Geometric effects in applied-field MPD thrustersThree applied-field magnetoplasmadynamic (MPD) thruster geometries were tested with argon propellant to establish the influence of electrode geometry on thruster performance. The thrust increased approximately linearly with anode radius, while the discharge and electrode fall voltages increased quadratically with anode radius. All these parameters increased linearly with applied-field strength. Thrust efficiency, on the other hand, was not significantly influenced by changes in geometry over the operating range studied, though both thrust and thermal efficiencies increased monotonically with applied field strength. The best performance, 1820 sec I (sub sp) at 20 percent efficiency, was obtained with the largest radius anode at the highest discharge current (1500 amps) and applied field strength (0.4 Tesla).
Document ID
19900065517
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Myers, R. M. (NASA Lewis Research Center; Sverdrup Technology, Inc. Brook Park, OH, United States)
Mantenieks, M. (NASA Lewis Research Center Cleveland, OH, United States)
Sovey, J. (NASA Lewis Research Center Cleveland, OH, United States)