大型固体火箭发动机喷管故障诊断的流场计算  

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

作　　者：徐旭[1] 蔡国飙[1] 吕振中[1] 

机构地区：[1]北京航空航天大学宇航学院

出　　处：《推进技术》1998年第3期39-43,共5页Journal of Propulsion Technology

基　　金：航空基金资助项目

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。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

关 键 词：固体火箭发动机 喷管 故障诊断 流场 数值仿真 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]