姿控发动机喷管内流场及推力计算研究

推进技术 ›› 1998, Vol. 19 ›› Issue (6): 50-53.

姿控发动机喷管内流场及推力计算研究

黄琳,郑忠华,吴其芬,任兵

国科科技大学航天技术系;国科科技大学航天技术系;国科科技大学航天技术系;国科科技大学航天技术系

发布日期:2021-08-15

NUMERICAL SIMULATION OF NOZZLE INTERNAL FLOWFIELD AND THRUST FOR ATTITUDE CONTROL ENGINE

Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073

Published:2021-08-15

摘要/Abstract

摘要： 运用时间相关法数值求解定常Ｎ－Ｓ方程和采用有限体积方法离散控制方程，对姿控发动机喷管内流场及其产生的推力进行了计算，得到了较为精细的流场图象。计算结果表明，不同壁面温度条件可以显著改变喷管壁面附近的流场结构及其产生的推力。

关键词: 姿控火箭发动机;喷管气流;纳维尔－斯托克斯方程;推力;计算方法

Abstract: The numerical calculation of the steady full Navier Stodes equations by means of time dependance was discussed.The finite volume method was used in the governing equation to calculate the nozzle interal flowfield and thrust for the attitude control thruster.The numerical results describe the fine structure of the flowfield and show that the varied temperature of nozzle wall will evidently change the flowfield stucture and the thrust

Key words: Attitude control rocket engine;Nozzle flow;Navior Stokes equation;Thrust;Calculation method

黄琳,郑忠华,吴其芬,任兵. 姿控发动机喷管内流场及推力计算研究[J]. 推进技术, 1998, 19(6): 50-53.