A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission
Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Liu, P. F. [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2014 |
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| Schlagwörter: |
Carbon fiber composite laminates Intralaminar damage and interlaminar delamination Single-leg three-point bending (SLB) and over-leg three-point bending (OLB) |
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| Anmerkung: |
© ASM International 2014 |
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| Übergeordnetes Werk: |
Enthalten in: Practical failure analysis - Springer New York, 2001, 15(2014), 1 vom: 11. Nov., Seite 101-121 |
|---|---|
| Übergeordnetes Werk: |
volume:15 ; year:2014 ; number:1 ; day:11 ; month:11 ; pages:101-121 |
| Links: |
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| DOI / URN: |
10.1007/s11668-014-9901-8 |
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SPR021670943 |
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| 520 | |a Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°16//0°16], [30°16//30°16], and [15°/−15°]3s//[15°/−15°]3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70 °C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates. | ||
| 650 | 4 | |a Carbon fiber composite laminates |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Intralaminar damage and interlaminar delamination |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Acoustic emission (AE) test |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Single-leg three-point bending (SLB) and over-leg three-point bending (OLB) |7 (dpeaa)DE-He213 | |
| 700 | 1 | |a Yang, J. |4 aut | |
| 700 | 1 | |a Wang, B. |4 aut | |
| 700 | 1 | |a Zhou, Z. F. |4 aut | |
| 700 | 1 | |a Zheng, J. Y. |4 aut | |
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10.1007/s11668-014-9901-8 doi (DE-627)SPR021670943 (SPR)s11668-014-9901-8-e DE-627 ger DE-627 rakwb eng Liu, P. F. verfasserin aut A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission 2014 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2014 Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°16//0°16], [30°16//30°16], and [15°/−15°]3s//[15°/−15°]3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70 °C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates. Carbon fiber composite laminates (dpeaa)DE-He213 Intralaminar damage and interlaminar delamination (dpeaa)DE-He213 Acoustic emission (AE) test (dpeaa)DE-He213 Single-leg three-point bending (SLB) and over-leg three-point bending (OLB) (dpeaa)DE-He213 Yang, J. aut Wang, B. aut Zhou, Z. F. aut Zheng, J. Y. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2014), 1 vom: 11. Nov., Seite 101-121 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2014 number:1 day:11 month:11 pages:101-121 https://dx.doi.org/10.1007/s11668-014-9901-8 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2014 1 11 11 101-121 |
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10.1007/s11668-014-9901-8 doi (DE-627)SPR021670943 (SPR)s11668-014-9901-8-e DE-627 ger DE-627 rakwb eng Liu, P. F. verfasserin aut A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission 2014 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2014 Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°16//0°16], [30°16//30°16], and [15°/−15°]3s//[15°/−15°]3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70 °C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates. Carbon fiber composite laminates (dpeaa)DE-He213 Intralaminar damage and interlaminar delamination (dpeaa)DE-He213 Acoustic emission (AE) test (dpeaa)DE-He213 Single-leg three-point bending (SLB) and over-leg three-point bending (OLB) (dpeaa)DE-He213 Yang, J. aut Wang, B. aut Zhou, Z. F. aut Zheng, J. Y. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2014), 1 vom: 11. Nov., Seite 101-121 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2014 number:1 day:11 month:11 pages:101-121 https://dx.doi.org/10.1007/s11668-014-9901-8 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2014 1 11 11 101-121 |
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10.1007/s11668-014-9901-8 doi (DE-627)SPR021670943 (SPR)s11668-014-9901-8-e DE-627 ger DE-627 rakwb eng Liu, P. F. verfasserin aut A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission 2014 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2014 Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°16//0°16], [30°16//30°16], and [15°/−15°]3s//[15°/−15°]3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70 °C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates. Carbon fiber composite laminates (dpeaa)DE-He213 Intralaminar damage and interlaminar delamination (dpeaa)DE-He213 Acoustic emission (AE) test (dpeaa)DE-He213 Single-leg three-point bending (SLB) and over-leg three-point bending (OLB) (dpeaa)DE-He213 Yang, J. aut Wang, B. aut Zhou, Z. F. aut Zheng, J. Y. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2014), 1 vom: 11. Nov., Seite 101-121 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2014 number:1 day:11 month:11 pages:101-121 https://dx.doi.org/10.1007/s11668-014-9901-8 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2014 1 11 11 101-121 |
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10.1007/s11668-014-9901-8 doi (DE-627)SPR021670943 (SPR)s11668-014-9901-8-e DE-627 ger DE-627 rakwb eng Liu, P. F. verfasserin aut A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission 2014 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2014 Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°16//0°16], [30°16//30°16], and [15°/−15°]3s//[15°/−15°]3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70 °C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates. Carbon fiber composite laminates (dpeaa)DE-He213 Intralaminar damage and interlaminar delamination (dpeaa)DE-He213 Acoustic emission (AE) test (dpeaa)DE-He213 Single-leg three-point bending (SLB) and over-leg three-point bending (OLB) (dpeaa)DE-He213 Yang, J. aut Wang, B. aut Zhou, Z. F. aut Zheng, J. Y. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2014), 1 vom: 11. Nov., Seite 101-121 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2014 number:1 day:11 month:11 pages:101-121 https://dx.doi.org/10.1007/s11668-014-9901-8 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2014 1 11 11 101-121 |
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10.1007/s11668-014-9901-8 doi (DE-627)SPR021670943 (SPR)s11668-014-9901-8-e DE-627 ger DE-627 rakwb eng Liu, P. F. verfasserin aut A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission 2014 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2014 Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°16//0°16], [30°16//30°16], and [15°/−15°]3s//[15°/−15°]3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70 °C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates. Carbon fiber composite laminates (dpeaa)DE-He213 Intralaminar damage and interlaminar delamination (dpeaa)DE-He213 Acoustic emission (AE) test (dpeaa)DE-He213 Single-leg three-point bending (SLB) and over-leg three-point bending (OLB) (dpeaa)DE-He213 Yang, J. aut Wang, B. aut Zhou, Z. F. aut Zheng, J. Y. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2014), 1 vom: 11. Nov., Seite 101-121 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2014 number:1 day:11 month:11 pages:101-121 https://dx.doi.org/10.1007/s11668-014-9901-8 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2014 1 11 11 101-121 |
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study on the intralaminar damage and interlaminar delamination of carbon fiber composite laminates under three-point bending using acoustic emission |
| title_auth |
A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission |
| abstract |
Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°16//0°16], [30°16//30°16], and [15°/−15°]3s//[15°/−15°]3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70 °C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates. © ASM International 2014 |
| abstractGer |
Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°16//0°16], [30°16//30°16], and [15°/−15°]3s//[15°/−15°]3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70 °C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates. © ASM International 2014 |
| abstract_unstemmed |
Abstract The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°16//0°16], [30°16//30°16], and [15°/−15°]3s//[15°/−15°]3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70 °C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates. © ASM International 2014 |
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| title_short |
A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission |
| url |
https://dx.doi.org/10.1007/s11668-014-9901-8 |
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true |
| author2 |
Yang, J. Wang, B. Zhou, Z. F. Zheng, J. Y. |
| author2Str |
Yang, J. Wang, B. Zhou, Z. F. Zheng, J. Y. |
| ppnlink |
886125871 |
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| doi_str |
10.1007/s11668-014-9901-8 |
| up_date |
2024-07-03T23:52:42.766Z |
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