Apparatus and method for potential control of a geosynchronous orbit spacecraft

Abstract

The invention discloses a geosynchronous orbit spacecraft potential control device and method. A spacecraft potential is controlled through an induction switch, a capacitor, a photoelectron emission device and a connecting circuit; wherein one end of the capacitor is connected with the photocathode end of the photoelectron emission device, the other end of the capacitor is connected with the electronic receiving end of the photoelectron emission device, the photocathode end of the photoelectron emission device is connected with the spacecraft, and the electronic receiving end of the photoelectron emission device is connected with the spacecraft through the induction switch; the induction switch is photo induction switch, the induction switch is closed with illumination and the induction switch is turned off without illumination. The geosynchronous orbit spacecraft potential control device and method have the advantages of significantly reducing the complexity of the potential active control technology, besides, being small in weight, low in the power consumption, and simple in structure, and having a small impact to the spacecraft.

Description

technical field [0001] The invention relates to the technical field of space environment effect protection for geosynchronous orbit spacecraft, in particular to a geosynchronous orbit spacecraft potential control device and a method thereof. Background technique [0002] In space, the plasma that is infinitely far away from the spacecraft is usually used as the "0 potential" reference point. When the spacecraft operates in the shadow area on orbit, the spacecraft interacts with the environment such as space plasma and high-energy electrons to generate electrostatic charges. Accumulated, the overall potential of the spacecraft will rise to the negative potential relative to the "0 potential". On-orbit measured data show that under harsh environmental conditions such as geomagnetic substorms, the overall potential of the spacecraft can reach tens of thousands of volts, which seriously affects the safe and stable operation of the spacecraft in orbit. [0003] For the above pro...

AI Technical Summary

Problems solved by technology

The active potential control technologies currently used all adopt an open method, that is, launching a beam of charged particles into space to establish a path between the spacecraft and the "zero potential" of the space plasma, thereby reducing the potential of the spacecraft, and the charged particles mainly It is obtained by relying on ionized gas working fluid or liquid metal. The current active potential control technology has a large weight, volume, and power consumption, and the control system is relatively complicated.

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