The Earth return orbiter component of a Mars sample return campaign is a high total impulse mission with challenging timeline constraints. These competing demands mean a hybrid chemical-electric propulsion architecture may be needed for a feasible design, with chemical propulsion providing timely impulse and electric propulsion providing high volume impulse. We describe an approach to map out the hybrid trajectory design space and create a database to use in conjunction with a spacecraft design tool, enabling co-optimization of trajectory and spacecraft. This method is applied to both the outbound and inbound legs of a Mars sample return mission concept.


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    Titel :

    Hybrid chemical-electric trajectories for a Mars Sample Return orbiter


    Beteiligte:
    Lock, Rob (Autor:in) / Woolley, Ryan (Autor:in) / Olikara, Zubin (Autor:in) / Nicholas, Austin (Autor:in) / Laipert, Frank (Autor:in)

    Erscheinungsdatum :

    2019-01-13


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch



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