FIELD: engines and pumps.
SUBSTANCE: invention is related to rocket and space equipment, namely, to cruising and control electrojet propulsion systems of spacecrafts. Electrojet engine comprises cathode in the form of tube with multi-cavity emitter, which is installed and insulated with the help of insulator inside anode arranged in the form of conical annular nozzle. Engine additionally comprises thermal tube with coolant, heat exchange element of which is installed and insulated by means of high-temperature annular insulator on anode external surface, and heat-transmitting element is located on cathode external surface. Thermal tube provides for transfer of part of thermal energy released on anode to cathode. It results in lowering of electrodes temperature and, accordingly, higher adsorption of working substance particles on cathode working surface, cathode work function is reduced, and thermionic emission current is increased.
EFFECT: increased efficiency factor and resource of high-current engine.
1 dwg
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