An external thermal protection coating was developed for the aerospace vehicle with high-mach number speed and long flight time. The effects of functional fillers including silicates, fibers and hollow microspheres on the forming process and the ablation resistance of the coating were studied. Meanwhile, the performance of thermal protection coating was investigated by wind tunnel tests under different heat flow conditions. When the coating thickness was 3~5 mm and the maximum heat flow of wind tunnel was 1460 kW/m2, the interfacial temperature between the composite sample and the coating varied between 64 and 72.