利用孤立导体建立等离子体探测载荷参考电位方法

李晓明; 刘超; 关燚炳; 张爱兵

doi:10.11728/cjss2020.01.052

利用孤立导体建立等离子体探测载荷参考电位方法

doi: 10.11728/cjss2020.01.052 cstr: 32142.14.cjss2020.01.052

李晓明^1,2,
刘超^1,3,4,
关燚炳^1,3,4,
张爱兵^1,2,3,4

1. 中国科学院国家空间科学中心北京 100190;
2. 中国科学院大学北京 100049;
3. 天基空间环境探测北京市重点实验室北京 100190;
4. 中国科学院空间环境态势感知技术重点实验室北京 100190

基金项目:

载人航天工程项目资助（Y79002AH40）

详细信息

作者简介:

刘超,E-mail:liuch@nssc.ac.cn

中图分类号: P352
计量
- 文章访问数: 1275
- HTML全文浏览量: 202
- PDF下载量: 59
- 被引次数:
  0(来源:Crossref)
  
  0(来源:其他)
出版历程
- 收稿日期: 2018-12-18
- 修回日期: 2019-07-23
- 刊出日期: 2020-01-15

Method of Establishing Reference Potential of Plasma Detector Using Isolated Conductor

LI Xiaoming^1,2,
LIU Chao^1,3,4,
GUAN Yibing^1,3,4,
ZHANG Aibing^1,2,3,4

1 National Space Science Center, Chinese Academy of Sciences, Beijing 100190;
2 University of Chinese Academy of Sciences, Beijing 100049;
3 Beijing Key Laboratory of Space Environment Explorations, Beijing 100190;
4 Key Laboratory of Environmental Space Situation Awareness Technology, Chinese Academy of Sciences, Beijing 100190

摘要

摘要: 研究讨论了一种利用孤立导体在空间等离子体环境中建立探测器参考电位的技术.将一个金属导体与航天器进行电隔离，利用电路将孤立导体电位引入探测器电源模块，为探测器建立参考电位.该技术可安全方便地应用于卫星等航天器，使探测器的地电位与空间等离子体电位基本一致，避免航天器本体电位对探测器的影响.该技术将应用于中国空间站等离子体原位探测器，通过测试验证了该技术方法可以建立-210～+210V的参考电位，满足空间站等离子体原位探测器-200～+200V的参考电位技术需求.
- 参考电位 /
- 探测器 /
- 孤立导体 /
- 等离子体
Abstract: A technique of using an isolated conductor for establishing a probe reference potential in space plasma environment is presented. In this technique, a metal conductor is electrically isolated from spacecraft. Potential established at the metal conductor is added to probe's power module by circuit, thus a reference potential for the probe is established. This technique can be applied to spacecraft such as satellites safely and conveniently, and it can make the ground potential of probe basically equal to the potential of space plasma, avoiding the impact of spacecraft potential on the probe. This technique will be applied to the plasma in situ detector of China's space station. Through testing, it is verified that the reference potential of -210~+210V can be built by this technique, and this reference potential range meets the technical requirements of -200~+200V that space station plasma in situ detector needs.
- Reference potential /
- Probe /
- Isolated conductor /
- Plasma

HTML全文

参考文献(19)

