Combined high and low thrust propulsion for fast piloted Mars missions

Details Combined high and low thrust propulsion for fast piloted Mars missions Combined high and low thrust propulsion for fast piloted Mars missions

Nov 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992svti.rept.....g&link_type=abstract

Final Report Sverdrup Technology, Inc., Brook Park, OH.

Computer Science

Performance

Interplanetary Spacecraft, Low Thrust Propulsion, Manned Mars Missions, Mission Planning, Nuclear Electric Propulsion, Nuclear Propulsion, Nuclear Rocket Engines, Propulsion System Configurations, High Impulse, Propulsion System Performance, Specific Impulse

Scientific paper

The mission benefits of using both high thrust nuclear thermal propulsion (NTP) and low acceleration, high specific impulse nuclear electric propulsion (NEP) to reduce piloted trip times to Mars with reasonable initial mass are assessed. Recent updates in mission design, such as the Earth fly-by return, are assessed for their impact on previous studies. In addition, the Synthesis Commission split mission to Mars in 2014 is also assessed using combined propulsion. Results show an 80 to 100 day reduction in trip time over the reference NTP or NEP systems and missions, with comparable or reduced vehicle initial masses. The impacts of the mission and system analyses upon technology planning and design are discussed.

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