Performance of a 100 kW class applied field MPD thrusterThe performance of a 100 kW class, applied field MPD thruster was evaluated and sensitivities of discharge characteristics to arc current, mass flow rate, and applied magnetic field were investigated. Thermal efficiencies as high as 60 percent , thrust efficiencies up to 21 percent, and specific impulses of up to 1150 s were attained with argon propellant. Thrust levels up to 2.5 N were directly measured with an inverted pendulum thrust stand at discharge input powers up to 57 kW. It was observed that thrust increased monotonically with the product of arc current and magnet current.
Document ID
19890059664
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mantenieks, M. A. (NASA Lewis Research Center Cleveland, OH, United States)
Sovey, J. S. (NASA Lewis Research Center Cleveland, OH, United States)
Haag, T. W. (NASA Lewis Research Center Cleveland, OH, United States)
Raitano, P. (NASA Lewis Research Center Cleveland, OH, United States)
Myers, R. M. (NASA Lewis Research Center Cleveland, OH, United States)
Parkes, J. E. (NASA Lewis Research Center; Sverdrup Technology, Inc. Cleveland, OH, United States)