Abstract: The rapid development of high-speed aircraft has created an urgent demand for anti- ablation and high-load-bearing ultra-high temperature ceramic matrix composites. C_f/C-SiC-ZrC composites exhibit well load-bearing capacity and excellent oxidation and ablation resistance, demonstrating tremendous application potential. The precursor infiltration pyrolysis (PIP) combined with reactive melt infiltration (RMI) process is an effective way to improve the preparation efficiency, reduces the cost, and enhance the performance of C_f/C-SiC-ZrC composites. However, in the PIP-RMI process, the ceramics formed during the initial PIP procedure hinder the subsequent infiltration and reaction of the liquid metal, which reduced the mechanical and ablation properties of the composite. This work proposed a novel process for preparing C_f/SiC-ZrC composites through firstly applying RMI (Si-Zr alloy) followed by PIP (SiC precursor). The microstructure, composition distribution, mechanical properties, and ablation resistance of the composites were investigated. The mechanical properties of the C_f/SiC-ZrC composites significantly improve with the increase of PIP cycles, the tensile, compressive and flexural strength reaching 197.0 MPa, 228.3 MPa and 301.3 MPa, respectively, after 3 cycles. The linear and mass ablation rates of C_f/SiC-ZrC composites are only −3.04×10⁻³ mm·s⁻¹ and 1.51×10⁻³ g·s⁻¹, respectively, after ablated at 2400℃ for 100 s by oxy-acetylene flame, which meeting the requirements for anti-ablation and high load-bearing, and demonstrating broad application prospects.