固体火箭技术2012，Vol.35Issue(1)：57-63,7.
MEMS-SPMT喷管内的粘性和热损失研究
Study on viscous and heat loss in nozzle of MEMS-SPMT
摘要
Abstract
Characteristics of the rocket motor can be largely affected by viscous force and heat transfer of fluid to the wall of micro-nozzles. In this paper,the effects of turbulence models(S-A and low Re k-e models),initial temperature and size of the micro-nozzle on viscous and heat loss were evaluated through parameters like the area ratio of subsonic layer to outlet,thrust and impulse loss et al. The results show that two turbulence models have some differences in calculating the subsonic layer; thrust losses attain 22% due to viscouse effects;heat transfer reduces not only the size of viscous boundary layer and the corresponding viscous effects, but also the impulse of micro-nozzle. Heat loss can be decreased through increasing initial temperature of the micro-nozzles wall, and viscous loss can be reduced by enlarging its size,thus improve impulse of the micro-nozzles.关键词
MEMS-固体微推力器/粘性损失/换热损失/亚声速边界层/微推力Key words
MEMS-SPMT/viscous loss/heat transfer loss/subsonic layer/micro-thurst分类
航空航天引用本文复制引用
吴素丽,胡松启,张斌,刘迎吉,刘凯,王鹏飞..MEMS-SPMT喷管内的粘性和热损失研究[J].固体火箭技术,2012,35(1):57-63,7.基金项目
总装备部预研基金资助项目 （）
西北工业大学创业种子基金资助. （）
