Time-shared stabilized control method of hall electric propulsion discharging current

Abstract

The invention relates to a time-shared stabilized control method of a hall electric propulsion discharging current. On the basis of a time-shared control strategy, a relatively stable anode throttler temperature is used as a closed-loop feedback parameter at an initial ignition stage, so that failed ignition caused by using a high-oscillation discharging current as a feedback parameter directly can be avoided. After successful ignition, the discharging current oscillation amplitude is reduced; and then the discharging current is used as the closed-loop feedback parameter directly, thereby realizing stable control of the discharging current of the hall electric propulsion system, suppressing the low-frequency oscillator of the discharging current, and improving the efficiency. According to the time-shared control strategy, ignition reliability of the hall electric propulsion system at the initial ignition stage is guaranteed and the working performance of the hall electric propulsion system during the operating process is also improved.

Description

technical field [0001] The invention relates to a time-sharing stable control method of discharge current, in particular to a time-sharing stable control method of Hall electric propulsion discharge current, which belongs to the field of electric propulsion. Background technique [0002] Hall electric propulsion technology is an efficient space propulsion technology, because the specific impulse is nearly an order of magnitude higher than that of traditional chemical propulsion technology, which can significantly reduce the amount of propellant carried by satellites, increase the payload weight, and reduce launch costs. One of the most advanced space propulsion technologies in the world. [0003] With the rapid development of my country's aerospace technology, the load capacity and service life of satellite platforms have become the main shortcoming that restricts the international competitiveness of my country's satellite platforms. Electric propulsion technology is an inev...

AI Technical Summary

Problems solved by technology

For the discharge current oscillation below 100 Hz caused by the fluctuation of the gas supply flow rate of the propellant, it is mainly realized by introducing the discharge current feedback to carry out precise closed-loop control of the gas supply flow rate, but this method will cause excessive discharge current oscillation in the initial stage of Hall electric propulsion ignition. Causes overshoot of supply flow rate, risking thruster flameout

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