Process-induced deformation in U-shaped honeycomb aerospace composite structures

This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core we...
Ausführliche Beschreibung

Gespeichert in:

Autor*in:	Al-Dhaheri, M. [verfasserIn] Khan, K.A. [verfasserIn] Umer, R. [verfasserIn] van Liempt, F. [verfasserIn] Cantwell, W.J. [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2020

Schlagwörter:	Process-induced deformation Spring-in Autoclave manufacturing Finite element analysis Residual stress Sandwich structure

Übergeordnetes Werk:	Enthalten in: Composite structures - Amsterdam : Elsevier, 1983, 248
Übergeordnetes Werk:	volume:248

DOI / URN:	10.1016/j.compstruct.2020.112503

Katalog-ID:	ELV004428161

Internformat


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520			\|a This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core were manufactured. For purposes of comparison, a U-shaped composite laminate, i.e. without the inclusion of a core, was also manufactured and modeled. Process-induced spring-in at different locations within the U-shaped parts were measured, both optically and using a feeler gauge. Thermo-chemical and stress-deformation finite element models were employed to predict the degree of spring-in for both the sandwich structures and the plain laminates using the ABAQUS/COMPRO. The predicted spring-in values were shown to be in good agreement with those measured experimentally. Parametric studies to investigate the effect of changing both the tooling material and the sandwich core have shown that employing an aluminum tool and an aluminum core reduced the degree of spring-in and warpage in the structures. However, spring-in phenomena is dominated by the core structure and geometry of the part. Finally, it has been shown that the process-induced deformation is less in the curved sandwich structures than in their laminated counterparts, with both structures deforming due to the combined effects of spring-in and warpage of the flat regions.
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700	1		\|a van Liempt, F. \|e verfasserin \|4 aut
700	1		\|a Cantwell, W.J. \|e verfasserin \|4 aut
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author_variant	m a d mad k k kk r u ru l f v lf lfv w c wc
matchkey_str	article:02638223:2020----::rcsidcdeomtoiuhpdoecmarsa
hierarchy_sort_str	2020
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publishDate	2020
allfields	10.1016/j.compstruct.2020.112503 doi (DE-627)ELV004428161 (ELSEVIER)S0263-8223(20)30549-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Al-Dhaheri, M. verfasserin aut Process-induced deformation in U-shaped honeycomb aerospace composite structures 2020 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core were manufactured. For purposes of comparison, a U-shaped composite laminate, i.e. without the inclusion of a core, was also manufactured and modeled. Process-induced spring-in at different locations within the U-shaped parts were measured, both optically and using a feeler gauge. Thermo-chemical and stress-deformation finite element models were employed to predict the degree of spring-in for both the sandwich structures and the plain laminates using the ABAQUS/COMPRO. The predicted spring-in values were shown to be in good agreement with those measured experimentally. Parametric studies to investigate the effect of changing both the tooling material and the sandwich core have shown that employing an aluminum tool and an aluminum core reduced the degree of spring-in and warpage in the structures. However, spring-in phenomena is dominated by the core structure and geometry of the part. Finally, it has been shown that the process-induced deformation is less in the curved sandwich structures than in their laminated counterparts, with both structures deforming due to the combined effects of spring-in and warpage of the flat regions. Process-induced deformation Spring-in Autoclave manufacturing Finite element analysis Residual stress Sandwich structure Khan, K.A. verfasserin aut Umer, R. verfasserin aut van Liempt, F. verfasserin aut Cantwell, W.J. verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 248 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:248 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 248
spelling	10.1016/j.compstruct.2020.112503 doi (DE-627)ELV004428161 (ELSEVIER)S0263-8223(20)30549-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Al-Dhaheri, M. verfasserin aut Process-induced deformation in U-shaped honeycomb aerospace composite structures 2020 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core were manufactured. For purposes of comparison, a U-shaped composite laminate, i.e. without the inclusion of a core, was also manufactured and modeled. Process-induced spring-in at different locations within the U-shaped parts were measured, both optically and using a feeler gauge. Thermo-chemical and stress-deformation finite element models were employed to predict the degree of spring-in for both the sandwich structures and the plain laminates using the ABAQUS/COMPRO. The predicted spring-in values were shown to be in good agreement with those measured experimentally. Parametric studies to investigate the effect of changing both the tooling material and the sandwich core have shown that employing an aluminum tool and an aluminum core reduced the degree of spring-in and warpage in the structures. However, spring-in phenomena is dominated by the core structure and geometry of the part. Finally, it has been shown that the process-induced deformation is less in the curved sandwich structures than in their laminated counterparts, with both structures deforming due to the combined effects of spring-in and warpage of the flat regions. Process-induced deformation Spring-in Autoclave manufacturing Finite element analysis Residual stress Sandwich structure Khan, K.A. verfasserin aut Umer, R. verfasserin aut van Liempt, F. verfasserin aut Cantwell, W.J. verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 248 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:248 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 248
