Numerical simulation of geometric scale effects in cylindrical self-field MPD thrustersA 2D, two-temperature, single fluid MHD code which incorporates classical plasma transport coefficients and Hall effects has been developed to predict steady-state, self-field MPD thruster performance. The governing equations and numerical methods of solution are outlined and discussed. Experimental comparisons are used to validate model predictions. The model accurately predicts thrust and reproduces trends in the discharge voltage for discharge currents below experimentally measured onset values. However, because the model does not include electrode effects the calculated voltage drops are significantly lower than experimentally measured values. Predictions of thrust and flow efficiency are made for a matrix of fifteen cylindrical thruster geometries assuming a fully ionized argon propellant.
Document ID
19920066261
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lapointe, M. (Sverdrup Technology, Inc., Brook Park; NASA, Lewis Research Center Cleveland, OH, United States)