A major challenge in formulating interplanetary mission concepts utilizing electric propulsion is the large number of trajectory variables that must be considered (thrust profile, flyby options, launch vehicle delivery), all of which are affected by spacecraft design variables (power, mass, thruster, payload, staging). This is significantly more complex than traditional ballistic/chemical mission design and early concepts are often suboptimal as a result, potentially missing valuable options. This paper presents a novel tool (MORT) for simultaneously optimizing the spacecraft design alongside the trajectory given mission constraints and objectives, including example results relevant to the exploration of Mars.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Simulaneous optimization of spacecraft and trajectory design for interplanetary missions utilizing solar electric propulsion


    Contributors:

    Publication date :

    2019-01-13


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English