Applying design principles to fusion reactor configurations for propulsion in space

Details Applying design principles to fusion reactor configurations for propulsion in space Applying design principles to fusion reactor configurations for propulsion in space

Jun 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993jpmc.confqt...c&link_type=abstract

AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993, 20 p.

Computer Science

Earth Orbital Environments, Fusion Reactors, Nuclear Engine For Rocket Vehicles, Nuclear Fuels, Reactor Design, Rocket Engine Design, Cost Analysis, Long Duration Space Flight, Manned Mars Missions

Scientific paper

We applied three design principles (DPs) to adapt and optimize three candidate-terrestrial-fusion-reactor configurations for propulsion in space. The three design principles are: (1) provide maximum direct access to space for waste radiation, (2) operate components as passive radiators to minimize cooling-system mass, and (3) optimize the plasma fuel, fuel mix, and temperature for best specific Jet power. The three candidate-terrestrial-fusion-reactor configurations are: (1) the thermal-barrier-tandem-mirror (TBTM), (2) field-reversed-mirror (FRM), and (3) levitated-dipole-field (LDF). The resulting three candidate-space-fusion-propulsion systems have their initial-mass-to-LEO minimized and their specific jet power and reusability maximized. We performed a preliminary rating of these configurations and concluded that the leading engineering-design solution to space fusion propulsion is a modified TBTM that we call the Mirror Fusion Propulsion System.

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