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Completed TRL 3 (started at 2, targeting 3)
New advancements in spacecraft power generation have driven the development of high-power electric propulsion thrusters. One such technology is the Rotating Magnetic Field – Field Reversed Configuration Thruster (RMF-FRC). Due to RMF-FRC’s pulsed nature, these devices have fully throttleable thrust control over a wide range of specific impulses in direct response to NASA TA 2.2.1.3. This control over performance parameters provides extreme versatility, allowing the RMF-FRC to be the only thruster on board missions that require both a high thrust mode and a high propellant-efficiency mode. One open question regarding the use and further development of RMF-FRCs is the ability for ejected plasma to detach from the accelerating magnetic field lines. While this has been an active and extensive area of research for magnetic nozzle devices, the detachment issues for RMF-FRCs have been dismissed without evidence in previous research work. I propose to investigate the interaction between ejected plasma and applied magnetic fields, specifically in RMF-FRC Thrusters as it pertains to thrust divergence, maximum plasmoid ejection rate, and impacts on spacecraft integration. My study will consist of coinciding experimentation and numerical modeling work leveraging UM’s new RMF-FRC test article, unique test facilities, and previous magnetic nozzle simulation codes.
This research will investigate the interaction between ejected plasma and applied magnetic fields in rotating magnetic field - field refversed configuration thrusters to support advancements in spacecraft power generation.
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