Self-designed oxygen-kerosene ablation system was employed to propose an ablation test method for testing the ablation property of the thermal structure and material of secondary combustion chamber in solid ducted rocket (SDR). Particle-free erosion and alumina particle erosion tests were performed on the silicone rubber insulation by using this method to analyze the erosion of particles on the surface micro-morphology of the silicone rubber material. Experiment results revealed that the samples without particle erosion swelled and delaminated after ablation

whose mean linear ablation rate was -0.025mm/s; the mean linear ablation rate of the samples with particle erosion was 1.901mm/s

the ceramic layer in center of samples was destroyed by particle absolutely

only the ultrathin pyrolytic layer and the head of carbon fiber (CF) were left

while the rubber matrix

particle fillers and aramid fiber (AF) around CF were oxidized and stripped by high speed flame flow

then the intense erosion damage effect of particle on insulation had been proved. The research shows that the method can simulate the ablation thermal condition of secondary combustion chamber in SDR

meanwhile

this method can also be applied to selection of insulation formula and ablation performance test of insulating materials.