Numerical Simulation of Cylindrical, Self-field MPD Thrusters with Multiple Propellants

A two-dimensional, two-temperature, single fluid MHD code was used to predict the performance of cylindrical, self-field magnetoplasmadynamic (MPD) thrusters operated with argon, lithium, and hydrogen propellants. A thruster stability equation was determined relating maximum stable J(sup 2)/m values to cylindrical thruster geometry and propellant species. The maximum value of J(sup 2)/m was found to scale as the inverse of the propellant molecular weight to the 0.57 power, in rough agreement with limited experimental data which scales as the inverse square root of the propellant molecular weight. A general equation which relates total thrust to electromagnetic thrust, propellant molecular weight, and J(sup 2)/m was determined using reported thrust values for argon and hydrogen and calculated thrust values for lithium. In addition to argon, lithium, and hydrogen, the equation accurately predicted thrust for ammonia at sufficiently high J(sup 2)/m values. A simple algorithm is suggested to aid in the preliminary design of cylindrical, self-field MPD thrusters. A brief example is presented to illustrate the use of the algorithm in the design of a low power MPD thruster.

[1]  W. D. Deininger,et al.  A review of nuclear electric propulsion spacecraft system concepts , 1990 .

[2]  Arnold J. Kelly,et al.  A high performance magnetoplasmadynamic thruster , 1984 .

[3]  Yukio Shimizu,et al.  Application of MPD thruster systems to interplanetary missions , 1986 .

[4]  Pavlos Mikellides,et al.  Application of the MACH 2 code to magnetoplasmadynamic arcjets , 1992 .

[5]  Roger M. Myers,et al.  100-kW class applied-field MPD thruster component wear , 1993 .

[6]  Monika Auweter-Kurtz,et al.  Numerical calculation of nozzle type and cylindrical MPD thrusters , 1992 .

[7]  Roger M. Myers,et al.  MPD thruster technology , 1991 .

[8]  H. Hugel,et al.  Effect of Self-Magnetic Forces on the Anode Mechanism of a High Current Discharge , 1980, IEEE Transactions on Plasma Science.

[9]  Eliahu Haym Niewood,et al.  An explanation for anode voltage drops in an MPD thruster , 1993 .

[10]  Kazuo Uematsu,et al.  MPD thruster performance with various propellants , 1985 .

[11]  M. Lapointe.  Numerical study of cathode emission constraints on cylindrical, self‐field MPD thruster performance , 1993 .

[12]  James S. Sovey,et al.  Performance and lifetime assessment of MPD arc thruster technology , 1988 .

[13]  Ernst Messerschmid,et al.  Gradient driven instabilities in stationary MPD thruster flows , 1990 .

[14]  Jeffrey C. Preble.  Onset in magnetoplasmadynamic thrusters : a model of an electrothermal instability , 1990 .

[15]  La Pointe,et al.  Numerical simulation of self-field MPD thrusters , 1991 .

[16]  Manuel Martinez-Sanchez,et al.  Structure of self-field accelerated plasma flows , 1991 .

[17]  J. H. Gilland,et al.  Multimegawatt electric propulsion system design considerations , 1990 .

[18]  Roger M. Myers,et al.  Applied-field MPD thruster geometry effects , 1991 .

[19]  A. M. Shroff,et al.  Performance and life tests of various types of impregnated cathodes , 1981 .

[20]  James H. Gilland,et al.  Low Power Pulsed MPD Thruster System Analysis and Applications , 1993 .

[21]  J. E. Polk,et al.  Alkali metal propellants for MPD thrusters , 1991 .

[22]  M. Lapointe,et al.  Numerical simulation of geometric scale effects in cylindrical self-field MPD thrusters , 1992 .

[23]  J. L. Lawless,et al.  Theory of onset in magnetoplasmadynamic thrusters , 1987 .

[24]  J. L. Lawless,et al.  Onset in magnetoplasmadynamic thrusters with finite-rate ionization , 1988 .