[1]	ZHOU Lidong, SUN Yongwei, MENG Zhicheng. Effects of complex space environment on spacecraft[J]. Aerodyn. Missile J., 2017, 7:65-68(周立栋, 孙永卫, 蒙志成. 复杂太空环境对航天器的影响[J]. 飞航导弹, 2017, 7:65-68)
[2]	GUAN Yibing, WANG Shijin, LIANG Jinbao, et al. Spacecraft potential control and potential monitor during spacecraft docking[J]. Sci. Technol. Rev., 2011, 29(29):27-31(关#
[3]	CARRUTH M R J, SCHNEIDER T, MCCOLLUM M, et al. ISS and space environment interactions in event of plasma contactor failure[C]//7th Spacecraft Charging Technology. Netherlands:NASA Marshall Space Flight Center, 2000:95
[4]	FERGUSON D C, GARDNER B. Modeling International Space Station (ISS) floating potentials[C]//Proceedings of 40th Aerospace Sciences Meeting and Exhibit. Reno:AIAA, 2002:93-97
[5]	National Aeronautics and Space Administration. NASA-HDBK-4006 Low earth orbit spacecraft charging design handbook[S]. Washington:National Aeronautics and Space Administration, 2007
[6]	RONALD M, HAGOP B, JOHN K, et al. Electrical charging of the international space station[J]. J. Mil. Ethics, 2011, 10(2):120-121
[7]	FERGUSON D C, CRAVEN P D, MINOW J I, et al. A theory for rapid charging events on the international space station[C]//AIAA Atmospheric and Space Environments Conference. Texas:American Inst. of Aeronautics and Astronautics, 2006:31-34
[8]	FENG Weiquan, XU Yanlin. Spacecraft failures and anomalies related with space environment[J]. Spacecraft Environ. Eng., 2011, 28(4):375-389(冯伟泉, 徐焱林. 归因于空间环境的航天器故障与异常[J]. 航天器环境工程, 2011, 28(4):375-389)
[9]	HANSON W B, HEELIS R A. Techniques for measuring bulk gas-motions from satellites[J]. Space Sci. Instrum., 1975, 1(1):493-524
[10]	ZHAO Ying, LIU Songzhe, JIN Haiwen. Controlling techniques of electrostatic cleanliness in design of solar arrays for electromagnetism survey satellite[J]. Chin. J. Power Sources, 2014, 38(2):276-278(赵颖, 刘松喆, 金海雯. 电磁监测卫星太阳电池阵表面等电位控制[J]. 电源技术, 2014, 38(2):276-278)
[11]	LIU Chao, GUAN Yibing, ZHANG Aibing, et al. The ionosphere measurement technology of Langmuir probe on China seismo-electromagnetic satellite[J]. Acta Phys. Sin., 2016, 65(18):330-337(刘超, 关燚炳, 张爱兵, 等. 电磁监测试验卫星朗缪尔探针电离层探测技术[J]. 物理学报, 2016, 65(18):330-337)
[12]	ZUCCARO D R, HOLT B J. A technique for establishing a reference potential on satellites in planetary ionospheres:For spacecraft charged particle sensors[J]. J. Geophys. Res. Space Phys., 1982, 87(A10):8327-8329
[13]	CAO Jinbin, WANG Xueyi, ZHOU Guocheng, et al. Plasma sheath of moving spacecraft in magnetized plasma of low earth orbit[J]. Chin. J. Geophys., 2000, 43(4):459-463(曹晋滨, 汪学毅, 周国成, 等. 低轨道磁化等离子体中运动航天器等离子体鞘层特性[J]. 地球物理学报, 2000, 43(4):459-463)
[14]	CAO Hefei, LIU Shanghe, SUN Yongwei, et al. Unbiased solid surface charging research in plasma environment[J]. Acta Phys. Sin., 2013, 62(11):119401(曹鹤飞, 刘尚合, 孙永卫, 等. 等离子体环境非偏置固体表面带电研究[J]. 物理学报, 2013, 62(11):119401)
[15]	GUAN Yibing, WANG Shijin, LIU Chao. Design and simulation for the sensor of the space based Langmuir Probe[J]. Chin. J. Space Sci., 2012, 32(5):750-756(关燚炳, 王世金, 刘超. 天基朗缪尔探针传感器设计与仿真[J]. 空间科学学报, 2012, 32(5):750-756)
[16]	MAN Feng. Research on Key Technologies of Spaceborne Electric Field Instrument[D]. Xi'an:Graduate University of Chinese Academy of Sciences, 2009
[17]	HAO Lingyan. Investigation on Characteristics of Surface Dielectric Barrier Discharge Plasma under Atmospheric-Pressure[D]. Jinan:Shandong University, 2016
[18]	HAO Lingyan, LI Qingquan, BI Xiaotian, et al. Simulation calculation of characteristic parameters of surface dielectric barrier discharge[J]. High Voltage Eng., 2014, 40(10):3018-3024
[54]	炳, 王世金, 梁金宝, 等. 航天器交汇对接电位控制研究与航天器电位监测[J]. 科技导报, 2011, 29(29):27-31)