中山大学学报（自然科学版）（中英文）2025，Vol.64Issue(4)：42-52,11.DOI:10.13471/j.cnki.acta.snus.ZR20240301
微牛级微波离子推力器的推力特性
Thrust characteristics of micro-newton microwave ion thrusters
摘要
Abstract
This study establishes a theoretical thrust estimation model for microwave ion thrusters,conducts thrust measurements using a thrust stand,and analyzes errors of thrust.Additionally,it explores the effects of propellant flow rate,microwave power,and grid voltage on grid current and thrust.Results show that using a plume divergence correction coefficient of 0.98 and an ion energy correction coefficient of 1.02 improves the theoretical estimation model.Experimental investigations on thrust performance reveal that the influence of grid voltage aligns with theoretical predictions.Moreover,increasing microwave power and propellant flow rate significantly affects the ionization of Xe atoms in the discharge chamber,promoting ionization reactions and consequently impacting thrust performance.关键词
引力波/微波离子推力器/推力特性Key words
gravitational wave/microwave ion thruster/thrust characteristics分类
航空航天引用本文复制引用
雷玟,陈煜,沈岩,刘辉,曾德迈,孟圣峰..微牛级微波离子推力器的推力特性[J].中山大学学报（自然科学版）（中英文）,2025,64(4):42-52,11.基金项目
国家重点研发计划(2020YFC2201001) （2020YFC2201001）
深圳市科技计划(ZDSYS20210623091808026) （ZDSYS20210623091808026）
