Please use this identifier to cite or link to this item: https://idr.l2.nitk.ac.in/jspui/handle/123456789/14795
Full metadata record
DC FieldValueLanguage
dc.contributor.authorSachin S.
dc.contributor.authorNayaka S.H.
dc.contributor.authorSanthosh B.
dc.contributor.authorKrishna P.
dc.date.accessioned2021-05-05T10:15:47Z-
dc.date.available2021-05-05T10:15:47Z-
dc.date.issued2020
dc.identifier.citationMaterials Today: Proceedings , Vol. 21 , , p. 1094 - 1098en_US
dc.identifier.urihttps://doi.org/10.1016/j.matpr.2020.01.055
dc.identifier.urihttp://idr.nitk.ac.in/jspui/handle/123456789/14795-
dc.description.abstractAn aerospace structural material T300/914 has been studied to understand the Mode I interlaminar fracture toughness. For experimental analysis a Double Cantilever Beam (DCB) test is conducted on the laminate to estimate the Mode I interlaminar fracture toughness of the sample. A 48-layer laminate was prepared by hand layup process and an insert included at the mid plane to produce the artificial initial crack required for the test. All the tests are conducted in accordance to the ASTM standards. Pulse-Echo test results and C-Scan images of the laminate were analyzed to find the defects in the laminate. The data from DCB test were analyzed by Modified Beam theory, Compliance calibration method and modified compliance calibration methods to find the interlaminar fracture toughness. A crack length correction method is implemented for data reduction. Numerical analysis of the data derives results in accordance with the experimental analysis. © 2019 Elsevier Ltd. All rights reserved.en_US
dc.titleExperimental investigation of mode I interlaminar fracture toughness in T300/914 compositeen_US
dc.typeConference Paperen_US
Appears in Collections:2. Conference Papers

Files in This Item:
There are no files associated with this item.


Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.