Research on the properties of carbon/carbon silicon carbide (C/C SiC) composites in hypersonic jets

DOI:	10.11809/bqzbgcxb2023.06.041
Keywords:	carbon/carbon silicon carbide (C/C SiC) composite; hypersonic; mechanical properties; microstructure; ablation mechanism
Abstract:	In order to improve the thermal protection performance of hypersonic aircraft, this paper prepares carbon/carbon silicon carbide (C/C SiC) composites through the axial rod method and chemical vapor infiltration process. The specimens are placed in hypersonic jets for ablation experiments to test their ablation rate and mechanical properties. The phase composition of the composites is analyzed through X ray diffractometer, their microstructure is observed by scanning an electron microscope and the ablation mechanism in the process is analyzed. The results show that the bending strength before and after the ablation is 92 MPa and 84 MPa respectively; the interlaminar shear strength is 10.6 MPa and 9.1 MPa respectively; the linear ablation rate is 0.047 4 mm/s and the mass ablation rate is 0.038 3 g/s. The carbon fiber of the composites is mainly thermochemical ablation, and the matrix material is subjected to both thermal chemical and mechanical denudation. The SiC particles in the composites are liquefied and deposited at a high temperature, which improves the ablation performance of the specimens. The composites generally show good mechanical properties and ablation resistance.
Published:	2023-06-28
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