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Failure Modeling of Titanium 6Al-4V and Aluminum 2024-T3 with the Johnson-Cook Material Model.

PB2004101411

Publication Date	2003
Personal Author	Kay, G.
Page Count	28
Abstract	Johnson-Cook failure strain parameters were developed for Ti-6Al-4V and 2024-T3 aluminum. The titanium parameters, obtained from simulations of split Hopkinson bar tensile tests, were successfully used to simulate blade fragment impact tests on 0.602, 0.250, and 0.737 thick titanium targets. Titanium failure parameters that were derived from scaled down ballistic limit testing produced a failure envelope which was not suitable for use on full-scale tests. 2024-T3 aluminum failure parameters were obtained from simulations of one-third-scale ballistic limit test results. The aluminum failure parameters were used to simulate three blade fragment impact tests against a commercial transport aircraft fuselage.
Keywords	Simulations Titanium Aluminum Aircraft Failure analysis Tensile tests Strain rate Mathematical equations Charts Tensile stress Blades Johnson-Cooke model Failure strain parameters Hopkinson bar tensile tests
Source Agency	Department of Transportation Federal Aviation Administration
Corporate Authors	Lawrence Livermore National Lab., CA.; Federal Aviation Administration, Washington, DC. Office of Aviation
Supplemental Notes	This document is color dependent and/or in landscape layout. It is currently available on CD-ROM and paper only. CD-ROM contains 24 page document. Sponsored by Federal Aviation Administration, Washington, DC. Office of Aviation Research.
Document Type	Technical Report
Title Note	Final rept.
NTIS Issue Number	200404

Failure Modeling of Titanium 6Al-4V and Aluminum 2024-T3 with the Johnson-Cook Material Model.

Failure Modeling of Titanium 6Al-4V and Aluminum 2024-T3 with the Johnson-Cook Material Model.
PB2004101411

Publication Date	2003
Personal Author	Kay, G.
Page Count	28
Abstract	Johnson-Cook failure strain parameters were developed for Ti-6Al-4V and 2024-T3 aluminum. The titanium parameters, obtained from simulations of split Hopkinson bar tensile tests, were successfully used to simulate blade fragment impact tests on 0.602, 0.250, and 0.737 thick titanium targets. Titanium failure parameters that were derived from scaled down ballistic limit testing produced a failure envelope which was not suitable for use on full-scale tests. 2024-T3 aluminum failure parameters were obtained from simulations of one-third-scale ballistic limit test results. The aluminum failure parameters were used to simulate three blade fragment impact tests against a commercial transport aircraft fuselage.
Keywords	Simulations Titanium Aluminum Aircraft Failure analysis Tensile tests Strain rate Mathematical equations Charts Tensile stress Blades Johnson-Cooke model Failure strain parameters Hopkinson bar tensile tests
Source Agency	Department of Transportation Federal Aviation Administration
Corporate Authors	Lawrence Livermore National Lab., CA.; Federal Aviation Administration, Washington, DC. Office of Aviation
Supplemental Notes	This document is color dependent and/or in landscape layout. It is currently available on CD-ROM and paper only. CD-ROM contains 24 page document. Sponsored by Federal Aviation Administration, Washington, DC. Office of Aviation Research.
Document Type	Technical Report
Title Note	Final rept.
NTIS Issue Number	200404