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.
出处
《兵器装备工程学报》
CAS
2016年第9期166-170,共5页
Journal of Ordnance Equipment Engineering
基金
国家自然科学基金"物-伞多体系统动力学与相似性研究"(51375486)
关键词
燃气舵
流固耦合
烧蚀
jet vane
fluid solid coupling
ablation
