Abstract
Pulsed magnetoplasmadynamic (MPD) thrusters offer ease of power scaling, reduced test facility requirements, and the potential of launch cost reductions through efficient high specific impulse operation at power levels which make them attractive for several primary propulsion missions. This work addresses the operational design of 10 kW class pulsed applied-field MPD thrusters for solar electric orbit transfer vehicles (SEOTVs). The design includes integration of heated cathode technology to meet lifetime requirements for orbit transfer. Propellant injection system design insures Paschen breakdown and high propellant utilization efficiency. Thermal modeling shows that the temperature distribution does not exceed any thruster material limits. This analysis illustrates the thermal issues involved with applied-field thruster average power scaling, and identifies necessary design modifications for cathode life issues. Applied magnetic fields enhance thruster efficiency, and experiments show that two insulating axial slits in the anode are sufficient to insure rapid pulsed field diffusion. 32 refs.
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