Ablation behavior of C/C-SiC-ZrB₂ composites in simulated solid rocket motor plumes

In order to improve the ablation resistance of carbon/carbon (C/C) composites, SiC-ZrB₂ was infiltrated into them by reactive melt infiltration (RMI). Their ablation behavior with a leading edge shape was investigated in the combustion environment of a simulated solid rocket motor (SRM). The results show that after introducing SiC-ZrB₂ ceramic phases into C/C composites, the linear and volume ablation rate of modified leading edge decreased by 26% and 45%, respectively. The high erosion rate of the composites leading edges was mainly attributed to the synergistic effect of thermochemical ablation and mechanical erosion in a high-velocity, high particle concentration two-phase flow of SRM plume environment.