航空学报2026，Vol.47Issue(14)：16-31,16.DOI:10.7527/S1000-6893.2026.32878
低温硝酸羟胺基单组元推力器气动谐振内加热快速催化点火起动
Gas dynamic resonance internal heating rapid catalytic ignition startup of low temperature hydroxylammonium nitrate-based monopropellant thruster
孙烨真 1陈君 2梁国柱 1王智刚 3夏连根 3王晓东3
作者信息
- 1. 北京航空航天大学 宇航学院,北京 102206||北京航空航天大学 航天液体动力全国重点实验室,北京 102206
- 2. 北京控制工程研究所,北京 100190
- 3. 中国科学院 大连化学物理研究所,大连 116023
- 折叠
摘要
Abstract
In order to achieve the rapid catalytic ignition startup of Hydroxylammonium Nitrate(HAN)-based monopro-pellant thrusters under low-temperature conditions(below 0℃),a gas dynamic resonance internal heating method is adopted to centrally heat the front section of the thruster's catalyst bed.Three low-temperature(-9℃)startup tests are conducted on a 20 N HAN-based monopropellant thruster,and the heat transfer process inside the combustion chamber of the internally heated monopropellant thruster is studied through system simulation calculations.The test re-sults show that using nitrogen as the resonant working medium,the HAN-based thruster can achieve rapid catalytic ig-nition and startup under low-temperature conditions,reducing the preheating time required for traditional catalyst bed electric heating from tens of minutes to tens of seconds,and significantly shortening the ignition delay time;the pre-heating time for low-temperature pre-pulse ignition is reduced to approximately 20 s.The heat transfer calculation re-sults show that the resonance heater can stably output a heating power of about 30-35 W;during the pre-pulse igni-tion phase,the pressure rise gradient is large,and the thermal accumulation effect promotes the rapid temperature rise inside the combustion chamber.At the end of this phase,the temperature difference between the casing and the catalyst bed is about 500℃;in the pulse operation phase,the catalyst bed is already at a relatively high temperature level,and the temperature difference between the casing and the catalyst bed is about 200℃;during the continuous operation phase,due to the continuous supply of propellant,the maximum temperature inside the catalyst bed can reach about 1 150℃,with a temperature difference of about 600℃from the casing.The application of gas dynamic resonance heating method can realize the rapid catalytic ignition startup of HAN-based monopropellant thrusters under low-temperature conditions.关键词
单组元推力器/硝酸羟胺/催化点火/气动谐振加热/低温起动Key words
monopropellant thruster/hydroxylammonium nitrate/catalytic ignition/gas dynamic resonance heating/low-temperature startup分类
航空航天引用本文复制引用
孙烨真,陈君,梁国柱,王智刚,夏连根,王晓东..低温硝酸羟胺基单组元推力器气动谐振内加热快速催化点火起动[J].航空学报,2026,47(14):16-31,16.
