Effect of a magnetic field in simulating the plume field of an anode layer Hall thruster
- Department of Aerospace Engineering, University of Michigan, Ann Arbor, Michigan 48109 (United States)
- Department of Mechanical and Aerospace Engineering, George Washington University, Washington, DC 20052 (United States)
In this study, we present axisymmetric simulations of xenon plasma plume flow fields from a D55 anode layer Hall thruster. A hybrid particle-fluid method is used for the simulations. The magnetic field surrounding the Hall thruster exit is included in the calculation. The plasma properties obtained from a hydrodynamic model are used as boundary conditions for the simulations. The electron properties are calculated using the Boltzmann model and a detailed fluid model, collisions of heavy particle are modeled with the direct simulation Monte Carlo method, and ion transport in the electric field uses the particle-in-cell technique. The accuracy of the simulation is assessed through comparison with various measured data. It is found that a magnetic field significantly affects the profile of the plasma in the detailed model. The plasma has a potential of 80 V at 10 mm from the thruster exit in the case of zero magnetic field, which decreases to 60 V when the magnetic field is included. Results predicted by the detailed model with the magnetic field are found to be in better agreement with experimental data.
- OSTI ID:
- 21185941
- Journal Information:
- Journal of Applied Physics, Vol. 105, Issue 1; Other Information: DOI: 10.1063/1.3055399; (c) 2009 American Institute of Physics; Country of input: International Atomic Energy Agency (IAEA); ISSN 0021-8979
- Country of Publication:
- United States
- Language:
- English
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