大型固体火箭发动机喷管故障诊断的流场计算

推进技术 ›› 1998, Vol. 19 ›› Issue (3): 39-43.

大型固体火箭发动机喷管故障诊断的流场计算

徐旭,蔡国飙,吕振中

北京航空航天大学宇航学院;北京航空航天大学宇航学院;北京航空航天大学宇航学院

发布日期:2021-08-15
基金资助:
航空基金资助项目

NUMERICAL SIMULATION FOR FAILUREOF NOZZLE BURN THROUGH INSOLID ROCKET MOTOR

School of Astronautics,Beijing Univof Aeronautics and Astronautics,Beijing,100083;School of Astronautics,Beijing Univof Aeronautics and Astronautics,Beijing,100083;School of Astronautics,Beijing Univof Aeronautics and Astronautics,Beijing,100083

Published:2021-08-15

摘要/Abstract

摘要： 针对某大型固体火箭发动机的喷管喉道后烧穿的故障进行了数值模拟，运用ＴＶＤ（ＴｏｔａｌＶａｒｉａｔｉｏｎＤｉｍｉｎｉｓｈｉｎｇ）ＭａｃＣｏｒｍａｃｋ格式求解了喷管内流场的二维轴对称Ｎ－Ｓ方程，获得了流场的详细结构图谱，分析了故障的成因，指出喷管型面的导数不连续会导致当地壁温升高，是引发故障的直接原因。

关键词: 固体推进剂火箭发动机;火箭发动机喷管;故障诊断;流动分布;数值仿真

Abstract: A high resolution TVD(Total Variation Diminishing)MacCormack scheme was used to solve the 2 D axisymmetric N S equation in a large solid rocket motor nozzleThe details of flow fields were examined carefully in order to find the reason of burn through failureThe research results show that the derivative function discontinuity of nozzle profile can cause a sudden rise of temperature,which greatly enhances the burning erosion of nozzle profile and may be the direct reason of the failureThis conclusion agrees with the results of simulation tests

Key words: Solid propellant rocket engine;Rocket engine nozzle;Failure diagnosis;Flow distribution;Numerical simulation

徐旭,蔡国飙,吕振中. 大型固体火箭发动机喷管故障诊断的流场计算[J]. 推进技术, 1998, 19(3): 39-43.