新型炭材料2017，Vol.32Issue(4)：365-373,9.DOI:10.1016/S1872-5805(17)60128-8
固体火箭发动机实验条件下基于拉瓦尔喷管变流道参数的4D编织C/C复合材料烧蚀性能
Ablation performance of a 4 D-braided C/C composite in a parameter-variable channel of a Laval nozzle in a solid rocket motor
摘要
Abstract
Ablation of a 4D-braided C/C composite fabricated with axial rods in the parameter-variable channel of a Laval nozzle ( or a convergent-divergent nozzle, a tube that is pinched in the middle) was performed in the experimental conditions of a solid rocket motor. Gas-solid flow and erosion were also simulated with the discrete phase model. The ablation of the composite was caused by thermochemical and mechanical erosion and was analyzed based on the morphology of different sections of the channel in the nozzle with different angles between the gas flow direction and the surface of the composite ( ablation angle) . Results showed that the ablation behavior was related to the velocity, concentration, collision angle to the surface and the wall shear force of parti-cles in the ablation gas. The ablation gradually increased with the rate of gas flow and was a maximum at the maximum ablation an-gle of 45° in the compression section. In the expansion section, beyond the throat, ablation decreased significantly. The maximum linear and mass ablation rates were 0. 056 mm/s and 0. 157 kg/m2·s, respectively. The carbon fibers formed a tapered tip, whose sharpness depended on the ablation angle and the braiding direction.关键词
炭/炭复合材料/喉衬/固体火箭发动机/轴向炭棒/烧蚀Key words
C/C composites/Throat insert/Solid Rocket Motor/Axial carbon rods/Ablation分类
化学化工引用本文复制引用
惠卫华,鲍福廷,魏祥庚,刘旸..固体火箭发动机实验条件下基于拉瓦尔喷管变流道参数的4D编织C/C复合材料烧蚀性能[J].新型炭材料,2017,32(4):365-373,9.基金项目
国家自然科学基金(51005179).Foundation item:National Natural Science Foundation of China (51005179). （51005179）
