螺旋波电推进羽流电磁矢量控制的原理性验证  

Verification on electromagnetic vector modulation of plasma flow generated in helicon plasma thruster

作　　者：丁亮[1] 郑慧奇[1] 彭毓川 任琼英[1] 赵华[1] DING Liang;ZHENG Huiqi;PENG Yuchuan;REN Qiongying;ZHAO Hua(Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China)

机构地区：[1]北京卫星环境工程研究所,北京100094

出　　处：《中国空间科学技术》2020年第4期38-43,共6页Chinese Space Science and Technology

基　　金：装备预研领域基金(61402060501);载人航天领域第四批预先研究基金(010202)

摘　　要：推进器羽流的电磁矢量控制是基于电磁位形的改变使得喷射的羽流改变方向。为了原理性验证电推进羽流电磁矢量控制技术,针对螺旋波电推进器,开展了磁场位形调制仿真设计和试验验证。说明了电磁矢量调制线圈能够改变磁场位型,并且在试验过程中验证了等离子体羽流随磁场位型变化而产生的羽流方向偏转。在周期性磁场调制过程中,验证了等离子体密度参数随之周期性涨落。螺旋波电推进羽流方向最大偏转角度60°,可控偏转频率15 Hz,说明了电推进羽流电磁矢量控制的可行性。The electromagnetic vector modulation of electrical thruster′s flow is based on magnetic field reforming which leads to the orientation altering of plasma flow.To verify the electromagnetic vector modulation of electrical thruster,the theoretical simulation and experiments were carried out for the helicon plasma thruster(HPT).The magnetic field can be altered with electromagnetic vector modulation coils illustrated in theoretical simulation results.The plasma flow is deflected as the magnetic field is adjusted as shown in experimental results.Plasma density fluctuates according to an accessional magnetic field generated periodically.The plasma flow changes its orientation with 60 degrees at most with a modulated frequency which reaches 15 Hz.The electromagnetic vector modulation for helicon plasma thruster is verified feasible.

关 键 词：电推进 矢量调节 电磁控制 螺旋波 等离子体参数 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]