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Fracture Study on 2014-T6 (LT) Alumi...

Mississippi State University.

Fracture Study on 2014-T6 (LT) Aluminum Alloy Sheet Using Critical-Crack-Tip-Opening-Angle Criterion.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	Fracture Study on 2014-T6 (LT) Aluminum Alloy Sheet Using Critical-Crack-Tip-Opening-Angle Criterion./
Author:	Himmiche, Sara.
Description:	1 online resource (84 pages)
Notes:	Source: Masters Abstracts International, Volume: 57-02.
Subject:	Aerospace engineering. -
Online resource:	click for full text (PQDT)
ISBN:	9780355513769

Fracture Study on 2014-T6 (LT) Aluminum Alloy Sheet Using Critical-Crack-Tip-Opening-Angle Criterion.
Himmiche, Sara.

Fracture Study on 2014-T6 (LT) Aluminum Alloy Sheet Using Critical-Crack-Tip-Opening-Angle Criterion. - 1 online resource (84 pages)

Source: Masters Abstracts International, Volume: 57-02.

Thesis (M.Eng.)--Mississippi State University, 2017.

Includes bibliographical references

A two-parameter fracture criterion (TPFC), relates the linear-elastic stress intensity factor KIe and net-section stress Sn at failure with two-material parameters, KF and m. The objective of this work was to validate the TPFC. Two-dimensional elastic-plastic finite-element analyses (FEA) were used with the critical crack-tip-opening-angle fracture criterion and a plane-strain-core height to match failure loads on middle-crack-tension, M(T), specimens made of 2014-T6 (LT) aluminum alloy. The same analyses were used on single-edge-crack-tension, SE(T), and-single-edge-crack-bend, SE(B), specimens. A wide range in specimen widths (w = 0.75 to 24 in.) were considered. The finite-element code, ZIP2D, was used to calculate critical stress-intensity factors at failure corresponding to all crack configurations for crack-length-to-width ratios of 0.2 to 0.8. The results from FEA agreed very well with the TPFC predictions for net-section stresses less than the material proportional limit. Further study is needed for higher net-section stresses on SE(T) and SE(T) specimens.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2018

Mode of access: World Wide Web

ISBN: 9780355513769Subjects--Topical Terms:

686400
Aerospace engineering.
Index Terms--Genre/Form:

554714
Electronic books.

Fracture Study on 2014-T6 (LT) Aluminum Alloy Sheet Using Critical-Crack-Tip-Opening-Angle Criterion.
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035 $a (MiAaPQ)msstate:13093
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040 $a MiAaPQ $b eng $c MiAaPQ
100 1 $a Himmiche, Sara. $3 1148640
245 1 0 $a Fracture Study on 2014-T6 (LT) Aluminum Alloy Sheet Using Critical-Crack-Tip-Opening-Angle Criterion.
264 0 $c 2017
300 $a 1 online resource (84 pages)
336 $a text $b txt $2 rdacontent
337 $a computer $b c $2 rdamedia
338 $a online resource $b cr $2 rdacarrier
500 $a Source: Masters Abstracts International, Volume: 57-02.
500 $a Adviser: James C. Newman.
502 $a Thesis (M.Eng.)--Mississippi State University, 2017.
504 $a Includes bibliographical references
520 $a A two-parameter fracture criterion (TPFC), relates the linear-elastic stress intensity factor KIe and net-section stress Sn at failure with two-material parameters, KF and m. The objective of this work was to validate the TPFC. Two-dimensional elastic-plastic finite-element analyses (FEA) were used with the critical crack-tip-opening-angle fracture criterion and a plane-strain-core height to match failure loads on middle-crack-tension, M(T), specimens made of 2014-T6 (LT) aluminum alloy. The same analyses were used on single-edge-crack-tension, SE(T), and-single-edge-crack-bend, SE(B), specimens. A wide range in specimen widths (w = 0.75 to 24 in.) were considered. The finite-element code, ZIP2D, was used to calculate critical stress-intensity factors at failure corresponding to all crack configurations for crack-length-to-width ratios of 0.2 to 0.8. The results from FEA agreed very well with the TPFC predictions for net-section stresses less than the material proportional limit. Further study is needed for higher net-section stresses on SE(T) and SE(T) specimens.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2018
538 $a Mode of access: World Wide Web
650 4 $a Aerospace engineering. $3 686400
655 7 $a Electronic books. $2 local $3 554714
690 $a 0538
710 2 $a ProQuest Information and Learning Co. $3 1178819
710 2 $a Mississippi State University. $b Aerospace Engineering. $3 1148641
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10640513 $z click for full text (PQDT)

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