Ramly R.,Flight Technology and Testing Center |
Kuntjoro W.,Flight Technology and Testing Center |
Wisnoe W.,Flight Technology and Testing Center |
Nasir R.E.M.,Flight Technology and Testing Center |
And 2 more authors.
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. © 2015 Penerbit UTM Press. All rights reserved. Source