Abstract: To meet the integrated requirements of lightweight design, high load-bearing capacity, and high-temperature resistance for critical thermal structural components such as aircraft wing and control surfaces, carbon/silicon carbide (C/SiC) honeycombs were fabricated using a combined process of stitched preform molding and chemical vapor infiltration (CVI). The mechanical behavior of these honeycombs under various loading conditions was systematically investigated. Through multiscale characterization of the woven architecture of the honeycomb walls, a meso-macro multiscale strength prediction model incorporating pore defects was developed to simulate the progressive damage and failure processes of the honeycomb structure under different compression and shear loading conditions. Results demonstrate that the fabricated C/SiC honeycombs exhibit high dimensional accuracy and exceptional compressive and shear properties, showcasing significantly enhanced specific stiffness and load-bearing capacity compared to conventional honeycomb structures.