Multimegawatt MPD thruster design considerations

Myers, Roger; Parkes, James E.; Mantenieks, M. A.

doi:10.1063/1.41750

Cited by 3 publications

(1 citation statement)

References 17 publications

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“…The NASA Lewis Research Center focused on steady-state additional magnetic field MPDT at 100kW levels. They studied eight different electrode configurations ranging from 20-130kW input powers to determine their impact on thruster specific impulse and efficiency [16][17][18][19][20][21] . Meanwhile, Japan's Osaka University Tahara group developed a series of MW-level magnetoplasmadynamic thrusters with an additional magnetic field.…”

Section: Introductionmentioning

confidence: 99%

Demonstration of High-Temperature Superconducting Applied field Magnetoplasmadynamic Thrusters

Zheng,

liu,

et al. 2024

Preprint

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Propelling the future of space exploration, electric propulsion stands as a transformative force, showcasing high efficiency, reliability, and environmental consciousness in comparison to conventional chemical propulsion. The applied field MPD thruster, as an electric propulsion device, can produce high thrust and impulse, provided that some known issues (such as cathode lifespan, cooling system, high payload, and theoretical challenges) hindering efficiency are addressed. At the vanguard of our breakthroughs is introduction of a sterling cooling system, for High-Temperature Superconducting magnet for Applied field MPD thruster. This system replaces large helium tanks, thereby increasing the payload capacity for more efficient flight missions. Our primary focus on ensuring stability and boosting efficiency, marking a significant step forward in the world of space propulsion. The introduction of a rare earth-doped nano-cathode is a breakthrough in addressing the challenge of cathode lifespan within the Applied Field MPD thruster. Through the strategic infusion of rare earth materials into tungsten, we have successfully shattered the limitations on cathode lifespan, an impediment that has long hindered efficiency in Applied field MPD thrusters. Our comprehensive theoretical model peels back the layers of complexity surrounding the Applied Field MPD thruster, offering profound insights. The interplay of plasma expansion within a magnetic nozzle geometry, set by the HTS magnet, unveils a discernible relationship between thrust and applied field strength. TSwirl emerges as the major conductor, orchestrating thrust at low mass flow rates. The story concludes with an experimental high note, where we achieve an awe-inspiring thrust of 283 mN at a mass flow rate of 20 mg/s. The pinnacle of our achievement, however, lies in the attainment of the highest specific impulse, reaching an astounding 3265 s at a mere 5 mg/s. Efficiency takes the spotlight with a remarkable 172% increase, surpassing the performance of a copper magnet in an equivalent configuration. This monumental success, achieved with argon propellant at a modest power input of 8 kW, heralds a paradigm shift in the efficiency of low-power Applied Field MPD thrusters.

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