Ablative materials play a strategic role in aerospace industry. These materials
produce a thermal protection system which protects the structure, the
aerodynamic surfaces and the payload of vehicles and probes during
hypersonic flight through a planetary atmosphere. In this work, we investigated the effect of refractory zirconium oxide on mechanical, heat stability and ablation properties of asbestos/phenolic/zirconia composites. The asbestos/phenolic/zirconia composites were produced with different percentages of zirconia filler from 7 to 21% with average size of 7 μm and different number of layers of asbestos, say 3 to 6 layers. These ablative composites were made by an autoclave curing cycle process.
The densities of the composites were in the range of 1.68 to 1.88 g/cm3. Ablation properties of composites were determined by oxy-acetylene torch environment and burn-through time, erosion rates and back surface temperature in the first required 20 seconds. Thermal stability of the produced materials was estimated by means of thermal gravimetric analysis, in both air and nitrogen which consisted of dynamic scans at a heating rate of 10°C/min from 30 to 1000°C with bulk samples of about 20±1 mg. The results showed that when the amount of zirconia was raised from 7% to 21%, the erosion rate and the back surface temperature of composites increased by
about 24% and 26% respectively, and the heat capacity of the composites increased by about 85%. Also, the result showed that when the thickness of composites of 4.2 mm was increased to 10.1mm the burn-through time raised by about 226% and erosion rate dropped by about 41%. These composites displayed the maximum flexural strength when the amount of zirconia was about 14%.