Fusion Propulsion Through a Magnetic Nozzle and Open Divertor

Details Fusion Propulsion Through a Magnetic Nozzle and Open Divertor Fusion Propulsion Through a Magnetic Nozzle and Open Divertor

Jan 2003

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2003aipc..654..510w&link_type=abstract

SPACE TECHNOLOGY AND APPLICATIONS INT.FORUM-STAIF 2003: Conf.on Thermophysics in Microgravity; Commercial/Civil Next Generation

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Ion And Plasma Propulsion, Spaceborne And Space Research Instruments, Apparatus, And Components

Scientific paper

A revised magnetic nozzle and open poloidal bundle divertor concept is proposed for a small aspect ratio, spherical torus reactor to be used in direct nuclear fusion space propulsion. A preliminary analysis of convergent/divergent flow through a magnetic nozzle illustrated the importance of high efficiency, where a power conversion efficiency of only 75% could lead to a doubling of exit area ratio requirements over ideal conditions. Preliminary MHD simulations have shown that as much as 50% of the mass flow could penetrate into the plasma-magnetic field boundary layer, leading to a thermal-to-directed jet power loss of 30% and a spacecraft payload mass ratio loss of ~ 60% of ideal. The importance of understanding the plasma-magnetic field interface and the inability of space/time dependent MHD simulations to resolve fine-scaled, gradient-driven micro-instabilities is currently under study. Preliminary plasma interface broadening mechanism studies have concluded that significant attachment of the plasma onto the magnetic field can occur at the nozzle inlet, that anomalous resistivity is likely to be a significant issue in the plasma regime of interest, that Rayleigh-Taylor instabilities may not be of immediate concern (but cannot be discounted), and that full Hall current effects must be incorporated into the ongoing simulations.

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