Ionentriebwerk, Modellierung, Plasma, Plasmaphysik, Electric Propulsion, Ion Thruster, Particle-in-Cell, Plasma Modeling, Plasmasimulation
The importance of ion propulsion devices as an option for in-space propulsion of space crafts and satellites continues to grow. They are more efficient than conventional chemi- cal thrusters, which rely on burning their propellant, by ionizing the propellant gas in a discharge channel and emitting the heavy ions at very high velocities. The ion emission region of a thruster is called the plume and extends several meters axially and radially downstream from the exit of a thruster. This region is particularly important for the effi- ciency of a thruster, because it determines energy and angular distribution of the emitted ions. It also determines the interaction with the carrier space craft by defining the electric potential shape and the fluxes and energies of the emitted high energy ions, which are the key parameters for sputter erosion of satellite components such as solar panels. Developing new ion thrusters is expensive because of the high number of prototypes and testing cycles required. Numerical modeling can help to reduce the costs in thruster development, but the vastly differing length and time scales of the system, particularly the large differences of scales between the discharge chamber and the plume, make a simulation challenging. Often both regions are considered to be decoupled and are treated with different models to make their simulation technically feasible. The coupling between channel and plume plasmas and its influence on each other is disregarded, ...
Kinetic and fluid modeling of ion thruster plumes
2019
1 Online-Ressource (PDF-Datei: 175 Seiten, 12552 Kilobyte)
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Literaturverzeichnis: Seite 53-62
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English
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