Finite element analysis of cohesive element for glass epoxy composite fuselage model

In this research, a numerical simulation on a newly introduced fabrication miniature composite fuselage structure - a glass epoxy composite laminated with adhesively bonded butt joint under axial compression loading is presented. A FEA via ABAQUS/Explicit is utilized to capture the complete compress...

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Main Author:	Ng, Wei Sim
Format:	Thesis
Language:	English
Published:	2011
Subjects:	Finite element method (Engineering analysis) Laminated materials
Online Access:	http://psasir.upm.edu.my/id/eprint/41770/1/FK%202011%202R.pdf
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id	my-upm-ir.41770
record_format	uketd_dc
spelling	my-upm-ir.417702016-02-15T09:21:06Z Finite element analysis of cohesive element for glass epoxy composite fuselage model 2011-01 Ng, Wei Sim In this research, a numerical simulation on a newly introduced fabrication miniature composite fuselage structure - a glass epoxy composite laminated with adhesively bonded butt joint under axial compression loading is presented. A FEA via ABAQUS/Explicit is utilized to capture the complete compressive response to predict the crushing behaviour and mechanical strength from initial compression loading up to the final failure is demonstrated. A woven C-glass fiber/epoxy 200 g/m2 composite laminated with the orthotropic elastic material properties is modeled as continuum composite lay-up in the proposed numerical model. The adhesively bonded joint progression is modeled using cohesive elements technology that allows the correct accounting for the energy involved in the crushing process and investigates the capability of the bonded joint to withstand the axial crushing impact from debonding failure. An experiment of Double Cantilever Beam (DCB) according to the ASTM Standard D5528 is performed to determine the adhesive Mode I critical toughness. The crushing load and collapse modes under axial compression loading from FEA results indicate good correlation with the experimental test. The discrepancy of the peak load is found to be at 1%. Finite element method (Engineering analysis) Laminated materials 2011-01 Thesis http://psasir.upm.edu.my/id/eprint/41770/ http://psasir.upm.edu.my/id/eprint/41770/1/FK%202011%202R.pdf application/pdf en public masters Universiti Putra Malaysia Finite element method (Engineering analysis) Laminated materials
institution	Universiti Putra Malaysia
collection	PSAS Institutional Repository
language	English
topic	Finite element method (Engineering analysis) Laminated materials
spellingShingle	Finite element method (Engineering analysis) Laminated materials Ng, Wei Sim Finite element analysis of cohesive element for glass epoxy composite fuselage model
description	In this research, a numerical simulation on a newly introduced fabrication miniature composite fuselage structure - a glass epoxy composite laminated with adhesively bonded butt joint under axial compression loading is presented. A FEA via ABAQUS/Explicit is utilized to capture the complete compressive response to predict the crushing behaviour and mechanical strength from initial compression loading up to the final failure is demonstrated. A woven C-glass fiber/epoxy 200 g/m2 composite laminated with the orthotropic elastic material properties is modeled as continuum composite lay-up in the proposed numerical model. The adhesively bonded joint progression is modeled using cohesive elements technology that allows the correct accounting for the energy involved in the crushing process and investigates the capability of the bonded joint to withstand the axial crushing impact from debonding failure. An experiment of Double Cantilever Beam (DCB) according to the ASTM Standard D5528 is performed to determine the adhesive Mode I critical toughness. The crushing load and collapse modes under axial compression loading from FEA results indicate good correlation with the experimental test. The discrepancy of the peak load is found to be at 1%.
format	Thesis
qualification_level	Master's degree
author	Ng, Wei Sim
author_facet	Ng, Wei Sim
author_sort	Ng, Wei Sim
title	Finite element analysis of cohesive element for glass epoxy composite fuselage model
title_short	Finite element analysis of cohesive element for glass epoxy composite fuselage model
title_full	Finite element analysis of cohesive element for glass epoxy composite fuselage model
title_fullStr	Finite element analysis of cohesive element for glass epoxy composite fuselage model
title_full_unstemmed	Finite element analysis of cohesive element for glass epoxy composite fuselage model
title_sort	finite element analysis of cohesive element for glass epoxy composite fuselage model
granting_institution	Universiti Putra Malaysia
publishDate	2011
url	http://psasir.upm.edu.my/id/eprint/41770/1/FK%202011%202R.pdf
_version_	1747811883203690496

Finite element analysis of cohesive element for glass epoxy composite fuselage model

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