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A Faraday Cup-Based Plasma Charging Current Monitoring Method on Satellite Surface

A surface plasmon and Faraday cup technology, applied in the field of space radiation, can solve problems such as the difficulty in determining the size relationship, the existence of deviations, and the inability to effectively judge and identify the risk of electrification on the surface of satellites.

Active Publication Date: 2021-09-07
BEIJING INST OF SPACECRAFT SYST ENG
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  • Abstract
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  • Application Information

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Problems solved by technology

The Langmuir probe is a metal material, and various types of materials are used on the surface of the satellite. It is difficult to completely match the parameters such as the secondary electron emission coefficient. Therefore, the relationship between the plasma current obtained by the Langmuir probe and the actual charging current Difficult to determine, there is a deviation when judging the charging state of the satellite surface based on the measurement data of the Langmuir probe, and the risk of electrification on the satellite surface cannot be effectively judged and identified

Method used

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  • A Faraday Cup-Based Plasma Charging Current Monitoring Method on Satellite Surface
  • A Faraday Cup-Based Plasma Charging Current Monitoring Method on Satellite Surface
  • A Faraday Cup-Based Plasma Charging Current Monitoring Method on Satellite Surface

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Embodiment Construction

[0042] The present invention will be described below in conjunction with the accompanying drawings and embodiments.

[0043] like figure 1 As shown, a method for monitoring the plasma charging current on the surface of a satellite based on a Faraday cup includes the following steps:

[0044] (1) Determine the measurement object and range of the charging current on the satellite surface

[0045] The charging current on the surface of the satellite is mainly formed by the electrons in the thermal plasma with an energy of 10eV to 100keV in space, so the measurement object is the charging current formed by the electrons, and the current density is greater than -0.01nA / cm 2 The probability of about 95% greater than -0.7nA / cm 2 The probability is about 0.1%, and the maximum charging current density actually measured on the track is -1.52nA / cm 2 , the design value of charging current density recommended by ESA is -10nA / cm 2. Considering the above factors comprehensively, the mea...

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Abstract

The invention relates to a method for monitoring the plasma charging current on the surface of a satellite based on a Faraday cup. By determining the measurement object and range of the satellite surface charging current; designing the Faraday cup probe; installing the Faraday cup probe on the satellite; determining the relationship between the real data of the satellite surface charging current and the measurement data of the Faraday cup probe, to realize the space plasma charging on the satellite surface Envelope and efficient inversion of currents. The method of the invention can effectively reflect the magnitude of the plasma charging current on the satellite surface, and provide a basis for the evaluation of the charged state and charged risk of the satellite surface.

Description

technical field [0001] The invention relates to a method for monitoring the plasma charging current on the surface of a satellite based on a Faraday cup. It belongs to the field of space radiation technology. Background technique [0002] When a strong geomagnetic storm or geomagnetic substorm occurs, a large amount of hot plasma will be injected from the earth's magnetotail into the orbital area of ​​the medium and high orbit satellites, causing surface charge and discharge effects on the satellite. Surface charging is divided into two types: absolute charging and relative charging. The main influence on the satellite is the relative potential, that is, there is a potential difference between different areas on the surface. When the potential difference is too high, discharge will occur, which will interfere with the normal operation of electronic components. cause the satellite to malfunction. Monitoring the charged state of the satellite surface can provide a basis for ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H05H1/00
CPCH05H1/0081
Inventor 李衍存蔡震波郑玉展盛丽艳乐群星马继楠向宏文王建昭贾晓宇张志平张弘曲少杰
Owner BEIJING INST OF SPACECRAFT SYST ENG
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