Abstract:
Ablative composites are also called as thermal protection system (TPS) which have a wide application in rocket nozzles, engine throats and leading edges. They are used to protect the metallic structure or component usually from high temperature environments by sacrificing its surface. In this particular case, carbon cloth from three different sources with different properties was used as reinforcement material and phenolic resin was used as matrix. The ablation behavior was observed at SCME, NUST.
For ablation test, a set up was made at workshop of SCME in which Oxy Acetylene flame was used as heating source and back face temperature of the sample was recorded by using data logger. The effect of different densities, carbon content and breaking load of carbon cloths on ablation resistance of the composite was observed while all other factors like weight percentage of reinforcement, orientation of fibers and curing temperature etc. were kept constant. It was observed that the composite with the most dense carbon cloth had the maximum resistance to ablation. The linear and mass ablation rates of the samples were also calculated and compared.
