Session
Session II: Liquid to Gas
Abstract
A xenon-fueled, micro rf ion engine suitable for small satellite propulsion was developed by Busek. Operating with a pair of grids that are 3 cm in diameter, the thruster demonstrates 1.4-2.1 mN thrust and 1500-2850 seconds Isp. Total power consumption ranges from 60 to 100 W. At the optimum Isp of 2500 seconds, the estimated thrust efficiency and propellant utilization is 49 % and 47%, respectively. Total efficiency, including 9 0% dc-to-rf conversion, is estimated at 21%. The total efficiency can potentially be increased up to 27% by reducing rf coupling loss. Busek is dedicated to further miniaturize rf ion engines with the development of a 1-cm thruster equipped with a propellant-less carbon nanotube field emission neutralizer. Projected performance of the 1-cm micro rf ion engine is 0.15 mN thrust, 1570 seconds Isp and 14 W total power consumption.
Presentation Slides
Micro RF Ion Engine for Small Satellite Applications
A xenon-fueled, micro rf ion engine suitable for small satellite propulsion was developed by Busek. Operating with a pair of grids that are 3 cm in diameter, the thruster demonstrates 1.4-2.1 mN thrust and 1500-2850 seconds Isp. Total power consumption ranges from 60 to 100 W. At the optimum Isp of 2500 seconds, the estimated thrust efficiency and propellant utilization is 49 % and 47%, respectively. Total efficiency, including 9 0% dc-to-rf conversion, is estimated at 21%. The total efficiency can potentially be increased up to 27% by reducing rf coupling loss. Busek is dedicated to further miniaturize rf ion engines with the development of a 1-cm thruster equipped with a propellant-less carbon nanotube field emission neutralizer. Projected performance of the 1-cm micro rf ion engine is 0.15 mN thrust, 1570 seconds Isp and 14 W total power consumption.
