摘要
固体火箭发动机燃气舵的烧蚀主要包括Al2O3颗粒冲刷、化学烧蚀,采用商业软件FLUENT对某型号的固体火箭发动机尾流场和钨渗铜燃气舵的流场进行模拟,通过气固双向耦合计算稳态和瞬态的燃气舵的内部温度场分布和变化过程;编写插入UDF函数计算燃气舵与高温气流发生反应造成的化学烧蚀,计算燃气舵的化学烧蚀量。
The ablation of jet vane in the solid rocket motor mainly includes the particle erosion of Al2O3 and chemical ablation. This paper used the commercial software FLUENT to simulate the flow field around the jet vane in the solid rocket motor. The internal temperature field distribution and change of the jet vane was calculated by means of gas solid two way coupling calculation. The UDF function was inserted to calculate the chemical ablation of jet vane caused by the reaction of jet vane and the high temperature gas flow.
引文
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