Magnetohydrodynamic Operating Regimes of Pulsed Plasma Accelerators for Efficient Propellant Utilization (2503.08889v2)

Abstract: The presence of magnetohydrodynamic (MHD) acceleration modes in pulsed plasma thrusters has been verified using the magnetic extension of Rankine-Hugoniot theory. However, the impact of initial conditions within the accelerator volume on the formation and structure of these modes remains poorly understood. This work develops a regime map to clarify how key initial conditions - such as propellant gas dynamics, pulse energy, and the timing between propellant injection and discharge initiation - govern transitions between two distinct MHD operating modes, a magneto-detonation and magneto-deflagration, along with an unstable transition regime that connects them. To characterize these regimes, a combination of time-of-flight and thrust stand diagnostics was used to assess their properties, scalability, and structure while operating with air. Time-of-flight measurements reveal that reducing the initial downstream propellant mass ($m_{dwn}$) of air from 120 $\mu$g to 60 $\mu$g shifts the thruster from the magneto-detonation to the magneto-deflagration regime, increasing exhaust velocity ($v_{ex}$) from 20 km/s to 55 km/s. In this regime, the thruster exhibits improved propellant utilization as less mass is injected. At a constant 8 kA of peak current, specific impulse (Isp) increases from ~100-2000 s as $m_{dwn}$ decreases from 70 to 10 $\mu$g, corresponding to an increase in utilization efficiency ($\eta$util) from 5% to 35%. Thrust-to-power ratios, measured using a thrust stand, also improve with peak current in the magneto-deflagration regime, increasing from 4.5 mN/kW to 8 mN/kW and 6.7 mN/kW for injected mass bits of 25 $\mu$g and 50 $\mu$g, respectively. This work provides critical insights into how the initial conditions in pulsed plasma thrusters dictate the formation of ionization waves, structure of plumes, and the performance of thrusters.