Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method

In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in auto...
Ausführliche Beschreibung

Gespeichert in:

Autor*in:	Feng, Wei [verfasserIn] Xu, Fei [verfasserIn] Yuan, Jialei [verfasserIn] Zang, Yuyan [verfasserIn] Zhang, Xiaoyu [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2018

Schlagwörter:	In-service repair Scarf repair CFRP Laminate thickness Vacuum bagging

Übergeordnetes Werk:	Enthalten in: Composite structures - Amsterdam : Elsevier, 1983, 207, Seite 826-835
Übergeordnetes Werk:	volume:207 ; pages:826-835

DOI / URN:	10.1016/j.compstruct.2018.09.096

Katalog-ID:	ELV001039563

Internformat


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520			\|a In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in autoclaves, high porosity levels may be induced when cured using vacuum bagging, which harms the mechanical properties of composites. This article aims to use an alternative material which shows better performance than the original one when using vacuum bagging for the patch. Four groups of scarf repaired composites with various laminate thicknesses were fabricated and tested. Experimental results indicate that the failure strengths of different groups are similar and the dominated failure mode is cohesive failure of adhesive, accompanied by partial 45° and 90° matrix cracks of composite patch. In addition, a finite element model was established to predict the failure strength and explain the damage mechanism. The numerical results show good agreement with test results and indicate that matrix cracks of composites initiate before the adhesive failure. Based on the validated model, the effects of overlap patch and 3D defects on the ultimate strength were discussed.
650		4	\|a In-service repair
650		4	\|a Scarf repair
650		4	\|a CFRP
650		4	\|a Laminate thickness
650		4	\|a Vacuum bagging
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700	1		\|a Yuan, Jialei \|e verfasserin \|4 aut
700	1		\|a Zang, Yuyan \|e verfasserin \|4 aut
700	1		\|a Zhang, Xiaoyu \|e verfasserin \|4 aut
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matchkey_str	article:02638223:2018----::ouignnevcrpitcmoieaiaeodfeethcnse
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publishDate	2018
allfields	10.1016/j.compstruct.2018.09.096 doi (DE-627)ELV001039563 (ELSEVIER)S0263-8223(18)32455-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Feng, Wei verfasserin aut Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method 2018 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in autoclaves, high porosity levels may be induced when cured using vacuum bagging, which harms the mechanical properties of composites. This article aims to use an alternative material which shows better performance than the original one when using vacuum bagging for the patch. Four groups of scarf repaired composites with various laminate thicknesses were fabricated and tested. Experimental results indicate that the failure strengths of different groups are similar and the dominated failure mode is cohesive failure of adhesive, accompanied by partial 45° and 90° matrix cracks of composite patch. In addition, a finite element model was established to predict the failure strength and explain the damage mechanism. The numerical results show good agreement with test results and indicate that matrix cracks of composites initiate before the adhesive failure. Based on the validated model, the effects of overlap patch and 3D defects on the ultimate strength were discussed. In-service repair Scarf repair CFRP Laminate thickness Vacuum bagging Xu, Fei verfasserin aut Yuan, Jialei verfasserin aut Zang, Yuyan verfasserin aut Zhang, Xiaoyu verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 207, Seite 826-835 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:207 pages:826-835 GBV_USEFLAG_U SYSFLAG_U GBV_ELV GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 51.75 Verbundwerkstoffe Schichtstoffe AR 207 826-835
spelling	10.1016/j.compstruct.2018.09.096 doi (DE-627)ELV001039563 (ELSEVIER)S0263-8223(18)32455-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Feng, Wei verfasserin aut Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method 2018 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in autoclaves, high porosity levels may be induced when cured using vacuum bagging, which harms the mechanical properties of composites. This article aims to use an alternative material which shows better performance than the original one when using vacuum bagging for the patch. Four groups of scarf repaired composites with various laminate thicknesses were fabricated and tested. Experimental results indicate that the failure strengths of different groups are similar and the dominated failure mode is cohesive failure of adhesive, accompanied by partial 45° and 90° matrix cracks of composite patch. In addition, a finite element model was established to predict the failure strength and explain the damage mechanism. The numerical results show good agreement with test results and indicate that matrix cracks of composites initiate before the adhesive failure. Based on the validated model, the effects of overlap patch and 3D defects on the ultimate strength were discussed. In-service repair Scarf repair CFRP Laminate thickness Vacuum bagging Xu, Fei verfasserin aut Yuan, Jialei verfasserin aut Zang, Yuyan verfasserin aut Zhang, Xiaoyu verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 207, Seite 826-835 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:207 pages:826-835 GBV_USEFLAG_U SYSFLAG_U GBV_ELV GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 51.75 Verbundwerkstoffe Schichtstoffe AR 207 826-835
