Fusion propulsion with the addition of indigenous gases

Details Fusion propulsion with the addition of indigenous gases Fusion propulsion with the addition of indigenous gases

Jun 1993

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

AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993, 12 p.

Computer Science

Performance

Air Breathing Engines, Nuclear Fusion, Nuclear Rocket Engines, Spacecraft Propulsion, Gaseous Rocket Propellants, Propulsion System Performance, Requirements

Scientific paper

A feasibility and performance projection study is conducted for a heavy-lift aerospace plane employing nuclear fusion propulsion in conjunction with the earth and Mars atmospheres' indigenous gases, which allows a great simplification of propulsion system design and a similar reduction in vehicle mass. The estimated earth takeoff weight of the vehicle for this 250-day earth-Mars (round trip) interplanetary mission was 2500 mt, which resembles that of the lunar-mission Saturn 5 launcher; the estimated weight of the system when taking off from Mars for its return to earth was about 1200 mt. While N2 was the propellant for earth takeoff, that from Mars employed CO2.

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