Effect of Thermo-Mechanical Gradient on the Damage Mechanisms of Composite Laminates
Abstract The main purpose of this work is to characterize and discriminate the respective roles of the thermo-mechanical gradient in the damage mechanisms of composite laminates used in aeronautics in order to understand the initiation and evolution of damage modes. For this purpose, a finite elemen...
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| Autor*in: |
El Moufari, Meryem [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2017 |
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| Schlagwörter: |
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| Anmerkung: |
© ASM International 2017 |
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| Übergeordnetes Werk: |
Enthalten in: Practical failure analysis - Springer New York, 2001, 17(2017), 5 vom: 29. Aug., Seite 935-941 |
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| Übergeordnetes Werk: |
volume:17 ; year:2017 ; number:5 ; day:29 ; month:08 ; pages:935-941 |
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| DOI / URN: |
10.1007/s11668-017-0321-4 |
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| 520 | |a Abstract The main purpose of this work is to characterize and discriminate the respective roles of the thermo-mechanical gradient in the damage mechanisms of composite laminates used in aeronautics in order to understand the initiation and evolution of damage modes. For this purpose, a finite element model of compact tension specimen with a series of virtual crack closure techniques is achieved in order to evaluate the energy release rate of transverse matrix cracking in composites. The continuum mechanics approach in combination with Hashin’s damage criterion is adopted to describe initiation and evolution for each damage mode proposed for carbon/epoxy laminates. The good agreement between the numerical results and experiments in other available literature shows the validation of the analysis and developed model in this paper. | ||
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10.1007/s11668-017-0321-4 doi (DE-627)SPR021675589 (SPR)s11668-017-0321-4-e DE-627 ger DE-627 rakwb eng El Moufari, Meryem verfasserin aut Effect of Thermo-Mechanical Gradient on the Damage Mechanisms of Composite Laminates 2017 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2017 Abstract The main purpose of this work is to characterize and discriminate the respective roles of the thermo-mechanical gradient in the damage mechanisms of composite laminates used in aeronautics in order to understand the initiation and evolution of damage modes. For this purpose, a finite element model of compact tension specimen with a series of virtual crack closure techniques is achieved in order to evaluate the energy release rate of transverse matrix cracking in composites. The continuum mechanics approach in combination with Hashin’s damage criterion is adopted to describe initiation and evolution for each damage mode proposed for carbon/epoxy laminates. The good agreement between the numerical results and experiments in other available literature shows the validation of the analysis and developed model in this paper. Composite laminates (dpeaa)DE-He213 Continuum mechanics (dpeaa)DE-He213 Thermo-mechanical loading (dpeaa)DE-He213 Finite element analysis (dpeaa)DE-He213 El Bakkali, Larbi aut Enthalten in Practical failure analysis Springer New York, 2001 17(2017), 5 vom: 29. Aug., Seite 935-941 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:17 year:2017 number:5 day:29 month:08 pages:935-941 https://dx.doi.org/10.1007/s11668-017-0321-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 17 2017 5 29 08 935-941 |
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10.1007/s11668-017-0321-4 doi (DE-627)SPR021675589 (SPR)s11668-017-0321-4-e DE-627 ger DE-627 rakwb eng El Moufari, Meryem verfasserin aut Effect of Thermo-Mechanical Gradient on the Damage Mechanisms of Composite Laminates 2017 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2017 Abstract The main purpose of this work is to characterize and discriminate the respective roles of the thermo-mechanical gradient in the damage mechanisms of composite laminates used in aeronautics in order to understand the initiation and evolution of damage modes. For this purpose, a finite element model of compact tension specimen with a series of virtual crack closure techniques is achieved in order to evaluate the energy release rate of transverse matrix cracking in composites. The continuum mechanics approach in combination with Hashin’s damage criterion is adopted to describe initiation and evolution for each damage mode proposed for carbon/epoxy laminates. The good agreement between the numerical results and experiments in other available literature shows the validation of the analysis and developed model in this paper. Composite laminates (dpeaa)DE-He213 Continuum mechanics (dpeaa)DE-He213 Thermo-mechanical loading (dpeaa)DE-He213 Finite element analysis (dpeaa)DE-He213 El Bakkali, Larbi aut Enthalten in Practical failure analysis Springer New York, 2001 17(2017), 5 vom: 29. Aug., Seite 935-941 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:17 year:2017 number:5 day:29 month:08 pages:935-941 https://dx.doi.org/10.1007/s11668-017-0321-4 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 17 2017 5 29 08 935-941 |
