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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    Title :

    Combined high and low thrust propulsion for fast piloted Mars missions


    Contributors:

    Publication date :

    1992-11-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Combined High and Low Thrust Propulsion for Fast Piloted Mars Missions

    Gilland, J. H. / Oleson, S. R. / American Nuclear Society; Eastern Idaho Section | British Library Conference Proceedings | 1992




    Nuclear electric propulsion mission performance for fast piloted Mars missions

    Hack, K. J. / George, J. A. / Dudzinski, L. A. | NTRS | 1991