HAN基200 N发动机低温启动工作过程分析OA

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.