The invention discloses a space micro-newton-level electric propulsion
control system which comprises an instruction analysis module, a remote measurement acquisition module, a thrust conversion module, a
thrust control module and a DA control module. The instruction analysis module is used for analyzing an instruction sent by a
satellite platform and outputting analyzed parameters to the
thrust control module; the remote measurement acquisition module is used for controlling the AD acquisition
chip, acquiring
voltage and current fed back by the thruster, performing mean value
processing on the acquired
voltage and current, and sending the processed
voltage and current to the thrust conversion module; the thrust conversion module is used for converting the received voltage and current subjected to mean value
processing into corresponding thrust values and sending the thrust values to the
thrust control module; the thrust control module realizes thrust control by selecting open-
loop control or closed-
loop control, calculates a voltage value based on the received data, and outputs the voltage value to the DA
chip control module; and the DA
chip control module is used for converting the received voltage value into an N value and outputting the N value to the DA chip, so that the micronewton thrust is output to the thruster.