Damage prediction of carbon-epoxy composite laminates using finite element analysis

Karumbaiah, K, Das, R and Campbell, S 2015, 'Damage prediction of carbon-epoxy composite laminates using finite element analysis', in Magd Abdel Wahab (ed.) Proceedings of the 4th International Conference on Fracture Fatigue and Wear (FFW 2015), Belgium, 27- 28 August 2015, pp. 304-310.


Document type: Conference Paper
Collection: Conference Papers

Title Damage prediction of carbon-epoxy composite laminates using finite element analysis
Author(s) Karumbaiah, K
Das, R
Campbell, S
Year 2015
Conference name FFW 2015: Volume 3
Conference location Belgium
Conference dates 27- 28 August 2015
Proceedings title Proceedings of the 4th International Conference on Fracture Fatigue and Wear (FFW 2015)
Editor(s) Magd Abdel Wahab
Publisher Ghent University
Place of publication Belgium
Start page 304
End page 310
Total pages 7
Abstract Continuous growth in the use of composite materials in advanced structural applications, such as aerospace, marine, and automotive, has been observed in the past two decades. This has motivated efficient design and manufacturing of composite products so as to obtain lighter structures with higher strength, durability and life. To contribute to develop an efficient design methodology, the present research has been undertaken. The accuracy and predictive capabilities of finite element models and failure analysis of a specific composite material using the commercial finite element program ABAQUS are evaluated. A set of unidirectional carbon-epoxy composite laminates are modelled under monotonic tensile and compressive loading, and their failure is assessed using the Hashin's failure criterion. The numerical results are compared against carefully conducted experimental test data. The differences between the experimental and numerically predicted values of the maximum principle stress are used to evaluate the accuracy of the finite element models. In the unidirectional (0-degree) composite laminates after the initial ply failure, a varied damage pattern is observed with a difference of 17.7% and 10.5% under tension and compression, respectively. The unidirectional composites under transverse loading (90-degree) show a difference of 10.8% and 0.4% under tensile and compressive loading, respectively. The variations between the experimental and the modelled results are mainly due to approximating and analysing the model in its 2D behaviour, which excludes delamination. Specifically, a composite tested under compression suffers from Brooming Gage Bottom (BGB); so the variation is expected. The Hashin's damage criterion is not suitable when delamination occurs as a dominant failure mode.
Subjects Mechanical Engineering not elsewhere classified
Keyword(s) Carbon-epoxy
Composite materials
Failure criteria
Damage prediction
Copyright notice © Labo Soete, Universiteit Gent
ISSN 2294-7868
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