Thrust estimate method of an on-orbit Hall thruster using Hall drift current  

作　　者：Ziying REN Liqiu WEI Zexin LIU Yanlin HU Liang HAN Hong LI Yongjie DING Xiufeng ZHONG 任姿颖;魏立秋;刘泽欣;扈延林;韩亮;李鸿;丁永杰;钟秀峰(School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,People’s Republic of China;Chang Guang Satellite Technology Co.,Ltd.,Changchun 130000,People’s Republic of China;Beijing Institute of Control Engineering,Beijing 100190,People’s Republic of China;Beijing SunWise Space Technology Ltd.,Beijing 101300,People’s Republic of China)

机构地区：[1]School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,People’s Republic of China [2]Chang Guang Satellite Technology Co.,Ltd.,Changchun 130000,People’s Republic of China [3]Beijing Institute of Control Engineering,Beijing 100190,People’s Republic of China [4]Beijing SunWise Space Technology Ltd.,Beijing 101300,People’s Republic of China

出　　处：《Plasma Science and Technology》2024年第12期150-159,共10页等离子体科学和技术（英文版）

基　　金：funded by the Basic Research on National Defense of China(No.JCKY2021603B033),which is gratefully acknowledged。

摘　　要：In order to realize the thrust estimation of the Hall thruster during its flight mission,this study establishes an estimation method based on measurement of the Hall drift current.In this method,the Hall drift current is calculated from an inverse magnetostatic problem,which is formulated according to its induced magnetic flux density detected by sensors,and then the thrust is estimated by multiplying the Hall drift current with the characteristic magnetic flux density of the thruster itself.In addition,a three-wire torsion pendulum micro-thrust measurement system is utilized to verify the estimate values obtained from the proposed method.The errors were found to be less than 8%when the discharge voltage ranged from 250 V to 350 V and the anode flow rate ranged from 30 sccm to 50 sccm,indicating the possibility that the proposed thrust estimate method could be practically applied.Moreover,the measurement accuracy of the magnetic flux density is suggested to be lower than 0.015 mT and improvement on the inverse problem solution is required in the future.

关 键 词：thrust estimation Hall effect thruster Hall drift current inverse problem Tikhonov regularization 

分 类 号：V439.4[航空宇航科学与技术—航空宇航推进理论与工程]