Abstract
A time dependent, 2-dimensional axisymmetric MHD simulation code, MACE2, is adopted to model both self-field and applied-field magneto-plasmadynamic thrusters. One of the NASA Lewis MFD thruster configurations is considered with operation at 1000 amp discharge current and 0.1 g/s mass flow rate. The applied field simulations include in-plane magnetic field contributions from induced azimuthal currents generated by the plasma. Simulations of both self-field and several low applied-field cases (varying the external magnet coil current) have successfully reached steady state and depict distributions of magnetic field, velocity and temperature.Overel1 arcjet performance in terms of specific impulse is estimated.
Original language | English (US) |
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State | Published - 1992 |
Externally published | Yes |
Event | AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992 - Nashville, United States Duration: Jul 6 1992 → Jul 8 1992 |
Other
Other | AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992 |
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Country/Territory | United States |
City | Nashville |
Period | 7/6/92 → 7/8/92 |
ASJC Scopus subject areas
- Mechanical Engineering
- Aerospace Engineering
- Energy Engineering and Power Technology
- Control and Systems Engineering
- Electrical and Electronic Engineering