<b>Development and Characterization of A </b><b>liquid-fed pulsed magnetoplAsmadynamic thruster for CubeSat applications</b>

<p dir="ltr">This dissertation presents the development and characterization of a low-voltage, liquid-fed pulsed magnetoplasmadynamic (LF-PMPD) thruster for CubeSat applications, utilizing ASCENT, a green monopropellant. Addressing the challenge of integrating electric propulsion into power-limited small satellites, the work explores the potential of coaxial pulsed plasma thrusters operating in a magnetoplasmadynamic regime at discharge voltages as low as 100–200 V. The system demonstrates peak discharge currents up to 10 kA and ion exhaust velocities reaching 30.6 km/s.</p><p dir="ltr">Key innovations include a dual-mode-compatible design, minimal cathode erosion, and extended operational lifetimes, verified over more than 10,000 pulses. Experimental characterization spans discharge parameters, time-resolved plasma imaging, ion velocity, and beam current profiles. Two prototype systems were developed with progressively refined ignition systems and electrode geometries, and diagnostics included ICCD imaging, current/voltage waveforms, and Langmuir probe analysis.</p><p dir="ltr">This research validates the feasibility of integrating electric and chemical propulsion within a single thruster architecture from tank to nozzle—using the same ASCENT propellant. It demonstrates low-power, high-performance operation suitable for missions requiring agility, extended lifetime, and compliance with rideshare constraints. The dissertation concludes with proposals for future optimization of thruster geometry and integration strategies for broader CubeSat and small-sat mission profiles.</p>