In order to improve the working performance of the reentry aircraft

the carbon/carbon-silicon carbide (C/CSiC) composite test specimens were prepared using the chemical vapor infiltration process

and the test specimens were tested for strength and thermal shock resistance. The ablation tests were performed in the reentry flight environment

the ablation rate of the test specimens were measured

the ablation morphology of the test specimens were observed

and the ablation mechanism was analyzed. The results show that the bending and tensile strengths of the test specimens are 286.5MPa and 184.3MPa respectively

and the thermal shock resistance parameter is 42.4kW/m. The ablation rate of the stagnation point of the specimen is the largest

and the line ablation rate is 0.0445mm/s

and the mass ablation rate is 0.0472g/s. Because of the SiC in this area is consumed by gasification

the protection effect is not obvious. The ablation mechanisms are gasification and oxidation reactions. In the other area

the SiO

2

produced by the reaction is precipitated around the specimens

thus effectively retarding oxidation reaction. On the whole

the material gives its outstanding mechanical properties and anti-ablative performance.