allfields_unstemmed	10.1016/j.compstruct.2018.09.096 doi (DE-627)ELV001039563 (ELSEVIER)S0263-8223(18)32455-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Feng, Wei verfasserin aut Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method 2018 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in autoclaves, high porosity levels may be induced when cured using vacuum bagging, which harms the mechanical properties of composites. This article aims to use an alternative material which shows better performance than the original one when using vacuum bagging for the patch. Four groups of scarf repaired composites with various laminate thicknesses were fabricated and tested. Experimental results indicate that the failure strengths of different groups are similar and the dominated failure mode is cohesive failure of adhesive, accompanied by partial 45° and 90° matrix cracks of composite patch. In addition, a finite element model was established to predict the failure strength and explain the damage mechanism. The numerical results show good agreement with test results and indicate that matrix cracks of composites initiate before the adhesive failure. Based on the validated model, the effects of overlap patch and 3D defects on the ultimate strength were discussed. In-service repair Scarf repair CFRP Laminate thickness Vacuum bagging Xu, Fei verfasserin aut Yuan, Jialei verfasserin aut Zang, Yuyan verfasserin aut Zhang, Xiaoyu verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 207, Seite 826-835 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:207 pages:826-835 GBV_USEFLAG_U SYSFLAG_U GBV_ELV GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 51.75 Verbundwerkstoffe Schichtstoffe AR 207 826-835
allfieldsGer	10.1016/j.compstruct.2018.09.096 doi (DE-627)ELV001039563 (ELSEVIER)S0263-8223(18)32455-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Feng, Wei verfasserin aut Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method 2018 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in autoclaves, high porosity levels may be induced when cured using vacuum bagging, which harms the mechanical properties of composites. This article aims to use an alternative material which shows better performance than the original one when using vacuum bagging for the patch. Four groups of scarf repaired composites with various laminate thicknesses were fabricated and tested. Experimental results indicate that the failure strengths of different groups are similar and the dominated failure mode is cohesive failure of adhesive, accompanied by partial 45° and 90° matrix cracks of composite patch. In addition, a finite element model was established to predict the failure strength and explain the damage mechanism. The numerical results show good agreement with test results and indicate that matrix cracks of composites initiate before the adhesive failure. Based on the validated model, the effects of overlap patch and 3D defects on the ultimate strength were discussed. In-service repair Scarf repair CFRP Laminate thickness Vacuum bagging Xu, Fei verfasserin aut Yuan, Jialei verfasserin aut Zang, Yuyan verfasserin aut Zhang, Xiaoyu verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 207, Seite 826-835 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:207 pages:826-835 GBV_USEFLAG_U SYSFLAG_U GBV_ELV GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 51.75 Verbundwerkstoffe Schichtstoffe AR 207 826-835
allfieldsSound	10.1016/j.compstruct.2018.09.096 doi (DE-627)ELV001039563 (ELSEVIER)S0263-8223(18)32455-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Feng, Wei verfasserin aut Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method 2018 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in autoclaves, high porosity levels may be induced when cured using vacuum bagging, which harms the mechanical properties of composites. This article aims to use an alternative material which shows better performance than the original one when using vacuum bagging for the patch. Four groups of scarf repaired composites with various laminate thicknesses were fabricated and tested. Experimental results indicate that the failure strengths of different groups are similar and the dominated failure mode is cohesive failure of adhesive, accompanied by partial 45° and 90° matrix cracks of composite patch. In addition, a finite element model was established to predict the failure strength and explain the damage mechanism. The numerical results show good agreement with test results and indicate that matrix cracks of composites initiate before the adhesive failure. Based on the validated model, the effects of overlap patch and 3D defects on the ultimate strength were discussed. In-service repair Scarf repair CFRP Laminate thickness Vacuum bagging Xu, Fei verfasserin aut Yuan, Jialei verfasserin aut Zang, Yuyan verfasserin aut Zhang, Xiaoyu verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 207, Seite 826-835 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:207 pages:826-835 GBV_USEFLAG_U SYSFLAG_U GBV_ELV GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 51.75 Verbundwerkstoffe Schichtstoffe AR 207 826-835
language	English
source	Enthalten in Composite structures 207, Seite 826-835 volume:207 pages:826-835
sourceStr	Enthalten in Composite structures 207, Seite 826-835 volume:207 pages:826-835
format_phy_str_mv	Article
bklname	Verbundwerkstoffe Schichtstoffe
institution	findex.gbv.de