allfields_unstemmed	10.1016/j.compstruct.2020.112503 doi (DE-627)ELV004428161 (ELSEVIER)S0263-8223(20)30549-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Al-Dhaheri, M. verfasserin aut Process-induced deformation in U-shaped honeycomb aerospace composite structures 2020 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core were manufactured. For purposes of comparison, a U-shaped composite laminate, i.e. without the inclusion of a core, was also manufactured and modeled. Process-induced spring-in at different locations within the U-shaped parts were measured, both optically and using a feeler gauge. Thermo-chemical and stress-deformation finite element models were employed to predict the degree of spring-in for both the sandwich structures and the plain laminates using the ABAQUS/COMPRO. The predicted spring-in values were shown to be in good agreement with those measured experimentally. Parametric studies to investigate the effect of changing both the tooling material and the sandwich core have shown that employing an aluminum tool and an aluminum core reduced the degree of spring-in and warpage in the structures. However, spring-in phenomena is dominated by the core structure and geometry of the part. Finally, it has been shown that the process-induced deformation is less in the curved sandwich structures than in their laminated counterparts, with both structures deforming due to the combined effects of spring-in and warpage of the flat regions. Process-induced deformation Spring-in Autoclave manufacturing Finite element analysis Residual stress Sandwich structure Khan, K.A. verfasserin aut Umer, R. verfasserin aut van Liempt, F. verfasserin aut Cantwell, W.J. verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 248 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:248 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 248
allfieldsGer	10.1016/j.compstruct.2020.112503 doi (DE-627)ELV004428161 (ELSEVIER)S0263-8223(20)30549-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Al-Dhaheri, M. verfasserin aut Process-induced deformation in U-shaped honeycomb aerospace composite structures 2020 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core were manufactured. For purposes of comparison, a U-shaped composite laminate, i.e. without the inclusion of a core, was also manufactured and modeled. Process-induced spring-in at different locations within the U-shaped parts were measured, both optically and using a feeler gauge. Thermo-chemical and stress-deformation finite element models were employed to predict the degree of spring-in for both the sandwich structures and the plain laminates using the ABAQUS/COMPRO. The predicted spring-in values were shown to be in good agreement with those measured experimentally. Parametric studies to investigate the effect of changing both the tooling material and the sandwich core have shown that employing an aluminum tool and an aluminum core reduced the degree of spring-in and warpage in the structures. However, spring-in phenomena is dominated by the core structure and geometry of the part. Finally, it has been shown that the process-induced deformation is less in the curved sandwich structures than in their laminated counterparts, with both structures deforming due to the combined effects of spring-in and warpage of the flat regions. Process-induced deformation Spring-in Autoclave manufacturing Finite element analysis Residual stress Sandwich structure Khan, K.A. verfasserin aut Umer, R. verfasserin aut van Liempt, F. verfasserin aut Cantwell, W.J. verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 248 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:248 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 248
allfieldsSound	10.1016/j.compstruct.2020.112503 doi (DE-627)ELV004428161 (ELSEVIER)S0263-8223(20)30549-3 DE-627 ger DE-627 rda eng 670 DE-600 51.75 bkl Al-Dhaheri, M. verfasserin aut Process-induced deformation in U-shaped honeycomb aerospace composite structures 2020 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core were manufactured. For purposes of comparison, a U-shaped composite laminate, i.e. without the inclusion of a core, was also manufactured and modeled. Process-induced spring-in at different locations within the U-shaped parts were measured, both optically and using a feeler gauge. Thermo-chemical and stress-deformation finite element models were employed to predict the degree of spring-in for both the sandwich structures and the plain laminates using the ABAQUS/COMPRO. The predicted spring-in values were shown to be in good agreement with those measured experimentally. Parametric studies to investigate the effect of changing both the tooling material and the sandwich core have shown that employing an aluminum tool and an aluminum core reduced the degree of spring-in and warpage in the structures. However, spring-in phenomena is dominated by the core structure and geometry of the part. Finally, it has been shown that the process-induced deformation is less in the curved sandwich structures than in their laminated counterparts, with both structures deforming due to the combined effects of spring-in and warpage of the flat regions. Process-induced deformation Spring-in Autoclave manufacturing Finite element analysis Residual stress Sandwich structure Khan, K.A. verfasserin aut Umer, R. verfasserin aut van Liempt, F. verfasserin aut Cantwell, W.J. verfasserin aut Enthalten in Composite structures Amsterdam : Elsevier, 1983 248 (DE-627)320509044 (DE-600)2013177-X (DE-576)094531447 0263-8223 nnns volume:248 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 248
language	English
source	Enthalten in Composite structures 248 volume:248
sourceStr	Enthalten in Composite structures 248 volume:248
format_phy_str_mv	Article
bklname	Verbundwerkstoffe Schichtstoffe
institution	findex.gbv.de
topic_facet	Process-induced deformation Spring-in Autoclave manufacturing Finite element analysis Residual stress Sandwich structure
dewey-raw	670
isfreeaccess_bool	false
container_title	Composite structures
authorswithroles_txt_mv	Al-Dhaheri, M. @@aut@@ Khan, K.A. @@aut@@ Umer, R. @@aut@@ van Liempt, F. @@aut@@ Cantwell, W.J. @@aut@@
publishDateDaySort_date	2020-01-01T00:00:00Z
