Spring-back simulation of unidirectional carbon/epoxy L- shaped laminate composites manufactured through autoclave processing
This paper presents an original method in predicting the spring-back for composite aircraft structures using non-linear Finite Element Analysis (FEA) and is an extension of the previous accompanying study on flat geometry samples. Firstly, unidirectional prepreg lay-up samples are fabricated on moul...
| Main Authors: | , , , , , |
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| Format: | Conference or Workshop Item |
| Language: | English English |
| Published: |
IOP Publishing
2016
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/50019/ http://irep.iium.edu.my/50019/ http://irep.iium.edu.my/50019/ http://irep.iium.edu.my/50019/3/50019.pdf http://irep.iium.edu.my/50019/5/50019-Spring-back%20simulation%20of%20unidirectional%20carbon-SCOPUS.pdf |
| Summary: | This paper presents an original method in predicting the spring-back for composite aircraft structures using non-linear Finite Element Analysis (FEA) and is an extension of the previous accompanying study on flat geometry samples. Firstly, unidirectional prepreg lay-up samples are fabricated on moulds with different corner angles (30o, 45o and 90o) and the effect on spring-back deformation are observed. Then, the FEA model that was developed in the previous study on flat samples is utilized. The model maintains the physical mechanisms of spring-back such as ply stretching and tool-part interface properties with the additional mechanism in the corner effect and geometrical changes in the tool, part and the tool-part interface components. The comparative study between the experimental data and FEA results show that the FEA model predicts adequately the spring-back deformation within the range of corner angle tested. |
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