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

Himmiche, Sara.

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

Record Type:	Language materials, printed : Monograph/item
Title/Author:	Fracture Study on 2014-T6 (LT) Aluminum Alloy Sheet Using Critical-Crack-Tip-Opening-Angle Criterion./
Author:	Himmiche, Sara.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2017,
Description:	84 p.
Notes:	Source: Masters Abstracts International, Volume: 57-02.
Contained By:	Masters Abstracts International57-02(E).
Subject:	Aerospace engineering. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10640513
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. - Ann Arbor : ProQuest Dissertations & Theses, 2017 - 84 p.

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

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

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.

ISBN: 9780355513769Subjects--Topical Terms:

686400
Aerospace engineering.

Fracture Study on 2014-T6 (LT) Aluminum Alloy Sheet Using Critical-Crack-Tip-Opening-Angle Criterion.
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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.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2017
300 $a 84 p.
500 $a Source: Masters Abstracts International, Volume: 57-02.
500 $a Adviser: James C. Newman.
502 $a Thesis (M.Eng.)--Mississippi State University, 2017.
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.
590 $a School code: 0132.
650 4 $a Aerospace engineering. $3 686400
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710 2 $a Mississippi State University. $b Aerospace Engineering. $3 1148641
773 0 $t Masters Abstracts International $g 57-02(E).
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856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10640513

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