Trans RINA, Vol 152, Part B2, Intl J Small Craft Tech, 2010 Jul-Dec
connected to Hinge 1 by an 8mm bolt. The loading mechanism was designed such that bending load was applied and the structure failed through delamination due to interlaminar tensile failure. Necessary care was taken while installing the specimens within the grips of the clamp to ensure proper alignment. Displacement controlled loading was applied, 15mm/min for four minutes and thereafter 5mm/min for next eight minutes to achieve a total deflection of 100mm.
Figure 2.1 Specimen Configuration
Figure 2.2b - Loading Mechanism using Bolt 2.2 ACOUSTIC EMISSION SETUP
A four-channel Acoustic Emission equipment of Physical Acoustic Corporation was used to acquire the stress waves generated by curved composite during the damage process. Two sensors were used, and AE events were acquired by the sensor as analogue signals. They were pre-amplified and converted into digital signals by an A/D converter. A 40dB system gain and a 45dB threshold were used for the AE acquisition. The AE data acquisition was synchronized with the mechanical loading. The acoustic emission information collected was stored in a parametric AE file. This allowed correlation of the AE parameters with the load-deflection at the time the AE signal was produced.
Figure 2.2a Experimental Setup 3.
The base of the specimen leg was secured using clamping arrangement as shown in Figure 2.2a. Bending load was applied using three-hinge arrangement shown in Figure 2.2b using Instron test machine. As no load was applied in transverse direction (z-axis), effect of Hinge 2 is negligible. A hole was drilled in the specimen arm and
©2010: The Royal Institution of Naval Architects NUMERICAL INVESTIGATION
3D Finite element analysis (FEA) using the commercially available MSC MARC MENTAT 2008r1 software was used to evaluate the
out of plane
displacement and damage mechanism to compare with the experimental results. The thickness of each element is
B-95
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