火箭推进2023，Vol.49Issue(6)：55-62,81,9.
环形燃烧室中自燃推进剂的非稳态旋转爆震现象
Unsteady rotating detonation phenomenon of hypergolic propellant in annular combustor
摘要
Abstract
To investigate the propagation characteristics of rotating detonation waves utilizing hypergolic propellant,the rotating detonation was organized in an annular combustor using methylhydrazine as the fuel and nitrogen tetroxide as the oxidizer,respectively.In the combustor with inner diameter 30 mm and outer diameter 60 mm,twenty-four pairs of impinging injection elements were used with oxidizer orifice 0.4 mm and fuel orifice 0.3 mm.Pressure sensors with low sampling rate and high frequency dynamic pressure sensors were used to record the supply and combustion pressures.The results show that the rota-ting detonation combustion of hypergolic propellant is highly unstable.The detonation wave strength is not only varying from cycle to cycle,but also changing very fast within one cycle.For the generation and maintenance process of rotational detonation combustion with hypergolic propellant,the external stimula-tion is not a significant factor,and the combustor geometry,mass flow rate and mixture ratio play more important role at rotating detonation.关键词
旋转爆震/自燃推进剂/环形燃烧室/实验/非稳态Key words
rotating detonation/hypergolic propellant/annular combustor/experiment/unsteady state分类
航空航天引用本文复制引用
严宇,王致程,胡洪波,洪流,杨宝娥..环形燃烧室中自燃推进剂的非稳态旋转爆震现象[J].火箭推进,2023,49(6):55-62,81,9.基金项目
国家自然科学基金(51506157,11602186) （51506157,11602186）
陕西省自然科学基础研究计划(2022JQ-490) （2022JQ-490）
重点实验室基金(HTKJ2022KL011002) （HTKJ2022KL011002）
