Abstract
Numericalmodeling of the NASALewis Research Center 100-kW, steady-state, applied- eld magnetoplasmadynamic thruster is performed using the magnetohydrodynamicscodeMACH2 for a range of applied magnetic eld strengths and discharge currents. Overall performance trends, obtained experimentally with argon propellant, are captured by the simulations. Magnitudes of plasma voltage vs applied eld strength also agree well. Interrogation of the calculated ow eld offers a new visualization of applied- eld magnetoplasmadynamic thruster operation, comprising the following elements: 1) the back electromotive force is the dominant contributor to the plasma voltage for the geometry examined; 2) viscous forces oppose applied azimuthal electromagnetic forces and limit the maximum rotational speed to a constant independent of applied eld or current value; 3) viscous heating and conversion of thermal energy to axial directed kinetic energy is the main acceleration mechanism; and 4) the low-density, low-conductivity argon plasma for the regime examined does not interact with the applied eld in the manner of a magnetic nozzle.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
