为了获得研制的一种基于绿色无毒ADN基推进剂的单组元0.2N微推力器性能，对其进行了试验研究。通过真空加热试验，获得微推力器的温启动加热性能；通过高空模拟热试车试验，获得微推力器稳态和脉冲工况下，微推力器的推力、温度分布等参数，考察微推力器的启动性能、稳态、脉冲工作稳定性，研究微推力器工作过程中推力室、前室和电磁阀温度变化规律，通过1000s长稳态点火试验，验证了微推力器长稳态工作的稳定性。结果表明，3W加热功率实现了微推力器200℃的温启动要求，微推力器完成了系列稳态、脉冲考核程序，工作过程中微推力器推力稳定，启动响应快，推力室温度最高达到1016℃。试验证明了研制的0.2N微推力器在完成结构微型化的同时，实现了微流量下推力器稳定工作，微推力器额定真空比冲大于200s，性能优良，200mN推力量级微推力器的成功研制，将进一步拓展ADN绿色无毒推进在微推进领域的应用。

To investigate the performance of a green, non-toxic, ADN-based 0.2N monopropellant micro-thruster, experiments were conducted. The heating performance to reach ignition temperature of the micro-thruster was obtained by vacuum heating test. Through the hot fire test in high altitude simulated vacuum chamber, the vacuum thrust, temperature distribution of the micro-thruster under steady-fire and pulse-fire were obtained. The starting performance, stability of steady state and pulse of the micro-thruster were investigated. The temperature variation of the thrust chamber, front catalytic bed and solenoid valve in the thruster operation process were studied. Stability of long steady state firing of the micro-thruster was verified by the 1000s long steady state firing test. The evaluation results indicated that the pre-heating energy requirement to reach its 200℃ ignition temperature was approximately 3W, and the micro-thruster accomplished series of steady state and pulse firings. The thrust of the micro-thruster was stable. The transition to steady-state thrust was rather fast. The temperature of the thrust chamber was near 1016℃. The test proved that the resulting ADN-based 0.2N micro-thruster achieved stable firing under the micro flow rate while realizing much reduction in engine size. The performance was good. The steady-state vacuum specific impulse at 0.2N was more than 200s. The successful development of the 200mN thrust level micro-thruster further expanded the application of ADN green, non-toxic, propulsion in micro-propulsion.

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