This paper presents several mission designs for heliospheric boundary exploration using spacecraft with low-thrust ion engines as the primary mode of propulsion The mission design goal is to transfer a 200-kg spacecraft to the heliospheric boundary in minimum time. The mission design is a combined trajectory and propulsion system optimization problem. Trajectory design variables include launch date, launch energy, burn and coast arc switch times, thrust steering direction, and planetary flyby conditions. Propulsion system design parameters include input power and specific impulse. Both SEP and NEP spacecraft arc considered and a wide range of launch vehicle options are investigated. Numerical results are presented and comparisons with the all chemical heliospheric missions from Ref 9 are made.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Trajectory Optimization of an Interstellar Mission Using Solar Electric Propulsion


    Contributors:

    Publication date :

    1996


    Size :

    24 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English