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Effect of Cutout Location on Postbuckiling Responses and Failure Characteristics of Composite Laminates

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dc.contributor.author Singh, Shamsher Bahadur
dc.date.accessioned 2021-12-07T04:54:41Z
dc.date.available 2021-12-07T04:54:41Z
dc.date.issued 2011
dc.identifier.uri http://www.aerojournalindia.com/
dc.identifier.uri http://dspace.bits-pilani.ac.in:8080/xmlui/handle/123456789/3859
dc.description.abstract The objective of the present investigation is to study effects of locations of various shaped (i.e., circular, square and diamond) cutouts on stability and failure characteristics of simply-supported, axially-compressed quasi-isotropic laminate, (+45/-45/0/90)2s using finite element method. The FEM formulation is based on first order shear deformation theory wherein von Karman’s assumptions are used to incorporate geometric nonlinearity. The 3-D Tsai-hill criterion is used to predict the failure of a lamina, while the onset of delamination is predicted by the interlaminar failure criterion. It is observed that the location of cutout has a significant effect on buckling and postbuckling strength of the laminate. It is also noted that the laminate with cutout centered at a distance greater than or equal to 0.75b (where, b is the width of the square laminate) from the loaded edge has negligible effect on buckling strength of the laminate. en_US
dc.language.iso en en_US
dc.publisher The Aeronautical Society of India en_US
dc.subject Civil Engineering en_US
dc.subject Buckling en_US
dc.subject Cutout location en_US
dc.subject Failure en_US
dc.title Effect of Cutout Location on Postbuckiling Responses and Failure Characteristics of Composite Laminates en_US
dc.type Article en_US


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