Large deflection dynamic response of composite laminated plates under in-plane loads

Papazoglou, VJ; Tsouvalis, NG

dc.contributor.author	Papazoglou, VJ	en
dc.contributor.author	Tsouvalis, NG	en
dc.date.accessioned	2014-03-01T01:11:09Z
dc.date.available	2014-03-01T01:11:09Z
dc.date.issued	1995	en
dc.identifier.issn	0263-8223	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/11565
dc.subject	Analytic Solution	en
dc.subject	Dynamic Response	en
dc.subject	galerkin method	en
dc.subject	Nonlinear Differential Equation	en
dc.subject	Oscillations	en
dc.subject	Parametric Study	en
dc.subject	Phase Ii	en
dc.subject	runge-kutta method	en
dc.subject	Classical Lamination Theory	en
dc.subject	Time Dependent	en
dc.subject.classification	Materials Science, Composites	en
dc.subject.other	Buckling	en
dc.subject.other	Composite structures	en
dc.subject.other	Deflection (structures)	en
dc.subject.other	Deformation	en
dc.subject.other	Differential equations	en
dc.subject.other	Dynamic response	en
dc.subject.other	Laminated composites	en
dc.subject.other	Nonlinear equations	en
dc.subject.other	Numerical analysis	en
dc.subject.other	Oscillations	en
dc.subject.other	Shear stress	en
dc.subject.other	Structural loads	en
dc.subject.other	Classical lamination theory	en
dc.subject.other	Composite laminated plates	en
dc.subject.other	Dynamic buckling	en
dc.subject.other	Galerkin method	en
dc.subject.other	Large deflection dynamic response	en
dc.subject.other	Runge-Kutta method	en
dc.subject.other	Plates (structural components)	en
dc.title	Large deflection dynamic response of composite laminated plates under in-plane loads	en
heal.type	journalArticle	en
heal.identifier.primary	10.1016/0263-8223(95)00126-3	en
heal.identifier.secondary	http://dx.doi.org/10.1016/0263-8223(95)00126-3	en
heal.language	English	en
heal.publicationDate	1995	en
heal.abstract	An analytical solution is presented for the dynamic buckling behaviour of a laminate subjected to time-dependent uniformly distributed normal and shear in-plane loads based on the Classical Lamination Theory and accounting for moderately large deflections. The assumed load-time variation is either linear or of a pulse type. The Galerkin method is applied and the obtained nonlinear differential equations are solved numerically by the Runge-Kutta method. The parametric study performed revealed three distinct phases in the undamped centre deflection time-history of a laminate. No significant deformations are produced in phase I, while the subsequent phase II reflects the dynamic buckling behaviour, exhibiting a rapid increase of the deformations. These magnitudes follow an oscillating motion in phase III, analogous to the loading condition under consideration. Relatively large initial imperfection values change completely the response of the laminate, by eliminating both the characteristic dynamic buckling phase II and the oscillations of phase III. © 1995.	en
heal.publisher	ELSEVIER SCI LTD	en
heal.journalName	Composite Structures	en
dc.identifier.doi	10.1016/0263-8223(95)00126-3	en
dc.identifier.isi	ISI:A1995TT69700005	en
dc.identifier.volume	33	en
dc.identifier.issue	4	en
dc.identifier.spage	237	en
dc.identifier.epage	252	en