Performance of a 4 cm iodine-fueled radio frequency ion thruster  

作　　者：Jinghua YANG Shaoxia JIA Zhenhua ZHANG Xinghua ZHANG Ting JIN Long LI Yong CAI Jian CAI 杨景华;贾少霞;张振华;张兴华;金婷;李龙;蔡勇;蔡建(Institute of Microelectronics,Chinese Academy of Sciences,Beijing 100029,People's Republic of China;Nanjing University of Aeronautics and Astronautics,Nanjing 210016,People's Republic of China;Suzhou Nano-Space Dynamics Technology Co.Ltd,Suzhou 215000,People's Republic of China)

机构地区：[1]Institute of Microelectronics,Chinese Academy of Sciences,Beijing 100029,People's Republic of China [2]Nanjing University of Aeronautics and Astronautics,Nanjing 210016,People's Republic of China [3]Suzhou Nano-Space Dynamics Technology Co.Ltd,Suzhou 215000,People's Republic of China

出　　处：《Plasma Science and Technology》2020年第9期44-50,共7页等离子体科学和技术（英文版）

基　　金：financial support from National Natural Science Foundation of China(No.11805265);Key Laboratory of Micro-Satellites,Chinese Academy of Sciences(No.KFKT201903)。

摘　　要：The performance of an iodine radio ion thruster with a 4 cm diameter(IRIT4)was studied experimentally in this paper.Regulation of the mass flow rates of the iodine propellant is achieved by using a temperature control method of the iodine reservoir.Performance of the thruster using iodine as propellants is obtained at different total thruster powers of 40.6–128.8 W,different grid voltages of 1000–1800 V and the iodine flow rate of 100μgs^(-1).Results show that thrust and specific impulse increase approximately linearly with the increasing total thruster power and the screen grid voltage.The thrust of 2.32 mN and the specific impulse of 2361 s are obtained at the nominal total thruster power of 95.8 W and the screen grid voltage of 1800 V.It is also indicated that performance of the iodine propellant is comparable to that of the xenon propellant;and a difference between them is that the iodine thrust is slightly higher than xenon when the total thruster power is more than 62 W.At the nominal 95.8 W total thruster power,the thrust values of them are 2.32 m N and 2.15 mN respectively,and the thrust-to-power ratios of them are 24.2 mN kW^(-1)and 23.5 mN kW^(-1),respectively.

关 键 词：electric propulsion iodine propellant radio frequency ion propulsion 

分 类 号：V439.1[航空宇航科学与技术—航空宇航推进理论与工程]