摘要
采用Fluent软件对火箭姿态控制系统小推力冷气推进器的内流场进行了数值仿真,得到了流场压力与马赫数的曲线图。气流在推进器控制口达到音速,通过控制口后加速并相互撞击产生激波,流束相对集中,超音速流经过激波变成亚音速流;亚音速流在直管段扩张达到超音速,在收缩段受压缩减速,流束集中后再次扩张加速,喷嘴喉部气流略大于音速,但喷嘴扩张段内没有激波,推进器工作状态正常。仿真结果与高模试验结果相吻合。
Numerical simulation of the flow field through an attitude control system thruster is conducted with FLUENT software. The distribution of/low field pressure and Mach number is obtained. The flow achieves sonic velocity through the control orifice and the compressed flow produces shock wave. After expanding and being compressed, the flow achieves sonic velocity at the nozzle orifice. The simulation results agree with that of ground experiments.
出处
《火箭推进》
CAS
2010年第2期36-39,共4页
Journal of Rocket Propulsion
关键词
姿态控制系统
推进器
喷嘴
流场
仿真
attitude control system
thruster
nozzle
flow field
simulation
