微型固体火箭脉冲发动机两相流数值模拟  

Numerical Simulation of Two-phase Flow in Micro Pulse Solid Rocket Motor

作　　者：张涵[1] 李旭昌[1] 王宏宇[1] 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《弹箭与制导学报》2014年第5期131-134,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：应用欧拉-拉格朗日模型对某弹用微型固体火箭脉冲发动机进行两相流模拟,建立了三维空间的物理模型和数学模型,研究了纯气相和1~50μm不同直径颗粒对脉冲发动机性能参数的影响。数值模拟结果表明,气相的惯性作用使发动机内流场呈现不均匀分布,不同直径的颗粒在内流场中的分布情况不一样。在同一质量分数下,颗粒直径越大,对气相的传热和阻碍作用就越小,颗粒直径越小,粒子的随流性越好,与气相能量和动量的交换越显著。Euler-Lagrange model was used to solve two-phase flow and simulation in micro pulse solid rocket motor,a three-dimension physics model and a mathematical model of motor flow field were established,the effects of pure gas and particles diameters from 1 ~ 50 μm on pulse solid rocket motor were studied. The numerical simulation result show that the pure gas inertia results in asymmetric distribution of gas-phase field,the distribution of particles is different from different diameter. In the same mass proportion,the bigger the particle is,the less diathermancy and baffle on gas-phase is; The smaller the particle is,the better the flowing property becomes,the more obvious the exchange of energy and kinetic energy with gas-phase is.

关 键 词：微型固体火箭脉冲发动机 两相流 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]