等截面微喷管性能的DSMC/EPSM研究  

Research on the Performance of Micro-nozzle by DSMC/EPSM Method

作　　者：辛国勋 刘屹巍 

机构地区：[1]沈阳飞机工业集团有限公司,沈阳110034 [2]空军驻沈飞军事代表室,沈阳110034

出　　处：《弹箭与制导学报》2011年第5期123-124,128,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中采用DSMC/EPSM混合算法研究了等截面微喷管几何结构、燃气来流参数对微推力器性能的影响。结果表明:调整等截面微喷管几何参数可以在很大程度上调节微推力器的推力和比冲,最大推力和比冲分别为0.2639mN和1081.9m/s;燃气来流的压强和温度对微推力器的推力和比冲均无显著影响;微推力器内的流动状态涉及连续流和滑移流,近羽流区为过渡流。文中的工作为等截面微喷管的优化设计提供了相关依据。In this paper,DSMC/EPSM method was employed to investigate the performance of micro-nozzle with uniform section.The two factors,geometrical structure of micro-nozzle and parameters of gas flow were investigated to understand how they act on the performance of micro-nozzle.The results showed：（1） the thrust and impulse of micro-thruster could be significantly affected by adjusting the parameters of geometrical structure of micro-nozzle,the maximum thrust and impulse were 0.2639 mN and 1081.9 m/s respectively,（2） the gas pressure and temperature had not obvious impact on the thrust and impulse of micro-thruster,（3） the flow state in micro-nozzle included continuous flow and slip flow and the flow state out of nozzle was transitional flow according to results of Knudsen number.The results of this paper provide relevant basis for optimal design of micro-thruster.

关 键 词：微推力器 微喷管 DSMC/EPSM 

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]