固体火箭发动机射流推力矢量喷管气固两相流数值模拟  

The Numerical Simulation on Gas-solid Two-phase Flow in Jet Thrust Vector Nozzle of SRM

作　　者：宋亚飞[1] 高峰[1] 张志峰[1] 文科[1] 

机构地区：[1]空军工程大学导弹学院,陕西三原713800

出　　处：《弹箭与制导学报》2011年第6期133-136,140,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：用颗粒轨道模型对基于激波控制的二维收缩扩张(2DCD)喷管中的气固两相流动进行了数值模拟,并与纯气相条件下的计算结果进行了对比分析,研究了1～40μm不同直径颗粒的运动轨迹和内流场参数的分布特征,并对矢量喷管的推力性能进行了研究。研究表明,颗粒相的加入和颗粒直径的变化对矢量喷管的内流场和推力性能都有较大影响。在进行射流推力矢量喷管的设计和性能计算时一定要考虑颗粒相的影响。Numerical simulation of gas-solid two-phase flow in jet thrust vector nozzle was carried out using particle trajectory model based on shock wave control.The simulation results were compared with that under the situation of pure gas.The particle track,parameters in internal flow,as well as the thrust performance were studied when particles＇ diameter changed in the range of 1~ 40μm.The results showed that the addition of particle had certain influence on both internal flow field and thrust performance of vector nozzle.Moreover,the change of particle diameter could affect these characteristics.Therefore,these influences must be taken into consideration for nozzle design and research.

关 键 词：固体火箭发动机 射流推力矢量喷管 两相流 颗粒轨道模型 数值模拟 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]