N2O单组元微推力器高空模拟实验研究

Simulated altitude experimental investigation for N2Omonopropellant micro-thruster

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

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。

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. 