558
H. Najmi et al.
Fig. 2 A picture presenting
dimension of an insulated
sample holder and the
position of a thermocouple
5660 fire norms [14]. In order to measure the back face temperature, a K-type thermocouple (0.2 mm diameter) is passed through the sample holder and placed at the
center in such a manner that it touches the center of the sample when the sample
is placed upon it. The thermocouple is connected to a data acquisition card which
records the transient variations of temperature during the test.
The multilayer composite (thickness 13 mm) used in the study consists of four
layers (see Fig. 3) and it is primarily used in aircraft seats and interior panels. In
this composite, the honeycomb structure (thickness 12 mm) is sandwiched between
two laminate sheets. Each laminate sheet (thickness 0.5 mm) is composed of two
layers of glass fiber/phenolic weaved in one another. Laminate sheets are fixed on
both sides of the honeycomb structure using an adhesive and paint is applied on the
laminate at the top. Please note that in Fig. 3, composite without paint and with paint
is shown in order to present different layers clearly. This study does not include the
results concerning composite without paint.
The experimental investigation is divided into two phases (see Table 1). In the
first one, each layer (i.e. laminate, honeycomb and paint) is tested separately at
the incident heat flux of 50 kW/m
2 . In order to observe the thermal decomposition
of paint, it is applied on an aluminum plate (thickness 1.2 mm) which being an
inert material does not take part in fire, and then tested under cone calorimeter. The
results from the first phase help in understanding the decomposition process of each
material individually. Phase 1 study will also help in identifying different stages of
Fig. 3 Picture of multilayer composite without paint (left) and with paint (right)
H. Najmi et al.
Fig. 2 A picture presenting
dimension of an insulated
sample holder and the
position of a thermocouple
5660 fire norms [14]. In order to measure the back face temperature, a K-type thermocouple (0.2 mm diameter) is passed through the sample holder and placed at the
center in such a manner that it touches the center of the sample when the sample
is placed upon it. The thermocouple is connected to a data acquisition card which
records the transient variations of temperature during the test.
The multilayer composite (thickness 13 mm) used in the study consists of four
layers (see Fig. 3) and it is primarily used in aircraft seats and interior panels. In
this composite, the honeycomb structure (thickness 12 mm) is sandwiched between
two laminate sheets. Each laminate sheet (thickness 0.5 mm) is composed of two
layers of glass fiber/phenolic weaved in one another. Laminate sheets are fixed on
both sides of the honeycomb structure using an adhesive and paint is applied on the
laminate at the top. Please note that in Fig. 3, composite without paint and with paint
is shown in order to present different layers clearly. This study does not include the
results concerning composite without paint.
The experimental investigation is divided into two phases (see Table 1). In the
first one, each layer (i.e. laminate, honeycomb and paint) is tested separately at
the incident heat flux of 50 kW/m
2 . In order to observe the thermal decomposition
of paint, it is applied on an aluminum plate (thickness 1.2 mm) which being an
inert material does not take part in fire, and then tested under cone calorimeter. The
results from the first phase help in understanding the decomposition process of each
material individually. Phase 1 study will also help in identifying different stages of
Fig. 3 Picture of multilayer composite without paint (left) and with paint (right)