Ablation Properties Experiments of C/SiC Throat-Insert in Operational Environment of Rocket Engine
The ablative performance of the C/SiC ceramic matrix composite material is studied experimentally using a experimental system based on solid rocket motor and liquid rocket engine in this paper. It is mainly studied how the ablative performance is influenced by ablation time, particle and temperature. It is indicated that the ablative performance decays with longer ablation time. The ablation becomes acute when the temperature is higher than 2973K, and the higher temperature, the more significant ablation. In addition, a large amount of vapor increases the thermochemical ablation of the material.
X. G. Wei et al., "Ablation Properties Experiments of C/SiC Throat-Insert in Operational Environment of Rocket Engine", Advanced Materials Research, Vol. 304, pp. 165-168, 2011