燃气二次喷射对推力矢量控制发动机内流场的影响

Effects of Secondary Hot Gas Injection on Inner Flow Field of Thrust Vector Control Motor

采用准一维非定常N-S方程对固体火箭发动机燃气二次喷射推力矢量控制过程进行数值仿真,研究燃气引出和燃气二次喷射对发动机燃烧室及喷管内流场的影响。重点研究了燃气引出对燃烧室压强波动的影响并对其形成机理进行了初步分析。结果表明,燃气二次喷射推力矢量控制工作过程中,燃烧室压强波动很大,速度在一定程度上脉动,温度基本上不受影响。由于高温高速二次燃气的加入,喷管扩散段二次喷射孔附近及其下游喷管内压强、速度和温度有明显的变化。

The working process of secondary hot gas injection thrust vector control for solid rocket motor is numerically simulated using quasi-one-dimensional unsteady N-S equations. The influences of the hot gas ejection and secondary hot gas injection on the inner flow field of the chamber and nozzle are studied. The influence of the hot gas ejection on the pressure fluctuation of the chamber is also studied and its forming mechanism is analyzed. Results indicate that the pressure fluctuation of the chamber is very large and the velocity of the chamber to a certain extent fluctuates and the temperature of the chamber is not influenced by the working process of secondary hot gas injection thrust vector control. The pres- sure, the temperature and the velocity of the nozzle nearby the secondary injecting hole, and its downstream are obviously changed as the injecting of the secondary hot gas with the high temperature and the high velocity.