固体火箭技术Issue(2)：220-224,5.DOI:10.7673/j.issn.1006-2793.2015.02.013
Metal/N2 O粉末火箭发动机实验研究
Experimental research on metal/N2 O powder rocket engine
摘要
Abstract
Hot fire tests of metal/N2O rocket engine were carried out,using pneumatic driving powder feeding device.The two-phase flow characteristics were investigated through analyzing piston displacement and combustion pressure oscillation.According to droplet combustion model,the influence of factors such as combustion chamber pressure,particle residence time and O/F ratio were analyzed.The study verifies good performance of the engine. The results show that the concentration pulsating amplitude of solid phase in pipeline is less than ±0.36% when two-phase flow void ratio is 97% and flow velocity is 27 m/s.The average characteristic velosity efficiency of Mg/N2 O tests are about 96.4% at 0.5 MPa combustion chamber pressure,and reaches 88.5% of Al/N2 O tests at 0.91 MPa. Increasing combustion chamber pressure and particle residence time can improve combustion efficiency,but the effect of O/F ratio on combustion efficiency is relatively complex.关键词
金属粉末/气固两相流/燃烧振荡/燃烧效率Key words
metal powder/gas-solid two phase flow/combustion oscillation/combustion efficiency分类
航空航天引用本文复制引用
邓哲,胡春波,卢子元,胡松启,张研,徐义华..Metal/N2 O粉末火箭发动机实验研究[J].固体火箭技术,2015,(2):220-224,5.基金项目
国家自然科学基金项目(51266013) （51266013）
国防基础科研基金( B0320132006) （ B0320132006）
西北工业大学基础研究基金( JC20110205)。 （ JC20110205）
