The invention belongs to the field of refractory metal and composite materials thereof, and discloses a thermal barrier ablation-resisting composite coating. The composite coating is arranged on a metallic matrix and sequentially comprises a bonding layer and a thermal barrier layer from the surface of the metallic matrix to the outer side. The thermal barrier layer is made of thermal insulation ceramics and tungsten and/or molybdenum composite powder. The thermal barrier ablation-resisting composite coating has good high-temperature resistance, ablation resistance, oxidation resistance, erosion resistance and antistrip performance and is especially suitable for being used in the environment with the powerful airflow and low the cost. The thermal barrier ablation-resisting composite coating can be applied to the surfaces of marine engines, ground gas turbines, wings, emages and rubber pieces of aircrafts and other components working at the high temperature to conduct thermal protection on the components, and therefore the service life of the metallic matrix is prolonged. The thermal barrier ablation-resisting composite coating can be used in different working environments or for meeting some special use requirements by changing the component content of the thermal barrier layer and the coating structure.