微推偏火箭喷管非对称内流场数值模拟

NUMERICAL SIMULATION FOR NONSYMMERICAL INTERNAL FLOW IN THE MINI THRUST MISALIGNMENT ROCKET NOZZLE

关键词:  火箭发动机喷管  偏航力矩  流动分布  数值仿真

Key words:  Rocket engine nozzle  Yawing moment  Flow field  Numerical simulation

摘要:

研究了入流倾斜于喷管超音速段轴线的微推偏喷管内流场。数值方法是具有高分辨率高精度的三维隐式有限体积的ＴＶＤ格式。针对一系列典型锥形喷管和钟型喷管，数值模拟结果得出非对称内流场的侧向力和侧向力矩随喷管几何结构以及入流条件变化的一些特征，并同有关实验结果符合良好，对微推偏喷管设计具有一定的指导意义。

Abstract:

The internal flow in the mini thrust misalignment nozzle where the inlet flow is not parallel with the axis of its supersonic section is studied.Three dimensional implicit finite volume TVD scheme with high distinguishability and accuracy resolution is used in the numerical method.For some typical conic and contour nozzles,the characteristics of the change of the side force and moment produced by non symmetrial internal flow with the geometrical structure and inlet flow conditions of nozzles are describled.The numerical results agree well with some related experiment results.This method can be used as a guide for the design of mini thrust misalignment nozzles and the selection of rocket nozzles.