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通过对密度1.8 g/cm3针刺炭纤维炭/炭复合材料喉衬中炭纤维、热解炭、树脂炭体积分数优化设计和控制,并匹配以大装炉量的三路进气、多沉积室均热法CVI与高效的树脂浸渍/炭化相结合致密工艺,2 600℃热处理,制备了低成本、低开孔率、低烧蚀率的针刺炭纤维炭/炭复合材料喉衬。其1 800℃的拉伸强度径向达到109.8 MPa,轴向达到21.3 MPa,在火箭弹高压强固体火箭发动机中的烧蚀率仅为0.05~0.09 mm/s。并揭示了炭纤维、热解炭、树脂炭互为补充优化组合及致密工艺与材料低开孔率的关联。为火箭弹高压强固体火箭发动机增添了一种低烧蚀率高可靠的喉衬材料。
By optimizing the volume fraction of carbon fiber, pyrolytic carbon and resin charcoal in the throat lining of carbon fiber carbon / carbon composites with a density of 1.8 g / cm3, the three-way inlet gas, Culvert carbon fiber carbon / carbon composite throat lining with low cost, low open porosity and low ablation rate was prepared by combining CVI with highly efficient resin impregnation / carbonization in a dense process and 2 600 ℃ heat treatment. The tensile strength at 1 800 ℃ reached 109.8 MPa in radial direction and 21.3 MPa in axial direction, and the ablation rate was only 0.05-0.09 mm / s in Rocket Launch High Pressure Solid Rocket Motor. The correlation between carbon fiber, pyrolytic carbon and resin-carbon, and the combination of densification process and material’s low porosity were revealed. Add a low-ablation rate, high-reliability throat lining material to rockets high-pressure solid rocket motors.