Hollow cathode charge exchange method and device

Abstract

The invention relates to a hollow cathode charge exchange method. The method comprises a step of constructing a simulation model of a hollow cathode, and calculating the C-V characteristic curve and main parameter of the hollow cathode, a step of determining multiple ground test equipment of the hollow cathode according to a preset space task, a step of carrying out ground test of the hollow cathode according to the parameter indexes of the ground test equipment, and a step of adjusting index requirements according to collected various working parameters of the hollow cathode in a ground test process until the working test of the hollow cathode is completed. According to the hollow cathode charge exchange method, under the condition of fixed power consumption, the working medium flow can be reduced, the emission current can be improved, the working efficiency of the hollow cathode is improved, in the same working medium flow and emitting current working conditions, the bias voltage and working power consumption can be reduced, the working index of the hollow cathode is raised to an international advanced level, the emission current, touch level voltage and other important parameters of the hollow cathode can be effectively improved, and the requirements of passive deorbit of a spacecraft is satisfied.

Description

technical field [0001] The invention relates to the field of comprehensive electronic technology, in particular to a hollow cathode charge exchange method and device. Background technique [0002] As human activities in space such as scientific experiments, deep space exploration, commercial services, and space military applications become more and more frequent, there are more and more garbage in the space environment. However, the existing propulsion system needs propellant, the system is heavy and the thrust produced is small, which is unfavorable for use. In order to ensure safe space activities, it is necessary to develop a propulsion system for passive de-orbiting of spacecraft. [0003] Compared with other propulsion systems, the electric power rope passive derailment system based on hollow cathode charge exchange technology has the advantages of no propellant, large thrust, and light system weight. It should be regarded as a priority development direction for resear...

AI Technical Summary

Problems solved by technology

[0005] In view of the defects that the existing propulsion system needs propellant, the system is heavy and the thrust generated is small, so it is not conducive to use, the present invention proposes a hollow cathode charge exchange method on the one hand, including:

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