Abstract
Magnetoplasmadynamic (MPD) rocket thrusters are investigated numerically and experimentally at the Institut für Raumfahrtsysteme (IRS). The self-magnetic plasma flow in thermal and reaction non-equilibrium is modeled with thirteen conservation equations. A new finite volume solver has been developed to compute the steady-state solution. The upwinding scheme for the species and the time-stepping procedure will be described in detail, and numerical results for the hot anode thruster will be presented.
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Auweter-Kurtz, M., Coclici, C., Heiermann, J., Munz, CD., Sleziona, C. (2001). Magnetoplasmadynamic Rocket Thruster Simulation. In: Freistühler, H., Warnecke, G. (eds) Hyperbolic Problems: Theory, Numerics, Applications. International Series of Numerical Mathematics, vol 140. Birkhäuser, Basel. https://doi.org/10.1007/978-3-0348-8370-2_11
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DOI: https://doi.org/10.1007/978-3-0348-8370-2_11
Publisher Name: Birkhäuser, Basel
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