为实现低温条件下（0 ℃以下）硝酸羟胺（简称HAN）基单组元推力器的快速催化点火起动，采用气动谐振内加热方式对推力器催化床前床进行集中加热，对一台20 N HAN基单组元推力器进行3次低温（?9 ℃）起动试验，并通过系统仿真计算研究内加热式单组元推力器燃烧室内的传热过程。试验结果表明：以氮气为谐振工质，HAN基推力器可实现低温条件下的快速催化点火起动，将传统催化床电加热预热时间从数十分钟缩短至数十秒，大幅减少点火延迟时间；实现低温预脉冲点火的预加热时间缩短至20 s左右。传热计算表明：谐振加热器可稳定输出约30~35 W的加热功率；预脉冲点火阶段升压梯度较大，热累积效应促使燃烧室内部迅速升温，该阶段结束时壳体与催化床温差约为500 ℃；脉冲工作阶段催化床已处于较高温度水平，壳体与催化床温差约为200 ℃；连续工作阶段因推进剂持续供应，催化床内最高温度可达1150 ℃左右，与壳体的温差约为600 ℃。研究证明了应用气动谐振加热技术可以实现HAN基单组元推力器在低温条件下的快速催化点火起动。

In order to achieve the rapid catalytic ignition startup of hydroxylammonium nitrate (HAN)-based monopropellant thruster under low temperature, a novel preheating technique called gas dynamic resonance heating is proposed and employed to efficiently heat the front section of the catalyst bed. Using nitrogen as the resonance working fluid, three starts under low temperature (?9 °C)were conducted on a 20N HAN-based monopropellant thruster equipped with a gas dynamic resonance heater, meanwhile the heat transfer process inside the combustion chamber of the internally heated monopropellant thruster was studied through simu-lation calculations. The test results show that using nitrogen as the resonant working medium, the HAN-based thruster can achieve rapid catalytic ignition and startup under low-temperature conditions, reducing the preheating time required for tradi-tional catalytic bed electric heating from tens of minutes to tens of seconds, significantly shortening the ignition delay time. The preheating time for low-temperature pre-pulse ignition was reduced to approximately 20 seconds. The heat transfer calculation shows that the resonance heater can stably output a heating power of about 30-35 W; During the pre-pulse ignition phase, the pressure rise gradient is large, and the thermal accumulation effect causes a rapid temperature increase inside the combustion chamber. At the end of this phase, the temperature difference between the casing and the interior of the catalyst bed is about 500°C. In the formal pulse operation phase, the catalyst bed has already reached a relatively high temperature level. The casing temperature is about 200°C lower than the temperature inside the catalyst bed. During the continuous operation phase, due to the continuous supply of propellant, the maximum temperature inside the catalyst bed reaches around 1150°C and the temperature difference from the casing is about 600°C. The research has shown that the application of the gas dynamic resonance heating technology can achieve the rapid catalytic ignition startup of HAN-based monopropellant thruster under low temperature.