Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model

Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model

In this paper, a finite element modeling via ABAQUS/Explicit simulation on a novel fabrication miniature composite fuselage structure is presented. The fuselage structure is modeled as a continuum composite layup that consisted of a woven C-glass fiber/epoxy 200 g/m 2 composite laminated [90 8] with...

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Main Authors: Mustapha, Faizal, Ng, Wei Sim, Shahrjerdi, Ali
Format: Article
Language:English
Published: Academic Journals 2011
Online Access:http://psasir.upm.edu.my/id/eprint/23085/
http://psasir.upm.edu.my/id/eprint/23085/
http://psasir.upm.edu.my/id/eprint/23085/1/Finite%20element%20analysis%20%28FEA%29%20modeling%20on%20adhesive%20joint%20for%20composite%20fuselage%20model.pdf
id upm-23085
recordtype eprints
spelling upm-230852015-12-03T07:07:52Z http://psasir.upm.edu.my/id/eprint/23085/ Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model Mustapha, Faizal Ng, Wei Sim Shahrjerdi, Ali In this paper, a finite element modeling via ABAQUS/Explicit simulation on a novel fabrication miniature composite fuselage structure is presented. The fuselage structure is modeled as a continuum composite layup that consisted of a woven C-glass fiber/epoxy 200 g/m 2 composite laminated [90 8] with the orthotropic elastic material properties and adhesively bonded butt joint. The adhesively bonded joint progression is modeled using cohesive elements technology. For the purpose of FEA modeling, an experiment of double cantilever beam (DCB) according to ASTM standard D5528 is performed to determine the adhesive mode-I critical toughness. The mode-I interlaminar fracture toughness data (G I) are calculated and compared by four different methods according to the ASTM standard: BT, beam theory, MBT, modified beam theory, CC, compliance calibration method and MCC, modified compliance calibration method. The results indicate that ABAQUS/Explicit is able to reproduce satisfactory adhesive joint behavior using cohesive elements and collapse modes under crushing process. Academic Journals 2011-10 Article PeerReviewed application/pdf en http://psasir.upm.edu.my/id/eprint/23085/1/Finite%20element%20analysis%20%28FEA%29%20modeling%20on%20adhesive%20joint%20for%20composite%20fuselage%20model.pdf Mustapha, Faizal and Ng, Wei Sim and Shahrjerdi, Ali (2011) Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model. International Journal of Physical Sciences, 6 (22). pp. 5153-5165. ISSN 1992-1950 http://www.academicjournals.org/journal/IJPS/article-abstract/6CBE96B19612
repository_type Digital Repository
institution_category Local University
institution Universiti Putra Malaysia
building UPM Institutional Repository
collection Online Access
language English
description In this paper, a finite element modeling via ABAQUS/Explicit simulation on a novel fabrication miniature composite fuselage structure is presented. The fuselage structure is modeled as a continuum composite layup that consisted of a woven C-glass fiber/epoxy 200 g/m 2 composite laminated [90 8] with the orthotropic elastic material properties and adhesively bonded butt joint. The adhesively bonded joint progression is modeled using cohesive elements technology. For the purpose of FEA modeling, an experiment of double cantilever beam (DCB) according to ASTM standard D5528 is performed to determine the adhesive mode-I critical toughness. The mode-I interlaminar fracture toughness data (G I) are calculated and compared by four different methods according to the ASTM standard: BT, beam theory, MBT, modified beam theory, CC, compliance calibration method and MCC, modified compliance calibration method. The results indicate that ABAQUS/Explicit is able to reproduce satisfactory adhesive joint behavior using cohesive elements and collapse modes under crushing process.
format Article
author Mustapha, Faizal
Ng, Wei Sim
Shahrjerdi, Ali
spellingShingle Mustapha, Faizal
Ng, Wei Sim
Shahrjerdi, Ali
Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model
author_facet Mustapha, Faizal
Ng, Wei Sim
Shahrjerdi, Ali
author_sort Mustapha, Faizal
title Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model
title_short Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model
title_full Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model
title_fullStr Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model
title_full_unstemmed Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model
title_sort finite element analysis (fea) modeling on adhesive joint for composite fuselage model
publisher Academic Journals
publishDate 2011
url http://psasir.upm.edu.my/id/eprint/23085/
http://psasir.upm.edu.my/id/eprint/23085/
http://psasir.upm.edu.my/id/eprint/23085/1/Finite%20element%20analysis%20%28FEA%29%20modeling%20on%20adhesive%20joint%20for%20composite%20fuselage%20model.pdf
first_indexed 2018-09-07T14:36:34Z
last_indexed 2018-09-07T14:36:34Z
_version_ 1610959809395294208

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