DETERMINATION OF DELAMINATION SIZE IN HONEYCOMB SANDWICH PANEL USING FINITE ELEMENT METHOD

Authors

  • Ramzyzan Ramly Flight Technology and Testing Centre, FTTC, Faculty of Mechanical Engineering, UiTM Shah Alam, Malaysia
  • Wahyu Kuntjoro Flight Technology and Testing Centre, FTTC, Faculty of Mechanical Engineering, UiTM Shah Alam, Malaysia
  • Wirachman Wisnoe Flight Technology and Testing Centre, FTTC, Faculty of Mechanical Engineering, UiTM Shah Alam, Malaysia
  • Rizal Effendy Mohd Nasir Flight Technology and Testing Centre, FTTC, Faculty of Mechanical Engineering, UiTM Shah Alam, Malaysia
  • Aman Mohd Ihsan Mamat Flight Technology and Testing Centre, FTTC, Faculty of Mechanical Engineering, UiTM Shah Alam, Malaysia
  • Firdaus Mohamad Flight Technology and Testing Centre, FTTC, Faculty of Mechanical Engineering, UiTM Shah Alam, Malaysia

DOI:

https://doi.org/10.11113/jt.v75.5220

Keywords:

Determination of delamination, size, honeycomb sandwich panel, finite element method

Abstract

This paper describes the determination of a relative delamination size of the skin to the honeycomb core of the honeycomb sandwich panel using the Finite Element Method approach. In the analysis, the honeycomb sandwich panel was modelled in the actual dimension using CATIA. The delamination of two different sizes (10 mm diameter and 30 mm diameter) were modelled to simulate the delamination cases. Using Nastran/Patran, the models underwent a three-point-bending test in order to simulate a result. The results were compared between the case of no delamination, 10 mm delamination, and 30 mm delamination. From the simulation, there was a significant difference of displacement of the skin (facing) between the 10 mm diameter delamination and the 30 mm diameter delamination.  

References

Herrmann, A. S., Zahlen, P. C. and Zuardy, I. 2005. Sandwich structures technology in commercial aviation: Present applications and future trends. Sandwich Structures 7: Advancing with Sandwich Structures and Materials. O. T. Thomas and e. al., Eds., ed Netherlands: Airbus Deutschland GmbH: 13-26.

Stickler, P. 2002. Composite materials for commercial transport-issues and future research directions. Americal Society for Composites 17th Technical Conference, West Lafayatte, Indiana, USA.

Niu, M. C. Y. 2008. Composite Airframe Structures: Practical Design Information and Data. Hong Kong: Hong Kong Conmilit Press Ltd.

Van-Tooren, M. J. L. 1998. Sandwich Fuselage Design. PhD, Faculty of Aerospace Engineering, Delft University of Technology, Delft, the Netherlands.

Takeda, N., Minakuchi, S. and Okabe, Y. 2007. Smart composite sandwich structures for future aerospace application - Damage detection and suppression-: A review. Journal of Solid Mechanics and Materials Engineering. 1: 3-17.

Davies, G. A. O., Hitchings, D. and Ankersen, J. 2006. Predicting delamination and debonding in modern aerospace composite structures. Composite Science and Technology. 66: 846-854.

Chen D. H. and Ozaki, S. 2009. Stress concentration due to defects in a honeycomb structure. Composite Structures. 89: 52-59.

Han, T.-S., Ural, A., Chen, C.-S., Zehnder, A. T., Ingraffea, A. R. and Billington, S. L. 2002. Delamination buckling and propagation analysis of honeycomb panels using a cohesive element approach. International Journal of Fracture.115: 101-123,.

Cerracchio, P., Gherlone, M., Sciuvia, M. D. and Tessler, A. 2015. A novel approach for displacement and stress monitoring of sandwich structures based on the inverse Finite Element Method. Composite Structures. 127: 69-76.

I. Core Composites. Nomex Honeycomb: Lightweight Non-Metallic Composite Honeycomb. [Online] From: www.corecomposites.com/composites/core/honeycomb/nomex/.[2012, 20 March 2013].

H. Corporation. 1999. HexWeb Honeycomb Attributes and Properties: A comprehensive guide to standard Hexcel honeycomb materials, configurations and mechanical properties. ed. Pleasanton, California: Hexcel Composite.

P. C. Ltd. Mechanical Properties of Carbon Fibre Composite Materials. [Online] From: www.performance-composites.com/carbonfibre/mechanicalproperties_2.asp. [2009, 20 March 2013].

Downloads

Published

2015-08-20

Issue

Section

Science and Engineering

How to Cite

DETERMINATION OF DELAMINATION SIZE IN HONEYCOMB SANDWICH PANEL USING FINITE ELEMENT METHOD. (2015). Jurnal Teknologi (Sciences & Engineering), 75(8). https://doi.org/10.11113/jt.v75.5220