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Abstract: The erosion resistance of the needled carbon/carbon composite leading edge was investigated by exposure to the solid rocket motor (SRM) plume. The erosion morphology and microstructure were examined and associated erosion mechanisms discussed. The composite leading edge was severely damaged with large recession and erosion rate after exposure. The results suggest that the erosion behavior was determined by the weak needling structure of the leading edge windward with small thickness in the severe environment of the plume impingement. Erosion mechanisms were combined effects of thermochemical ablation by oxidizing species and thermomechanical erosion by both aerodynamic force and alumina particles. The former weakens the strength of the composite while the latter contributes primarily to high erosion rate in the oxy-lean SRM plume environments. [Copyright &y& Elsevier]

Ti3SiC2/SiC composite has been synthesized by in situ displacement reaction of Si and TiC powders. Its relative density is >98%. Its Vickers hardness was measured to be 8.7 GPa. Its flexural strength and the fracture toughness were 505 MPa and 5.3 MPa·m1/2, respectively. Scanning electron micrograph (SEM) and transmission electron micrograph (TEM) were used to observe the microstructure of the composite. Mechanisms for its high flexural strength and fracture toughness were discussed, respectively. The composite shows a better oxidation resistance than monolithic Ti3SiC2 at high temperatures. The oxidation layers were comprised of an outer layer with coarse TiO2 grains and an inner layer with a mixture of fine-grained SiO2 and TiO2. Its weight gain is only about 7.9 mg/cm2 at 1200 °C in air for 21 h. However, that of Ti3SiC2 is 30 mg/cm2. The results suggested that the in situ formation of SiC improved its oxidation resistance. [Copyright &y& Elsevier]