scholarly journals Numerical Analysis of a DMA Epoxy-Carbon Composite Study

2018 ◽  
Vol 9 (4) ◽  
pp. 101-112
Author(s):  
Paweł KOWALECZKO ◽  
Andrzej PANAS ◽  
Mirosław NOWAKOWSKI

The results of numerical simulations performed for Dynamic Mechanical Analysis (DMA) measurements of thermal and mechanical (or thermomechanical) properties performed on a model composite structure are presented herein. The simulated elastic response of an epoxy-carbon fibre composite specimen was analysed for a case by which the model specimen was subjected to three-point bending with a free support. The epoxy-carbon fibre composite studied as explained herein exhibited extreme differences between the resilient properties of the epoxy resin matrix and the carbon fibre reinforcement. In addition, the carbon fibre reinforcement was both internally and structurally anisotropic. The numerical simulations were performed to demonstrate a qualitative dependence of the DMA measurement results on a certain structure of the investigated specimen and to determine if the DMA results could be qualified as effective or apparent. A macro-mechanical model of the specimen was developed and had the numerical calculations run with COMSOL/M, a FEM modelling software suite. The carbon fibre reinforcement was modelled with an orthotropic structure of laminar or circular inclusions with different characteristic dimensions. Representative material properties were assumed from the results of proprietary experimental investigations and certain reference literature data. The effect of the composite layers’ configuration and their characteristic dimensions on the evaluated model’s elastic modulus value was also studied. The results presented herein suggested a qualitative agreement with the results of the DMA investigations performed on real-life composite structures. They also proved the effectiveness of the developed numerical simulation methodology, shown herein, in the DMA of micro- and macromechanical phenomena

2009 ◽  
Vol 17 (3) ◽  
pp. 329-346 ◽  
Author(s):  
Garth M. Pearce ◽  
Alastair F. Johnson ◽  
Rodney S. Thomson ◽  
Donald W. Kelly

2019 ◽  
Vol 161 ◽  
pp. 376-385 ◽  
Author(s):  
Yu Jia ◽  
Xueyong Wei ◽  
Liu Xu ◽  
Congsi Wang ◽  
Peiyuan Lian ◽  
...  

1990 ◽  
Vol 9 (10) ◽  
pp. 1165-1168 ◽  
Author(s):  
P. Jackson ◽  
J. A. Barnes ◽  
N. J. Clayden ◽  
T. A. Carpenter ◽  
L. D. Hall ◽  
...  

Author(s):  
Dirk Aljets ◽  
Alex Chong ◽  
Steve Wilcox ◽  
Karen Holford ◽  
Rhys Pullin ◽  
...  

Recent publications show that there is an increasing interest in the aircraft industry in monitoring the actual condition of a structure in real time and while the structure is in service. It is hoped that this Structural Health Monitoring (SHM) could make some regular inspections unnecessary and allow maintenance only when required. This is particularly important for CFRP structures for which aircraft manufacturers are increasingly interested. For these new composite structures where the experience of fatigue failure is relatively low, this technique could potentially be economical and improve the safety of the structures. Acoustic Emission is reported to be sensitive to the four failure types in composite materials, namely matrix cracking, delamination, debonding and fibre fracture. These failure modes can have different impacts on structural integrity and it is therefore of interest to identify these failure types before further maintenance steps are conducted. This report discusses different features in AE signals which can be used to identify the actual flaw type. These features were then applied to AE data collected from two different experiments on carbon fibre composite plates. These experiments were designed to induce the two different failure modes of matrix cracking and delamination. The data collected was used to train a neural network to recognise the two failure modes.


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