一种用于临近空间飞行器的吸气式电推进技术  

An Air-Breathing Electric Thruster for Near-Space Vehicle

作　　者：陈盼[1] 武志文[1] 刘向阳[1] 谢侃[1] 王宁飞[1] 

机构地区：[1]北京理工大学,北京100081

出　　处：《宇航学报》2016年第2期203-208,共6页Journal of Astronautics

基　　金：高等学校博士学科点专项科研基金(20121101120004)

摘　　要：针对低速临近空间飞行器提出了一种新型吸气式电推进方案,该方案采用单介质阻挡放电(SDBD)作为等离子体源,因此能在较大气压范围(数Pa^1atm)内电离大气产生等离子体并产生推力。为探究该吸气式电推进方案的推力性能,测量了实验样机在多个气压和电压条件下产生的推力。推力测量结果显示在10~90 k Pa气压范围内,实验样机产生的推力在102~103μN量级;气压一定时,产生的推力与驱动电压呈幂次相关;而电压一定时,随着气压自1atm逐渐降低,产生的推力先增大后减小,且达到最大推力的气压与所加驱动电压相关。An air-breathing electric thruster,which uses the Single Dielectric Barrier Discharge（ SDBD） technique to generate the plasma,is proposed in this paper for near-space propulsion missions. Using the SDBD plasma source,this airbreathing electric thruster can theoretically operate in a wide range of pressure（ from several Pa to 1atm）. To investigate the performance of this kind of air-breathing electric thruster,a simple thruster is manufactured and the thrust it produces under different ambient pressure and applied voltage conditions are measurement. The measuring results shows that under a moderate applied voltage,when the pressure ranges from 10 k Pa to 90 k Pa,the thrust is on the order of 102~ 103μN. At a certain pressure,the power law correlation is found between the thrust and the applied voltage. With a constant voltage,the thrust increases first to a maximum and then decreases with the gradual decrease of pressure,and the pressure at which the maximum thrust is obtained is a function of the applied voltage.

关 键 词：吸气式电推进 临近空间飞行器 单介质阻挡放电 

分 类 号：V237[航空宇航科学与技术—航空宇航推进理论与工程]