Low energy trajectories that enable spacecraft landing on airless bodies using minimum propellant consumption are currently being proposed to support various mission proposals.However, this direct approach to landing poses a risk because the abort options are limited and time-sensitive. A way to deal with this limitation is to declare the approach to landing a critical event, i.e., it must happen as planned or the entire mission is compromised. However,with the appropriate tools and techniques, a number of abort options can be identified, yielding a much more robust design. In this study, multi-body dynamics techniques are exploited to design abort trajectories for low energy transfers, using Earth’s Moon and Jupiter’s moon Europa as examples. As a result, periodic structures are identified for staging purposes in case of emergency, and the propellant cost associated with entering and departing these orbits prior to landing is evaluated.


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    Title :

    Analysis and Design of Abort Options for Low Energy LandingTrajectories


    Contributors:

    Publication date :

    2022-01-03


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English





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