FIELD: motors and pumps.
SUBSTANCE: invention is used in satellite engineering. The electric propulsion system contains, at least, one electric motor (10), the power supply system of the propulsion (10) containing the high pressure tank (1) for ionized gas, the low pressure buffer tank (2) connected with the high pressure tank (1) by means of the valve (5, 6) and system of pipelines for gas transfer from the low pressure buffer tank (2) to the anode (26) and the cathode (40) of the propulsion. The low pressure buffer tank (2) is joined by the open interconnection with the propulsion (10). The electric propulsion system contains devices for detection of drop of discharge current between the anode (26) and the cathode (40) below the threshold value, and for cutting off of the discharge voltage as a result of this detection.
EFFECT: design improvement.
4 cl, 8 dwg