topic_facet	In-service repair Scarf repair CFRP Laminate thickness Vacuum bagging
dewey-raw	670
isfreeaccess_bool	false
container_title	Composite structures
authorswithroles_txt_mv	Feng, Wei @@aut@@ Xu, Fei @@aut@@ Yuan, Jialei @@aut@@ Zang, Yuyan @@aut@@ Zhang, Xiaoyu @@aut@@
publishDateDaySort_date	2018-01-01T00:00:00Z
hierarchy_top_id	320509044
dewey-sort	3670
id	ELV001039563
language_de	englisch
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author	Feng, Wei
spellingShingle	Feng, Wei ddc 670 bkl 51.75 misc In-service repair misc Scarf repair misc CFRP misc Laminate thickness misc Vacuum bagging Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method
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topic_title	670 DE-600 51.75 bkl Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method In-service repair Scarf repair CFRP Laminate thickness Vacuum bagging
topic	ddc 670 bkl 51.75 misc In-service repair misc Scarf repair misc CFRP misc Laminate thickness misc Vacuum bagging
topic_unstemmed	ddc 670 bkl 51.75 misc In-service repair misc Scarf repair misc CFRP misc Laminate thickness misc Vacuum bagging
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title	Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method
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title_full	Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method
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title_sort	focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method
title_auth	Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method
abstract	In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in autoclaves, high porosity levels may be induced when cured using vacuum bagging, which harms the mechanical properties of composites. This article aims to use an alternative material which shows better performance than the original one when using vacuum bagging for the patch. Four groups of scarf repaired composites with various laminate thicknesses were fabricated and tested. Experimental results indicate that the failure strengths of different groups are similar and the dominated failure mode is cohesive failure of adhesive, accompanied by partial 45° and 90° matrix cracks of composite patch. In addition, a finite element model was established to predict the failure strength and explain the damage mechanism. The numerical results show good agreement with test results and indicate that matrix cracks of composites initiate before the adhesive failure. Based on the validated model, the effects of overlap patch and 3D defects on the ultimate strength were discussed.
abstractGer	In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in autoclaves, high porosity levels may be induced when cured using vacuum bagging, which harms the mechanical properties of composites. This article aims to use an alternative material which shows better performance than the original one when using vacuum bagging for the patch. Four groups of scarf repaired composites with various laminate thicknesses were fabricated and tested. Experimental results indicate that the failure strengths of different groups are similar and the dominated failure mode is cohesive failure of adhesive, accompanied by partial 45° and 90° matrix cracks of composite patch. In addition, a finite element model was established to predict the failure strength and explain the damage mechanism. The numerical results show good agreement with test results and indicate that matrix cracks of composites initiate before the adhesive failure. Based on the validated model, the effects of overlap patch and 3D defects on the ultimate strength were discussed.
abstract_unstemmed	In terms of in-service components, sometimes it is difficult to undertake repairing with an autoclave due to the structure configurations and repair conditions. In order to conduct in-service soft patch repair, vacuum bagging process can be used. However, for composite materials manufactured in autoclaves, high porosity levels may be induced when cured using vacuum bagging, which harms the mechanical properties of composites. This article aims to use an alternative material which shows better performance than the original one when using vacuum bagging for the patch. Four groups of scarf repaired composites with various laminate thicknesses were fabricated and tested. Experimental results indicate that the failure strengths of different groups are similar and the dominated failure mode is cohesive failure of adhesive, accompanied by partial 45° and 90° matrix cracks of composite patch. In addition, a finite element model was established to predict the failure strength and explain the damage mechanism. The numerical results show good agreement with test results and indicate that matrix cracks of composites initiate before the adhesive failure. Based on the validated model, the effects of overlap patch and 3D defects on the ultimate strength were discussed.
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title_short	Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method
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author2	Xu, Fei Yuan, Jialei Zang, Yuyan Zhang, Xiaoyu
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doi_str	10.1016/j.compstruct.2018.09.096
up_date	2024-07-06T20:01:19.605Z
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score	7.401597

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Focusing on in-service repair to composite laminates of different thicknesses via scarf-repaired method

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Vorhandene Bände

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