Electromagnetic effects in an applied-field magnetoplasmadynamic thruster

TLDR

Experimental and analytical studies have examined the performance and thrust production mechanisms of an applied‑field magnetoplasmadynamic thruster. From performance measurements and theoretical analysis, the thruster operation is governed by the parameter B²/m, where B is the applied magnetic field strength and m is the propellant mass flow rate. The thruster achieved high performance driven by strong electromagnetic effects, attaining over 20 % thrust efficiency across a 1000–7000 s specific‑impulse range with hydrogen, helium, and argon propellants at 2.2–15.9 kW input power. The paper cites nine references.

Abstract

Experimental and analytical studies have been conducted on the performance and thrust production mechanisms of an applied-field magnetoplasmadynamic thruster. The thruster was able to run with a high-thruster performance due to large electromagnetic effects related to the applied magnetic field. Using hydrogen, helium, and argon as the propellant, over 20 percent thrust efficiency was obtained over a wide specific impulse range from 1000 to 7000 s at input power levels between 2.2 and 15.9 kW. From the measurements of performance characteristics and current densities in the acceleration region, and by a theoretical analysis, it is found that the thruster operation is characterized by a parameter, B-squared/m (B: applied magnetic field strength, m: propellant mass flow rate). 9 refs.