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Article: Composite laminated solid shell element for geometrically nonlinear analysis

TitleComposite laminated solid shell element for geometrically nonlinear analysis
Authors
KeywordsComposite
Geometrically Nonlinear
Solid Shell
Stabilization
Thickness Locking
Issue Date2003
Citation
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica, 2003, v. 20 n. 3, p. 7-12 How to Cite?
AbstractStarting from defining generalized stress, this paper presents a modified stiffness matrix method to overcome the thickness locking of solid shell elements and guarantee the continuous distribution of the transverse normal stress of composite laminate shell structures. By splitting the stress into lower order term and higher order term, a nonlinear variation principle is developed and a 9-node solid shell element with 6 DOF per node is derived for the geometrically nonlinear analysis of composite laminated shells. The higher order assumed stress modes are judiciously selected to vanish at the sampling points of the second order quadrature and their energy products with the displacement-derived covariant strain can be programmed without resorting to numerical integration. The accuracy of the present element is virtually identical to that of the uniformly reduced integration (URI) element yet with a little additional computational cost for the stabilization matrix. The stabilization matrix is of prime importance as the global tangential stiffness matrices resulting from the URI elements often become singular after a few iterations.
Persistent Identifierhttp://hdl.handle.net/10722/156713
ISSN
2015 SCImago Journal Rankings: 0.238
References

 

DC FieldValueLanguage
dc.contributor.authorZheng, Sen_US
dc.contributor.authorSze, KYen_US
dc.date.accessioned2012-08-08T08:43:39Z-
dc.date.available2012-08-08T08:43:39Z-
dc.date.issued2003en_US
dc.identifier.citationFuhe Cailiao Xuebao/Acta Materiae Compositae Sinica, 2003, v. 20 n. 3, p. 7-12en_US
dc.identifier.issn1000-3851en_US
dc.identifier.urihttp://hdl.handle.net/10722/156713-
dc.description.abstractStarting from defining generalized stress, this paper presents a modified stiffness matrix method to overcome the thickness locking of solid shell elements and guarantee the continuous distribution of the transverse normal stress of composite laminate shell structures. By splitting the stress into lower order term and higher order term, a nonlinear variation principle is developed and a 9-node solid shell element with 6 DOF per node is derived for the geometrically nonlinear analysis of composite laminated shells. The higher order assumed stress modes are judiciously selected to vanish at the sampling points of the second order quadrature and their energy products with the displacement-derived covariant strain can be programmed without resorting to numerical integration. The accuracy of the present element is virtually identical to that of the uniformly reduced integration (URI) element yet with a little additional computational cost for the stabilization matrix. The stabilization matrix is of prime importance as the global tangential stiffness matrices resulting from the URI elements often become singular after a few iterations.en_US
dc.languageengen_US
dc.relation.ispartofFuhe Cailiao Xuebao/Acta Materiae Compositae Sinicaen_US
dc.subjectCompositeen_US
dc.subjectGeometrically Nonlinearen_US
dc.subjectSolid Shellen_US
dc.subjectStabilizationen_US
dc.subjectThickness Lockingen_US
dc.titleComposite laminated solid shell element for geometrically nonlinear analysisen_US
dc.typeArticleen_US
dc.identifier.emailSze, KY:szeky@graduate.hku.hken_US
dc.identifier.authoritySze, KY=rp00171en_US
dc.description.naturelink_to_subscribed_fulltexten_US
dc.identifier.scopuseid_2-s2.0-0347983856en_US
dc.relation.referenceshttp://www.scopus.com/mlt/select.url?eid=2-s2.0-0347983856&selection=ref&src=s&origin=recordpageen_US
dc.identifier.volume20en_US
dc.identifier.issue3en_US
dc.identifier.spage7en_US
dc.identifier.epage12en_US
dc.publisher.placeChinaen_US
dc.identifier.scopusauthoridZheng, S=7403146551en_US
dc.identifier.scopusauthoridSze, KY=7006735060en_US

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