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dc.contributor.authorSahu, S K-
dc.contributor.authorDatta, P K-
dc.identifier.citationProceedings of the I MECH E Part G Journal of Aerospace Engineering, Vol 214, Iss 5, P 295-312en
dc.descriptionCopyright for this article belongs to Professional Engineering Publishingen
dc.description.abstractThe dynamic instability behaviour of isotropic, cross-ply and angle-ply laminated composite plates under combined uniaxial and harmonically varying in-plane point or patch loads is investigated using finite element analysis. The first-order shear deformation theory is used to model the composite laminates, considering the effects of transverse shear deformation and rotary inertia. The effects of various geometrical parameters, boundary conditions, lamination and load parameters on the principal dynamic instability regions of composite plates are studied in detail. The preferential orientations depending on the instability regions for simply supported patch and point loaded plates have been suggested for angle-ply plates. The dynamic instability region has been influenced by the restraint provided at the edgesen
dc.format.extent832186 bytes-
dc.publisherProfessional Engineering Publishingen
dc.subjectfinite element methoden
dc.subjectdynamic instabilityen
dc.subjectrectangular platesen
dc.titleDynamic Instability of Laminated Composite Rectangular Plates Subjected to Non-Uniform Harmonic In-Plane Edge Loadingen
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