This paper presents the methodology used in optimizing extended propulsion time NEP missions considering realistic thruster lifetime constraints. These missions consist of a powered spiral escape from a 700-km circular orbit at the earth, followed by a powered heliocentric transfer with an optimized coast phase, and terminating in a spiral capture phase at the target planet. This analysis is most applicable to those missions with very high energy requirements such as outer planet orbiter missions or sample return missions where the total propulsion time could greatly exceed the expected lifetime of an individual thruster. This methodology has been applied to the investigation of NEP missions to the outer planets where examples are presented of both constrained and optimized trajectories.


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    Title :

    Optimization of extended propulsion time nuclear-electric propulsion trajectories


    Contributors:

    Conference:

    Astrodynamics Specialist Conference ; 1981 ; Lake Tahoe, NV, US


    Publication date :

    1981-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Optimal EarthMoon Trajectories Using Nuclear Electric Propulsion

    Craig A. Kluever / Bion L. Pierson | AIAA | 1997





    Optimal Earth-Moon Trajectories Using Nuclear Electric Propulsion

    Kluever, C. A. / Pierson, B. L. / American Astronautical Society| American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 1996