Mission maps for use in the choice of specific impulse for manned Mars missions

Details Mission maps for use in the choice of specific impulse for manned Mars missions Mission maps for use in the choice of specific impulse for manned Mars missions

Aug 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992asdy.conf.1563m&link_type=abstract

IN: Astrodynamics 1991; Proceedings of the AAS/AIAA Astrodynamics Conference, Durango, CO, Aug. 19-22, 1991. Pt. 2 (A92-43251 18

Computer Science

Performance

Engine Design, Manned Mars Missions, Mission Planning, Nuclear Propulsion, Propulsion System Performance, Rocket Engines, Space Power Reactors, Spacecraft Propulsion, Specific Impulse, Computer Programs, Launch Windows

Scientific paper

The choice of engine concept for the initial manned missions to Mars should be driven by what can be feasibly built and flight qualified in the near term, and by the level of engine performance that is required for these missions. This paper addresses how mission requirements affect the choice of specific impulse, and consequently what values of the specific impulse best serve these missions. Broad mission surveys and sensitivity studies were performed to determine the specific impulse values that allow for fast transfer times and wide launch windows. We find that a specific impulse of around 1000 to 1200 sec is sufficient. Choosing an engine concept that has a higher specific impulse value is not justified for these missions because the modest reduction in propellant requirements and further widening of the launch windows does not compensate for the substantially greater technical risk.

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