FIELD: electrical engineering.
SUBSTANCE: invention relates to the field of electrical engineering, in particular to the field of space technology, and can be used to eliminate the accumulated static surface charges (electrons) on the elements of the outer structure of spacecraft. The electrification regulator (ER) of the spacecraft contains sensors for controlling the level of electrification of the spacecraft surface fragments and plasma engines with systems for power supply, control and supply of the working fluid to the engine chambers. Spacecraft ER also contains accelerator channels (AC) of plasma engines, which in the zone of low-temperature plasma creation are connected by side inlet gas lines, which have semi-cylindrical intake shells at the beginning in the AC, and side outlet gas lines with electrovalves located on them with neutralizers limited from all sides and communicating with the external environment through only gas lines. The composition of the gas mains includes metallized fragments of the spacecraft surface and thermoelements rigidly placed on them and having a galvanic connection with them.
EFFECT: emission of electrons of differential charging from the surfaces of the spacecraft that are in contact with the PD plasma is improved.
1 cl, 2 dwg
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Authors
Dates
2022-04-25—Published
2021-11-10—Filed