The numerical simulation and modeling of plasma detachment from a
magnetic nozzle is presented. The detachment problem is of key importance to
the plasma-based propulsion concepts that employ a guiding magnetic field to
control plasma flow and motivated by the needs of the VASIMR (Variable Specific
Impulse Magnetoplasma Rocket) project. The detachment of the plasma
exhaust is required to produce directed thrust. In the present scenario plasma
can stretch the magnetic field lines to infinity, similar to the solar wind. In
order to extend the magnetic nozzle model beyond the limitations of analytic
theory, a numerical code is developed to simulate steady-state kinetic plasma
flows and to evaluate nozzle efficiency. The direct solution of a steady-state
problem, as opposed to an initial value problem, eliminates the need to deal
with transient phenomena that are of secondary importance for continuously
operated plasma thrusters. The new simulation code is verified against the
analytic results and then used to model the plasma behaviour for the conditions
of the Detachment Demonstration Experiment (DDEX) at the NASA
Marshall Propulsion Research Center, Huntsville, Alabama. / text
| Identifer | oai:union.ndltd.org:UTEXAS/oai:repositories.lib.utexas.edu:2152/ETD-UT-2010-12-2458 |
| Date | 09 February 2011 |
| Creators | Tushentsov, Mikhail R. |
| Source Sets | University of Texas |
| Language | English |
| Detected Language | English |
| Type | thesis |
| Format | application/pdf |
Page generated in 0.0023 seconds