Experimental Identification of Thrust Components Imparted by an Electrodeless Helicon Plasma Thruster

Abstract

Thrust components imparted by an electrodeless helicon plasma thruster including a magnetic nozzle are experimentally measured and analytically derived from momentum equations assuming a cold ion, negligible electron inertia and radial ion inertia. The magnetic nozzle of the maximum field strength of ~180 Gauss is provided by a solenoid coil located near the thruster exit. It is found that the total thrust can be given by the sum of an electron pressure force onto the source boundary and a Lorentz force generated by a radial magnetic field and an azimuthal electron diamagnetic drift current in the magnetic nozzle. Further, a permanent magnet helicon plasma thruster for more efficient and compact plasma thruster is also designed and tested.