N_2O单组元微推力器高空模拟实验研究  

Simulated altitude experimental investigation for N_2O monopropellant micro-thruster

作　　者：李茂[1] 韩乐[1] 方杰[1] 孙威[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《推进技术》2011年第3期307-311,共5页Journal of Propulsion Technology

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。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.

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 

分 类 号：V439.7[航空宇航科学与技术—航空宇航推进理论与工程]