基于FLUENT的固体火箭发动机点火瞬态内流场仿真影响因素分析  

A FLUENT analysis of influencing factors for SRM inner flow field simulation at ignition

作　　者：杨乐[1] 余贞勇[1] 何景轩[1] 

机构地区：[1]中国航天科技集团公司第四研究院第四十一研究所固体火箭发动机燃烧热结构与内流场国防科技重点实验室,西安710025

出　　处：《固体火箭技术》2011年第4期474-477,共4页Journal of Solid Rocket Technology

摘　　要：应用FLUENT流体计算软件,采用UDF接口编程进行二次开发,用侧壁加质的方法模拟燃烧室加质,对固体火箭发动机内流场进行了数值模拟。针对影响仿真结果的主要因素,即点火器简化方式、点火器出口参数的选取方式和点燃方式三个方面进行分析。结合试验数据,得出点火器采用多条环形缝结构和点火器出口参数采用实测曲线,同时,点燃方式为动态温度判据时,可使仿真结果与实际情形更加吻合。The secondary development based on FLUENT software was implemented using UDF interface programme,in which the additional mass of combustion chamber was simulated with profile adding mass,and the inner flow field of SRM was simulated.The main influence factors of simulation,including simplifying mode of igniter,selection mode of igniter output parameters and firing mode,all three cases were analyzed.In order that the simulation results are well consistent with practical situation,it is concluded based on test data that igniter of these should be taken in form with many cirque and it＇s output parameters be taken practical curve,as well as,firing mode be taken dynamic temperature criterion.

关 键 词：固体火箭发动机 内流场 数值模拟 点燃方式 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]