火箭推进2026，Vol.52Issue(3)：126-133,8.DOI:10.3969/j.issn.1672-9374.2026.03.012
HAN基200 N发动机低温启动工作过程分析
Analysis on the low-temperature startup process of a HAN-based 200 N thruster
摘要
Abstract
To meet the application requirements of high-performance green hydroxylammonium nitrate(HAN-based)propulsion systems in low-temperature environments,this paper elucidates the fundamental properties of HAN-based propellants,reviews their domestic and international development history and ignition hot-fire performance,identifies limitations in current research,conducts design and performance validation studies for a 200 N thruster.Stainless steel 316L was adopted to reduce manufacturing costs,while a segmented convergent structure was designed to achieve weight reduction.Based on ground ignition hot-fire test experiments,the low-temperature startup characteristics at-10 ℃and catalytic decomposition/combustion processes were analyzed.Experimental results demonstrate that the thruster achieves reliable ignition within 4.1 s through pre-pulse mode operation.Under steady-state conditions,it attains a combustion pressure of 2.26 MPa,thrust of 203.10 N,specific impulse of 215.24 s,with a minimum pulse operating interval of 30 ms,fulfilling both low-temperature startup and operational stability requirements.This research validates the rationality of the thruster design and provides technical support for the application of non-toxic propulsion systems in spacecraft and weapon equipment.关键词
硝酸羟胺/低温启动/工作过程/发动机Key words
hydroxylammonium nitrate/low-temperature start-up/operational/thruster分类
航空航天引用本文复制引用
王丝萦,顾永金,高翠普,陈君,谢继香,刘旭辉..HAN基200 N发动机低温启动工作过程分析[J].火箭推进,2026,52(3):126-133,8.基金项目
国家自然科学基金面上项目(52472392) （52472392）
航天系统部预先研究项目(305060107). （305060107）
