冷气推进器流场仿真和分析  

Simulation and research of the nitrogen thruster flow field

作　　者：王定军[1] 宋会玲[1] 刘伟[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2010年第2期36-39,共4页Journal of Rocket Propulsion

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.

关 键 词：姿态控制系统 推进器 喷嘴 流场 仿真 

分 类 号：V439.7[航空宇航科学与技术—航空宇航推进理论与工程]