Abstract
In this paper an overview is given on a numerical simulation program for applied field magnetoplasmadynamic (AF–MPD) thrusters, which is currently under development at the Institute of Space Systems (IRS). The program allows the simulation of argon plasma flows under thermal and chemical non–equilibrium. The code is based on an axisymmetric finite volume method on unstructured, adaptive meshes. An externally applied magnetic field can be taken into account employing the vector potential formulation. Azimuthal velocity and magnetic field are handled by a quasi–three dimensional approach with vanishing azimuthal derivatives. Besides the numerical analysis, a radiation–cooled laboratory model of an AF– MPD thruster is under development at IRS. The thruster model is to be assembled into a thrust balance. The modular design allows adjustments of the electrode and magnetic field configuration to find an optimized thruster geometry based on numerical and experimental results.
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