Abstract: To meet the multiple requirements of dimensional stability, light weight, and high load-bearing capacity for the high resolution spacecraft bearing platform, four different sizes of carbon/carbon (C/C) honeycomb were prepared by the combination of hot pressing and resin impregnation-carbonization processes. Carbon fiber prepreg was used as the raw material to form corrugated sheets by hot pressing, and inorganic adhesive was used to bond the corrugated sheets to form the honeycomb. C/C honeycomb was formed by the impregnation-carbonization process. The mechanical behaviors of different sizes of C/C honeycomb under different load modes were investigated. The results show that the C/C honeycombs prepared by the proposed combined process do not experience nodal debonding, and the compressive strength of the 5 mm edge length honeycomb is 8.2 MPa. The main failure mode of C/C honeycomb is double wall debonding delamination under out-of-plane compression, L and W direction shear process loads. The C/C honeycombs show high compressive strength and good designability and may meet the requirements of future lightweight and high strength spacecraft bearing platforms.