Method for controlling electrification effect on surface of spacecraft in orbit

Abstract

The invention discloses a method for controlling an electrification effect on the surface of a spacecraft in orbit. The method for controlling the electrification effect on the surface of the spacecraft in orbit comprises the steps that firstly, a flux threshold value and a temperature threshold value are obtained based on the relationship between an electron flux and a spacecraft surface potential and the relationship between a plasma temperature and the spacecraft surface potential and according to a potential threshold value borne by the spacecraft surface; and in real-time control, the electron flux and an electron temperature are monitored in real time so that a potential active controller switch can be controlled to achieve the purpose of surface potential control. Since the electronflux and the plasma temperature are observed, whether the spacecraft surface can reach the potential threshold value or not is predicted and the surface potential control is carried out instead of carrying out the surface potential control after electrons and plasmas accumulate on the spacecraft surface to reach the potential threshold value, so that the response speed can be improved, and stability and accuracy of active control over spacecraft surface electrification can be improved.

Description

technical field [0001] The invention belongs to the technical field of spacecraft space environment effect protection, and in particular relates to a method for controlling the electrification effect on the orbital surface of a spacecraft. Background technique [0002] Magnetospheric storms / substorms will cause severe disturbances in the Earth’s space environment, and various particle events, thermospheric atmospheric density increases, ionospheric storms, etc. will cause serious threats to spacecraft activities, communication and navigation systems. Such as thermal plasma enhancement events, the energy injected by the space thermal plasma caused by the disturbance of the magnetosphere can be as high as tens of keV, which will cause the surface of the satellite to be charged to a higher potential and affect the safe and stable operation of the satellite. Studies have shown that the injected thermal plasma electron flux and electron temperature have an important impact on the...

AI Technical Summary

Problems solved by technology

Passive control is through grounding, or coating or wrapping a layer of anti-static film on the surface of the spacecraft, which reduces the surface charge to a certain extent, but cannot completely reduce the surface potential of the spacecraft

Active control is a potential control method developed in recent years, which releases the charge accumulated on the surface of the spacecraft by launching a particle beam, but the existing method is 1) triggered by surface potential monitoring, but there is a delay; 2 ) Set the potential active control system to trigger regularly, which cannot respond to changes in the environment in time; 3) Trigger through ground telemetry, due to the delay of signal transmission, the lag of the control is serious.

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