空间电动力绳系电流峰值点变化规律研究

doi:10.13675/j.cnki.tjjs.180653

推进技术 ›› 2020, Vol. 41 ›› Issue (2): 469-480.DOI: 10.13675/j.cnki.tjjs.180653

• 电推进和其它推进 • 上一篇

空间电动力绳系电流峰值点变化规律研究

于博^1,2,王仲远³,乔彩霞²,康小录²,赵青¹

1.电子科技大学资源与环境学院，四川成都 611731;2.上海空间推进研究所，上海 201112;3.上海宇航系统工程研究所，上海 201108

发布日期:2021-08-15

Investigation on Change Laws of Current Peak Position in Electrodynamic Space Tether

1.College of Resource and Environment,University of Electronic Science and Technology of China, Chengdu 611731, China;2.Shanghai Institute of Space Propulsion, Shanghai 201112, China;3.Aerospace System Engineering Shanghai, Shanghai 201108， China

Published:2021-08-15

摘要/Abstract

摘要： 为研究电流峰值点在几种影响因素下的变化规律，建立一种能够捕捉绳系电子发射与收集自洽平衡过程的新算法——电路空间耦合算法。为验证该方法的计算精度，以1.35kW霍尔推力器为等离子体源，在真空舱内开展绳系的电荷收集试验，在电路参数方面，计算精度约为12.8%，在场参数方面，计算精度约为3.6%。在此基础上，针对不同偏置电压、绳系长度以及绳系直径，对绳系的绳上电流分布、电势分布以及空间电势分布等参数进行数值计算。结果显示：电动力绳系的电流峰值点会随着偏置电压升高、绳系长度增加及绳系直径增大而发生比例上的向阳极端漂移，揭示了电子轨道运动限制的机制在各类壁面电荷输运机制中占优，导致电流峰值点漂移的产生。

关键词: 电动力绳系;电流峰值点;耦合算法;数值计算

Abstract: In order to precisely study the self-consistent process between the collection and emission of electrons in a whole electrodynamic tether system, a new hybrid model named 3D circuit and space coupling calculation (3D-CSC) has been established. This model can help to study the change law of peak position under several influencing factors. In order to verify the feasibility and accuracy of 3D-CSC model, experimental tests of current collection using a bare tether have been conducted, and a 1.35kW class Hall thruster is employed as the plasma generator in the vacuum chamber. Comparisons between calculation and measurement results show that the error of calculation in circuit is about 12.8%, while in space is about 3.6%. Based on 3D-CSC, we simulated the steady-state operating characteristics of an on-orbit electrodynamic tether including the current and potential distribution on tether, as well as the plasma potential distribution in space, under the working conditions of different bias voltages, different tether lengths or diameters. The calculation results showed that, the current peak position would move to the anode end with the bias voltage increasing, the tether length increasing or the tether diameter increasing. The present study revealed that the difference of the three types of charge transportation， which are the orbital motion limit, the thermionic emission and the secondary electron emission, respectively, was the reason of the current-peak-position change.

Key words: Electrodynamic space tether;Current peak position;Coupling model;Numerical simulation

于博,王仲远,乔彩霞,康小录,赵青. 空间电动力绳系电流峰值点变化规律研究[J]. 推进技术, 2020, 41(2): 469-480.

YU Bo^1,2,WANG Zhong-yuan³,QIAO Cai-xia²,KANG Xiao-lu²,ZHAO Qing¹. Investigation on Change Laws of Current Peak Position in Electrodynamic Space Tether[J]. Journal of Propulsion Technology, 2020, 41(2): 469-480.

