Spacecraft tail area ion atmosphere ground-based simulation method

Abstract

The invention provides a spacecraft tail area ion atmosphere ground-based simulation method. According to the method, combination of a specific plasma source and an ion accelerating grid mesh is utilized, and therefore a polar-orbiting ion environment required by a charging experiment of a ground polar-orbiting satellite tail area can be effectively generated; the advantage of the simple structure is achieved. The method comprises the steps that on the basis of the principle of conservation of energy, a bias voltage of the ion accelerating grid mesh and a bias voltage of a main anode grid mesh in the plasma source are designed; on the basis of a Charlie Langmuir equation, the distance d between the main anode grid mesh in the plasma source and the ion accelerating grid mesh is designed; in the experiment process, the plasma source is controlled to generate ions; a power source of the ion accelerating grid mesh is switched on to form a parallel electric field, and the ions generated by the plasma source are guided out under action of the parallel electric field to form an ion beam flow; a Faraday cup is started, and the strength of the ion beam flow is measured; when the strength reaches the requirement, the experiment in the tail area ion environment is started.

Description

technical field [0001] The invention belongs to the field of space plasma environment ground simulation, and is applicable to the ground simulation of the ion environment in the tail area of ​​the low-orbit-orbit spacecraft including polar orbits, and in particular relates to an ion environment in the background plasma environment that causes the electrification effect in the spacecraft tail area ground simulation method. Background technique [0002] When a polar-orbiting satellite operates in a low-temperature, high-density polar plasma environment, an obvious "track" is formed at its tail, which is an unequal electron and ion depletion region. Since the orbital velocity of satellites is greater than the thermal velocity of ions but lower than the thermal velocity of electrons, electrons can easily enter this region to form a negative potential barrier, which is the so-called "wake effect". Its obvious effect on the satellite is that the surface of the tail medium will be...

AI Technical Summary

Problems solved by technology

[0006] At present, in the ground simulation experiment of the electrified effect in the tail region of the polar orbiting spacecraft,

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