Spacecraft potential active control device based on helicon wave plasma and application thereof

Abstract

The invention discloses a spacecraft potential active control device based on a helicon wave plasma, comprising a discharge chamber, a magnet and a potential control electrode. The magnet is externally arranged on one end of the discharge chamber; a radio-frequency antenna is winded outside the discharge cavity and is adjacent to the magnet; the position of the discharge chamber working medium gas inlet of a discharge chamber working medium gas pipe is not beyond the front end of the adjacent radio-frequency antenna; the potential control electrode which is electrically connected with the conductive structural element of a spacecraft is arranged in the discharge cavity; a radio-frequency source is used for providing power supply for the radio-frequency antenna; and the working medium gas is ionized into the plasma, under the action of the electromagnetic field generated by the radio-frequency antenna and the magnetic field generated by the magnet. The invention further discloses the application of the spacecraft potential active control device based on the helicon wave plasma. The spacecraft potential active control device based on the helicon wave plasma has the advantages of low power consumption, light weight of used working medium, high potential control efficiency, high starting frequency and is superior to the prior art in the spacecraft potential control and the orbit energization effect risk control.

Description

technical field [0001] The invention belongs to the field of spacecraft potential control, and in particular relates to a spacecraft potential active control device and the application of the device. Background technique [0002] Usually, the spacecraft in space will produce a charging effect due to the interaction with the space plasma, which will cause potential differences between different positions on the spacecraft, cause electrostatic discharge, and ultimately endanger the safety of the spacecraft in orbit. For manned spaceflight, the electrification effect of the spacecraft may also cause the astronauts to generate electrostatic discharge after leaving the cabin, posing a threat to the health and life of the astronauts. [0003] At present, most foreign countries use hot wire emission, hollow cathode plasma emission, xenon plasma engine emission, indium ion source emission, pulse plasma source emission and other emission methods to generate artificial charged particl...

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Problems solved by technology

However, there have been no reports on the active control equipment and application of helicon wave plasma in spacecraft potential.

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