Aiming at meeting the application requirements of high-power electric propulsion systems for the deep space explorations in China

such as Jupiter detection and asteroid sampling return

we performed research on a high-power ion thruster. A high-power ion thruster prototype model was completed by using four ring-cusp field discharge chamber

40 cm beam current extraction diameter three-grid ion optics system

LaB6 hollow cathode with a graphite keeper electrode

higher temperature stabilized magnets and other advanced technologies and materials. The operating parameters and performance of the 40 cm ion thruster were tested

which included discharge loss

discharge propellant utilization efficiency

accelerator current

decelerator current

beam flatness parameter

thrust

specific impuls

e and total efficiency. The results show that its thrust

specific impulse

efficiency and beam flatness parameter at the power of 6.94 kW are 232 m N

4367 s

71%

and 0.72

respectively.