大长径比固体火箭发动机点火瞬态内流场特性分析  

Analysis of Inner Flow Characteristic of Ignition Transient for Large Aspect Ration Solid Rocket Motor

作　　者：杨乐 余贞勇 何景轩 Yang Le;Yu Zhen-yong;He Jing-xuan(National Key Lab of Combustion,Flow and Thermo-structure,Xi’an,710025)

机构地区：[1]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》2018年第4期33-36,共4页Missiles and Space Vehicles

摘　　要：基于FLUENT流体力学软件,通过用户自定义函数(User-defined Function,UDF)及进口边界条件考虑燃烧室侧壁加质方式,针对大长径比固体火箭发动机燃烧室内流场进行数值分析,研究了发动机内压强、温度随时间变化规律及发动机内燃气的流动特性。计算结果表明:带有翼槽的大长径比固体火箭发动机点火初始时刻头部压强会出现振荡,翼槽末端燃气会有涡流现象发生;同时,翼槽处火焰传播呈现一定的连续性。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 the large aspect SRM is simulated.The rule of pressure and temoerature change with time and inner flow characteristic is mainly annlyzed.The results show that the front pressure of the large aspect SRM with fin-slot will be oscillated in the initial ignition time.Vortex is generated in the bottom of th fin-slot.Meanwhile,the flame spreading speed of the fin-slot expresses continuity.

关 键 词：固体火箭发动机 内流场 数值模拟 火焰传播 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]