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Article: A higher order finite element including transverse normal strain for linear elastic composite plates with general lamination configurations

TitleA higher order finite element including transverse normal strain for linear elastic composite plates with general lamination configurations
Authors
KeywordsAngle-ply
Bottom surfaces
Compatibility conditions
Composite plates
Displacement field
Issue Date2012
PublisherElsevier BV. The Journal's web site is located at http://www.elsevier.com/locate/finel
Citation
Finite Elements in Analysis and Design, 2012, v. 48 n. 1, p. 1346-1357 How to Cite?
AbstractThis paper describes a higher-order global–local theory for thermal/mechanical response of moderately thick laminated composites with general lamination configurations. In-plane displacement fields are constructed by superimposing the third-order local displacement field to the global cubic displacement field. To eliminate layer-dependent variables, interlaminar shear stress compatibility conditions have been employed, so that the number of variables involved in the proposed model is independent of the number of layers of laminates. Imposing shear stress free condition at the top and the bottom surfaces, derivatives of transverse displacement are eliminated from the displacement field, so that C0 interpolation functions are only required for the finite element implementation. To assess the proposed model, the quadratic six-node C0 triangular element is employed for the interpolation of all the displacement parameters defined at each nodal point on the composite plate. Comparing to various existing laminated plate models, it is found that simple C0 finite elements with non-zero normal strain could produce more accurate displacement and stresses for thick multilayer composite plates subjected to thermal and mechanical loads. Finally, it is remarked that the proposed model is quite robust, such that the finite element results are not sensitive to the mesh configuration and can rapidly converge to 3-D elasticity solutions using regular or irregular meshes.
Persistent Identifierhttp://hdl.handle.net/10722/150591
ISSN
2015 Impact Factor: 2.175
2015 SCImago Journal Rankings: 1.278
ISI Accession Number ID
Funding AgencyGrant Number
University of Hong Kong
National Natural Sciences Foundation of China10802052
11072156
Program for Liaoning Excellent Talents in UniversityLR201033
Program for Science and Technology of ShenyangF10-205-1-16
Funding Information:

The work described in this paper was supported by the University Development Fund (2009) on Computational Science and Engineering at the University of Hong Kong, the National Natural Sciences Foundation of China (Nos. 10802052, 11072156), the Program for Liaoning Excellent Talents in University (LR201033), and the Program for Science and Technology of Shenyang (F10-205-1-16).

References

 

DC FieldValueLanguage
dc.contributor.authorWu, Zen_HK
dc.contributor.authorLo, SHen_HK
dc.contributor.authorSze, KYen_HK
dc.contributor.authorChen, Wen_HK
dc.date.accessioned2012-06-26T06:05:58Z-
dc.date.available2012-06-26T06:05:58Z-
dc.date.issued2012en_HK
dc.identifier.citationFinite Elements in Analysis and Design, 2012, v. 48 n. 1, p. 1346-1357en_HK
dc.identifier.issn0168-874Xen_HK
dc.identifier.urihttp://hdl.handle.net/10722/150591-
dc.description.abstractThis paper describes a higher-order global–local theory for thermal/mechanical response of moderately thick laminated composites with general lamination configurations. In-plane displacement fields are constructed by superimposing the third-order local displacement field to the global cubic displacement field. To eliminate layer-dependent variables, interlaminar shear stress compatibility conditions have been employed, so that the number of variables involved in the proposed model is independent of the number of layers of laminates. Imposing shear stress free condition at the top and the bottom surfaces, derivatives of transverse displacement are eliminated from the displacement field, so that C0 interpolation functions are only required for the finite element implementation. To assess the proposed model, the quadratic six-node C0 triangular element is employed for the interpolation of all the displacement parameters defined at each nodal point on the composite plate. Comparing to various existing laminated plate models, it is found that simple C0 finite elements with non-zero normal strain could produce more accurate displacement and stresses for thick multilayer composite plates subjected to thermal and mechanical loads. Finally, it is remarked that the proposed model is quite robust, such that the finite element results are not sensitive to the mesh configuration and can rapidly converge to 3-D elasticity solutions using regular or irregular meshes.en_HK
dc.languageengen_US
dc.publisherElsevier BV. The Journal's web site is located at http://www.elsevier.com/locate/finelen_HK
dc.relation.ispartofFinite Elements in Analysis and Designen_HK
dc.subjectAngle-plyen_HK
dc.subjectBottom surfacesen_HK
dc.subjectCompatibility conditionsen_HK
dc.subjectComposite platesen_HK
dc.subjectDisplacement fielden_HK
dc.titleA higher order finite element including transverse normal strain for linear elastic composite plates with general lamination configurationsen_HK
dc.typeArticleen_HK
dc.identifier.emailWu, Z: nashwzhg@hku.hken_HK
dc.identifier.emailLo, SH: hreclsh@hkucc.hku.hken_HK
dc.identifier.emailSze, KY: kysze@hku.hk-
dc.identifier.authorityLo, SH=rp00223en_HK
dc.identifier.authoritySze, KY=rp00171en_HK
dc.description.naturelink_to_subscribed_fulltexten_US
dc.identifier.doi10.1016/j.finel.2011.08.003en_HK
dc.identifier.scopuseid_2-s2.0-80052133928en_HK
dc.identifier.hkuros206005-
dc.relation.referenceshttp://www.scopus.com/mlt/select.url?eid=2-s2.0-80052133928&selection=ref&src=s&origin=recordpageen_HK
dc.identifier.volume48en_HK
dc.identifier.issue1en_HK
dc.identifier.spage1346en_HK
dc.identifier.epage1357en_HK
dc.identifier.eissn1872-6925-
dc.identifier.isiWOS:000296537700002-
dc.publisher.placeNetherlandsen_HK
dc.identifier.scopusauthoridWanji, C=6701386210en_HK
dc.identifier.scopusauthoridSze, KY=7006735060en_HK
dc.identifier.scopusauthoridLo, SH=7401542444en_HK
dc.identifier.scopusauthoridZhen, W=11638893400en_HK
dc.identifier.citeulike9768370-

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