Volt-ampere characteristics, nozzle temperature and thruster performances in a low power argon arcjet

Argon gas with simple atomic structure and\nfavorite arcing stability at low input power was used as\nthe propellant. The thruster with a regeneratively cooled\nnozzle were tested in a vacuum system capable of\nkeeping the chamber pressure at about 10 Pa at a\npropellant feeding rate of 5 slm. Arc current, arc voltage,\nthrust, nozzle temperature and propellant feeding rate\nwere measured in situ simultaneously. Effects of the\nworking parameters such as the propellant feeding rate\nand arc current on the thruster performances, mainly the\nproduced thrust, specific impulse and thrust efficiency,\nwere examined. The variation of arc volt-ampere\ncharacteristics with running time and the effect of nozzle\ntemperature on thruster property are discussed.