Crash Simulation Of A Composite Unmanned Aerial Vehicle Fuselage

In this research the results of experimental works and numerical simulation works pertaining to the crash behavior and crashworthiness characteristic of the upper part of the composite unmanned aerial vehicle (UAV) fuselage sections that were subjected to quasi-static transverse compressive loading...

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Main Author:	Yidris, Noorfaizal
Format:	Thesis
Language:	English English
Published:	2007
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Online Access:	http://psasir.upm.edu.my/id/eprint/5251/1/FK_2007_47.pdf
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spelling	my-upm-ir.52512013-05-27T07:21:28Z Crash Simulation Of A Composite Unmanned Aerial Vehicle Fuselage 2007 Yidris, Noorfaizal In this research the results of experimental works and numerical simulation works pertaining to the crash behavior and crashworthiness characteristic of the upper part of the composite unmanned aerial vehicle (UAV) fuselage sections that were subjected to quasi-static transverse compressive loading are presented in detail. The influence of varying angles of lamina and special cases of laminates is thoroughly analyzed. The fuselage sections were made of 8 plies of C-glass/epoxy in a [45/-45/90/0]s layup. Two types of density of C-glass/epoxy, 200 g/m2 and 600 g/m2, were used with a total thickness of 0.00224 m and 0.004 m respectively for the 8-plies. Each ply has a thickness of 0.00028 m for C-glass/epoxy 200 g/m2 and 0.0005 m for C-glass/epoxy 600 g/m2. The C-glass/epoxy fuselage section was compressed using MTS machine of 250 kN loading capacity at very low-strain rate typical for static testing. The experimental data are correlated with predictions from a finite element model developed using the ABAQUS/Standard with user subroutine. The simulation of the composite fuselage sections was carried out, refined several times and validated with the experimental results. The ABAQUS analysis results for both the C-glass/epoxy 200 g/m2 and C-glass/epoxy 600 g/m2 fuselage sections agreed well with the experimental data. ABAQUS analyses predicted the location of progressive damage to the sections using three failure theories, Maximum Stress Failure Theory, Tsai-Hill Failure Theory and Tsai-Wu Failure Theory. Tsai-Hill Failure Theory is found to have the least error percentage compared to the other two failure theories used. Finally, the finite element model was then used to study the influence of varying angles of lamina and special cases of laminates. 15o angle of lamina and cross-ply laminate is found to have the most energy absorption. 2007 Thesis http://psasir.upm.edu.my/id/eprint/5251/ http://psasir.upm.edu.my/id/eprint/5251/1/FK_2007_47.pdf application/pdf en public masters Universiti Putra Malaysia Faculty of Engineering English
institution	Universiti Putra Malaysia
collection	PSAS Institutional Repository
language	English English
topic
spellingShingle	Yidris, Noorfaizal Crash Simulation Of A Composite Unmanned Aerial Vehicle Fuselage
description	In this research the results of experimental works and numerical simulation works pertaining to the crash behavior and crashworthiness characteristic of the upper part of the composite unmanned aerial vehicle (UAV) fuselage sections that were subjected to quasi-static transverse compressive loading are presented in detail. The influence of varying angles of lamina and special cases of laminates is thoroughly analyzed. The fuselage sections were made of 8 plies of C-glass/epoxy in a [45/-45/90/0]s layup. Two types of density of C-glass/epoxy, 200 g/m2 and 600 g/m2, were used with a total thickness of 0.00224 m and 0.004 m respectively for the 8-plies. Each ply has a thickness of 0.00028 m for C-glass/epoxy 200 g/m2 and 0.0005 m for C-glass/epoxy 600 g/m2. The C-glass/epoxy fuselage section was compressed using MTS machine of 250 kN loading capacity at very low-strain rate typical for static testing. The experimental data are correlated with predictions from a finite element model developed using the ABAQUS/Standard with user subroutine. The simulation of the composite fuselage sections was carried out, refined several times and validated with the experimental results. The ABAQUS analysis results for both the C-glass/epoxy 200 g/m2 and C-glass/epoxy 600 g/m2 fuselage sections agreed well with the experimental data. ABAQUS analyses predicted the location of progressive damage to the sections using three failure theories, Maximum Stress Failure Theory, Tsai-Hill Failure Theory and Tsai-Wu Failure Theory. Tsai-Hill Failure Theory is found to have the least error percentage compared to the other two failure theories used. Finally, the finite element model was then used to study the influence of varying angles of lamina and special cases of laminates. 15o angle of lamina and cross-ply laminate is found to have the most energy absorption.
format	Thesis
qualification_level	Master's degree
author	Yidris, Noorfaizal
author_facet	Yidris, Noorfaizal
author_sort	Yidris, Noorfaizal
title	Crash Simulation Of A Composite Unmanned Aerial Vehicle Fuselage
title_short	Crash Simulation Of A Composite Unmanned Aerial Vehicle Fuselage
title_full	Crash Simulation Of A Composite Unmanned Aerial Vehicle Fuselage
title_fullStr	Crash Simulation Of A Composite Unmanned Aerial Vehicle Fuselage
title_full_unstemmed	Crash Simulation Of A Composite Unmanned Aerial Vehicle Fuselage
title_sort	crash simulation of a composite unmanned aerial vehicle fuselage
granting_institution	Universiti Putra Malaysia
granting_department	Faculty of Engineering
publishDate	2007
url	http://psasir.upm.edu.my/id/eprint/5251/1/FK_2007_47.pdf
_version_	1747810384155246592

Crash Simulation Of A Composite Unmanned Aerial Vehicle Fuselage

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