Performance characterization of a helicon double layer thruster using direct thrust measurements

Abstract

The performance of a helicon double layer thruster (HDLT) has been characterized using a pendulum type thrust stand and retarding field energy analyser. Data recorded for a fixed propellant flow rate of 16 sccm of krypton and fixed magnetic field topology show that the thrust generated increases linearly with increasing radio frequency input power over a range 250–650 W. Over the power range investigated thrust levels of approximately 1–2.8 mN were achieved. A maximum effective specific impulse of 280 s was determined using the thrust data. Ion energy distribution functions indicate that increasing power corresponds to improved plasma generation processes as general trends show increasing plasma and beam currents with increasing power.