Estimation of Mode-III Interlaminar Fracture Toughness in GFRP Laminates
J.V. Sai Prasanna Kumar
J.V. Sai Prasanna Kumar, Department of Aeronautical Engineering Vel Tech Rangarajan Dr Sagunthala R&D Institute of Science and Technology Chennai.
Manuscript received on November 22, 2019. | Revised Manuscript received on December 15, 2019. | Manuscript published on December 30, 2019. | PP: 4256-4262 | Volume-9 Issue-2, December, 2019. | Retrieval Number: B3040129219/2019©BEIESP | DOI: 10.35940/ijeat.B3040.129219
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: The composite material is heterogenous in nature has several applications ranging from sports to defence industries replacing the conventional materials. Assessing the strength composite material for out of plane delamination characterization is a challenging task. One of the test specimens which can simulate the out of the plane loading is the Edge crack torsion (ECT) specimen, to study thedelamination growth in composite laminates in a controlled environment. For the present work a fixture was developed to simulate out of plane loading and hence to estimate mode-III fracture toughness. The testcoupons werecast using from bi-directional satin glass fibre woven mat, subsequently a starter crack was introduced in the mid plane. A 100 KNInstron Universal test loadingframe was used in static condition. It was observed that the crack growth did initiate from specimen centre.The fracture parameter experimentally measured was found to bedependent on the crack growth.
Keywords: Delamination, Edge Crack Torsion Test Specimen Fracture toughness, GFRP Mode III, Out of Plane Loading, Radiographic Scanning.