摘要
在火箭尾焰电磁波衰减影响研究中,需要了解火箭尾焰流场等离子体浓度分布。使用数值方法计算了固体火箭尾焰流场参数,应用等离子体浓度计算模型,对火箭尾焰流场等离子体浓度分布进行了数值计算,并对仿真计算结果进行分析,为研究穿越火箭尾焰电磁波干扰提供研究数据。
The plasma density distribution field of the rocket plume flow was needed for research of the electromagnetic wave attenuation through the rocket plume. The parameter distribution of a solid propellant rocket plume flow field was computed using the method of numerical simulation. Then the plasma density distribution field of the rocket plume flow was simulated with a computational plasma density model. The results of the numerical simulation of the solid propellant rocket plume flow field were analyzed. The data of simulation results are provided for research of the electromagnetic wave attenuation through the rocket plume.
出处
《科学技术与工程》
2008年第4期965-970,共6页
Science Technology and Engineering
关键词
固体火箭发动机
数值分析
尾焰流场
等离子体
solid propellant rocket engine numerical simulation rocket plume flow field plasma
