N_2O单组元微推力器真空试验设计与分析  

Vacuum experiment study on a N_2O monopropellant micro-thruster

作　　者：韩乐[1] 李茂[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：《航空动力学报》2011年第10期2358-2363,共6页Journal of Aerospace Power

摘　　要：提出了N2O单组元微推力器冲量测量方案.通过多次试验结果拟合稳态推力与压力之间的关系,再采用动态压力计算动态推力和冲量.对催化床尺寸为8mm×35mm和10mm×25mm两个微推力器进行了高空模拟试验研究,考察了流量对微推力器比冲的影响,得到了不同流量条件下稳态推力和压力之间的关系.试验方案与分析结果为微推力器精确冲量控制提供了参考.Impulse measurement scheme for a nitrous oxide（N_2O） monopropellant micro-thruster was presented.The experiment results were used to fit the relationship between the steady thrust and the pressure.Dynamic pressure was utilized to calculate the thrust and impulse.Two different micro-thrusters with catalytic bed of 8 mm×35 mm and 10 mm×25 mm were fabricated and experimented.The influence of the mass flow on the specific impulse performance was studied.The relationship between the steady thrust and the pressure in different mass flow rates was obtained.Experiment strategy and analysis result can provide some reference for accurate control of the micro-thruster impulse.

关 键 词：N2O微推力器 高空模拟试验 推力 比冲 冲量 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]