放电特性对静电发射推进性能影响的实验研究  

Experimental study on the effect of discharge characteristics on electrostatic emission propulsion performance

作　　者：叶继飞 韩枭 宋航 杜邦登 YE Jifei;HAN Xiao;SONG Hang;DU Bangdeng(Department of Aerospace Science and Technology,Space Engineering University,Beijing 101416,China)

机构地区：[1]航天工程大学宇航科学与技术系,北京101416

出　　处：《航天工程大学学报》2025年第1期37-44,共8页

基　　金：国家自然科学基金资助项目(11602304)。

摘　　要：为进一步明确不同气压下的静电发射状态与性能差异,基于静电发射推进基本原理:构建发射电压、束流电流、推力和比冲等推进性能参数的测量方法与实验装置,获取了在常压和真空下多种极间距静电发射推进性能随发射电压变化规律,界定了静电发射正常工作的气压范围,研究了放电特性对静电发射推进性能的影响规律。结果表明:气压范围0.5~8000 Pa,静电发射不能正常启动,真空放电下的静电发射极间所能施加的最大电压远小于常压下,正极性的发射电压峰值在3200 V左右,负极性的峰值在3700 V左右;受常压下电晕放电的影响,真空下的推进性能更优,但两种条件所能达到的峰值推力和比冲相近。To clarify differences in electrostatic emission states and performance under varying pressures,on basic principles of electrostatic emission propulsion,we establish measurements and an experimental setup for propulsion performance parameters,including emission voltage,beam current,thrust,and specific impulse.This study investigates variations in propulsion performance with emission voltage across different electrode gaps under both atmospheric and vacuum conditions,defines the operational pressure range for stable electrostatic emission,and examines the influence of discharge characteristics on propulsion performance.Results show that within pressure range of 0.5~8000 Pa,stable electrostatic emission cannot be achieved.Under vacuum discharge,the maximum voltage applicable across the electrodes is significantly lower than under atmospheric pressure,with positive emission voltage peaking at around 3200 V and negative emission voltage peaking at around 3700 V.While corona discharge under atmospheric pressure adversely affects performance,vacuum conditions exhibit superior propulsion performance.However,peak thrust and specific impulse in both conditions are comparable.

关 键 词：微推进 电喷雾 场发射 真空放电 电晕放电 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]