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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    Title :

    Hybrid chemical-electric trajectories for a Mars Sample Return orbiter


    Contributors:

    Publication date :

    2019-01-13


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English



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