固体火箭发动机点火瞬时内流场轴对称数值分析  

Axisymmetric numerical analysis for ignition transient interior flow field of SRMs

作　　者：陈军涛[1] 蹇泽群[1] 陈林泉[1] 

机构地区：[1]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2004年第3期173-176,共4页Journal of Solid Rocket Technology

摘　　要：应用流体计算软件(FLUENT),通过UDF(用户定义函数)编程,考虑了辐射热量的影响,对固体火箭发动机点火瞬时内流场进行了轴对称数值分析,得出了点火瞬时的压强 时间曲线、各时刻的流场和推进剂燃面上的辐射热量。从具体数值上分析了辐射热量对点火瞬时的影响。研究结果表明,该方法可较好地预示点火瞬时的内流场和压强变化情况。Through fluid calculation software (FLUENT) and user definition function (UDF) programming, an axisymmetric numerical analysis method which takes into account the influence of heat radiation was used for analysis of the ignition transient interior flow field of SRM. The results show that the curve of pressure vs time, flow field at different time, heat radiation on the burning surface of propellant can be obtained. The influence of heat radiation on ignition transient can be analyzed through the concrete figures, and the method can be used to predict the flow field and pressure variation at ignition transient.

关 键 词：固体火箭发动机 点火 推进剂 FLUENT 流场 轴对称 瞬时 变化情况 数值分析 曲线 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] U116.2[交通运输工程]