Abstract
Numerical modeling of the NASA LeRC 100 kW, steady-state, applied-field MPD thruster is performed using the magnetohydrodynamics code, MACH2, for a range of applied magnetic field strengths and discharge currents. Overall performance trends, obtained experimentally, are captured by the simulations. Magnitudes of plasma voltage versus applied field strength also agree well. Interrogation of the calculated flow field offers a new visualization of applied-field MPD thruster operation, comprising the following elements: a) the back electromotive force is the dominant contributor to the plasma voltage for the geometry examined. b) viscous forces oppose applied azimuthal electromagnetic forces and limit the maximum rotational speed to a constant independent of applied field or current value. c) viscous heating and conversion of thermal energy to axial directed kinetic energy is the main acceleration mechanism. d) the low density, low conductivity plasma for the regime examined does not interact with the applied field in the manner of a magnetic nozzle.
| Original language | English (US) |
|---|---|
| Title of host publication | 31st Joint Propulsion Conference and Exhibit |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| ISBN (Print) | 9780000000002 |
| State | Published - 1995 |
| Externally published | Yes |
| Event | 31st Joint Propulsion Conference and Exhibit, 1995 - San Diego, United States Duration: Jul 10 1995 → Jul 12 1995 |
Other
| Other | 31st Joint Propulsion Conference and Exhibit, 1995 |
|---|---|
| Country | United States |
| City | San Diego |
| Period | 7/10/95 → 7/12/95 |
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ASJC Scopus subject areas
- Energy Engineering and Power Technology
- Electrical and Electronic Engineering
- Mechanical Engineering
- Control and Systems Engineering
- Aerospace Engineering
Cite this
Theoretical model for applied-field MPD thrusters. / Mikellides, Pavlos; Turchi, Peter J.; Roderick, Norman F.
31st Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1995. AIAA 95-2676.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Theoretical model for applied-field MPD thrusters
AU - Mikellides, Pavlos
AU - Turchi, Peter J.
AU - Roderick, Norman F.
PY - 1995
Y1 - 1995
N2 - Numerical modeling of the NASA LeRC 100 kW, steady-state, applied-field MPD thruster is performed using the magnetohydrodynamics code, MACH2, for a range of applied magnetic field strengths and discharge currents. Overall performance trends, obtained experimentally, are captured by the simulations. Magnitudes of plasma voltage versus applied field strength also agree well. Interrogation of the calculated flow field offers a new visualization of applied-field MPD thruster operation, comprising the following elements: a) the back electromotive force is the dominant contributor to the plasma voltage for the geometry examined. b) viscous forces oppose applied azimuthal electromagnetic forces and limit the maximum rotational speed to a constant independent of applied field or current value. c) viscous heating and conversion of thermal energy to axial directed kinetic energy is the main acceleration mechanism. d) the low density, low conductivity plasma for the regime examined does not interact with the applied field in the manner of a magnetic nozzle.
AB - Numerical modeling of the NASA LeRC 100 kW, steady-state, applied-field MPD thruster is performed using the magnetohydrodynamics code, MACH2, for a range of applied magnetic field strengths and discharge currents. Overall performance trends, obtained experimentally, are captured by the simulations. Magnitudes of plasma voltage versus applied field strength also agree well. Interrogation of the calculated flow field offers a new visualization of applied-field MPD thruster operation, comprising the following elements: a) the back electromotive force is the dominant contributor to the plasma voltage for the geometry examined. b) viscous forces oppose applied azimuthal electromagnetic forces and limit the maximum rotational speed to a constant independent of applied field or current value. c) viscous heating and conversion of thermal energy to axial directed kinetic energy is the main acceleration mechanism. d) the low density, low conductivity plasma for the regime examined does not interact with the applied field in the manner of a magnetic nozzle.
UR - http://www.scopus.com/inward/record.url?scp=84964497115&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84964497115&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84964497115
SN - 9780000000002
BT - 31st Joint Propulsion Conference and Exhibit
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
ER -