Helicon plasma thruster discharge model
By considering particle, momentum, and energy balance equations, we develop a semi-empirical quasi one-dimensional analytical discharge model of radio-frequency and helicon plasma thrusters. The model, which includes both the upstream plasma source region as well as the downstream diverging magnetic nozzle region, is compared with experimental measurements and confirms current performance levels. Analysis of the discharge model identifies plasma power losses on the radial and back wall of the thruster as the major performance reduction factors. These losses serve as sinks for the input power which do not contribute to the thrust, and which reduce the maximum plasma density and hence propellant utilization. With significant radial plasma losses eliminated, the discharge model (with argon) predicts specific impulses in excess of 3000 s, propellant utilizations above 90%, and thruster efficiencies of about 30%.
- OSTI ID:
- 22252971
- Journal Information:
- Physics of Plasmas, Journal Name: Physics of Plasmas Journal Issue: 4 Vol. 21; ISSN PHPAEN; ISSN 1070-664X
- Country of Publication:
- United States
- Language:
- English
Similar Records
Operating a magnetic nozzle helicon thruster with strong magnetic field
Direct thrust measurement of a permanent magnet helicon double layer thruster
Helicon thruster plasma modeling: Two-dimensional fluid-dynamics and propulsive performances
Journal Article
·
Tue Mar 15 00:00:00 EDT 2016
· Physics of Plasmas
·
OSTI ID:22599081
Direct thrust measurement of a permanent magnet helicon double layer thruster
Journal Article
·
Mon Apr 04 00:00:00 EDT 2011
· Applied Physics Letters
·
OSTI ID:21518370
Helicon thruster plasma modeling: Two-dimensional fluid-dynamics and propulsive performances
Journal Article
·
Mon Apr 15 00:00:00 EDT 2013
· Physics of Plasmas
·
OSTI ID:22130482