Spring-back simulation of unidirectional carbon/epoxy L- shaped laminate composites manufactured through autoclave processing

2nd International Manufacturing Engineering Conference; 3rd Asia-Pacific Conference on Manufacturing Systems

Nasir, M.N.M.^1 ; Mezeix, L.^1 ; Aminanda, Y.^1 ; Seman, M.A.^2 ; Rivai, A.^2 ; Ali, K.M.^3

Department of Mechanical Engineering, International Islamic University Malaysia, Kuala Lumpur

50728, Malaysia^1

Faculty of Mechanical Engineering, Universiti Teknikal Malaysia Melaka, Durian Tunggal

76100, Malaysia^2

Aerospace Malaysia Innovation Centre, Cyberjaya

63000, Malaysia^3

关键词: Autoclave processing;    Comparative studies;    Composite aircraft structure;    Geometrical changes;    Interface property;    Laminate composites;    Non-linear finite-element analysis;    Physical mechanism;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/114/1/012025/pdf
DOI  :  10.1088/1757-899X/114/1/012025

来源: IOP

【 摘 要 】

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 (30°, 45° and 90°) 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.