Electric propulsion plume test evaluation method

Abstract

The invention discloses an electric propulsion plume test evaluation method, which comprises the following steps: measuring ion beam density, electron concentration and space plasma potential of a main beam plume region and a backflow plume region to obtain a force effect of plume on a satellite solar wing and a thermal radiation effect evaluation result; measuring charging voltage and leakage current of different materials on the surface of a solar cell array in a plume plasma environment and surface potential of the solar cell array in the plume plasma environment to obtain charging and discharging effect evaluation results of the plume for the surfaces of the satellite solar wing and a satellite body; and measuring plasma plume pollution amount of sensitive equipment test samples on thesurfaces of the satellite solar wing and the satellite body to obtain a sediment pollution effect evaluation result of the plume for the sensitive equipment on the surfaces of the satellite solar wing and the satellite body. The method realizes test analysis and research of plume's pollution to satellite surface, ion sputtering corrosion and the impact of plume on satellite surface potential.

Description

technical field [0001] The invention belongs to the technical field of electric propulsion systems, in particular to an electric propulsion plume test evaluation method. Background technique [0002] The electric propulsion plume refers to the feather-like flow field formed by the expansion of the jet flow to the external vacuum environment when the electric thruster is working. The components of the ion thruster plume are ions, electrons, unionized neutral particles, charge-exchange ions, and sputtering pollutants generated by the ionization of the propellant. strongly coupled. The plasma generated by the electric thruster can be divided into two parts, one is the beam plasma directly ejected from the thruster, the beam ion energy is high, and because it is little affected by the electromagnetic field, the trajectory is almost a straight line. The beam ions are mainly distributed in the conical surface with a half angle of 15°-60°. The other part is composed of exchanged...

AI Technical Summary

Problems solved by technology

[0007] (2) The charge deposition of the plume on the surface of the spacecraft will change the electrostatic environment of the spacecraft, and may cause charging and discharging effects;

[0011] (6) The current fluctuation of the thruster will cause various high-frequency plasma oscillations, which will interfere with the radio communication of the spacecraft

Images