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타이틀	Theta-Pinch Thruster for Piloted Deep Space Exploration
저자	Mike R. LaPointe
Keyword	Advanced propulsion; Plasma physics
URL	http://gltrs.grc.nasa.gov/reports/2000/CR-2000-210355.pdf
보고서번호	NASA CR-2000-210355
발행년도	2000
출처	NASA Glenn Research Center
ABSTRACT	A new high-power propulsion concept that combines a rapidly pulsed theta-pinch discharge with upstream particle reflection by a magnetic mirror was evaluated under a Phase I grant awarded through the NASA Institute for Advanced Concepts. Analytic and numerical models were developed to predict the performance of a theta-pinch thruster operated over a wide range of initial gas pressures and discharge periods. The models indicate that a 1-m radius, 10-m long thruster operated with hydrogen propellant could provide impulse-bits ranging from 1 N-s to 330 N-s with specific impulse values of 7,500 s to 2,500 s, respectively. A pulsed magnetic field strength of 2-T is required to compress and heat the preionized hydrogen over a 10-3 s discharge period, with about 60% of the heated plasma exiting the chamber each period to produce thrust. The unoptimized thruster efficiency is low, peaking at approximately 16% for an initial hydrogen chamber pressure of 100-Torr. The specific impulse and impulse-bit at this operating condition are 3,500 s and 90 N-s, respectively, and the required discharge energy is approximately 9?06 J. For a pulse repetition rate of 10-Hz, the engine would produce an average thrust of 900 N at 3,500 s specific impulse. Combined with the electrodeless nature of the device, these performance parameters indicate that theta-pinch thrusters could provide unique, long-life propulsion systems for piloted deep space mission applications.