微型推进器流场数值模拟  

Numerical Simulation of Micro Thruster Flows

作　　者：杨海威[1] 朱卫兵[1] 赵阳[2] 

机构地区：[1]哈尔滨工程大学,哈尔滨150001 [2]哈尔滨工业大学,哈尔滨150001

出　　处：《导弹与航天运载技术》2009年第5期53-56,共4页Missiles and Space Vehicles

摘　　要：深入研究微喷管内流场性能有助于微推进系统的优化设计。利用微喷管内流动与壁面传热的耦合计算,对微喷管流场进行数值模拟。对喷管内流体模拟采用直接蒙特卡罗法,壁面材料热响应采用瞬时热传导方程进行建模,并用有限差分法求解。研究结果表明,针对高温流体,分别以壁面固定温度加载和以时时更新的热流密度加载壁面材料,流场马赫数、温度和压力显现出较大差异,较高的压力能提高微喷管的推进效果,但高压力也使微喷管的热损失增加。Further study on flow field character in micro nozzle will contribute to optimize the design of micro propulsion system. The coupling calculation of thermal-fluid in the simulation of micro-nozzle and mural heat transfer are adopted. The gas flow solution is modeled by the direct simulation Monte Carlo method. The thermal response of mural material is modeled by the transient heat conduction equation which is solved by the finite element method. The Simulation results show that for high-temperature fluid, loading the mural material with the fixed temperature or the heat flux updated time by time, the flow field March number, temperature and pressure show great differences, and the higher pressure can improve the propulsion effect of micro nozzle, but it also increases the heat loss of micro nozzle.

关 键 词：微喷管 数值模拟 蒙特卡罗法 尺度效应 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]