Publication

Abstract : Modern atmosphere re-entry space capsule, international space stations (ISS), rockets and missiles are protected using thermal protection system (TPS) materials, thermal barrier coating (TBC) and ultra high temperature ceramic (UHTC) materials. Designing thermal protection system (TPS) is a challenging task for the success of re-entry space vehicles. The TPS may be ablative or non-ablative heat shield material which is subjected to very high thermal stress at the time of re-entry. To design a heat shield, the prediction of aerodynamic heating is an important parameter, which has to be known very accurately for hypersonic speed. Modeling the catalytic recombination of nitrogen and oxygen on a silica based material for re-entry heating results are compared with experimental data (Jumper et al. 1993). A new model for similar reaction was proposed and predicted over silica TPS material (Nasuti et al 1993). Chemical-kinetic parameters which govern the flow in the shock layer over a blunt body configuration entering Earth’s atmosphere for carbon phenolic was derived and reported (Park et al 2001). Experimental investigation of the interaction of SiO2 fine powders with shock-heated nitrogen test gas in a shock tube was studied extensively (Jayaram et al 2019).