Damage initiation and propagation in metal laminates

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The metal laminates proposed here for aircraft structures are Al alloy interlayers between Al alloy based metal matrix composite (MMC) plates reinforced with Si carbide particles. Properties to be tailored for jet engine fan containment and wing and auxiliary support structures include the important property fracture toughness. A method was developed for simulating and predicting crack initiation/growth using finite element analysis and fracture mechanics. An important key in predicting the failure is the tie- break slideline with prescribed (chosen based on J Integral calculations) effective plastic strain to failure in elements along the slideline. More development of the method is ... continued below

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20 p.

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Riddle, R.A.; Lesuer, D.R. & Syn, C.K. July 26, 1996.

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Description

The metal laminates proposed here for aircraft structures are Al alloy interlayers between Al alloy based metal matrix composite (MMC) plates reinforced with Si carbide particles. Properties to be tailored for jet engine fan containment and wing and auxiliary support structures include the important property fracture toughness. A method was developed for simulating and predicting crack initiation/growth using finite element analysis and fracture mechanics. An important key in predicting the failure is the tie- break slideline with prescribed (chosen based on J Integral calculations) effective plastic strain to failure in elements along the slideline. More development of the method is needed, particularly in its correlation with experimental data from various fracture toughness and strength tests of metal laminates. Results show that delamination at the interface of the ductile interlayer and MMC material can add significantly to the energy required to propagate a crack through a metal laminate. 11 figs, 7 refs.

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20 p.

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OSTI as DE96050501

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  • 1996 international mechanical engineering congress and exhibition, Atlanta, GA (United States), 17-22 Nov 1996

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  • Other: DE96050501
  • Report No.: UCRL-JC--122850
  • Report No.: CONF-961105--15
  • Grant Number: W-7405-ENG-48
  • Office of Scientific & Technical Information Report Number: 382314
  • Archival Resource Key: ark:/67531/metadc674985

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  • July 26, 1996

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  • July 25, 2015, 2:20 a.m.

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  • Feb. 16, 2016, 6:14 p.m.

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Riddle, R.A.; Lesuer, D.R. & Syn, C.K. Damage initiation and propagation in metal laminates, article, July 26, 1996; California. (digital.library.unt.edu/ark:/67531/metadc674985/: accessed December 11, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.