Development and testing of a low-current applied-field magnetoplasmadynamic thruster with a rectangular discharge channel

Abstract This study explores the possibility of miniaturizing magnetoplasmadynamic thrusters (MPDTs) to significantly lower power and discharge current levels compared most conventional MPDTs. A design alternative for MPDTs using a channel with rectangular cross-section is presented that enables implementation strong external magnetic fields increase applied-field Lorentz force. The thruster concept uses heaterless calcium aluminate electride (C12A7:e-) hollow cathodes as electron source. prototype intended low-amp range generates thrust in low millinewton specific impulse ranging between 400 s 1200 at below 500 W but shows high thermal losses anode. further miniaturized version sub-amp thermally more sustainable requires mass flow rates achieve stable discharge, limiting achievable impulse.