Abstract: Simulated altitude experiments for two different size monopropellant micro-thrusters were conducted in a vacuum chamber with a micro thrust measurement facility. The maximal specific impulses, measured in the experiment, were 1.608 N·s/g and 1.639 N·s/g for the different size micro-thrusters, respectively. The analysis of the influence of the key design parameters on the micro-thruster performance was also carried out. Results show that the performance is influenced remarkably by the heat loss, the catalyze bed load, as well as the catalyze bed length. There exist an optimum catalyze bed load and an optimum matching of the catalyze bed load to the catalyze bed length. 

Key words: Micro-thruster; Nitrogen oxide monopropellant; Simulated altitude test; Specific impulse performance; Decomposition temperature

摘要： 在真空舱中进行了N₂O单组元两种尺寸的微推力器的高空模拟试验研究,分析了微推力器设计参数对比冲等性能的影响。结果表明,两种尺寸微推力器的最大比冲分别为1.608 N·s/g和1.639 N·s/g,热损失、床载和床长对微推力器性能影响明显,存在最佳床载值、床载和床长的匹配。

关键词: 微推力器;N₂O单组元推进剂;高空模拟试验;比冲性能;分解温度