MATEC Web Conf.
Volume 139, 20172017 3rd International Conference on Mechanical, Electronic and Information Technology Engineering (ICMITE 2017)
|Number of page(s)||4|
|Published online||05 December 2017|
Study on Design and Test of Composite WIG Vehicle Considering on Impact Loading
Department of Defense Science & Technology – Aeronautics, Howon University, 54058, 64 Howondae 3gil, Impi, Gunsan, Rep. of Korea
* Corresponding author: email@example.com
This study proposed an example on preliminary structural design including trade-off study and design evaluation such as structural safety and stability analysis of a 20-seat composite WIG craft using the netting rule and the rule of mixture and a commercial FEM tool. The structural configuration of the wing adopted the skin-spar semi-monocoque type structure with foam sandwich, and the fuselage also used the semi-monocoque type structure with the skin to carry shear flow, the stringers to carry bending moments and the ring frames to carry local loads under consideration of various design local load cases. The used materials were Carbon/Epoxy (UD) for wing spar flanges and fuselage stringers and ring frames, Carbon/Epoxy (Fabric) for fuselage skins, the sandwich with Carbon/Epoxy face sheet (Fabric) and Al honeycomb core for the fuselage floor, and the sandwich with Carbon/Epoxy face sheet (UD) and Urethane foam core for wing skins and spar webs. Through the structural analysis, the structural safety and stability were confirmed.
© The Authors, published by EDP Sciences, 2017
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (http://creativecommons.org/licenses/by/4.0/).
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