Numerical study of cathode emission constraints on cylindrical, self-field MPD thruster performance

Conference · Wed Jan 20 04:00:00 EST 1993 · AIP Conference Proceedings (American Institute of Physics); (United States)

DOI:https://doi.org/10.1063/1.43110· OSTI ID:5460246

LaPointe, M R ^[1]

---

1. Sverdrup Technology, Inc. 2001 Aerospace Parkway, Brook Park, OH 44142 (United States)

A stability equation relating thruster discharge current, argon propellant mass flow rate, and electrode geometry has been solved for a variety of cylindrical self-field MPD thruster configurations and discharge currents code was employed to provide better estimates of the maximum achievable specific impulse, thrust, and flow efficiency for cases of interest. The model results indicate that long life, cyclindrical self-field MPD thrusters operated with argon propellant may not be able to provide specific impulse values in excess of 2100 s. Alternate electrode geometries, applied magnetic fields, and/or low molecular weight propellants may be necessary to achieve higher values of specific impulse.

• OSTI ID: 5460246
• Report Number(s): CONF-930103--
• Conference Information: Journal Name: AIP Conference Proceedings (American Institute of Physics); (United States) Journal Volume: 271:3
• Country of Publication: United States
• Language: English

Related Subjects

21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS
210600* -- Power Reactors
Auxiliary
Mobile Package
& Transportable
30 DIRECT ENERGY CONVERSION
300403 -- Thermionic Converters-- Materials
Components
& Auxiliaries
ARGON
CATHODES
COMPUTER CODES
CURRENT DENSITY
ELECTRODES
ELEMENTS
EMISSION
FLUIDS
GASES
IONIZATION
MAGNETIC FIELDS
MATHEMATICS
NESDPS Office of Nuclear Energy Space and Defense Power Systems
NONMETALS
NUMERICAL ANALYSIS
PERFORMANCE TESTING
PLASMA GUNS
RARE GASES
TESTING
THERMIONIC EMISSION
THRUSTERS