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Abstract The main purpose of this work is to characterize and discriminate the respective roles of the thermo-mechanical gradient in the damage mechanisms of composite laminates used in aeronautics in order to understand the initiation and evolution of damage modes. For this purpose, a finite element model of compact tension specimen with a series of virtual crack closure techniques is achieved in order to evaluate the energy release rate of transverse matrix cracking in composites. The continuum mechanics approach in combination with Hashin’s damage criterion is adopted to describe initiation and evolution for each damage mode proposed for carbon/epoxy laminates. The good agreement between the numerical results and experiments in other available literature shows the validation of the analysis and developed model in this paper. © ASM International 2017 |
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Abstract The main purpose of this work is to characterize and discriminate the respective roles of the thermo-mechanical gradient in the damage mechanisms of composite laminates used in aeronautics in order to understand the initiation and evolution of damage modes. For this purpose, a finite element model of compact tension specimen with a series of virtual crack closure techniques is achieved in order to evaluate the energy release rate of transverse matrix cracking in composites. The continuum mechanics approach in combination with Hashin’s damage criterion is adopted to describe initiation and evolution for each damage mode proposed for carbon/epoxy laminates. The good agreement between the numerical results and experiments in other available literature shows the validation of the analysis and developed model in this paper. © ASM International 2017 |
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Abstract The main purpose of this work is to characterize and discriminate the respective roles of the thermo-mechanical gradient in the damage mechanisms of composite laminates used in aeronautics in order to understand the initiation and evolution of damage modes. For this purpose, a finite element model of compact tension specimen with a series of virtual crack closure techniques is achieved in order to evaluate the energy release rate of transverse matrix cracking in composites. The continuum mechanics approach in combination with Hashin’s damage criterion is adopted to describe initiation and evolution for each damage mode proposed for carbon/epoxy laminates. The good agreement between the numerical results and experiments in other available literature shows the validation of the analysis and developed model in this paper. © ASM International 2017 |
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For this purpose, a finite element model of compact tension specimen with a series of virtual crack closure techniques is achieved in order to evaluate the energy release rate of transverse matrix cracking in composites. The continuum mechanics approach in combination with Hashin’s damage criterion is adopted to describe initiation and evolution for each damage mode proposed for carbon/epoxy laminates. The good agreement between the numerical results and experiments in other available literature shows the validation of the analysis and developed model in this paper.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Composite laminates</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Continuum mechanics</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Thermo-mechanical loading</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Finite element analysis</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">El Bakkali, Larbi</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">Practical failure analysis</subfield><subfield code="d">Springer New York, 2001</subfield><subfield code="g">17(2017), 5 vom: 29. Aug., Seite 935-941</subfield><subfield code="w">(DE-627)886125871</subfield><subfield code="w">(DE-600)2893589-5</subfield><subfield code="x">5555-1313</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:17</subfield><subfield code="g">year:2017</subfield><subfield code="g">number:5</subfield><subfield code="g">day:29</subfield><subfield code="g">month:08</subfield><subfield code="g">pages:935-941</subfield></datafield><datafield tag="856" ind1="4" ind2="0"><subfield code="u">https://dx.doi.org/10.1007/s11668-017-0321-4</subfield><subfield code="z">lizenzpflichtig</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_SPRINGER</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">17</subfield><subfield code="j">2017</subfield><subfield code="e">5</subfield><subfield code="b">29</subfield><subfield code="c">08</subfield><subfield code="h">935-941</subfield></datafield></record></collection>
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