield criterion, CTOA/CTOD criterion and averagestress criterion. Ligament yield criterion (Swift criterion) and average stress criterion got moreaccurate prediction results than other criteria
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/55/transtech_doi~10.4028%252Fwww.scientific.net%252FKEM.348-349.489.pdf
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  • 4
    Electronic Resource
    Electronic Resource
    Stochastic Characteristics of Fatigue Crack Propagation for 2024-T3 Aluminium Alloy in Corrosive Environments (2007)
    s.l. ; Stafa-Zurich, Switzerland
    Key engineering materials Vol. 348-349 (Sept. 2007), p. 517-520 
    Details
    ISSN: 1013-9826
    Source: Scientific.Net: Materials Science & Technology / Trans Tech Publications Archiv 1984-2008
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Crack propagation tests were conducted with CCT specimens made by 2024-T3 Aluminumalloy in benign and corrosive environments to investigate the stochastic characteristics of crackgrowth. A random variable probability crack growth model, base on the modified form of Paris law,was used to characterize the stochastic performance. Distribution significance test has been done,which shows that the random variable X can be considered reasonably to follow log-normaldistribution in all the 4 kind of environments. Variance analysis indicates that the scatter in wet air isgreater than that in laboratory air significantly. Expressions for the probability distribution of cracksize at any given loading cycle and the probability distribution of the random fatigue life at which agiven crack size is reached were discussed. The corresponding calculations for the crack lengthdistribution and P-a-N curves with certain reliability were carried out. The comparisons withexperimental data indicate the validity of the proposed method
    Type of Medium: Electronic Resource
    URL: http://www.tib-hannover.de/fulltexts/2011/0528/01/55/transtech_doi~10.4028%252Fwww.scientific.net%252FKEM.348-349.517.pdf
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