DESIGN OF AN RF ION THRUSTER

Abstract

Today, it is quite common for many space propulsion applications of satellites and spacecrafts to practice the electric propulsion techniques, where both ion thruster and Hall thrusters have been successful. The trend is not restricted to an alternative thruster design with higher specific impulse (Isp), efficiency and long operation time that leads to increment in payload mass and available electric power. One of the promising electric thrusters is Radio Frequency Ion Thruster (RIT) that utilizes electro-magnetic field for plasma production and was first presented by Hittorf in 1884. Later on, there were various Radio Frequency plasma devices built from his ideal. These include RF ion sources for neutral beam injection systems of fusion devices, plasma processing for microelectronics, plasma etching, plasma deposition and plasma propulsion. Ideally, the work at Applied Aerodynamics Research Laboratory in University of Ulsan is focused on the development of RF ion thruster, which is called iU-50 ion thruster. The 50 W-class RF Ion Engine is an experimental ion thruster and will be tested in the vacuum chamber at Applied Aerodynamics Research Laboratory in University of Ulsan. The iU-50 has a conical discharge chamber having an inner and outer diameter of 50 mm and 61 mm respectively, with 61 mm length. A double grid system with 211 holes is implemented. iU-50 Ion Thruster is expected to produce a thrust and Isp of about 5 mN and 2600s at 2 sccm and 50 w of power consumption.