参考文献

[1] Ohkawa Y , Kawamoto S ， Okumura T ， et al . Perparation for On-Orbit Demonstration of Electrodynamic Tether on HTV[C]. Japan： 34th International Electric Propulsion Conference， 2015.
[2] Ohkawa Y ， Kitamura S ， Kawamoto S ， et al . A Carbon Nanotube Field Emission Cathode for Electrodynamic Tether Systems [C]. Wiesbaden： 32nd International Electric Propulsion Conference， 2011.
[3] Bilen S ， McTernan J ， Gilchrist B ， et al . Harnessing the “Orbital Battery” for Propulsion via Energy-Harvesting Electrodynamic Tethers [C]. Wiesbaden： 32nd International Electric Propulsion Conference， 2011.
[4] Bonometti J ， Sorensen K . 2006 State of the Momentum Excharge Electrodynamic Re-Boost (MXER) Tether Development [C]. Sacramento： 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference， 2006.
[5] Ahedo E ， Sanmartin J . Analysis of Bare-Tether Systems for Deorbiting Low-Earth-Orbit Satellites[J]. Journal of Spacecraft and Rockets， 2002， 39( 2): 198- 205.
[6] Sanmartin J ， Estes R ， Lorenzini E ， et al . Efficiency of Electrodynamic Tether Thrusters[J]. Journal of Spacecraft and Rockets， 2006， 43( 3): 659- 666.
[7] Zhu Z H ， Larouche B ， James G . Design of a Electrodynamic Tether Nanosatellite Mission[C]. Long Beach： AIAA SPACE 2011 Conference & Exposition， 2011.
[8] Zhong R ， Zhu Z H . Dynamics of Nanosatellite Deorbit by Bare Electrodynamic Tether in Low Earth Orbit[J]. Journal of Spacecraft and Rockets， 2013， 50( 3): 691- 700.
[9] Zhong R ， Zhu Z H . Optimal Control of Nanosatellite Fast Deorbit Using Electrodynamic Tether[J]. Journal of Guidance， Control and Dynamics， 2014， 37( 4): 1182- 1192.
[10] Sanmartin J ， Martinez-Sanchez M ， Ahedo E . Bare Wire Anodes for Electrodynamic Tether [J]. Journal of Propulsion and Power， 1993， 9( 3): 353- 360.
[11] Sanmartin J ， Estes R . The Orbital-Motion-Limited Regime of Cylindrical Langmuir Probes[J]. Physics of Plasmas， 1999， 6( 1): 395- 405.
[12] Mott-Smith H ， Langmuir I . The Theory of Collectors in Gaseous Discharges[J]. Physical Review， 1926， 28: 727- 763.
[13] Fuhrhop K ， Gilchrist B . Electrodynamic Tether System Analysis Comparing Various Mission Scenarios [C]. Tucson： 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference， 2005.
[14] Janeski J ， Hall C ， Scales W . Effects of Local Plasma Environment on Dynamics of Electrodynamic Tether Systems [J]. Journal of Spacecraft and Rockets， 2015， 52( 2): 496- 505.
[15] Arriaga G ， Bombardelli C ， Chen X . Impact of Nonideal Effects on Bare Electrodynamic Tether Performance[J]. Journal of Propulsion and Power， 2015， 31( 3): 951- 955.
[16] Xie K ， Martinez R ， Williams J . Current-Voltage Characteristics of a Cathodic Plasma Contactor with Discharge Chamber for Application in Electrodynamic Tether Propulsion[J]. Journal of Physics D: Applied Physics， 2014， 47( 15).
[17] Xie K ， Xia Q ， Williams J ， et al . Extracted Current， Bias Voltage， and Ion Production of Cathodic Hollow-Cathode-Driven Plasma Contactor [J]. Journal of Spacecraft and Rocket， 2015， 52( 4): 1181- 1192.
[18] Xie K ， Farnell C ， Williams J . The Plasma Properties and Electron Emission Characteristics of Near-Zero Differential Resistance of Hollow Cathode-Based Plasma Contactors with a Discharge Chamber[J]. Physics of Plasmas， 2014， 21( 8): 353- 360.
[19] Qin Y ， Xie K ， Guo N ， et al . The Analysis of High Amplitude of Potential Osillations Near the Hollow Cathode of Ion Thruster [J]. Acta Astronautica, 2017， 134( 1): 265- 277.
[20] Qin Y ， Xie K ， Ouyang J . Self-Pulsing in a Low-Current Hollow Cathode Discharge: From Townsend to Glow Discharge [J]. Physics of Plasmas， 2016， 23( 2).
[21] Santos R ， Ahedo E . Accuracy Improvements in a Hall Thruster PIC/Fluid Code[C]. Denver： 45thAIAA/ASME/SAE/ASEE Joint Propulsion Conference， 2009.
[22] Onishi T ， Martinez-Sanchez M ， Cooke D . Computation of Current to a Moving Bare Tether [C]. Kitakyushu： 26th International Electric Propulsion Conference， 1999.
[23] Onishi T ， Martinez-Sanchez M ， Cooke D ， et al . PIC Computation of Electron Current Collection to a Moving Bare Tether in the Mesothermal Condition [C]. Pasadena： 27th International Electric Propulsion Conference， 2001.
[24] 潘杰 . 大气压Ar、N ₂和 Ar/O ₂气体脉冲介质阻挡放电等离子体机理及特性的数值模拟 [D]. 济南: 山东大学， 2016.
[25] Shunsuke S ， Toshiyuki K ， Junichiro A ， et al . Discharge Modes and Characteristics of Hollow Cathode [C]. Florence： 30th International Electric Propulsion Conference， 2007.
[26] Boltachev G ， Zubarev N . Space Charge Influence on the Angle of Conical Spikes Developing on a Liquid-Metal Anode [J]. Physical Review E， 2012， 77: 1- 10.
[27] 林祖伦，王小菊 . 阴极电子学（第一版）[M]. 北京：国防工业出版社， 2013.

空间电动力绳系电流峰值点变化规律研究

Investigation on Change Laws of Current Peak Position in Electrodynamic Space Tether

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