固体火箭发动机点火瞬态内流场计算模型分析  

Calculation Model of Inner Flow Field of Solid Rocket Motor in Ignition Transient

作　　者：杨乐 余贞勇 何景轩 

机构地区：[1]西安航天动力技术研究所,燃烧、流动和热结构国家级重点实验室,西安710025

出　　处：《导弹与航天运载技术》2015年第6期75-77,共3页Missiles and Space Vehicles

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,对带有翼槽的固体火箭发动机内流场进行了数值模拟,比较了不同计算模型下的仿真结果。计算结果表明,考虑了翼槽结构对点火瞬态过程的火焰传播速度影响的计算模型更加符合实测值。The secondary development based on FLUENT software is implemented using UDF interface programme, in which the additional mass of combustion chamber is simulated with profile adding mass and the inner flow field of SRM is simulated. The simulation results of different calculation models are compared and the calculation results show that the calculation model considering the influence of fin-slot structure on flame spreading speed in ignition transient is more consistent with practical situation.

关 键 词：固体火箭发动机 内流场 火焰传播速度 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]