hierarchy_top_id	320509044
dewey-sort	3670
id	ELV004428161
language_de	englisch
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author	Al-Dhaheri, M.
spellingShingle	Al-Dhaheri, M. ddc 670 bkl 51.75 misc Process-induced deformation misc Spring-in misc Autoclave manufacturing misc Finite element analysis misc Residual stress misc Sandwich structure Process-induced deformation in U-shaped honeycomb aerospace composite structures
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topic_title	670 DE-600 51.75 bkl Process-induced deformation in U-shaped honeycomb aerospace composite structures Process-induced deformation Spring-in Autoclave manufacturing Finite element analysis Residual stress Sandwich structure
topic	ddc 670 bkl 51.75 misc Process-induced deformation misc Spring-in misc Autoclave manufacturing misc Finite element analysis misc Residual stress misc Sandwich structure
topic_unstemmed	ddc 670 bkl 51.75 misc Process-induced deformation misc Spring-in misc Autoclave manufacturing misc Finite element analysis misc Residual stress misc Sandwich structure
topic_browse	ddc 670 bkl 51.75 misc Process-induced deformation misc Spring-in misc Autoclave manufacturing misc Finite element analysis misc Residual stress misc Sandwich structure
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title	Process-induced deformation in U-shaped honeycomb aerospace composite structures
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title_full	Process-induced deformation in U-shaped honeycomb aerospace composite structures
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title_sort	process-induced deformation in u-shaped honeycomb aerospace composite structures
title_auth	Process-induced deformation in U-shaped honeycomb aerospace composite structures
abstract	This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core were manufactured. For purposes of comparison, a U-shaped composite laminate, i.e. without the inclusion of a core, was also manufactured and modeled. Process-induced spring-in at different locations within the U-shaped parts were measured, both optically and using a feeler gauge. Thermo-chemical and stress-deformation finite element models were employed to predict the degree of spring-in for both the sandwich structures and the plain laminates using the ABAQUS/COMPRO. The predicted spring-in values were shown to be in good agreement with those measured experimentally. Parametric studies to investigate the effect of changing both the tooling material and the sandwich core have shown that employing an aluminum tool and an aluminum core reduced the degree of spring-in and warpage in the structures. However, spring-in phenomena is dominated by the core structure and geometry of the part. Finally, it has been shown that the process-induced deformation is less in the curved sandwich structures than in their laminated counterparts, with both structures deforming due to the combined effects of spring-in and warpage of the flat regions.
abstractGer	This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core were manufactured. For purposes of comparison, a U-shaped composite laminate, i.e. without the inclusion of a core, was also manufactured and modeled. Process-induced spring-in at different locations within the U-shaped parts were measured, both optically and using a feeler gauge. Thermo-chemical and stress-deformation finite element models were employed to predict the degree of spring-in for both the sandwich structures and the plain laminates using the ABAQUS/COMPRO. The predicted spring-in values were shown to be in good agreement with those measured experimentally. Parametric studies to investigate the effect of changing both the tooling material and the sandwich core have shown that employing an aluminum tool and an aluminum core reduced the degree of spring-in and warpage in the structures. However, spring-in phenomena is dominated by the core structure and geometry of the part. Finally, it has been shown that the process-induced deformation is less in the curved sandwich structures than in their laminated counterparts, with both structures deforming due to the combined effects of spring-in and warpage of the flat regions.
abstract_unstemmed	This study presents the findings of a combined experimental and numerical investigation to study process-induced deformation in sandwich structures manufactured using autoclave molding techniques. U-shaped sandwich structure based on woven carbon prepregs and an over-expanded Nomex honeycomb core were manufactured. For purposes of comparison, a U-shaped composite laminate, i.e. without the inclusion of a core, was also manufactured and modeled. Process-induced spring-in at different locations within the U-shaped parts were measured, both optically and using a feeler gauge. Thermo-chemical and stress-deformation finite element models were employed to predict the degree of spring-in for both the sandwich structures and the plain laminates using the ABAQUS/COMPRO. The predicted spring-in values were shown to be in good agreement with those measured experimentally. Parametric studies to investigate the effect of changing both the tooling material and the sandwich core have shown that employing an aluminum tool and an aluminum core reduced the degree of spring-in and warpage in the structures. However, spring-in phenomena is dominated by the core structure and geometry of the part. Finally, it has been shown that the process-induced deformation is less in the curved sandwich structures than in their laminated counterparts, with both structures deforming due to the combined effects of spring-in and warpage of the flat regions.
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title_short	Process-induced deformation in U-shaped honeycomb aerospace composite structures
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author2	Khan, K.A. Umer, R. van Liempt, F. Cantwell, W.J.
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up_date	2024-07-06T22:57:27.380Z
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Process-induced deformation in U-shaped honeycomb aerospace composite structures

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