A supersonic oxygen-enriched ablation test method for the controllable internal flow-field of the ablation thermal en-vironment was constructed by using the design principles of oxygen/kerosene liquid rocket engines.Then,a combination of ablation engine ignition test and CFD numerical simulation was used to analyze and validate the reliability of the constructed ablation test method and mathematical model,and further analyze the key ablation thermal environment characteristic parameters during the abla-tion test process.Then,the ablation resistance and ablation mechanism of three-dimensional four-way braided C/C composites under supersonic oxygen-enriched ablation environment were analyzed.The results show that changes in the ablative thermal environment can have a certain degree of impact on the material's ablation resistance and mechanism.In the convergent high-temperature and low-speed ablative thermal environment,the linear ablation rate of C/C composites is relatively low,about 6.50×10-3 mm/s,and the material's ablation is mainly thermal oxidation ablation.In the straight section area of the ablation specimen throat,the linear abla-tion rate of C/C composites gradually increases,reaching 1.35×10-2 mm/s.At this time,the ablation of the material is manifested as mechanical ablation after thermal oxidation ablation.After a sharp increase in gas velocity in the expansion section of the ablation sample,the linear ablation rate of C/C composites significantly increased,reaching 2.61×10-2 mm/s at the sample outlet,and the main manifestation of material ablation is mechanical ablation.
维普
万方数据
