A Time-sharing Stabilization Control Method for Hall Electric Propulsion Discharge Current

A stable control method and discharge current technology, which are applied in the field of Hall electric propulsion time-division stable control of discharge current and discharge current time-division stability control, which can solve the problem of overshooting of air supply flow rate, thruster flameout, excessive discharge current oscillation, etc. problems, to achieve the effect of improving efficiency, suppressing low-frequency oscillation, and improving work performance

Active Publication Date: 2018-02-06
BEIJING INST OF CONTROL ENG
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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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  • A Time-sharing Stabilization Control Method for Hall Electric Propulsion Discharge Current
  • A Time-sharing Stabilization Control Method for Hall Electric Propulsion Discharge Current
  • A Time-sharing Stabilization Control Method for Hall Electric Propulsion Discharge Current

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Embodiment Construction

[0028] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0029] figure 1 is the flow chart of the time-sharing stabilization control strategy of the Hall electric propulsion discharge current, from figure 1 It can be seen that a time-sharing stable control method for Hall electric propulsion discharge current proposed by the present invention comprises the following steps:

[0030] (1) At the beginning of the ignition process of the Hall electric propulsion system, judge whether the anode flow closed-loop control bFlowControl is enabled in each control cycle, if bFlowControl=1, start the anode flow closed-loop control, that is, set FlowControlStart=1, and enter the step ( 2) Continue the electric propulsion ignition process, if bFlowControl=0, then close the anode flow closed-loop control, that is, set FlowControlStart=0, and stop the electric propulsion ignition process;

[0031] figure...

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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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B19/04
CPCG05B19/04
Inventor 高俊汤章阳刘国西李永邹达人刘忠汉武葱茏王戈马彦峰沈岩
Owner BEIJING INST OF CONTROL ENG
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