GLTRS--Glenn
TITLE AND SUBTITLE:
Numerical Study of Cathode Emission Constraints on Cylindrical Self-Field MPD Thruster Performance


AUTHOR(S):
Michael R. LaPointe

REPORT DATE:
January 1993

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
Sverdrup Technology, Inc.
Lewis Research Center Group
2001 Aerospace Parkway
Brook Park, Ohio 44142

PERFORMING ORGANIZATION REPORT NUMBER:
E-7416

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Lewis Research Center
Cleveland, Ohio 44135-3191

REPORT TYPE AND DATES COVERED:
Final Contractor Report

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA CR-190795

SUPPLEMENTARY NOTES:
Prepared for the Tenth Symposium on Space Nuclear Power and Propulsion sponsored by the Institute for Space Nuclear Power Studies, Albuquerque, New Mexico, January 10-14, 1993. Project Manager, James S. Sovey, (216) 433-7454.

ABSTRACT:
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. Realistic values for cathode emission current densities were used to provide additional constraints on the thruster geometries. A two-dimensional MPD 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, cylindrical 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.

SUBJECT TERMS:
MPD; Electric propulsion; Numerical simulation

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