摘要
采用计算流体方法获得氢氧火箭发动机地面试验射流特征,开展了几何模型、燃烧模型和湍流模型对射流场的影响分析以及与试验结果的定性和定量对比。依据不同试验模式下的射流场温度的数值分布,提出试验台钢板防护方案并进行防护,试验证明方案可靠有效。
The plume characteristics of the hydrogen/oxygen rocket engine were studied with the method of CFD ( computational fluid dynamics ) .The influences of the geometry model , the combus-tion model and the turbulence model on the characteristics of the combustion flowfield were ana-lyzed .The results from the numerical simulation were compared with those from the experiments qualitatively and quantitatively .Based on the distributions of the temperature from the numerical simulation results in the different tests , the armor plate was designed for the thermal protection and applied for the test stage .It is confirmed that the approach is effective and reliable .
出处
《载人航天》
CSCD
2014年第5期421-426,共6页
Manned Spaceflight
关键词
火箭发动机
射流
热防护
数字仿真
rocket engine
injection plume
thermal protection
numerical simulation
