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为预测无纬布复合毡穿刺C/C复合材料固体火箭发动机的喷管烧蚀性能，探究材料热导率与喷管烧蚀率之间的关系，在Fluent平台上建立喷管烧蚀模型，以70-lb BATES发动机为算例进行验证。对材料的单胞模型进行稳态热仿真，获得材料的导热属性；利用喷管烧蚀模型对材料烧蚀性能进行仿真分析。结果表明：喷管材料的烧蚀率随推进剂中Al质量分数的增加而降低，在Al质量分数为15%、18%、21%的工况下，无纬布复合毡穿刺C/C复合材料喷管的烧蚀率均低于石墨材料喷管，差值为0.045～0.070 mm/s;烧蚀过程在约4 s时达到稳定状态，烧蚀率在喷管喉部前端达到峰值；烧蚀率在低温下主要受温度影响，高温下则主要受组分扩散速率的影响；喷管喉部的烧蚀率在材料x、y方向上随热导率的增大而增大，在材料z方向上则随热导率增大而减小。
Abstract：A nozzle ablation model was established on the Fluent platform, to predict the nozzle ablation performance of weftless composite felt-punctured C/C composites and investigate the correlation between material thermal conductivity and the nozzle ablation rate. The model was validated through the use of the 70-lb BATES engine nozzle. A steady-state thermal simulation of the material's single-cell model was conducted to ascertain its thermal conductivity properties. The ablation properties of the material were simulated and analyzed using the nozzle model. The results reveal that the ablation rate decreases as the aluminum(Al) mass fraction in the propellant increases. The ablation rate of weftless composite felt pierced C/C composite nozzle is lower than that of graphite nozzle under Al mass fraction of 15%, 18% and 21%, with the difference ranging from 0.045 to 0.070 mm/s. The ablation process attains a steady state at approximately 4 s, with the ablation rate peaking at the front end of the nozzle throat. At lower temperatures, the ablation rate is primarily governed by temperature, whereas at higher temperatures, it is mainly influenced by the diffusion rate of components. The ablation rate of the nozzle throat increases with higher thermal conductivity in the x and y directions of the material but decreases in the z direction.
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基本信息:
DOI：10.19886/j.cnki.dhdz.2024.0328
中图分类号:V435;V258
引用信息:
[1]孙志宏,李俊杰,曲志洋.穿刺C/C复合材料固体火箭发动机喷管烧蚀性能仿真[J].东华大学学报(自然科学版),2025,51(06):169-175.DOI:10.19886/j.cnki.dhdz.2024.0328.
基金信息:
上海市轻质结构复合材料重点实验室开放课题基金(2232021A4-04)