Experimental Investigation on Thermal Degradation of Multilayer Honeycomb Core Laminate Sandwich Composite in a Cone Calorimeter

摘要

There are a number of composites available but cannot be used in the aircraft because they do not possess the required fire-resistant properties. The fire norms set by the aviation regulatory bodies are very stringent, in order to use any material in aircraft interiors, it should comply with FAR 25.853 norms. This regulation demands that each material in a multilayer material as well as its assembly should comply with the regulation. Therefore, in the present study, a multilayer composite material consisting of four layers is tested in an ISO 5660 cone calorimeter at the incident heat flux of 50 kW/m~2. At first, all the constitute layers (i.e. paint, laminate, and honeycomb) are tested separately at the same heat flux (i.e. 50 kW/m~2) to identify the thermal decomposition process of each material individually. Thereafter, step by step layers are added and three different assemblies are formed and tested under the same heat flux to identify the thermal interaction between each layer. The obtained results confirm that the time to attain the maximum surface temperature increases with an increase in the layers of materials. However, the peak surface temperature attained by the materials increases while the CO emission for the first 300 s decreases with the increase in the material layers.