Fabrication of 2D C/ZrC–SiC composite and its structural evolution under high-temperature treatment up to 1800°C

Calculation and synthesis of ZrC by CVD from ZrCl4–C3H6–H2–Ar system with high H2 percentage

“…They have been widely used in aircraft and aerospace as thermal protection systems (TPS) [1][2][3][4]. However, the ablation resistance of C/SiC cannot meet the requirements of TPS in the environments with high-speed gas flow washout and high-pressure because the protecting silica layer becomes active at ultrahigh temperatures [5,6]. Thus, refractory compound coatings are usually used to increase the performance of C/SiC materials.…”

Fabrication of C/SiC composites by combining liquid infiltration process and spark plasma sintering technique

“…Moreover, it is expected that the graphitization treatment also contributes to increase the thermal conductivity of the composite and improves its oxidation resistance [12][13][14]. Figure 1 shows the evolution of pore size distribution, obtained by Hg porosimetry, with the number of infiltration/carbonization cycles applied.…”

Ablation mechanism of C/C–ZrB 2 –ZrC–SiC composite fabricated by polymer infiltration and pyrolysis with preform of C f /ZrB 2

“…In comparison with the case of ZrC, the oxidation of the ZrB 2 phase can produce some B 2 O 3 gas (melting point 723 K), which can be volatilized rapidly during ablation. It was reported [23] that the addition of ZrB 2 into the C/SiC composites could decrease the maximum surface temperature of the composites, and the low emissivity of ZrB 2 was responsible for the lower emissivity of the composites. Additionally, the fusion and evaporation of the SiO 2 phase (melting point 1923 K) are considered to play a positive role in dissipating the heat in the composites.…”