Date of Award
2026
Document Type
Thesis
Degree Name
Master of Science (MS)
Department
Mechanical and Aerospace Engineering
Committee Chair
Jason Cassibry
Committee Member
Gabe Xu
Committee Member
Kirk Boehm
Research Advisor
Jason Cassibry
Subject(s)
Space vehicles--Propulsion systems, Rockets (Aeronautics)--Nozzles, Nuclear propulsion, Pinch effect (Physics), Plasma (Ionized gases)
Abstract
Interplanetary travel using chemical or electrical propulsion faces two major obstacles: the long mission timelines and the health risks to human crews from prolonged radiation exposure. Fusion propulsion offers a potential solution through high specific impulse and moderate thrust values. Z-pinch fusion, a pulsed magneto-inertial fusion approach, is promising for propulsion as the plasma is confined through current-driven compression, eliminating the need for external confinement coils to achieve ignition conditions, and the confinement configuration is simple. A 3-dimensional model of a novel linear magnetic nozzle geometry was developed with the propellant, dissociated ammonia, oriented sideways in the nozzle, assuming prior thermalization of energy from a z-pinch fusion plasma. This linear profile, specifically a triangular solenoidal profile, is beneficial as it takes advantage of the inherent cylindrical symmetry of a z-pinch. Coil currents, nozzle angle, and sacrificial plate configuration were systematically varied. Results show an optimum current (2 MA current for 45° angle) and nozzle angle (30° angle when y-width is varied, for 1 MA current) exist for peak specific impulse and efficiency, with a maximum calculated efficiency of 55%. Efficiency increases with the presence of a wall near the nozzle apex, though high-current cases with a wall were inconclusive due to early simulation end times.
Recommended Citation
Manasterski, Stephanie, "Modelling novel planar nozzle geometries for a z-pinch fusion propulsion system" (2026). Theses. 835.
https://louis.uah.edu/uah-theses/835